document title / titre du document
TRP WORK PLAN 2008 – 2010
COMPLETE LIST
prepared by/préparé par
TRP Management Office
reference/réference
issue/édition
revision/révision
date of issue/date d’édition
status/état
Document type/type de document
Distribution/distribution
TEC-SB/7934/dc
1
0
22/06/2009
02/06/2009
Information Note
OF
ACTIVITIES
a
TEC-SB_7934_TRP2008-2010
TRP WORKPLAN 2008-2010
Complete Llist of Activities
issue 1 revision 0 3page ii of iii
A P P R O V A L
Title
Titre
TRP Work Plan 2008-2010 – Complete List of Activities
issue
issue
author
auteur
TRP Management Office
date 22/06/2009
date
approved by
approuvé par
revision
revision
date
date
C H A N G E
reason for change /raison du changement
L O G
issue/issue
C H A N G E
revision/revision
date/date
R E C O R D
Issue: Revision:
reason for change/raison du changement
page(s)/page(s)
paragraph(s)/paragraph(s)
TRP WORKPLAN 2008-2010
Complete Llist of Activities
issue 1 revision 0 3page iii of iii
T A B L E
O F
C O N T E N T S
1
INTRODUCTION
2
COMPLETE LIST OF ACTIVITIES
3
DESCRIPTION OF ACTIVITIES
TRP WORKPLAN 2008-2010
Complete List of Activities
issue 1 revision 0
page 1 of 5
1
INTRODUCTION
This information note presents the complete list of activities that constitute the TRP 2008-2010
work plan cycle, their status and descriptions.
The document is structured as follows:
Chapter 1, Introduction
Chapter 2 includes tables listing all activities divided by following Service Domains:
1. Technologies related to Earth Observation
2. Technologies related to Science
3. Technologies related to Human Spaceflight & Exploration Preparation
4. Technologies related to Space Transportation & Re-entry Technologies
5. Technologies related to Telecommunication
6. Technologies related Navigation
7. Generic Technologies & Techniques
and provides following information:
IPC Approval:
Status of approval of the corresponding procurement proposal.
(YXXXX= Year of approval for workplan activities previously
endorsed & corresponding procurement proposals approved, if
applicable.
Status:
Proposed: Not yet approved/submitted to AC/IPC
Intended: Approved by IPC but not committed yet
Committed: Contractor selected and successful negotiation
Contracted: Contract signed
Closed: Contract closed, all deliverables received
Deleted: Removed from work plan
Deferred: Previously approved but postponed
TRP WORKPLAN 2008-2010
Complete List of Activities
issue 1 revision 0
page 2 of 5
Budget:
Budget planned for this activity. Total Contract Authorisation (CA)
values, given in KEURO, at yearly economic conditions.
Procurement Policy:
C
= Open Competitive Tender; (Ref. Article 5.1 ESA Contract
Regulations).
C(1)*
=
C(2)*
=
C(3)*
=
Activity restricted to SMEs & R&D organisations, preferably in
cooperation.
The measure is proposed when the technology activity relates to
early phases of the technology development (TRL<3) with strong
expectations on innovation contents, or to technology spin-in,
and when SMEs & R&D organisations have recognised expertise
and capabilities in the technology domain.
Note: (Otherwise, the bid will not be considered for further
evaluation).
C(4)*
=
Activities in open
subcontracting clause.
Activities in open competition limited to the non-Large-System
Integrators.
Note: In these activities, LSIs are not allowed to submit prime
proposals to ESA. LSIs can participate as subcontractors. In this
case, the proposal must demonstrate that:
- the tasks assigned to the LSI do not constitute the core
activities of the proposed development;
- The technical expertise provided by the LSI is essential to the
activity;
- the non-LSI in the team retains the key capabilities to develop
and exploit the results of the technology activity;
- the presence of the LSI in the proposal does not
undetermined or limit the leading role of the non-LSI in the
team.
(Otherwise, the bid will not be considered for further evaluation).
Activities in open competition, where a significant participation
of non-Large-System Integrators is requested.
Note: These activities are open to all potential bidders, LSIs and
non-LSIs. However, LSIs that submit bids are requested to
include in those bids a relevant participation of non-LSIs, in
quality and quantity, in accordance with the ITT guidelines - in
the form of a percentage range of expected participation of nonLSIs – on which the C(2) measure is applied. (Otherwise, the bid
will not be considered for further evaluation).
competition,
subject
to
the
SME
TRP WORKPLAN 2008-2010
Complete List of Activities
issue 1 revision 0
page 3 of 5
Note: Bidders are required to do their utmost to include in their
bid an adequate participation of SMEs as subcontractor(s)
(judged in terms of quantity indicated as guidelines of the ITT on
which the C(4) measure is applied). Offers shall provide an
analysis of the potential advantages of the proposed
participation (e.g. long-term rospects for future work). If no such
participation is offered, the bid shall contain evidence of the
effort made to meet these requirements and the reasons for the
lack of success. (Otherwise, the bid will not be considered for
further evaluation).
C(R)
=
DN/S
=
DN/C
=
Competition is restricted to a few companies, indicated in the
"Remarks'' column; (Ref. Article 5.2 ESA Contract Regulations).
Direct Negotiation/Specialisation; the contract will be awarded
by direct negotiation in implementation of a defined industrial
policy or resulting from a sole supplier situation (Ref. Articles
6.1.A,D,F ESA Contract Regulations).
Direct Negotiation/Continuation; the contract will be awarded in
direct negotiation being the immediate continuation of a previous
activity with the same contractor (Ref. Article 6.1.C ESA
Contract Regulations)
Country:
Prime contractor country
Remarks:
Provides information on Prime contractor and sub-contractors in case the
activity is contracted or gives other additional info.
Chapter 3 provides the descriptions of the activities. The Technology Activity Template provide
following information:
Objectives:
Provides short summary of the main goals of the activity.
Description:
Describes the activity, providing the context information, the purpose of
the activity and the main tasks.
Deliverables:
Provides short description of the tangible outcome e.g. breadboard,
demonstrator, S/W, test data. A final report is standard for every
activity.
Current TRL:
Describes the current NASA TRL level of the product that is going to be
developed in this activity.
TRP WORKPLAN 2008-2010
Complete List of Activities
issue 1 revision 0
page 4 of 5
Target TRL:
The NASA TRL level expected for the product at the end of the activity.
For equipments TRP usually concludes with TRL 3, GSTP at level 5/6.
However in the case of components target TRL level in TRP could be
higher. It is also understood that TRL levels do not apply to S/W and tools.
For these cases description of SW quality, i.e: architecture, beta version,
prototype, or full operational, achieved at the end of the activity.
Application Need/Date:
Describes the required TRL level and date for the technology development
of which the respective activity is part of on the base of the maturity
required by the application. The general rule is that a requirement specifies
the need date for a product. For equipments/payloads this is in general
TRL 5/6, - the level generally required for Phase B of a project. The
exceptions are components, where TRL 8 (flight readiness) should be
achieved. For S/W and tools separate readiness levels are defined below
Application/Mission: Describes the first possible mission/application/follow-on and the flight
date.
Technology Readiness Level, as stated by NASA, to be achieved at end of the activity for
TRL1 - Basic principles observed and reported
TRL2 - Technology concept and/or application formulated
TRL3 - Analytical and experimental critical function and/or characteristic proof-of-concept
TRL4 - Component and/or breadboard validation in laboratory environment
TRL5 - Component and/or breadboard validation in relevant environment
TRL6 - System/subsystem model or prototype demonstration in a relevant environment (ground
or space)
TRL7 - System prototype demonstration in a space environment
TRL8 - Actual system completed and "flight qualified" through test and demonstration (ground
or space)
TRL9 - Actual system "flight proven" through successful mission operations
Readiness Levels for S/W and tools
Algorithm
Single algorithms are implemented and tested to allow their characterisation
and feasibility demonstration.
Prototype
A subset of the overall functionality is implemented to allow e.g. the
demonstration of performance.
Beta Version Implementation of all the software (software tool) functionality is complete.
Verification & Validation process is partially completed (or completed for
only a subset of the functionality).
TRP WORKPLAN 2008-2010
Complete List of Activities
issue 1 revision 0
page 5 of 5
S/W Release Verification and Validation process is complete for the intended scope. The
software (software tool) can be used in an operational context.
Research & feasibility
demonstration
predevelopment
prequalification
TECHNOLOGY R&D
CAT. A
Innovative/Prospective
Technology
Support to Programmes &
Generic Technologies
Support to Industry’s
Competitiveness
(Short Term)
T.R.L. 1-2
TRP
T.R.L. 3
T.R.L. 4 and/or T.R.L. 5
CAT. B
T.R.L. 4 and/or T.R.L. 5
CAT. C
ESA Technology Landscape (NASA TRL's)
Contract Duration:
Duration of the activity (e.g. 24 month)
Dossier 0 Reference:
Identifies the related Dossier 0 (ESTER) Requirement
SW clause applicability:
Special approval is required for activities labelled:
either “Operational Software” or “Open Source Code”,
for which the Clauses/sub-clauses 42.8 and 42.9 (“Operational
Software”) and 42.10 and 42.11 (“Open Source Code”) of the
General Clauses and Conditions for ESA Contracts (ESA/C/290,
rev.6), respectively, are applicable.
Consistency with Harmonisation Roadmap and Conclusions:
Consistency with any related Harmonisation Roadmap or Dossier or
Conclusion report, if applicable.
f
Chapter 2
TRP Work Plan 2008-2010
Complete List of Activities
TEC-SB/7934/dc
22/Jun/09
TRP Work Plan 2008-2010
TEC-SB/7934/dc
Complete List of Activities
22/Jun/09
1 - Earth Observation
1-01 - Microwave Payloads
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
350
DN/S
C'try
Remarks
S/W
Clause
TD
Contract
Number
UK
ABSL Space Products
N/A
TD07
C21923
Y2007
Contracted
T107-023EE
Low mass Calibration load
Y2007
Intended
T101-001ED
Digital Beam Forming Technological Elements
250
C
N/A
TD01
Y2007
Intended
T106-006ET
Calibration loads for radiometers
400
C(1)
N/A
TD06
Y2007
Intended
T107-025EE
Assimilation of high temporal resolution SAR data into land process models
200
C(3)
N/A
TD07
Y2007
Intended
T107-029EE
Advanced modelling of coherent propagation effects on active microwave remote sensing
200
C(3)
Open
source
TD07
Y2007
Intended
T107-030EE
ESA manual towards a new scattering statistics database for different terrain types
50
C(3)
N/A
TD07
Y2007
Intended
T108-033SM
Analysis of Normalised Differential Spectral Attenuation (NDSA) Technique for Inter-Satellite
Atmospheric Profiling
200
C(3)
N/A
TD08
Y2008
Intended
T106-002ET
Integrated Circulators for TR modules
300
C(1)
N/A
TD06
Y2008
Intended
T106-005ET
Micro- and millimetre wave detectors
400
C(2)
N/A
TD06
Y2008
Intended
T106-008ET
MM-Wave Power Amplifier
500
C (2)
N/A
TD06
Y2008
Intended
T106-009ET
Frequency-Multipliers for Submm
450
C(3)
N/A
TD06
Y2008
Intended
T106-010ET
Direct-Detection Radiometers
800
C
N/A
TD06
Y2008
Intended
T106-014ET
Swath precipitation radar instrument
200
C
N/A
TD06
Y2008
Intended
T106-017ET
Study of a high spatial resolution MIRAS (Super-MIRAS)
200
C
N/A
TD06
N/A
TD07
C for prime.
Universidad Politecnica
Madrid (E) + Queen's
University of Belfast (UK)
must be involved.
Y2008
Intended
T107-020EE
Innovative reconfigurable systems based on liquid crystals
450
C
Y2008
Intended
T107-031EE
Capability of atmospheric parameter retrieval and modelling for wide-swath spaceborne
atmospheric radars
180
C(3)
N/A
TD07
Y2008
Intended
T107-032EE
Potential and characterisation of geophysical parameter retrieval using a passive
interferometer
150
C(3)
N/A
TD07
Y2008 /
Y2009
Intended
T107-021EE
Large Antennas for P-Band SAR - Critical Breadboarding (OLD TITLE: Advanced Feed
System allowing Signal Processing capability for Large Earth Monitoring Antennas)
500
C
N/A
TD07
Page 1 of 27
Activity revised, budget
increased
TRP Work Plan 2008-2010
TEC-SB/7934/dc
Complete List of Activities
22/Jun/09
1-01 - Microwave Payloads
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
C'try
Remarks
S/W
Clause
TD
Y2008 /
Y2009
Intended
T116-034PI
Long Life Scanning Mechanism - Contactless Power and Data Transmission
500
C(1)
Activity revised, Budget
increased
N/A
TD15
Y2009
Intended
T106-013ET
Study into Ka-band SAR
150
C
Total budget 250kE,
150kE TRP + 100kE
EOPA or IPD
N/A
TD06
C
I
Activity revised and
original budget split
between two parallel
contracts, to be linked to
EO "Ku-band antenna feed
breadboarding" contract.
Team selected: TAS +
ComDev (UK)
N/A
TD07
D
Activity revised and
original budget split
between two parallel
contracts, to be linked to
EO "Ku-band antenna feed
breadboarding" contract.
Team selected: Astrium +
ComDev (UK) + Saab
Space (S)
N/A
TD07
Y2009
Intended
T107-018EE
Light Weight, Dual Frequency Antenna Configuration for Earth Observation SAR applications
245
Y2009
Intended
T107-018EE
Light Weight, Dual Frequency Antenna Configuration for Earth Observation SAR applications
245
C
Y2009
Intended
T107-022EE
Antenna Architecture for Radio Occultation for GRAS-2
200
C
N/A
TD07
Deferred
T106-003ET
Photo-HBV for sub-millimetre wave LO generation and distribution
250
C(1)
N/A
TD06
Deferred
T106-004ET
Single GaN chip HPA/LNA for Radar Applications
450
C(1)
Will be reconsidered in
2010
N/A
TD06
Deferred
T106-007ET
Low-Noise Amplifiers for 300 GHZ
600
C
Will be reconsidered in
2010
N/A
TD06
Deferred
T106-011ET
1THZ Schottky Mixer
450
C(1)
Will be reconsidered in
2010
N/A
TD06
Deferred
T106-012ET
1THZ LO Unit
950
C(2)
Will be reconsidered in
2010
N/A
TD06
Deferred
T106-015ET
Integrated Scalable Tile Beam Former
650
C
N/A
TD06
Deferred
T106-016ET
High Bandwidth programmable DDS for chirp generation
800
C(2)
N/A
TD06
Deferred
T107-026EE
The generic radiative transfer toolbox for the Earth environment, ESAS-Light: from a
prototype tool to a community tool
250
C(1)
Open
source
TD07
Deferred
T107-028EE
Improvement of the Tenti model for atmospheric Rayleigh-Brillouin scattering
150
C(3)
Will be reconsidered in
2010
N/A
TD07
Deleted
T107-019EE
Millimeterwave Radar Antenna Technology
500
To be reconsidred for 2011
N/A
TD07
Deleted
T107-024EE
Antenna Architecture for Radio Occultation for LEO-LEO
To be reconsidred for 2011
N/A
TD07
200
Page 2 of 27
C
Contract
Number
TRP Work Plan 2008-2010
TEC-SB/7934/dc
Complete List of Activities
22/Jun/09
1-01 - Microwave Payloads
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
Total 1-01 - Microwave Payloads
350.00
C'try
Remarks
S/W
Clause
TD
Contract
Number
C'try
Remarks
S/W
Clause
TD
Contract
Number
Deleted, merged with
T116-051MM
N/A
TD16
6,970.00 5,050.00
1-02 - Optical Payloads
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
Y2006
Deleted
T103-04FP
Lightweight large aperture deployable telescope for lidar applications
Y2007
Contracted
T108-036SM
Y2007
Contracted
T116-041MM Mercury cadmium telluride avalanche photodiode detector with >2 um cut-off wavelength.
Y2007
Contracted
T116-042MM
Y2007
Intended
Y2007
C
C
B
Royal Meteorological Inst
Belgium
N/A
TD08
C22460
C(1)
UK
Selex Sensors & Airborne
Systems
N/A
TD17
C21751
250
C(1)
D
FHG
N/A
TD17
C22281
T116-040MM Low dark current 2D TIR CMT detectors based on p/n technology
800
C(1)
N/A
TD17
Intended
T116-047MM High efficiency volume Bragg gratings (VBG) for spectrometry
250
C(1)
N/A
TD16
Y2007
Intended
T120-055MC Advanced Laser Instrument Thermal Design
400
C
N/A
TD21
Y2007
Intended
T124-056QM
500
C
N/A
TD25
Y2007 /
Y2008
Intended
T116-051MM Large Aperture Telescope Technology
800
C
Budget increased,
approved at 237th IPC
N/A
TD16
Y2007 /
Y2009
Intended
High-performance low-straylight gratings for compact high resolution optical spectroscopy:
T116-048MM Immersed grating technology for compact high resolution optical spectroscopy in the
near-infrared
600
C(1)
Activity title revised.
Budget increased (400kE
TRP approved as per
ESA/IPC(2007)3 add.3 +
200kE EO).
N/A
TD16
Y2008
Deleted
T116-037MM Ultra narrow linewidth phase locked laser for beam splitting
350
C(3)
To be reconsidred for 2011
N/A
TD17
C(1)
To be reconsidered for
2011
N/A
TD16
1000
C
To be revised towards
post-EPS, will be
reconsidered for 2011
N/A
TD17
E2V
N/A
TD17
N/A
TD07
N/A
TD16
Y2008
Deleted
Sensitivity study on the influence of a target spectral signature in the unfiltering process for
broadband radiometers
Development of an adhesive-free bonding technique for optical components through
substrate metallisation and hard soldering
Optical Components materials and process development and validation for high power space
borne lasers
T116-049MM Micro Optics Filtering Technology
150
500
270
Critical Technology for future imaging spectrometers in the UV to SWIR range and Fourier
Transform Spectrometers (FTS)
Y2008
Deleted
T116-052SF
Y2008
Intended
T116-038MM Red-enhanced L3CCD and gain stability evaluation
800
DN/S
Y2009
Intended
T107-027EE
Atmospheric Corrections for Fluorescence Signal Retrieval
200
C(3)
Y2009
Intended
T116-053SF
Critical Technology Activities for high spectral resolution fluorescence imaging spectrometer
1000
C
Page 3 of 27
UK
Activity and budget
revised.
TRP Work Plan 2008-2010
TEC-SB/7934/dc
Complete List of Activities
22/Jun/09
1-02 - Optical Payloads
IPC
Status as of
Approval 02/06/2009
Y2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
Intended
T116-054SF
VLWIR Detector breadboarding for an Infrared Limb sounder
Deferred
T101-035ED
New Techniques for efficient multi-spectral data compression
Deferred
1000
C'try
C
Remarks
S/W
Clause
TD
Activity revised
N/A
TD16
250
C(3)
N/A
TD01
T116-043MM Laser Source for Atmospheric CO2 and Methane Monitoring
400
C(1)
N/A
TD17
Deferred
T116-044MM High-Stability Laser with Fibre Amplifier for Interferometric Earth Gravity Measurements
400
C(1)
N/A
TD17
Deferred
T116-050MM Optical filtering for onboard LIDAR calibration
400
C(2)
N/A
TD16
Deleted
T116-039MM Solar-blind UV Lidar Detector
To be reconsidred for 2011
N/A
TD17
Deleted
T116-045MM Back-thinned InGaAs array for visible-SWIR imaging
To be reconsidered for
2011
N/A
TD17
Deleted
T116-046MM Pulsed Laser Source at 1.57 micro-meters for Atmospheric Greenhouse Gas Monitoring
To be reconsidered for
2011
N/A
TD17
Remarks
S/W
Clause
TD
Will be reconsidered in
2010
800
1000
Total 1-02 - Optical Payloads
C
350
500.00
Contract
Number
9,520.00 2,450.00
1-03 - Platforms/others
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
C'try
Y2007
Intended
T106-059ET
Advanced Techniques for High Data Rate Links for Earth Exploration Satellites
400
C
Operati
onal SW
TD06
Y2007
Intended
T107-061EE
Ka-band payload data downlink antennas definition for Earth Observation
250
C
N/A
TD07
Y2007 /
Y2008
Intended
T101-057ED
SpaceFibre Very High Speed Link Technology Demonstrator
500
DN/S
N/A
TD01
Y2008
Intended
T107-060EE
Innovative planar highly directive antenna based on artificial surfaces
150
C
N/A
TD07
Y2008
Intended
T118-063MP High Efficiency Inert Gas thruster
150
C(1)
N/A
TD19
Y2008
Intended
T125-065GR Open Rich Client Platform (RCP) for user service tools
200
C
N/A
TD26
Y2008
Intended
T125-066GR Support to topology
200
C
N/A
TD26
Y2009
Intended
T105-068EC
Modern attitude control of EO satellites with large flexible elements
150
C
300kE (50% TRP/50%
EOPA)
N/A
TD05
Y2009
Intended
T106-067EE
Channel modelling for design of EO Ka band data downlink systems
150
C
300kE (50% TRP/50%
EOPA)
TBD
TD06
Deferred
T122-064QC
Radiation Evaluation of DDR-2/DDR-3 Memories for future high throughput Solid State
Recorders (1Gbit/2Gbit)
Hirex Engineering
N/A
TD23
Page 4 of 27
300
DN
UK
F
Change of PP, U. Dundee
Contract
Number
TRP Work Plan 2008-2010
TEC-SB/7934/dc
Complete List of Activities
22/Jun/09
1-03 - Platforms/others
IPC
Status as of
Approval 02/06/2009
Deleted
Proposed
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
T118-062MP Development of a Highly Throtteable Low Power Hall Effect Thruster for Earth Observation.
T105-058EC
C'try
500
On-board autonomous dynamic planning for operational observation wrt AOCS constraints
200
Total 1-03 - Platforms/others
2,650.00
Remarks
S/W
Clause
TD
To be reconsidered for
2011
N/A
TD19
N/A
TD05
C
Contract
Number
500.00
3 - Human Spaceflight and Exploration Preparation
3-01 - Robotics Assistance technologies
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
C'try
Remarks
S/W
Clause
TD
Contract
Number
D
DLR
Operati
onal SW
TD13
C21929
C21737
Y2007
Contracted
T313-004MM Dexterous Robot Hand
500
DN/S
Y2007
Contracted
T313-009MM Motion Control Chip
1000
C(1)
Operati
onal SW
TD13
Y2007
Intended
T313-006MM Autonomous Controller
700
C
Operati
onal SW
TD13
Y2008
Intended
T309-001GD MMI for Exploration Missions
200
C(1)
Operati
onal SW
TD09
Y2008
Intended
T310-003GF
90
C(3)
Operati
onal SW
TD10
Y2008
Intended
T313-005MM Human Hand Exoskeleton
500
C(1)
Operati
onal SW
TD13
Y2008
Intended
T313-007MM Heavy Duty Planetary Chassis
200
C
N/A
TD13
Radio tracking of a landed spacecraft: determination of the spacecraft position and of the
planet's ephemeris and orientation in space
Total 3-01 - Robotics Assistance technologies
1,500.00 1,690.00
3-02 - Life and Physical Sciences
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
Y2007
Contracted
T314-012MM X-ray based analytical and imaging devices
Y2007
Contracted
T314-013MM Non-stochastic detectors of bio-markers for space applications
550
150
Page 5 of 27
C'try
Remarks
S/W
Clause
TD
Contract
Number
C
D
Un. Dresden
N/A
TD14
C22237
C(3)
UK
Un. Cranfield
N/A
TD14
C21869
TRP Work Plan 2008-2010
TEC-SB/7934/dc
Complete List of Activities
22/Jun/09
3-02 - Life and Physical Sciences
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
C'try
Remarks
S/W
Clause
TD
Contract
Number
Y2007
Contracted
T314-017MM Computer aided medical diagnostics and surgery
450
C(2)
B
Space Application
Services
Operati
onal SW
TD14
C21843
Y2007
Contracted
T314-018MM In-situ, continuous biochemical analyzer
500
DN/C
D
EADS-Astrium
N/A
TD14
C21903
Y2007
Intended
T314-016MM Invasive Physiological Monitoring
250
DN/C
NL
Telemetronics
N/A
TD14
Y2008
Intended
T314-010MM Continuous Physiological and Medical Monitoring (non-invasive)
500
C(1)
N/A
TD14
Y2008
Intended
T314-014MM Imaging of wave scattering in solids
400
C(1)
N/A
TD14
Y2008
Intended
T314-015MM Time Resolved Correlation Spectroscopy and Total Internal reflection Scattering
350
C(3)
Operati
onal SW
TD14
Proposed
T314-011MM Integrated Countermeasures with biofeedback and actuators
C(2)
N/A
TD14
600
Total 3-02 - Life and Physical Sciences
1,100.00 2,050.00
600.00
3-03 - Human Exploration Technologies
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
T308-021SW Crew Information System
400
Remarks
S/W
Clause
TD
Contract
Number
NL
TNO // (proof-of-concept
only)
N/A
TD08
C21947
Y2007
Contracted
Y2007
Intended
T319-022MC Window design for Manned Spacecraft
300
C
N/A
TD20
Y2007
Intended
T319-023MC Flexible window concept for inflatable and expandable habitat modules
300
C
N/A
TD20
Y2007
Intended
T321-027MC Removal of specific chemical contaminants in water
250
C(1)
N/A
TD22
Y2007
Intended
T321-029MC Preliminary definition of on-line chemical water quality analysis equipment
250
C(1)
N/A
TD22
Y2008
Intended
T304-019EE
400
C(3)
Open
Source
TD04
Y2008
Intended
T319-024MC Hypervelocity Impacts on Expandable Protections for Space Vehicles
400
C
N/A
TD20
Y2008
Intended
T321-025MC Characterisation of a Nitrogen recycling unit for water recovery
450
C(2)
N/A
TD22
Y2008
Intended
T321-026MC Microbial pathogen identification in water
350
C(1)
N/A
TD22
Y2008
Intended
T321-028MC Extraction of specific chemical contaminants in the Air
350
C(3)
N/A
TD22
Proposed
T304-020EE
C
N/A
TD04
Physics models for biological effects of radiation and shielding
Radiation shielding by ISRU and/or innovative composites for EVA, vehicles and habitats
Page 6 of 27
DN/C
C'try
400
(Physics model
developments)
TRP Work Plan 2008-2010
TEC-SB/7934/dc
Complete List of Activities
22/Jun/09
3-03 - Human Exploration Technologies
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
Total 3-03 - Human Exploration Technologies
400.00
3,050.00
C'try
Remarks
S/W
Clause
TD
Contract
Number
C'try
Remarks
S/W
Clause
TD
Contract
Number
N/A
TD16
Remarks
S/W
Clause
TD
Additional work
N/A
TD24
400.00
3-04 - Autonomous Robotic Exploration missions
IPC
Status as of
Approval 02/06/2009
Y2008
Intended
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
T316-030MM Miniaturized Imaging Lidar system (Ph.1)
450
Total 3-04 - Autonomous Robotic Exploration missions
C(1)
450.00
4 - Space Transportation
4-01 - Launchers oriented Technologies
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Proposed
Proposed
MPC-846
Y2007
Intended
Y2007
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
C'try
Acquisition and Evaluation of Cryo-Solid Propulsion: Additional Testing
150
DN(C)
T409-002GI
Assessment of the suitability of ESOC Ground Segment infrastructure S/W for its use in the
launcher field.
250
C
Operati
onal SW
TD09
Intended
T415-003PV
Study for an on-board contamination measurement for launchers
50
C(1)
N/A
TD15
Y2007
Intended
T417-004MP Launcher stage separation and plume interaction validation
300
C
N/A
TD18
Y2007
Intended
T418-010MP Simulation models for Solid Rocket Motor’s (SRM’s) Ignition Transient (IT)
150
C
N/A
TD19
Y2007
Intended
T419-011MC Delamination assessment tool for composite structures
350
C
N/A
TD20
Y2007
Intended
T419-013MC Structural integrity of pressurized structures: Advanced non-linear methodology
300
C(2)
N/A
TD20
Deleted
Experimental Investigation of Key Technologies for a Turbine Based Combined
T418-034MP
Airbreather-Rocket Engine
N/A
TD19
Y2008
Page 7 of 27
500
DN/S
UK
Approval covers both 2008
and 2009. // REL +
ASTRIUM (D), Univ. of
Bristol (UK) // Ref. to
ESA/IPC(2008)1,add.24
Contract
Number
C22219
TRP Work Plan 2008-2010
TEC-SB/7934/dc
Complete List of Activities
22/Jun/09
4-01 - Launchers oriented Technologies
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
C'try
Remarks
S/W
Clause
TD
N/A
TD18
N/A
TD19
Y2008
Intended
T417-005MP Launcher base flows and shock interaction regions improved load characterization
300
C
Y2008
Intended
T418-007MP European medium thrust engine concept
200
C
Y2008
Intended
T418-008MP Dynamic Characterization of Cavitating Turbopumps and Inducers for POGO Suppression
300
C(1)
N/A
TD15
Y2008
Intended
T419-012MC Fracture Control/Damage Tolerance methods for highly loaded launcher components
350
C
N/A
TD20
Y2008
Intended
T420-014MC Development of nano-structured cryogenic foam insulations
150
C(1)
N/A
TD21
Proposed
T418-006MP Experimental Investigation of Rotordynamic Fluid Forces on Cavitating Helical Inducers
300
C(1)
N/A
TD15
Proposed
T418-009MP Technology feasibility of cryogenic PMD elements
350
C
N/A
TD19
Proposed
T423-015MC Passive / Active oxidation of CMC structural materials
300
C(1)
N/A
TD24
Total 4-01 - Launchers oriented Technologies
500.00
2,850.00
Anticipated
Contract
Number
950.00
4-02 - Human Space Flight oriented Technologies
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
Y2007
Contracted
T405-017EC
Robust Skip-entry Guidance and Control Techniques
250
Y2007
Contracted
T420-019MC Development of a European ablative material for heatshields of sample return missions
Y2007
Intended
T401-016ED
Y2007
Intended
Y2008
Intended
400
Safety oriented reference architecture
C
C'try
Remarks
S/W
Clause
TD
Contract
Number
F
Astrium
N/A
TD05
C22125
HPS
N/A
TD21
C21827
C
600
C
N/A
TD01
T417-018MP Planetary Probe Standard model testing in High enthalpy facilities
400
C
N/A
TD18
T418-034MP Solid Modulated Propulsion for Space Exploration
300
C
N/A
TD19
S/W
Clause
TD
Total 4-02 - Human Space Flight oriented Technologies
400.00
1,550.00
4-03 - Generic Space Transportation Technologies
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
Page 8 of 27
C'try
Remarks
Contract
Number
TRP Work Plan 2008-2010
TEC-SB/7934/dc
Complete List of Activities
22/Jun/09
4-03 - Generic Space Transportation Technologies
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
250
C'try
Remarks
S/W
Clause
TD
Contract
Number
DN/C
F
Astrium + Sub's
N/A
TD05
C21687
Y2007
Contracted
T405-021EC
Hybrid Navigation (HiNAV) System Architecture Consolidation
Y2007
Contracted
T405-022EC
Advanced Reentry Flying Qualities Analysis Framework
350
C
E
Deimos Space
N/A
TD05
C22115
Y2007
Contracted
T420-032MC
Development of lightweight flight sensors and measurement techniques for planetary entry
probes and vehicles
200
C(3)
D
HPS
N/A
TD21
C22155
Y2007
Intended
T417-026MP
Definition and validation of transfer functions for intrusive measurement techniques in re-entry
and entry environments
300
C(1)
N/A
TD18
Y2007
Intended
T418-027MP Aerodynamics of down load systems: parachutes
350
C(2)
N/A
TD18
Y2007
Intended
T418-030MP Innovative PED bladder technology
200
C
N/A
TD19
Y2008
Contracted
T420-031MC
Material characterization of European ODS material candidate, Kanthal APMT, for application
in metallic TPS
Y2008
Intended
T403-03MC.B
Improvement of the gas-surface interaction models, to account for the coupling
pyrolisis-catalysis. Integration of models into a CFD code. Validation.
Y2008
Intended
T405-020EC
Y2008
Intended
Y2008
Y2008
DN/S
S
Kanthal
N/A
TD21
C21936
250
DN/C
IRL
ESIL
N/A
TD18
C19631
Robust Flight Control System Design, Verification and Validation Framework
450
C
N/A
TD05
T406-023EE
Re-entry Vehicle Communications Technology
300
C
N/A
TD06
Intended
T417-025MP
Development of an innovative validation strategy of gas-surface interaction modelling for
re-entry applications.
300
C(3)
N/A
TD18
Intended
T418-028MP Extra light nozzle extension for upper stage engine and in space propulsion
400
C(2)
N/A
TD19
Proposed
T405-001EC
On-line System Identification Technology
250
C
N/A
TD05
Proposed
T417-024MP
Damping derivatives assessment for hypersonic re-entry vehicles exhibiting high angle of
attack
400
C
N/A
TD18
Proposed
T418-029MP Battleship chamber for unsteady combustion process analysis
300
C
N/A
TD19
Proposed
T420-033MC Zero Boil Off propulsion system feasibility demonstration
300
C
N/A
TD21
Total 4-03 - Generic Space Transportation Technologies
5 - Telecommunications
5 - Telecommunications
Page 9 of 27
100
350.00
3,100.00 1,250.00
TRP Work Plan 2008-2010
TEC-SB/7934/dc
Complete List of Activities
22/Jun/09
5 - Telecommunications
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
Y2007
Contracted
T506-003ET
Study of high order modes and fringing fields in Multipactor effect
Y2007
Contracted
T516-016MM Interchip-Optical Communciations and Photonic PCBs for next gereration OBP
Y2007
Contracted
T516-016MM Interchip-Optical Communciations and Photonic PCBs for next gereration OBP
Y2007
Contracted
T516-017MM Electro-Photonic ADC
Y2007
Intended
T504-001EE
Y2007
Intended
Y2007
C'try
Remarks
S/W
Clause
TD
Contract
Number
275
C
E
Aurora Software & Testing
N/A
TD06
C22368
200
C
F
Astrium
N/A
TD17
C22188
C
FIN
VTT
N/A
TD17
C21873
200
C
F
Thales Detexis
N/A
TD17
C22241
Slot Region radiation environment
200
C(1)
Operati
onal SW
TD04
T506-004ET
Widely-tunable MEMS LC tank for Wideband Oscillators
325
C
N/A
TD06
Intended
T506-005ET
High-Q MEMS resonator for high-performance oscillators
325
C(1)
N/A
TD06
Y2007
Intended
T506-006ET
Efficient Techniques for On-Board Processing
250
C
N/A
TD06
Y2007
Intended
T506-007ET
Reconfigurable multi-mission payload feasibility study
250
C
N/A
TD06
Y2007
Intended
T507-009EE
RF MEMS based reconfigurable telecommunication dual reflector antenna
500
C
N/A
TD07
Y2007
Intended
T507-011EE
Circular polarisation dual-optics proof-of-concept
350
C
N/A
TD07
Y2007
Intended
T507-012EE
Assessment of propagation modelling risk for Satcom system design
125
C
N/A
TD07
Y2007
Intended
T520-020MC
400
C
N/A
TD21
Y2008
Contracted
03/ETM-001
SAW Filter Development
N/A
TD06
Y2008
Intended
T506-008ET
Payload/system evaluation of beam hopping techniques
250
C
N/A
TD06
Y2008
Intended
T507-010EE
Self focussing retroreflective Tx Rx antennas for Mobile Terminal Applications
150
C
N/A
TD07
Y2008
Intended
T516-018MM Opto-microwave based front-end for a multi-beam large direct radiating array antenna
300
C
N/A
TD16
Y2008
Intended
T518-019MP
Electronic pressure regulator for Small GEO Electric and-cold gas propulsion system
applications
300
C(1)
N/A
TD19
Y2009
Intended
T506-009ET
Benefits of the introduction of GaN technology on an L- band GEO mobile payload
150
DN/S
N/A
TD06
Proposed
T506-002ET
Modelling and Design of Optimized Waveguide Components utilizing 3D Manufacturing
Techniques
275
C
Operati
onal SW
TD06
Proposed
T507-013EE
Combination of tropospheric and local environment propagation effects for MSS above 10Ghz
125
C(3)
N/A
TD07
Proposed
T507-014EE
Advanced propagation tool for satellite ATM & aeronautical communications
200
C(1)
Operati
onal SW
TD07
200
High conductive CFRP sandwich technologies for platforms
350
Page 10 of 27
DN/C
N
Norspace
(Anticipated, from
Preliminary Selection)
UK
Astrium
20002
TRP Work Plan 2008-2010
TEC-SB/7934/dc
Complete List of Activities
22/Jun/09
5 - Telecommunications
IPC
Status as of
Approval 02/06/2009
Proposed
TRP Ref.
T507-015EE
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
Compact Low-mass global antennas
350
Total 5 - Telecommunications
550.00
4,550.00
C'try
Remarks
C
S/W
Clause
TD
N/A
TD07
Contract
Number
950.00
6 - Navigation
6 - Navigation
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
C'try
Remarks
S/W
Clause
TD
Contract
Number
Y2007
Contracted
T606-006ET
Real time ODTS Algorithms for navigation satellites
150
C(3)
E
Un. Polit. Catalunya
N/A
TD06
22045
Y2007
Contracted
T606-006ET
Real time ODTS Algorithms for navigation satellites
150
C(3)
P
Deimos Engenharia
N/A
TD06
21973
Y2007
Contracted
T612-011MM Demonstration of optical clocks based on cryogenic resonators
250
C(1)
UK
NPL
N/A
TD12
Y2007
Intended
T604-001EE
Highly miniaturized active MEO radiation monitor Ph.A-B
250
C
Combined ITT for
T704-027 & T604-001EE
N/A
TD04
Y2007
Intended
T606-005ET
Peer2peer positioning
250
C(1)
Operati
onal SW
TD06
Y2007
Intended
T606-007ET
Design and pre-development of Techniques and Technologies for Payload Autonomous
integrity monitoring
300
C
N/A
TD06
Y2007
Intended
T606-008ET
Advanced signal-in-space Techniques (Mod, Cod, Message)
250
C(3)
N/A
TD06
Y2007
Intended
T606-009ET
Autonomous on-board timing reference
200
C
N/A
TD06
Y2007
Intended
T607-010EE
Assessment techniques of tropospheric effects for local augmentation systems
200
C(3)
N/A
TD07
Y2007
Intended
T616-012MM Applications of optical-quantum links to GNSS
300
C(2)
N/A
TD16
Y2007 /
Y2008
Deleted
T604-003EE
N/A
TD04
Y2007 /
Y2008
Intended
T604-002EE
Dose enhancement in high electron environment as source of under-prediction
Energetic electron shielding, charging and radiation effects and reduction of margins
Page 11 of 27
150
C(1)
700
C(1)
Deleted (merged to
T604-002EE).
(Open Source for Physics
models).
Operati
Merge of T604-002EE,
onal SW
T604-003EE (now
deleted), T704-028EE
(now deleted).
TD04
TRP Work Plan 2008-2010
TEC-SB/7934/dc
Complete List of Activities
22/Jun/09
6 - Navigation
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
C'try
Remarks
S/W
Clause
TD
Contract
Number
Y2008
Contracted
T606-004ET
Innovative algorithms for multi-system Precise Point Positioning
193
C(2)
E
Un. Polit. Catalunya
N/A
TD06
C21799
Y2008
Contracted
T606-004ET
Innovative algorithms for multi-system Precise Point Positioning
250
C(2)
UK
Nottingham Scientific
N/A
TD06
C21857
Y2009
Intended
T612-013GS
Optical cavity cryo resonator breadboard for ground optical clocks
C(1)
N/A
TD12
Y2009
Intended
T616-013ET
Advanced receiver architectures
250
C
N/A
TD06
Y2009
Intended
T616-014ET
Enhancement of GALILEO system robustness exploiting Signal-of Opportunity
300
C
N/A
TD26
Y2009
Intended
T616-015ET
GaN Power stage based on European technology for Navigation SSPA in L-Band
500
C(2)
N/A
TD06
Y2009
Intended
T616-016GS
Development, integration and test of critical ground optical clocks elements
C(1)
N/A
TD12
Remarks
S/W
Clause
TD
T701-012ED +
T701-103ED single ITT
and contract.
N/A
TD01
Total 6 - Navigation
250
400
893.00
3,350.00 1,050.00
7 - Generic Technology and Techniques
7-01 - On-board Data Systems
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
C(1)
Contract
Number
AC
Proposed
T701-012ED
Space internetworking protocols (Ph.1 of T701-012ED +T701-103ED)
Y2007
Contracted
T701-003ED
Demonstration test bed for efficient on board sensor networks - STEP 1
200
C
F
Astrium (F) + Acra Control
(IRL)
N/A
TD01
C21968
Y2007
Contracted
T701-003ED
Demonstration test bed for efficient on board sensor networks - STEP 1
200
C
I
Kaiser Italia + Thales
Alenia Space (I)
N/A
TD01
C21761
Y2007
Contracted
T701-003ED
Demonstration test bed for efficient on board sensor networks - STEP 1
200
C
I
Kayser Italia + Thales
Alenia Space (I)
N/A
TD01
C21761
Y2007
Intended
T701-004ED
Techniques for radiation effects mitigation in ASICs and FPGAs
100
C(1)
N/A
TD01
Y2007
Intended
T701-005ED
High capacity, high speed IC test system for automatic fault injection and analysis
(FT-UNSHADES2)
150
DN/C
N/A
TD01
Y2007
Intended
T701-007ED
European DSP Trade-off and Definition Study
200
C
N/A
TD01
Page 12 of 27
100
C'try
E
AICIA-GTE / University of
Seville
TRP Work Plan 2008-2010
TEC-SB/7934/dc
Complete List of Activities
22/Jun/09
7-01 - On-board Data Systems
IPC
Status as of
Approval 02/06/2009
Y2007
Intended
TRP Ref.
T701-011ED
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
Security architecture for command and control
75
350
Remarks
S/W
Clause
TD
C
N/A
TD01
DN/S
SciSys
Open
Source
TD01
C(2)
N/A
TD01
C'try
Y2007
Intended
T701-014ED
SOIS proof of concept
Y2008
Deferred
T701-002ED
Demonstration test bed for a secure TMTC system - step 1/Securing space communications –
Cryptographic line replaceable units
Y2008
Intended
T701-010ED
SpaceWire Evolutions
150
C
N/A
TD01
Y2008
Intended
T701-013ED
SOIS interfacing to PUS
75
C
N/A
TD01
Proposed
T701-001ED
PowerLink : Two- wire Power and Data Link
250
C
N/A
TD01
Proposed
T701-006ED
Asynchronous design in space IC (Phase1): Methods, tools, design
200
C(1)
N/A
TD01
Proposed
T701-008ED
European DSP Application Development Environment and Software Libraries
200
C
Open
source
TD01
Proposed
T701-009ED
SpaceWire Backplane
100
C
N/A
TD01
Remarks
S/W
Clause
TD
C(1)
Merge of T702-018SW +
T607-08EM. Unique ITT.
Compulsory
subcontractors (Astrium
and TAS, 20% each).
Operati
onal SW
TD02
Merge of T702-018SW +
T607-08EM. Unique ITT.
Compulsory
subcontractors (Astrium
and TAS, 20% each).
Operati
onal SW
TD02
Total 7-01 - On-board Data Systems
300
600.00
UK
Contract
Number
1,200.00 1,050.00
7-02 - Space System Software
IPC
Status as of
Approval 02/06/2009
AC
Proposed
TRP Ref.
T607-08EM
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
Standardisation and Building Blocks: Standardisation watch and verification
245
C'try
Contract
Number
AC
Proposed
T702-018SW Interface Standardisation verification by data modeling
245
C(1)
Y2007
Contracted
T702-015SW Schedulability analysis techniques and tools for cached processors
250
C(2)
I
Un. Padova
N/A
TD02
C22167
Y2008
Contracted
T702-016SW Complexity, cost and change impact based on models
C(2)
E
GMV
N/A
TD02
C22133
Proposed
T702-017SW Development environment for future DSP/multicore
250
DN
F / UK
/P
Consortium AdaCore,
Aonix, Edisoft // (GNU
S/W reuse)
Open
Source
TD02
Proposed
T702-019SW Dependability design/approach for critical flight software
250
C
N/A
TD02
250
Page 13 of 27
TRP Work Plan 2008-2010
TEC-SB/7934/dc
Complete List of Activities
22/Jun/09
7-02 - Space System Software
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
Total 7-02 - Space System Software
250.00
740.00
C'try
Remarks
S/W
Clause
TD
Contract
Number
C'try
Remarks
S/W
Clause
TD
Contract
Number
C
F
Astrium
N/A
TD03
C21814
500.00
7-03 - Spacecraft Power
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
Y2007
Contracted
T703-021EP
High Power Battery - Supercapacitor system study
200
Y2007
Contracted
T703-022EP
Carbon Nanofibres for advanced Lithium-Ion Batteries
125
C
D
Futurecarbon
N/A
TD03
C22194
Y2007
Contracted
T703-023EP
Further Advanced Lithium Cell development
350
C(1)
F
CEA
N/A
TD03
C22245
Y2007
Intended
T703-026EP
Solar cell development based on nano technology for new materials
300
C(1)
N/A
TD03
Y2008
Intended
T703-020EP
Investigations on avoidance of Solar Array thermal/electrical unbalance in power systems
equipped with Maximum Power Point Tracker interface.
350
C
N/A
TD03
Y2008
Intended
T703-024EP
Development of Next Generation triple junction Cells & SCAs
500
DN/C
N/A
TD03
Proposed
T703-025EP
Manufacturing Technologies of ultra-thin GaAs based solar cells
N/A
TD03
Total 7-03 - Spacecraft Power
700
200.00
1,625.00
D
AZUR Solar, ISE (D) +
Umicore (B)
C(1)
700.00
7-04 - Spacecraft Environment & Effects
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
C'try
Remarks
S/W
Clause
TD
Contract
Number
D
Un. Bielefeld
Operati
onal SW
TD04
C21928
Y2007
Contracted
T704-030EE
Update of meteoroid flux model
100
C(3)
Y2007
Deleted
T704-028EE
Reduction of margins in radiation analysis
150
C
Deleted (merged to
T604-002EE).
N/A
TD04
Y2007
Intended
T704-027EE
Highly miniaturised radiation monitoring
200
C(1)
Combined ITT for
T704-027 & T604-001EE
N/A
TD04
Y2007
Intended
T704-029EE
Simplified standard MEO/GEO tools for spacecraft charging
150
C
Open
source
TD04
Total 7-04 - Spacecraft Environment & Effects
250.00
Page 14 of 27
350.00
TRP Work Plan 2008-2010
TEC-SB/7934/dc
Complete List of Activities
22/Jun/09
7-05 - Space System Control
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
C'try
Remarks
S/W
Clause
TD
Contract
Number
Y2007
Contracted
T705-033EC
Feasibility of GNSS sensors for AOCS applications in GEO and higher altitudes
200
C
D
Astrium
N/A
TD05
C21953
Y2007
Contracted
T705-033EC
Feasibility of GNSS sensors for AOCS applications in GEO and higher altitudes
200
C
p
Deimos Engenharia
N/A
TD05
C21954
Y2007
Contracted
T705-036EC
Mathematical Optimisation Methods for Concurrent Early Design of Trajectories, Propulsion,
and Aerothermodynamics
150
C
D
Astos Solutions
N/A
TD05
C22047
Y2007 /
Y2008
Contracted
T705-034EC
Active and passive disturbance isolation for high accuracy control systems
350
C
F
Budget increased
N/A
TD05
C21983
Y2007 /
Y2008
Contracted
T705-035EC
Versatility of Filtering Techniques in Non-Linear Programming Optimization
150
DN/S
UK
U. Birmingham
N/A
TD05
C22170
Y2007 /
Y2008
Intended
T705-037EC
Enhanced LFT Toolbox
250
C(1)
Budget increased
Open
Source
TD05
Y2008
Intended
T705-032EC
Accelerometer for IMU feasibility demonstrator
400
C(1)
N/A
TD05
Y2008
Intended
T705-038EC
Maturation of Robust LPV Techniques
250
C(2)
N/A
TD05
Y2009
Intended
T603-04ES
Robust Model Predictive Control (MPC) for Space Constrained Systems
400
C
Deleted
T705-039EC
Space MPC-On-a-Chip Building Blocks
Proposed
T705-031EC
Star Tracker on a chip pre-development (Phase 1)
Total 7-05 - Space System Control
550.00
1,800.00
0
C
200
C(1)
Budget increased (original
Operati
activity approval:
onal SW
ESA/IPC(2006)3, add.4)
Deleted
TD05
N/A
TD05
N/A
TD05
200.00
7-06 - RF Payload Systems
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
Y2006 /
Y2008
Intended
T603-40ET
Evaluation and validation of electromagnetic software, test facilities and test standards in
Europe to predict and test RF breakdown and passive intermodulation (PIM)
530
DN/S
Y2007
Intended
T706-040ET
Cryptographic Pseudo-noise codes and related acquisition techniques for direct sequence
spread spectrum transponders
300
C
Page 15 of 27
C'try
Remarks
S/W
Clause
TD
F
Budget increased / PP
change.
CNES + subco's (Astrium
(F), Thales Alenia Space
(F), Saab Ericsson Space
(S), UAM (E), Aurorasat
(E), TESAT (D) +
COMDEV (UK), Uni.
Valencia (E), UPV (E),
ONERA (F), CSIC (E), Uni.
Darmstadt (D), Uni.
Chalmers (S), Intespace
(F), Rymsa (E))
N/A
TD06
N/A
TD06
Contract
Number
TRP Work Plan 2008-2010
TEC-SB/7934/dc
Complete List of Activities
22/Jun/09
7-06 - RF Payload Systems
IPC
Status as of
Approval 02/06/2009
Y2008
Y2008
Intended
Intended
TRP Ref.
T706-041ET
T706-186ET
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
Wireless integrated communications and navigation system for formation flying missions
250
Millimetre-wave measurements at MilliLab
Total 7-06 - RF Payload Systems
S/W
Clause
TD
N/A
TD06
N/A
TD06
Remarks
S/W
Clause
TD
Contract
Number
C'try
Remarks
FIN
Millilab, 2008-2012 frame
contract
C'try
C
300
150
1,380.00
150.00
DN/C
Contract
Number
7-07 - Electromagnetics Technology
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
Y2007
Contracted
T707-042EE
Electromagnetic field prediction tool for solar panels
200
C(1)
F
Ginkgo Solutions
N/A
TD07
C22099
Y2007
Contracted
T707-045EE
Advanced grounding rail concepts for satellite applications
150
C
D
HPS
N/A
TD07
C21974
Y2007
Contracted
T707-047EE
Feasibility of Very Large Effective Receiving Antenna Aperture in Space
150
C
NL
Astron
N/A
TD07
C22108
Y2007
Intended
T707-048EE
Design study for precision microwave radiometer in ESA Ground stations
C
N/A
TD07
Proposed
T707-043EE
Advanced shielding techniques for spacecraft harness
150
C
N/A
TD07
Proposed
T707-044EE
Reverberating chambers
100
C
N/A
TD07
Proposed
T707-046EE
Polarimetric (sub)millimeter wave antenna architectures
200
C
N/A
TD07
Total 7-07 - Electromagnetics Technology
100
500.00
100.00
450.00
7-08 - System Design & Verification
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
C'try
Remarks
S/W
Clause
TD
Contract
Number
Y2007
Contracted
T708-049SW Space Simulation Reference Architecture
400
C(2)
D
Vega IT
Operati
onal SW
TD08
C21804
Y2007
Contracted
T708-050SW Conformance Kit
200
C
B
Spacebel
Operati
onal SW
TD08
C22107
Y2008
Intended
T708-051SW Automatic generation of database MMI from a domain ontology
250
C(1)
N/A
TD08
Y2008
Intended
T708-052SW Automation of space system test data collecting, processing and reporting
200
C
N/A
TD08
Page 16 of 27
TRP Work Plan 2008-2010
TEC-SB/7934/dc
Complete List of Activities
22/Jun/09
7-08 - System Design & Verification
IPC
Status as of
Approval 02/06/2009
Y2008
Y2008
Intended
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
T708-053SW Tools from non-space domains to support space system testing
Intended
200
T708-185SW Autocoding for PUS and satellite database
300
Total 7-08 - System Design & Verification
600.00
S/W
Clause
TD
C
N/A
TD08
C
Open
source
TD08
S/W
Clause
TD
Operati
onal SW
TD09
Operati
onal SW
TD09
C'try
Remarks
Contract
Number
950.00
7-09 - Mission operation and Ground Data Systems
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
C'try
Remarks
Y2007
Intended
T709-057GI
Suitability of emerging service based technologies in ground data systems
250
C
Y2008
Intended
T709-054GI
European Technology Harmonisation on Ground Systems Software - Phase 2 - Second set of
standard interfaces
400
C(1)
Y2008
Intended
T709-055GI
Flight Control Team Multi-Agent System
300
C(1)
N/A
TD09
Y2008
Intended
T709-056GI
Linux and multi-core processor technology for simulators
200
C(1)
Operati
onal SW
TD09
Total 7-09 - Mission operation and Ground Data Systems
P
Contract
Number
1,150.00
7-10 - Flight Dynamics and GNSS
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
Y2007
Contracted
T710-058GF
Interactive Design of Interplanetary Trajectories
225
Y2008
Contracted
T710-059GF
GNSS contribution to next generation global ionospheric monitoring
Total 7-10 - Flight Dynamics and GNSS
225
225.00
C'try
Remarks
S/W
Clause
TD
Contract
Number
C
E
GMV
Operati
onal SW
TD10
C22061
C(1)
D
EDS Operation Services
Operati
onal SW
TD10
C22267
C'try
Remarks
S/W
Clause
TD
Contract
Number
N/A
TD11
225.00
7-11 - Space Debris
IPC
Status as of
Approval 02/06/2009
Y2007
Intended
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
T711-061GR Preliminary design and analysis of new generation space debris cameras
Page 17 of 27
150
C
TRP Work Plan 2008-2010
TEC-SB/7934/dc
Complete List of Activities
22/Jun/09
7-11 - Space Debris
IPC
Status as of
Approval 02/06/2009
Y2008
Intended
Proposed
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
T711-062GR Development and simulation of strategies for the detection and tracking of MEO objects
180
T711-060GR Space Debris Stare and Chase
120
Total 7-11 - Space Debris
330.00
S/W
Clause
TD
C(3)
Operati
onal SW
TD11
DN/S
TD11
C'try
Remarks
Contract
Number
D
FGAN
Operati
onal SW
C'try
Remarks
S/W
Clause
TD
Contract
Number
120.00
7-12 - Ground Station Systems and Networks
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
Y2007
Contracted
T712-064GS
New and improved cryocooler technologies for deep space antennas cryogenic sub system
270
C(1)
F
Callisto
N/A
TD12
C22065
Y2008
Contracted
T712-063GS
Study on the architecture for the next generation of ESA TT&C processors
500
C(2)
UK
BAE
Operati
onal SW
TD12
C21707
Y2008
Intended
T712-065GS
Feasibility and breadboarding of a multiple frequency cryogenic receiver
N/A
TD12
Total 7-12 - Ground Station Systems and Networks
180
770.00
C(1)
180.00
7-13 - Automation, Telepresence & Robotics
IPC
Status as of
Approval 02/06/2009
Y2007
Contracted
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
T713-066MM Multi wafer hybrid integration: Robotics IMU I
350
Total 7-13 - Automation, Telepresence & Robotics
DN/S
C'try
Remarks
S/W
Clause
TD
Contract
Number
S
Angstrom Aerospace
Corp. (AAC) (S) / SEA
(UK)
N/A
TD13
C22236
C'try
Remarks
S/W
Clause
TD
Contract
Number
N/A
TD14
350.00
7-14 - Life & Physical Sciences Instrumentation
IPC
Status as of
Approval 02/06/2009
Y2008
Intended
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
T714-067MM High Temperature Sensors with self calibrating capabilities
350
Total 7-14 - Life & Physical Sciences Instrumentation
Page 18 of 27
350.00
C(1)
TRP Work Plan 2008-2010
TEC-SB/7934/dc
Complete List of Activities
22/Jun/09
7-15 - Mechanisms & Tribology
IPC
Status as of
Approval 02/06/2009
Y2007
Intended
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
T715-068MM European Space Tribology Laboratory Technology Application Programme
Total 7-15 - Mechanisms & Tribology
400
200
400.00
200.00
DN/C
C'try
Remarks
S/W
Clause
TD
Contract
Number
UK
ESR Technology (ESTL),
Phased contract
N/A
TD15
19959
C'try
Remarks
S/W
Clause
TD
Contract
Number
N/A
TD16
S/W
Clause
TD
N/A
TD17
S/W
Clause
TD
7-16 - Optics
IPC
Status as of
Approval 02/06/2009
Y2007
Intended
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
T716-070MM Innovative Technologies for Large Deployable Optical Telescopes
350
Total 7-16 - Optics
350.00
C
7-17 - OptoElectronics
IPC
Status as of
Approval 02/06/2009
Proposed
TRP Ref.
T716-069MM
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
Use of the Novel Modelocked Semiconductor Lasers technique in the Sub-Picosecond
Regime for Space Missions
350
Total 7-17 - OptoElectronics
C'try
Remarks
C
Contract
Number
350.00
7-18 - Aerothermodynamics
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
C'try
Remarks
Y2008
Intended
T717-071MP Laminar to Turbulent transition in hypersonic flow
250
C
N/A
TD18
Y2008
Intended
T717-072MP Multi-phase aspects in propulsion systems
250
C(1)
N/A
TD18
Total 7-18 - Aerothermodynamics
500.00
7-19 - Propulsion
Page 19 of 27
Contract
Number
TRP Work Plan 2008-2010
TEC-SB/7934/dc
Complete List of Activities
22/Jun/09
7-19 - Propulsion
IPC
Status as of
Approval 02/06/2009
Y2007
Contracted
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
T718-076MP Surface tension PMD for low-fill fraction and horizontal transportation
Y2007 /
Y2009
Intended
Y2008
Contracted
Y2008
Intended
T718-075MP
Y2008
Intended
T718-077MP Throttable Flow Control Valves for Spacecraft class thrusters
Proposed
T718-074MP Development of a Hollow Cathode Thruster
100
C
C'try
F
Remarks
S/W
Clause
TD
Contract
Number
C22075
Astrium
N/A
TD19
Approval of SW clause
(activity originally
approved with no SW
clause, ESA/IPC(2007)3,
add.3)
Open
source
TD19
Snecma
N/A
TD19
T718-073MP Assessment of the interaction between spacecraft and electric propulsion systems
400
C
T718-078MP Performance characterisation of aged Hall Effect thrusters
200
C(1)
225
C(2)
N/A
TD19
350
C(1)
N/A
TD19
C(1)
N/A
TD19
S/W
Clause
TD
Preliminary characterization test campaign of Electric Propulsion technology with non
conventional propellants.
225
Total 7-19 - Propulsion
1,275.00
F
C22129
225.00
7-20 - Structures & Pyrotechnics
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
C'try
Remarks
Y2007
Intended
T719-079MC Mechanical design and verification methodologies for ceramic structures
300
C(2)
N/A
TD20
Y2007
Intended
T719-081MC Verification of New Sources of Composite Materials for Spacecraft Structures Applications
250
C
N/A
TD20
Y2007
Intended
T719-082MC Innovative curing systems for polymerisation in space
300
C
N/A
TD20
Y2008
Contracted
T719-084MC Vulnerability of spacecraft equipment against space debris impacts
300
DN/C
D
FHG
N/A
TD20
Y2008
Intended
T601-50MC
350
DN/C
F
Astrium (F) + CSL (B) +
Astrium (D)
N/A
TD20
Y2008
Intended
T719-083MC Methodology for analysis of structural born micro-vibration
400
C
N/A
TD20
Proposed
T719-080MC Self-Deploying Structures PHASE-1 : Concepts and Tools
C
N/A
TD20
Advancement in Thermo-Elastic Distortion Verification Methods for Spacecraft Structures
(Phase 2)
250
Total 7-20 - Structures & Pyrotechnics
1,900.00
7-21 - Thermal
Page 20 of 27
250.00
Contract
Number
C22372
TRP Work Plan 2008-2010
TEC-SB/7934/dc
Complete List of Activities
22/Jun/09
7-21 - Thermal
IPC
Status as of
Approval 02/06/2009
Y2007
Contracted
Y2007
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
C'try
Remarks
S/W
Clause
TD
Contract
Number
F
Astrium
N/A
TD21
C22373
T720-085MC Innovative Analysis Methods for Improved Thermal Testing
300
C
Intended
T720-089MC Linear Fluid Pump
200
C(1)
N/A
TD21
Y2007
Intended
T720-090MC Thermo-Electric Cooler
300
C(1)
N/A
TD21
Y2008
Intended
T720-086MC Integrating the Finite Element Method into the Space Thermal Analysis Process
150
C
N/A
TD21
Y2008
Intended
T720-088MC Small Scale Cooler
300
C(1)
N/A
TD21
Y2008
Intended
T720-092MC Heat Pump conceptual study and design
200
C
N/A
TD21
Proposed
T720-087MC Thermal-radiative analysis of systems with wavelength dependent thermo-optical surfaces
100
C(3)
N/A
TD21
Proposed
T720-091MC Extra Flat Mini Two-Phase Loop
200
C(1)
N/A
TD21
Total 7-21 - Thermal
1,450.00
300.00
7-24 - Materials & Processes
IPC
Status as of
Approval 02/06/2009
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
TRP Ref.
Title
Stress Corrosion Testing of Particle Metal Matrix Composite (PMMC) and Friction Stir Welded
(FSW) of Particle Metal Matrix Composite (PMMC) Materials
Y2007
Contracted
T723-094QM
Y2007
Contracted
T723-095QM Carbon Nano Fibre based material for high conductivity
Y2007
Contracted
T723-096QM Coefficient of Thermal Expansion (CTE) variation of thermally stable materials
Y2008
Intended
150
T723-093QM Gecko mimetic Tape as new joining technology.
Total 7-24 - Materials & Processes
150.00
C'try
Remarks
S/W
Clause
TD
Contract
Number
100
C
UK
Aerospace Metal
Composites
N/A
TD24
C22195
199
C(1)
UK
Un. Cambridge
N/A
TD24
C22116
90
C
B
Un. Liege
N/A
TD24
C21975
200
C(3)
N/A
TD24
S/W
Clause
TD
N/A
TD05
589.00
7-26 - Spacecraft Avionic System
IPC
Status as of
Approval 02/06/2009
-
Deleted
TRP Ref.
T705-113EC
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
Anytime Monitoring and Control
300
Page 21 of 27
C
C'try
Remarks
Contract
Number
TRP Work Plan 2008-2010
TEC-SB/7934/dc
Complete List of Activities
22/Jun/09
7-26 - Spacecraft Avionic System
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
C'try
Remarks
S/W
Clause
TD
T701-012ED +
T701-103ED single ITT
and contract.
N/A
TD01
Contract
Number
AC
Proposed
T701-103ED
Delay Tolerant Networking prototyping (Ph.2 of T701-012ED +T701-103ED)
200
C(1)
Y2007
Contracted
T701-099ED
Spacecraft Controller on Chip (SCOC3) ASIC manufacturing & test
600
DN/C
F
EADS-Astrium
N/A
TD01
C22358
Y2007
Contracted
T702-105SW Guidelines for the selection of architectures
C
F
Astrium(F)
N/A
TD02
C22105
Y2007
Contracted
T706-114ET
Securely Partitioning Spacecraft Computing Resources
250
C
F
Astrium
Operati
onal SW
TD06
C22280
Y2007
Contracted
T706-114ET
Securely Partitioning Spacecraft Computing Resources
250
C
UK
Scisys
Operati
onal SW
TD06
C22186
Y2007
Contracted
T709-115GI
Ground Segment Data System Architecture to support CFDP, Bundle Protocol & IP
300
C
UK
Scisys
Operati
onal SW
TD09
C22183
Y2007
Deleted
T705-112EC
FDIR using Model Predictive Control
Deleted (replaced by
T705-185EC)
N/A
TD05
Y2007
Intended
T701-098ED
Requirements Definition for On Board Data Systems and software for end to end security
Y2007
Intended
Y2007
Intended
Y2007
Intended
T709-116GI
Y2007
Intended
T710-118GF
Y2008
Intended
Y2008
150
400
C
150
C
N/A
TD01
T702-110SW HW-SW Codesign
250
C
N/A
TD02
T702-111SW Full Model Driven Development for o/b software
300
C
Open
source
TD02
Global Security: The Ground Component
250
C
Operati
onal SW
TD09
Concepts for common utilisation of advanced emulation and validation tools
250
C
Operati
onal SW
TD10
T702-104SW Software Reference Architecture implementation prototype
300
C
Operati
onal SW
TD02
Intended
T702-107SW System impact of distributed multicore systems
250
C
N/A
TD02
Y2008
Intended
T702-108SW Verification of failure impact by model checking
200
C
Operati
onal SW
TD02
Y2008
Intended
T702-109SW Spacecraft Controller on Chip (SCOC3) software support
250
C
Open
Source
TD02
Y2008
Intended
T705-185EC
AOCS unit simulation models
450
C
N/A
TD05
Y2008
Intended
T709-121GI
Ground Segment Data Systems Plug & Operations
300
C
Operati
onal SW
TD09
Y2008
Intended
T710-120GF
New concepts for relative navigation at planetary approach
300
C
Operati
onal SW
TD10
Y2008
Proposed
T705-113EC
Mathematical Library for On-board AOCS Algorithms
250
C
Operati
onal SW
TD05
Proposed
T701-097ED
Reference Architecture for High Reliability - Availability systems
400
C
N/A
TD01
Proposed
T701-100ED
Network Discovery Protocols
200
C
N/A
TD01
Page 22 of 27
(GNU S/W reuse)
Replaces T705-112EC.
TRP Work Plan 2008-2010
TEC-SB/7934/dc
Complete List of Activities
22/Jun/09
7-26 - Spacecraft Avionic System
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Proposed
T701-101ED
Proposed
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
Avionics System Integration and Validation
C'try
Remarks
S/W
Clause
TD
400
C(1)
N/A
TD01
T702-106SW Functional requirements and verification techniques for the software reference architecture
350
C
N/A
TD02
Proposed
T710-117GF
Flight Dynamics Components for Rapid Support System Generation
200
C
Operati
onal SW
TD10
Proposed
T710-119GF
Common concepts and components for environmental modelling
200
C
Operati
onal SW
TD10
Total 7-26 - Spacecraft Avionic System
550.00
Contract
Number
4,850.00 2,300.00
7-27 - End to End System Design Processes
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
C'try
Remarks
S/W
Clause
TD
Contract
Number
Y2007
Contracted
T708-127EE
Model-based System Engineering components of antennas
400
C
I
Satimo
Operati
onal SW
TD08
C21961
Y2007
Contracted
T709-130GI
Knowledge Capturing, Transfer and Recovery
300
C
UK
Logica CMG
Operati
onal SW
TD09
C22058
Y2007
Intended
T708-122MC
Next generation requirements engineering as a basis for MBSE and E2E performance
analysis
C(2)
Operati
onal SW
TD08
TD08
400
Y2007
Intended
T708-126SY
Space instrument design modelling
400
C
Operati
onal SW
Y2007
Intended
T709-132GI
Model Based Operations Validation System
450
C(2)
Operati
onal SW
TD09
Y2008
Contracted
T708-133TC
Portable Virtual AIT Visualiser
400
C(1)
Space Application
Services
Operati
onal SW
TD08
Y2008
Deferred
T709-131GI
Collaborative Environment for Space Systems Engineering
Deferred in favour of
T709-056GI (awaiting for
another study results)
Operati
onal SW
TD09
Y2008
Intended
T708-124MC
Simple interface for near real-time provision of EGSE sensor data to tools of other
engineering domains
250
C(1)
Operati
onal SW
TD08
Y2008
Intended
T708-125SY
Global CE infrastructure for Space Project Lifecycle
250
C(1)
N/A
TD08
Y2008
Intended
T708-128EE
Innovative RF testing approaches for reduced antenna/payoload AIT/AIV
250
C
N/A
TD08
Y2008
Intended
T708-129EE
Innovative EMI/EMC testing and modelling approaches for full development cycle support and
reduced AIT/AIV
250
C
N/A
TD08
Y2008
Intended
T708-134SW Low Cost Functional System Qualification Testbench and Electrical AIT
600
C(2)
N/A
TD08
Proposed
T708-123MC System to Discipline Integration Layer
C(2)
N/A
TD08
450
500
Page 23 of 27
C(2)
B
C22149
TRP Work Plan 2008-2010
TEC-SB/7934/dc
Complete List of Activities
22/Jun/09
7-27 - End to End System Design Processes
IPC
Status as of
Approval 02/06/2009
Proposed
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
T708-135SW Model Based System Tools Integration
600
Total 7-27 - End to End System Design Processes
700.00
C'try
Remarks
C(2)
S/W
Clause
TD
Open
Source
TD08
Contract
Number
3,250.00 1,550.00
7-28 - Electronic Components
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
75
C'try
Remarks
S/W
Clause
TD
Contract
Number
DN/S
F
EADS-Astrium
N/A
TD23
C22112
Y2007
Contracted
T722-137QC Evaluation of new assembly methods of IGBT dice on hybrids
Y2007
Contracted
T722-143QC
Utilisation of a Heavy and Light Ion Facility at UCL for Component Radiation Studies (Time
period 2008-2012)
180
180
180
DN/S
B
UCL Louvain-la-Neuve
(HIF/LIF) // Frame
Contract
N/A
TD23
C12471
Y2007
Contracted
T722-144QC
Utilisation of the High Energy Heavy Ion Test Facility at JYFL for Component Radiation
Studies (Time period 2008-2012)
120
120
120
DN/S
FIN
JYFL (HIF)
N/A
TD23
18197??
??
Y2007
Contracted
T722-145QC
Utilisation of the Proton Irradiation Facility at PSI for Component Radiation Studies (Time
period 2008-2012)
120
120
120
DN/S
CH
PSI (PIF) // Frame
Contract
N/A
TD23
C18465
Y2007
Contracted
T722-146QC MTSL Laboratory Test Service
75
75
75
DN/S
IRL
NMRC (MTSL)
N/A
TD23
10582
Y2007
Contracted
T722-158QC Avoidance of MEMS dielectric charge trapping
150
C
F
Xlim
N/A
TD23
C22081
Y2007
Intended
T722-138QC Evaluation Of Junction Temp reduction techniques on metal ceramic substrate
100
C
N/A
TD23
Y2007
Intended
T722-139QC Very high dissipative RF/LF package
175
C
N/A
TD23
N/A
TD23
Y2007
Intended
T722-142QC SMT Evaluation of LCC and micro-BGA packages on LTCC boards
100
DN/C
Y2007
Intended
T722-147QC Enabling of Ultra short gate length commercial MMIC process
265
C(1)
N/A
TD23
Y2007
Intended
T722-148QC Laser diode reliability study, derating and optimization of screening and qualification
250
C
N/A
TD23
Y2007
Intended
T722-154QC Radiation Testing Methodology's for FLASH Memories
150
DN/S
I
Un. Padova
N/A
TD23
Y2007
Intended
T722-155QC Radiation Assessment of Deep Submicron CMOS Devices
250
DN/S
B
IMEC
N/A
TD23
Y2007
Intended
T722-156QC TID characterization of power-up behaviour for FPGAs
100
C
N/A
TD23
Y2007
Intended
T722-157QC
150
DN/S
N/A
TD23
Y2007
Intended
T722-161QC RF potentialities of Carbon nanotubes for nanoscale interconnections
125
C
N/A
TD23
Development of 2-D imaging devices (CCD, APS, etc.) displacement damage test guideline First Assessment
Page 24 of 27
I
Thales Alenia Space
(TAS)
UK
SSTL
19135
????
TRP Work Plan 2008-2010
TEC-SB/7934/dc
Complete List of Activities
22/Jun/09
7-28 - Electronic Components
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
Y2007
Intended
T722-162QC Hot Vias MMICs
70
Y2007
Intended
T722-163QC Evaluation of new FPGA technologies (hardened-SRAM, Flash, mixed-signal)
Y2007/Y2
008
Intended
T722-150QC High Temperature RF/Microwave interconnection
Y2008
Intended
T703-136EP
Y2008
Intended
Y2008
300
Remarks
S/W
Clause
TD
D or F
?
TSAT (D) or UMS (F or D)
?
N/A
TD23
N/A
TD23
N/A
TD23
C
150
Study of mitigation techniques/optimisation for analogue circuits in space radiation
environment
DN
C'try
C
Deferred to 2010
300
C
N/A
TD03
T722-141QC Evaluation of high fatigue resistance of lead free solder
100
C(1)
N/A
TD23
Intended
T722-149QC Base metal electrode ceramic capacitors studies
100
C
Anticipated
N/A
TD23
Y2008
Intended
T722-151QC
Technology assessment of DRAM and advanced memory productsfollowing in from Radiation
test and benchmark of commercial products against space requirements.
400
C
Deferred
N/A
TD23
Y2008
Intended
T722-152QC
Reliability testing of Commercial Available Flash memories (Follow on from: Radaition
assessment of Commercial Flash)
150
C
Deferred
N/A
TD23
Y2008
Intended
T722-153QC Comparative Study of the PGS test as a relaibility assessment tool for MOSFET devices
150
C(1)
Deferred
N/A
TD23
Y2008
Intended
T722-159QC
150
C(1)
Deferred
N/A
TD23
Proposed
Influence of glob top thickness on reliability of GaAs dice and the successful application of the
T722-140QC
process.
200
C(1)
N/A
TD23
Proposed
T722-160QC Possible micro power sources and associated architectures
75
C
N/A
TD23
Development of standard test methods for Single Event Transient characterisation in CMOS
using FPGA as test vehicle
Total 7-28 - Electronic Components
495.00
4,035.00
Contract
Number
990.00
7-29 - NEOMEX
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
300
C'try
Remarks
S/W
Clause
TD
Contract
Number
C
UK
SEA
N/A
TD05
C22314
Y2007
Contracted
T705-167EC
Definition and sizing of AOCS for NEOMEX Nanosatellite
Y2007
Contracted
T707-171EE
Miniaturised multi-functional antenna system for micro/nano-satellites
250
C
CH
EPFL
N/A
TD07
C22014
Y2007
Contracted
T707-171EE
Miniaturised multi-functional antenna system for micro/nano-satellites
250
C
I
Ingegneria dei Sistemi
N/A
TD07
C22016
Y2007
Intended
T713-172MM Architect of the System-of-Microsystems nanospacecraft
200
C
N/A
TD13
Y2007
Intended
T713-173MM Standard modular microsystems interface definition and proof-of-concept
400
C(1)
N/A
TD13
Y2007
Intended
T720-181MC Micro heat management systems
200
C
N/A
TD21
Page 25 of 27
TRP Work Plan 2008-2010
TEC-SB/7934/dc
Complete List of Activities
22/Jun/09
7-29 - NEOMEX
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
C'try
Remarks
S/W
Clause
TD
Contract
Number
D
Azurspace Solar Power
N/A
TD03
C21858
C21835
Y2008
Contracted
T703-166EP
Very thin GaAs MJ solar cell development
500
C(2)
Y2008
Contracted
T705-168EC
Digital sun sensor on a chip prototyping
850
C(2)
N/A
TD05
Y2009
Intended
T701-164ED
Data handling system design and proof-of-concept for modular system-of-microsystems
approach
300
C(1)
N/A
TD01
Y2009
Intended
T703-165EP
Thin-film Lithium Batteries
300
C(1)
N/A
TD03
Y2009
Intended
T706-169ET
Transmitter Vacuum Electric Power Amplifier
500
C(1)
N/A
TD06
Y2009
Intended
T713-174MM Integrated harness technology
300
C(1)
N/A
TD13
Y2009
Intended
T718-176MP Medium delta-v, low-power, low-voltage microthruster module breadboarding
300
C(1)
N/A
TD19
Y2009
Intended
T719-178MC Multifunctional structure
200
C(1)
N/A
TD20
Y2009
Intended
T720-179MC Temperature-dependent thermal coatings
200
C(1)
N/A
TD21
Y2009
Intended
T722-182QC Connectivity and Packaging of systems-of-microsystems
400
C(2)
N/A
TD23
Y2009
Intended
T722-183QC Reliability and standardisation for systems-of-microsystems
200
C
N/A
TD23
Proposed
T706-170ET
400
C(1)
N/A
TD06
Proposed
T716-175MM Space instruments based on microtelescope array, proof-of-concept
500
C(1)
N/A
TD16
Proposed
T718-177MP Propellant management and storage module
300
C(1)
N/A
TD19
Proposed
T720-180MC Micro-phase-change materials
150
C(1)
N/A
TD21
Proposed
T723-184QM Advanced manufacturing methods for systems-of-microsystems nanospacecraft
250
C(1)
N/A
TD24
S/W
Clause
TD
N/A
TD22
Receiver low-power analogue decoder
Total 7-29 - NEOMEX
1,850.00 3,800.00 1,600.00
7-27 - Electronic Components
IPC
Status as of
Approval 02/06/2009
Y2009
Intended
TRP Ref.
T709-133QT
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
SEE Testing of european GaAs Technologies
200
Total 7-27 - Electronic Components
200.00
Page 26 of 27
C
C'try
Remarks
Contract
Number
TRP Work Plan 2008-2010
TEC-SB/7934/dc
Complete List of Activities
22/Jun/09
7-27 - Electronic Components
IPC
Status as of
Approval 02/06/2009
TRP Ref.
Budget 2008 Budget 2009 Budget 2010 Proc.
(K€)
(K€)
(K€)
Policy
Title
Page 27 of 27
C'try
Remarks
S/W
Clause
TD
Contract
Number
f
Chapter 3
TRP Work Plan 2008-2010
Descriptions of Activities
TEC-SB/7934/dc
22/Jun/09
TRP Work Plan 2008-2010
Description of Activities
1 - Earth Observation
1-01 - Microwave Payloads
TRP Reference:
T101-001ED
Title:
Digital Beam Forming Technological Elements
TD:
TD01
Objectives
Development and demonstration set of parametric IP cores to implement digital beamforming functions
Description
The digital beam forming techniques combine the signals from two or more sub-apertures into one signal. The
operations used here are signal scaling, time domain interpolation and summation. These operation would be
implemented in ASIC (or FPGA) technology in order to meet the processing speed at the optimum power
consumption. The required accuracy and precision greatly depends on the overall system design. In this activity a set
of basic parametric IP cores shall be developed which are able adapt to a wide range of applications by only choosing
the correct set of parameters. The function of these IP cares shall be demonstrated in a breadboard based on
commercial FPGA.
Deliverables:
parametric IP cores
Current TRL:
TRL 1
Target TRL:
TRL 3
Application/Mission: GMES 2nd generation, 2018
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
TRL5 by 2012
18 months
Dossier0 Ref.: T-8240
On-board Paylaod Data Processing - D2
TRP Reference:
T106-002ET
TD:
Title:
Integrated Circulators for TR modules
TD06
Objectives
Development and demonstration of integrated circulators at C and Ku band
Description
Circulators are essential parts of TR modules and receiver architecture where they perform important functions such
as TX/RX routing, isolating receiver modules from each other or providing good input matches to eliminate amplitude
ripples. Circulators are available as drop-in or connectorised components. Connectorised circulators are often not
compatible with today's requirement of compact receiver modules. Drop-in circulators are much more compact and
can be integrated in high density receiver modules but the integration is costly, high performance and repeatability
form unit to unit is difficult to achieve and multipaction risk is crucial. This is in particular true for TR modules where
from several hundreds up to thousands of modules are needed per antenna. These disadvantages can be overcome
by integrated circulators where the different material layers are collectively assembled using very cost competitive
LTCC technology. However this requires sintering temperatures to be compatible with the LTCC process
temperatures. Modifying standard ferromagnetic garnets, initial research resulted in promising ferromagnetic
properties employing sintering temperatures only 20% above the LTCC process temperatures with the potential to
obtain a good match.Hence goal of this activity is to develop and built a 20W C-band integrated circulator and a 10W
Ku-band integrated circulator demonstrate this enabling technology and fully evaluate the anticipated significant
manufacturing cost savings.
Deliverables:
Integrated C and Ku-band circulator breadboard
Current TRL:
TRL 1
Target TRL:
TRL 3
Application/Mission: GMES 2nd generation, 2018
N/A
SW Clause :
Page 1 of 217
Application
Need/Date:
Contract Duration:
TRL5 by 2012
24 months
Dossier0 Ref.: T-7736, T-8284
TEC-SB/7934/dc
22/Jun/09
TRP Work Plan 2008-2010
Description of Activities
Consistency with Harmonisation
Roadmap and Conclusions:
N/A
TRP Reference:
T106-003ET
TD:
TD06
Title:
Photo-HBV for sub-millimetre wave LO generation and distribution
Objectives
To design, realise and test a photo-HBV operating at frequencies beyond 100 GHz.
Description
Generating local oscillator at frequencies beyond 100 GHz is a challenge in many Earth Observation missions. This
usually realised with a relatively low frequency LO generation followed by a number of multipliers, ending up in a
rather narrow-band operation and pretty inefficient RF power conversion. Furthermore, the LO has to be implemented
very close to the receiver since “cable” losses are high at those frequencies. Microwave Photonics offers the
possibility of a tunable direct high frequency generation, with easy distribution via fibre, as demonstrated in the activity
102-05ET “Microwave Photonics Millimetre-wave Generation” of the TRP 2007 workplan. This activity, addressing an
efficient built-in multiplier at the output, is complementary.
In a first phase, the state of the art of hetero-structure barrier varactor (HBV) as well high-speed photo-detectors shall
be reviewed. From this, some preliminary structures of photo-HBV aiming at frequency generation of 100 GHz and
beyond, shall be proposed and analysed via simulations. In a second phase, the detailed design of the most promising
structure shall take place and this photo-HBV shall be realised. This device shall be tested into a breadboard of a local
oscillator (LO) operating at frequencies beyond 100 GHz.
Deliverables:
Breadboard of a LO generator operating at frequencies beyond 100 GHz
Current TRL:
TRL 1
Target TRL:
TRL 3
Application/Mission: Post-EPS, 2018
SW Clause :
Contract Duration:
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
TRL5 by 2012
24 months
Dossier0 Ref.:
T-8200, T-8216, T-8229,
T-8206, T-8209
TD:
TD06
N/A
TRP Reference:
T106-004ET
Title:
Single GaN chip HPA/LNA for Radar Applications
Objectives
Develop a single chip HPA+LNA including power protection for radar based on GaN technology
Description
The aim of this activity is to develop a single GaN chip providing HPA and LNA functionality for highly integrated T/R
modules applications at C or X band.
HPA in the 20W range shall be developed. The LNA shall feature embedded power protection in order to avoid any
external additional circuitry.
Operation at high temperature shall be investigated.
GaN technology has demonstrated significantly capability to provide ruggedised LNA with enhanced power
survivability. Using GaN standard process, LNA with good Noise figure performance have also been demonstrated.
GaN offers the capability to reduce the size of HPA and LNA by a factor of 5 when compared to equivalent GaAs
based circuits.
In order to further reduce the price of phased arrays, this activity propose integrate both LNA and HPA on the chip
(size reduction).
Due to the capability of GaN to operate at higher junction temperature, phased array shall fully benefit of the use of
GaN technology by further simplification of heat control/removal systems.
Follow on of Sentinel 1 and corresponding national programs shall benefit of application of the proposed integrated
GaN chip.
Deliverables:
HPA+LNA MMIC + design documentation
Current TRL:
TRL 1
Target TRL:
TRL 3
Page 2 of 217
Application
Need/Date:
TRL5 by 2012
TEC-SB/7934/dc
22/Jun/09
TRP Work Plan 2008-2010
Description of Activities
Application/Mission: GMES 2nd generation, 2018
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Contract Duration:
18 months
Dossier0 Ref.: T-8284
Consistent
TRP Reference:
T106-005ET
TD:
Title:
Micro- and millimetre wave detectors
TD06
Objectives
Development of sensitive and linear detectors for micro- and millimetre waves;
Sensitivity, bandwidth, power, and mass improvement of heterodyne and direct detection receivers in EO
Description
EO radiometer payloads include typically narrowband spectrometer type receivers and wideband totalpower type
receivers.
Totalpower receivers can be implemented using either heterodyne principle or simpler direct detection principle where
no local oscillator neither mixer are needed. Both types of the total power radiometers employ a detector element for
detecting the total power over the receiver noise bandwidth. Typically, Schottky diodes are used.
However, the Schottky detectors are rather insensitive and have high noise temperature and thus require a plenty of
amplification in the receiver chain. This gain could be reduced if the detector were more sensitive. This would be
advantageous to any heterodyne radiometer having the IF at microwave region but especially advantageous to direct
detection receivers at mm-waves. Along the developments in the LNA technology, direct detection receivers become
soon feasible at very high frequencies (200 to 300 GHz) where it is crucial to limit the number of amplifying stages to
minimum due to the price of gain, better gain stability, wider bandwidth, reduced tuning, and lower consumption.
This activity aims at development of sensitive, linear and broadband detectors at dedicated frequency bands from low
frequencies up to 300 GHz and above. First, different technologies (GaAs Schottky, low barrier Schottky/Ge/Sb,
bolometer,…) shall be reviewed and assessed in terms of sensitivity and linearity. Next, based on the best selected
technology, the demonstrator breadboards in waveguide blocks shall be designed, manufactured, and tested.
Deliverables:
Detector breadboards
Current TRL:
TRL 1
Target TRL:
TRL 3
Application/Mission: Post-EPS radiometers, 2018
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
TRL5 by 2012
24 months
Dossier0 Ref.:
T-8178, T-8200, T-8201,
T-8209
TD:
TD06
N/A
TRP Reference:
T106-006ET
Title:
Calibration loads for radiometers
Objectives
Development of compact calibration loads for radiometers;
Support all types of EO missions making use of microwave and millimetre-wave radiometry both
conventional and interferometer types
Description
Page 3 of 217
TEC-SB/7934/dc
22/Jun/09
TRP Work Plan 2008-2010
Description of Activities
The accuracy of radiometer observation is based on the accuracy of the calibration subsystem. The key element in the
calibration subsystem is the calibration load whose effective noise temperature is used as a referenece. The
requirements for the load (or termination) are stringent in terms of absolute noise temeperature and long term stability.
Calibration loads are typically based on blackbodies and noise diodes. Known problem with the noise diodes is their
quite poor stability. Recently developed active cold loads (ACL) are becoming attractive at microwave and lower
millimetre wave frequencies where they can offer improvements in calibration accuracy.
It is obvious that depending on the application and frequency different types of calibration elements are required, most
probably both noise diodes and ACLs together with passive blackbodies.
This activity aims at developing very stable and compact calibration loads of different types that can be used as
building blocks in optimised calibration subsystems in microwave and millimetre wave radiometers. Hot and cold
calibration standards shall be addressed and their target specifications shall be derived from the identified
applications.
Deliverables:
Calibrator breadboards, test reports
Current TRL:
TRL 1
Target TRL:
TRL 3
Application/Mission: Post-EPS, 2018
SW Clause :
Contract Duration:
TRL5 by 2012
24 months
T-8206, T-8216, T-8219,
Dossier0 Ref.: T-8220, T-8225, T-8228,
T-8232,
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
N/A
TRP Reference:
T106-007ET
TD:
Title:
Low-Noise Amplifiers for 300 GHZ
TD06
Objectives
Demonstration of low-noise amplification at 300 GHz
Description
At high mm-wave frequencies (above 100 GHz) the reduction of gate length of the active device (HEMT) has only a
limited effect. It is expected that in order to reach good low-noise performance at frequencies above 300 GHz,
fundamental changes have to be introduced in the material structure (e.g. antimonides) and/or device configuration
(e.g. double-sided gates). This activity aims to explore the various ways of achieving low-noise amplification at 300
GHz and above.
Deliverables:
Samples of LNA chips
Packaged LNA demonstrator
Current TRL:
TRL 1
Target TRL:
TRL 3
Application
Need/Date:
TRL5 by 2012
24 months
Application/Mission: GOMAS, CIWSIR, Post-EPS, 2018 Contract Duration:
N/A
SW Clause :
Dossier0 Ref.: T-8216, T-8206, T-8209
Consistency with Harmonisation
Roadmap and Conclusions:
Passive mm & sub-mm instruments: Activity A17
TRP Reference:
T106-008ET
Title:
MM-Wave Power Amplifier
TD:
TD06
Objectives
Development of power amplifier MMIC chips for W-band and demonstration of state-of-the-art
performance in a packaged power amplifier module.
Description
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Description of Activities
Heterodyne receivers operating at mm/sub-mm waves are needed in instruments for Space Science and Earth
Observation. HEMT-based power amplifiers are increasingly used at W-band (75 – 110 GHz), together with frequency
multiplier chains to realise local oscillators (LO) for the highest frequencies. Output power of 100 mW was achieved in
a past activity using European GaAs technology, while the technology selection is wider today, and 1 W is currently
available from a U.S. source.
This activity aims to encourage the development of European MMIC power processes for the high mm-wave
frequencies by realising power amplifier chips for W-band and above, and to develop a SSPA module with
state-of-the-art output power (around 0.5 to 1 W).
The activity includes the selection of the technology (GaN, GaAs, InP, MHEMT), two iterations for the design,
fabrication and testing of the chips, and the design, fabrication and testing of the waveguide demonstrator using
power-combining techniques
Deliverables:
Samples of MMIC chips
SSPA module in a waveguide package
Current TRL:
TRL 1
Target TRL:
TRL 3
Application/Mission: Post-EPS, CIWSIR, 2018
SW Clause :
Contract Duration:
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Dossier0 Ref.:
TRL5 by 2012
24 months
T-8200, T-8216, T-8206,
T-8209
Passive mm & sub-mm instruments: Activity A21
TRP Reference:
T106-009ET
TD:
Title:
Frequency-Multipliers for Submm
TD06
Objectives
To demonstrate the 2nd frequency multiplier with state-of-the-art performance by using European
Schottky/HBV technology.
Description
High-efficiency multipliers are needed for the generation of LO signal in sub-mm-wave superheterodyne receivers of
Space Science and Earth Observation. State-of-the-art results have been demonstrated in the past at mm-waves by
using HBV devices, and the present activity aims to continue the work by developing the second frequency multiplier
in the frequency multiplication chain (that follows a power amplifier and the first multiplier), and to demonstrate
sufficient output power to drive room-temperature mixers. European Schottky/HBV devices are used.
Deliverables:
Multiplier demonstrator in waveguide package
Current TRL:
TRL 2
Target TRL:
TRL 3
Application/Mission: Post-EPS, CIWSIR, 2018
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
Dossier0 Ref.:
TRL5 by 2012
24 months
T-8200, T-8216, T-8229,
T-8206, T-8209
Passive mm & sub-mm instruments: Activity A22
TRP Reference:
T106-010ET
TD:
Title:
Direct-Detection Radiometers
TD06
Objectives
Development of all the critical building blocks and their integration into a complete mm-wave
direct-detection radiometer
Description
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Description of Activities
Millimetre-wave direct-detection radiometers are a very attractive option for future Earth observation and Science
instruments, and are already employed in Planck. Recent developments in low-noise amplifier technology have made
such receivers feasible also at higher frequencies, currently up to around 200 GHz. However, in addition to LNAs, also
filters and detectors with very wide bandwidth are needed in direct-detection receivers. These should be compatible
with MMIC LNAs, i.e. monolithic HEMT or diode detectors would be preferable.
In this activity all the critical building blocks (detectors, filters and LNAs) are developed for 89/157/183 GHz
radiometers. Different detector configurations are investigated and compared. Using the building blocks, a
direct-detection radiometer is constructed and its signal-handling, temperature and short/long-term stability
characteristics are investigated.
Deliverables:
Samples of MMIC chips and other building blocks, Direct-detection radiometer
Current TRL:
TRL 2
Target TRL:
TRL 3
Application/Mission: Post-EPS (MWS), GOMAS, 2018
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
TRL5 by 2012
24 months
Dossier0 Ref.: T-8216
Passive mm & sub-mm instruments: Activity A34
TRP Reference:
T106-011ET
TD:
Title:
1THZ Schottky Mixer
TD06
Objectives
Demonstration of a 1 THz mixer with SOA performance by using European technologies
Description
Design, fabrication and testing of a waveguide mixer, using integrated Schottky devices from a European source.
Deliverables:
Developed mixer
Current TRL:
TRL 1
Target TRL:
TRL 3
Application/Mission: Post-EPS, CIWSIR, 2018
SW Clause :
Contract Duration:
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
TRP Reference:
T106-012ET
Title:
1THZ LO Unit
Application
Need/Date:
Dossier0 Ref.:
TRL5 by 2012
18 months
T-8200, T-8216, T-8229,
T-8206, T-8209
Passive mm & sub-mm instruments: Activity B9
TD:
TD06
Objectives
Enabling future THz instruments. Development of a 1 THz LO source with SOA performance by using
European technologies
Description
Uncooled THz instruments are currently not practical due to the lack of sufficient LO power to drive Schottky mixers.
This activity aims to set a new SOA power level at 1 THz by capitalising on the on-going developments in European
MMIC power amplifiers and HBV/Schottky frequency multipliers. Design, fabrication and testing of a 1 THz LO unit,
consisting of a multiplier chain, driven by a W-band SSPA.
Deliverables:
Developed LO unit
Current TRL:
TRL 1
Target TRL:
TRL 3
Page 6 of 217
Application
Need/Date:
TRL5 by 2012
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Description of Activities
Application/Mission:
Future EO heterodyne instruments
Contract Duration:
operating at THz., by 2018
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
18 months
Dossier0 Ref.: T-343, T-7711
Passive mm & sub-mm instruments: Activity B13
TRP Reference:
T106-013ET
TD:
Title:
Study into Ka-band SAR
TD06
Objectives
To study the feasibility of a Ka-band SAR and other radars
Description
The study will look in to technological aspects of the feasibility of Ka-band radar –in particular SAR with special
emphasis on simultaneous interferometric SAR but also altimetry, precipitation etc in general. In the case of SAR
power generation is crucial while in receive scanned pencil beams can help to relax the transmit power requirements.
The study shall look in to critical elements for transmit e.g. tubes and antennas and in receive in low noise front-ends
capable to form scanned high gain beams. An overall SAR concept shall be worked. Reuse of elements for Ka-band
radar like altimeter and rain radars shall be investigated.
Deliverables:
Study report on technology aspects of Ka-band SAR and Radar
Current TRL:
TRL 1
Target TRL:
TRL 3
Application/Mission: Water, by 2018
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL5 by 2012
Application
Need/Date:
Contract Duration:
12 months
Dossier0 Ref.: T-8215, T-8213, T-8214
N/A
TRP Reference:
T106-014ET
TD:
Title:
Swath precipitation radar instrument
TD06
Objectives
Study into the potential of beamforming for precipitation radar
Description
This activity will look at the potential for realising a side-looking precipitation radar using beamforming on receive. The
complete radar design shall need to be analysed considering choice of centre frequency, bandwidth, pulse
compression weighting, PRF etc and of course the number of beams to be formed and how to achieve this
considering both analogue and digital techniques. A nadir looking precipitation radar (precipitation profiling radar) is
limited in its operation due to the ground return either requiring a very short pulse or for a chirped pulse weighting
must be applied to reduce the sidelobes of the impulse response function to around -60dB. This results in a
broadening of the mainlobe and hence loss of spatial resolution as well as a reduction in SNR. If instead the radar is
made to be side-looking then the requirements on the sidelobe suppression can be less stringent releasing more and
it is then possible to consider multiple beams allowing a swath to be formed. For this the idea is to consider
beamforming techniques.
Deliverables:
Report on the feasibility and potential of applying beamforming techniques to precipitation radar
Current TRL:
TRL 2
Target TRL:
TRL 3
Application/Mission: Post-EPS, 2018
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
TRL5 by 2012
12 months
Dossier0 Ref.: T-8236, T-8237
N/A
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Description of Activities
TRP Reference:
T106-015ET
Title:
Integrated Scalable Tile Beam Former
TD:
TD06
Objectives
Design, manufacturing and test of integrated proof-of-concept beam former demonstrator based on
advanced silicon technology for Active Array SAR
Description
New implementation ideas for SAR base on multibeam and wide swath high resolution concepts allowing significant
improvements in spatial coverage. These concepts will require centralised beam forming units on tile level in order to
handle the dense wiring requirements inherent with digital circuitry and analogue multibeam concepts.
In addition, upcoming GaN technology for microwave power generation will call for a spatial separation of Si and GaAs
based beam forming elements, in order to gain full advantage of high temperature capabilities not possible for Si and
GaAs.
Furthermore removing gain and phase control function from TR modules will lead to considerable cost reductions due
to significantly reduced test effort vs. full temperature range. Within the proposed activity a proof of concept
demonstrator for an integrated, in terms of number of input channels scalable, digital beam former shall be built and
investigated. Latest silicon technology based on e.g. SiGe shall be used, providing integration advantages due to the
access to highly integrated digital control circuits. The activity shall include:
- SiGe based MMIC chip design for frequency converter and beam forming element
- High density Multilayer RF board design in e.g. LTCC technology
- FPGA design for digital beam setting control
- Local oscillator and chirp signal generation
- Test in a representative proof-of-concept environment
The activity will be strongly supported by the results of the TRP study: “Advanced SAR Instruments based on Digital
Beam Forming”.
The study will finish in 2008.
The technology will be inherently radar band independent and therefore useful L-, C-, X- band systems.
European SAR instruments based on active arrays, e.g. ESA Sentinel 1 follow on,
Habitat L-band system including receive only instruments and national programs will significantly benefit from this new
architecture.
Deliverables:
- Integrated scalable tile beam former demonstrator breadboard
- Documentation
TRL 3
Current TRL:
TRL 2
Application/Mission:
GMES 2nd generation, Habitat,
2018
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-7736, T-353, T-8240, T-8210
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
TRL5 by 2012
18 months
Consistent
TRP Reference:
T106-016ET
Title:
High Bandwidth programmable DDS for chirp generation
TD:
TD06
Objectives
Design, manufacturing and test of integrated high bandwidth chirp generator breadboard based on DDS
techniques
Description
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Description of Activities
Spaceborne radar applications as SAR and Altimeter need high bandwidth signals for achieving high range resolution.
Current state-of-the art for space uses low bandwidth chirp generators while the high bandwidth is achieved by
frequency multiplication.
Major drawback of this technique is loss of proper amplitude control due to the highly non-linear multiplication stages.
Phase distortions are caused by the high number of filtering stages in the multipliers which need extensive tuning
effort during manufacturing for keeping distortions within acceptable limits.
State-of-the-art semiconductor technology would allow direct digital generation of chirps with high bandwidth up to 600
MHz suitable for all spaceborne radar applications complying with current and foreseeable future ITU regulations.
The major benefit of direct digital synthesising (DDS) of chirp signals at full bandwidth will allow for digital pre-distorted
of chirps in order to compensate imperfections in the analogue part of the instrument. Manual tuning will be avoided
leading to cost reduction and improved performance. It will furthermore allow to shape the transmit pulse in amplitude
for ultra low (time) sidelobe applications as needed in nadir looking rain profiling radars. Other applications are direct
signal generators for navigation signals.
Within the activity a breadboard demonstrator shall be realised consisting of
- High bandwidth (up to 600 MHz) DDS circuit design with integrated DAC.
- Implementation in high speed state-off-the art mixed signal silicon technology.
- PCB design with supporting circuitry as I/Q up-converters
- Testing in representative proof-of-concept environment
The activity will make use of the TRP 2007 activity on "Broadband low-power DAC design and prototyping".
Future Precipitation Profiling Missions, GMES Sentinel 3 2nd generation altimeter,
future high resolution SAR and national programs will benefit form this activity.
Deliverables:
- Integrated high bandwidth DDS demonstrator breadboard
- Documentation
Current TRL:
TRL 2
Target TRL:
TRL 3
Application/Mission: GMES 2nd generation, 2018
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
TRL5 by 2012
24 months
Dossier0 Ref.: T-8242
N/A
TRP Reference:
T106-017ET
Title:
Study of a high spatial resolution MIRAS (Super-MIRAS)
TD:
TD06
Objectives
To define optimum system architectures for a high spatial resolution L-band interferometer.
Description
The challenge of future L-band microwave radiometers is the improvement of spatial resolution. The aperture
synthesis technique, demonstrated by SMOS, is scalable in that the size of the antenna can be increased to get better
spatial resolution. However in doing so, some problems appear, as loss of sensitivity and decorrelation effects. This
study aims at providing optimum array geometries and system architectures to improve spatial resolution while
maintaining sensitivity of future L-band SMOS like missions with much higher spatial resolution.
Deliverables:
Study report
Current TRL:
TRL 1
Target TRL:
TRL 3
Application/Mission: SMOS 2nd generation, by 2015
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
TRL5 by 2011
24 months
Dossier0 Ref.: T-343
Consitent with RF Remote Passive Instruments chapter in the
harmonisation workplan 2006 (EUI-PHH/5160/LM)
TRP Reference:
T107-018EE
TD:
TD07
Title:
Light Weight, Dual Frequency Antenna Configuration for Earth Observation SAR
applications
Objectives
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Description of Activities
The objective is to investigate and design a very light antenna configuration with low loss, dual polarised,
dual-frequency (9.6 & 17.2 GHz) capability for a sensitive SAR system (@ -25 dB), medium resolution (50
m, 50 m, 5 looks) and large swath (~ 100 km).
Description
A compact and light weight SAR antenna with dual-frequency and dual polarisation is required for the CoReH2O Earth
Explorer Core candidate mission entering phase A. Antenna concepts based on multi-beam feed illuminating a
deployable reflector were developed during the phase 0 studies, which permit a wide swath coverage (100 km) with
the required resolution (50 m x 50 m, > 5 looks) using a ScanSAR scheme. Starting from the concepts as derived
during phase 0, the design of the Ku-band feed sub-system including the beam-switching matrix shall be elaborated.
Critical technology elements shall be breadboarded and tested for demonstrating the feasibility of the concept.
The budget and description of this activity have been revised in light of a very similar EOEP activity in an on-going
open tender and selection process. An ITT ref. AO/1-5794/08/NL/CT with the title "Ku-Band Antenna Feed
Breadboarding" was issued by EOEP for a single activity of 490 k. Following the proposal evaluation, two proposals
led respectively by Astrium GmbH and Thales Alenia Space Italy received an identical and good overall marking.
Given the similarity of the objectives and consistency with the programmatic intention of the original activity proposal,
two contracts will be placed with TRP and EOEP co-funding.
Deliverables:
Antenna design and detailled design of the feed system.
TRL 3
Current TRL:
TRL 1
Application/Mission:
CoReH2O, All SAR reflector
antennas, 2015
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-8203
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
TRL5 by 2011
14 months
N/A
TRP Reference:
T107-018EE
TD:
TD07
Title:
Light Weight, Dual Frequency Antenna Configuration for Earth Observation SAR
applications
Objectives
The objective is to investigate and design a very light antenna configuration with low loss, dual polarised,
dual-frequency (9.6 & 17.2 GHz) capability for a sensitive SAR system (@ -25 dB), medium resolution (50
m, 50 m, 5 looks) and large swath (~ 100 km).
Description
A compact and light weight SAR antenna with dual-frequency and dual polarisation is required for the CoReH2O Earth
Explorer Core candidate mission entering phase A. Antenna concepts based on multi-beam feed illuminating a
deployable reflector were developed during the phase 0 studies, which permit a wide swath coverage (100 km) with
the required resolution (50 m x 50 m, > 5 looks) using a ScanSAR scheme. Starting from the concepts as derived
during phase 0, the design of the Ku-band feed sub-system including the beam-switching matrix shall be elaborated.
Critical technology elements shall be breadboarded and tested for demonstrating the feasibility of the concept.
The budget and description of this activity have been revised in light of a very similar EOEP activity in an on-going
open tender and selection process. An ITT ref. AO/1-5794/08/NL/CT with the title "Ku-Band Antenna Feed
Breadboarding" was issued by EOEP for a single activity of 490kE. Following the proposal evaluation, two proposals
led respectively by Astrium GmbH and Thales Alenia Space Italy received an identical and good overall marking.
Given the similarity of the objectives and consistency with the programmatic intention of the original activity proposal,
two contracts will be placed with TRP and EOEP co-funding.
Deliverables:
Antenna design and detailled design of the feed system.
TRL 3
Current TRL:
TRL 1
Application/Mission:
CoReH2O, All SAR reflector
antennas, 2015
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-8203
Target TRL:
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Application
Need/Date:
TRL5 by 2011
14 months
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TRP Work Plan 2008-2010
Description of Activities
Consistency with Harmonisation
Roadmap and Conclusions:
N/A
TRP Reference:
T107-019EE
TD:
Title:
Millimeterwave Radar Antenna Technology
TD07
Objectives
To investigate antenna architectures for a Millimetre Wave Radars operating at 95 GHz and to design,
manufacture and test a reduced-scale elegant bread-board antenna
Description
Space-based millimetre-wave radar antennas (example: cloud radar) operate with high power levels (pulsed), posing
requirements to the antenna configuration and surface finishing. High eficiency requires high reflectivity and low loss
at the operating wavelength. A trade off shall result in a selected antenna configuration, for which a reduced size
demonstrator antenna is realised with characteristics as needed for a cloud radar like low mass, high surface
accuracy, high mechanical, power handling and thermal stability and shall be equipped with a simple feed for RF
experimental assessment. Low reflectivity is required for the visible and IR spectrum to avoid damage of focal units when exposed to solar flux. This puts requirements to surface treatments and coatings. A full scale 2.6 metre sized
antenna configuration shall be designed.
Deliverables:
Reduced scale antenna demonstrator
Current TRL:
TRL 1
Target TRL:
Application/Mission: Post-EPS, 2018
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
TRL5 by 2012
18 months
Dossier0 Ref.: T-8238
N/A
TRP Reference:
T107-020EE
TD:
TD07
Title:
Innovative reconfigurable systems based on liquid crystals
Objectives
Two innovative reconfigurable systems based on liquid crystals (LC) will be investigated.
The first is an electronically steered double reflector antenna to demonstrated the viability of exploiting the
dielectric properties of liquid crystals to create electronically steered reflector antennas. This type of
structure offers many advantages over the mechanically scanned systems that are currently employed in
mm and sub mm wave limbsounder instruments.
The second one is a reconfigurable frequency selective surface (FSS). The electrical properties of liquid
crystals to produce Frequency Selective Surfaces (FSS) which can generate an electronically tunable
bandpass filter response at mm wave frequencies will be exploited. These quasi-optical switches can be
employed in the feed chain of (1) conical scan radiometers to replace the motor driven hot and cold target
calibration subassemblies and (2) in limbsounders to significantly reduce the antenna scan angle
requirements by removing the need to use an external cold calibration target.
Description
In this project two innovative reconfigurable systems based on liquid crystals (LC) will be investigated. The first is an
electronically steered double reflector antenna, the second one is a reconfigurable frequency selective surface (FSS).
Electronically steered double reflector antenna
In a recent study (ESTEC/19571/06/NL/JA) the Universidad Politecnica de Madrid (UPM) presented a focused
Cassegrain double reflector configuration, which uses a flat reflectarray as subreflector, able to scan a beam in the
elevation plane. Queen’s University Belfast (QUB) has recently demonstrated that a phase agile reflectarray can be
created by inserting liquid crystals (LC) in the cavity between the periodic array and the ground plane of the antenna.
The first objective of this project is to use the results obtained from these two innovative programmes to demonstrate
an electronically steered double reflector antenna which combines the broad bandwidth property of the parabolic main
reflector with the simplicity of manufacturing a small active reflectarray. The main advantage of LC technology is that it
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Description of Activities
can be used even for frequencies above 300GHz, where other active array technologies fail. An offset Cassegrain
reflector antenna will be designed to fulfil the bandwidth, beam shape and scan angle requirements for a typical
limbsounder instrument. The permittivity and loss tangent values of various commercially available liquid crystal
mixtures will be measured in the frequency range around 300GHz by comparing numerical results with open resonator
measurements. The dielectric parameters will be used to design an experimental reflectarray subreflector. Then, a
breadboard reconfigurable subreflector will be constructed and measured to demonstrate the ability to create an
electronically controlled progressive phase across the aperture.
Reconfigurable frequency selective surface
Very low loss bandpass FSS have been developed (up to 600GHz) by Queen’s University Belfast (QUB) for single
sideband filtering and channel demultiplexing in quasi-optical receivers that used in several limbsounder instruments
(A0/1-4850/05/NL/JA). Recently QUB has demonstrated also that a phase agile reflectarray can be created by
inserting liquid crystals (LC) in the cavity between the periodic array and the ground plane of the antenna.The purpose
of this project is to combine these two innovative programmes to create a reconfigurable FSS which can be designed
to switch between ‘ON’ and ‘OFF’ states over a frequency range which fulfils the signal detection requirements of an
existing limbsounder radiometer eg. 316.5-325.5GHz. The quasi-optical switch will be constructed by printing the
periodic slot arrays on two thin quartz wafers and inserting the LC in the gap between these. First of all, the
permittivity and loss tangent values of various commercially available liquid crystal mixtures will be determined in the
frequency range around 300GHz by comparing numerical results with the high Q measured spectral response of the
FSS. Then, these dielectric parameters will be used to design a structure which gives a low insertion loss in the
passband for the unbiased state and a large reflection coefficient in the biased state. The outcome from this
investigation is to demonstrate that the active FSS can be used in the quasi-optical feed train to detect the signals
received from the scene and the hot and cold calibration loads in a time sharing mode.
Deliverables:
Electronically reconfigurable reflectarray subreflector, reports detailing design, results obtained from numerical
models, dielectric properties of liquid crystals, construction details and measurements
Current TRL:
TRL 1
Target TRL:
TRL 2
Application/Mission: Post-EPS, limb sounder, by 2018
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
TRL5 by 2012
12 months
Dossier0 Ref.: T-8217
N/A
TRP Reference:
T107-021EE
TD:
TD07
Title:
Large Antennas for P-Band SAR - Critical Breadboarding (OLD TITLE: Advanced
Feed System allowing Signal Processing capability for Large Earth Monitoring
Antennas)
Objectives
The objective of this activity is the critical breadboarding/proof-of-concept and evaluation of the
components, materials, equipments and assemblies to retire risks for the antenna development as
required for BIOMASS Earth Explorer candidate mission.
Description
For the development of large antennas with effective apertures of ~ 70 m^2 and operating at P-band, innovative and
novel technologies are needed to ensure mass and stowing envelope compatible with small launchers while
complying with instrument performance requirements.
Consequently, there will be a need to demonstrate and evaluate such technologies by means of critical
bread-boarding to retire risks in antenna development during later phases.
This activity will cover the development of a selected number of items proposed and justified by the bidder in an initial
development plan already provided with the proposal.
Initial and final TRL levels will have to be identified for all the selected critical items as well as items definition and
proposed test plan. The existing instrument and antenna designs from the work performed during two parallel
BIOMASS phase 0 studies will be made available as input to this activity.
Deliverables:
RF and/or mechanical components designs analyses and test reports.
Design, development and test plan update.
Critical bread-boarding.
Current TRL:
TRL 2
Target TRL:
TRL 3-4
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Application
Need/Date:
TRL5 by 2012
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Description of Activities
Application/Mission: BIOMASS, 2015
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Contract Duration:
18 months
Dossier0 Ref.: T-8195, T-8210
N/A
TRP Reference:
T107-022EE
TD:
TD07
Title:
Antenna Architecture for Radio Occultation for GRAS-2
Objectives
The objective is to investigate antenna architectures for occultation tasks and define critical antenna
hardware
Description
With the increasing number of navigational satellites, availability of precision signal in space permit occultation
measurements to be carried out more frequently. Receive multiple beam capability drives towards digital beamforming
on receive and results with on-board processing in more frequent available processing of occulted signals. Following
initial architectural studies and trade-offs detailed antenna designs are investigated. The results obtained with the
GRAS system can act as a reference in comparison to which the result shall be improved. Filled and sparse array
configurations are compared and consideration is given to reduction of sidelobes in the direction of undesired signals.
Mass and volume constraints have to be considered in view of nr of elements allowed . Digital BFN in combination
with front end receiver capabilities to be considered.
Deliverables:
Study and demonstrator
TRL 2
Current TRL:
TRL 1
Application/Mission:
Post-EPS (Occultation GRAS-2),
by 2018
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-8235
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
TRL5 by 2012
18 months
N/A
TRP Reference:
T107-023EE
TD:
Title:
Low mass Calibration load
TD07
Objectives
Radiometer instruments need hot and cold calibration measurements to achieve a high radiometric
accuracy. Cold calibration is usually done by looking into cold space, but for the hot calibration a special
load is needed. An absorber type of load is used as a typical hot calibration target. However, if not only the
feeds but also the reflector has to be included in the hot calibration measurement the absorber can
become quite large (comparable to reflector aperture size). Therefore, it is very important that for future
radiometer instruments with relatively large reflector sizes (e.g. Post-EPS) the mass of the hot load needs
to be minimised in order to be compliant with the instrument mass requirement.
The objective is to demonstrate the feasability of low-mass low volume calibration loads.
Description
This activity is aimed at achieving low mass 0.5 to 1-m class of hot calibration targets for future passive remote
sensing instruments. To derive the main requirements for such hot loads, an assessment shall be performed of the
possible passive millimetre- and submillimetre-wave instruments for missions like Post-EPS and Post-MSG. Driving
parameters will be thermal environment, reflector aperture size and frequency envelop. Based on the derived generic
requirements, a preliminary design and analysis shall be performed of at least two promising solutions where low
mass and low volume is a driver. It is also foreseen to do some sample testing during this task.
Deliverables:
Hot calibration load at sample level
Current TRL:
TRL 2
Target TRL:
TRL 3
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Application
Need/Date:
TRL5 by 2012
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TRP Work Plan 2008-2010
Description of Activities
Application/Mission: Post-EPS, 2018
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Contract Duration:
15 months
Dossier0 Ref.: T-8219
Technologies for (sub) millimeter wave passive instruments - 2006
TRP Reference:
T107-024EE
TD:
TD07
Title:
Antenna Architecture for Radio Occultation for LEO-LEO
Objectives
The objective is to investigate antenna architectures for occultation tasks and define critical hardware
Description
Antenna configurations are investigated for LEO to LEO intersatellite link to support occultation measurement
capability. Transmit receive functionality and accurate phase stability will be driving requirements. The selection of the
observation frequency should be an input (around and including the 22 GHz waterline)
Deliverables:
Study and definition of critical hardware
Current TRL:
TRL 1
Target TRL:
Application/Mission: Occultation LEO-LEO, by 2016
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 2
Application
Need/Date:
Contract Duration:
TRL5 by 2011
12 months
Dossier0 Ref.: T-343
N/A
TRP Reference:
T107-025EE
TD:
TD07
Title:
Assimilation of high temporal resolution SAR data into land process models
Objectives
Relying on recently acquired campaign data, this activity aims at exploiting the temporal dimension of SAR
acquisitions so as to bring infomation on land processes.
Description
Dramatic advances in the retrieval of land variables and their assimilation into process models can be expected
through the operational use of SAR data with high temporal repetitivity. The temporal dimension has seldom been fully
investigated in retrieval algorithms for SAR data as the temporal sampling of past/current operational missions is too
coarse. A high temporal sampling results in the possibility of tracking temporal signatures of land cover types, and can
also contribute to a much higher data quality through optimised filtering. The current interest in missions
characterised by a shorter time interval between repeat passes (Sentinel-1, CoreH2O, Radarsat-2, COSMO-Skymed)
make this topic highly valuable and the recent availability of suitable airborne data from ESA campaigns data make
this research possible. Investigations of the added value of these SAR data for land process models will be based on
recent campaign data, theoretical models.and on the revisit of past ERS-1 data (Ice phase). Available datasets:
- AGRISAR data: ESA managed airborne campaign with SAR datatakes at X-, C-, L- and P-band (including
interferometry) over an agricultural site (spring-summer 2006)
This campaign was a series of airborne acquisitions throughout the growing season (April to July) with appropriate
SAR/Optical instruments along with coincident in-situ measurements.
There have been 3-4 intense measurement periods of a few days each (with airborne acquisitions every day) spread
over the growing season. this gives a very good time sampling.
- BIOSAR/ICESAR data: ESA managed campaign with SAR datatakes at X-, C-, L- and P-band (including
interferometry) over a forest site (temperate/boreal) and an ice sheet acquired several times over a period of ~40 days
(spring 2007), together with in situ measurements.
- ERS-1 SAR data available for the ice phase (3-day repeat) over Middle-Zeeland (agricultural site) and other sites
Deliverables:
Deliverables:
- final report
- prototype algorithms (retrieval of biogeophysical variables from time series of SAR data)
Current TRL:
-
Target TRL:
Software:
Algorithm
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Application
Need/Date:
TRL5 by 2011
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TRP Work Plan 2008-2010
Description of Activities
Application/Mission:
GMES 1, CoreH2O (Phase 1),
2015
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-8153
Consistency with Harmonisation
Roadmap and Conclusions:
24 months
N/A
TRP Reference:
T107-026EE
TD:
TD07
Title:
The generic radiative transfer toolbox for the Earth environment, ESAS-Light:
from a prototype tool to a community tool
Objectives
Under the General Study Progamme, a Generic Radiative Transfer Model for the Earth’s
Surface-Atmosphere System,
ESAS-Light, is being prototyped (activity has started). The objective of this activity is further develop the
ESAS-Light to give full access to actors in the field of remote sensing of Earth Observation and planetary
environments to a user friendly, well documented and free of charge radiative transfer toolbox
Description
In the frame of the General Study Programme (GSP), a demonstration version of a radiative transfer toolbox,
hereafter referred to as the ESAS-Light toolbox, providing forward modeling capability from the UV to the TIR spectral
domain, for the Earth atmosphere-surface system is being prototyped. At completion of this activity, in mid-2009, the
delivered ESAS-Light prototype version shall serve a dual objective: a) strengthen ESA radiative transfer forward
modeling capability for internal purposes (instrument design and prototyping of inversion algorithms) and b) provide a
set of standard forward radiative transfer tools for the development of ESA commissioned inversion schemes and ESA
commissioned calibration/validation activities (for its current and future EO missions). Contractually wise, at the end of
the current GSP activity, ESAS-Light will be available only for ESA commissioned activities and to ESA internal
activities. However, because such tool is valuable to entities in the ''outside world'' (laboratories, universities,
companies) that cannot afford the cost of such a development, it is proposed in a subsequent TRP activity, to take
action to broaden its distribution to a wider community. This will be achieved by expanding its functionalities, imposing
high software quality standards, putting in place an appropriate distribution strategy and the web infrastructure to offer
an ESAS-Light consolidated version to the Earth Observation and Planetary Remote Sensing community.
Deliverables:
The main output of this activity is the consolidated of ESAS-Light radiative transfer toolbox and its associated
documentation
Software: Beta
Version
Current TRL:
-
Application/Mission:
EO mission with UV to TIR
instruments, by 2015
Contract Duration:
SW Clause :
Open source
Dossier0 Ref.: T-7770
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
TRL5 by 2012
12 months
N/A
TRP Reference:
T107-028EE
TD:
TD07
Title:
Improvement of the Tenti model for atmospheric Rayleigh-Brillouin scattering
Objectives
Improve an existing model for Rayleigh-Brillouin scattering, used for the modelling of Rayleigh
backscattered light from lasers
Description
The so-called Tenti model is the most widely used model for correction of Brillouin scattering contribution to the
Rayleigh return signal from atmospheric lasers. The model was developed in the 1970s, and has been validated by
measurements of monoatomic gases (N2 and O2) and CO2 only. A GSP study is being launched to validate the
model by comparing it to measurements in gas mixtures; N2+O2, H2O and air, representative for the Earths
Atmosphere. This TRP is foreseen to improve/refine the Tenti model according to the findings from the experimental
model validation. The resulting improved model should be used for the up-coming lidar Earth Explorer Missions
ADM-Aeolus, EarthCARE, and for the proposed lidars within the post-EPS.
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TRP Work Plan 2008-2010
Description of Activities
Deliverables:
Model description (Detailed Processing Model / Algorithm Theoretical Basis Document), input-output data, example
model description, Technical Notes and Final Report
Software:
Prototype
Current TRL:
-
Application/Mission:
Post-EPS/Earth Explorer laser
instruments, 2018
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-7772
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
TRL5 by 2012
12 months
N/A
TRP Reference:
T107-029EE
TD:
TD07
Title:
Advanced modelling of coherent propagation effects on active microwave
remote sensing
Objectives
To develop an atmosphere/ionosphere microwave propagation model that accounts for phase-related
effects and is applicable to Earth Observation specificities
Description
When reaching frequencies as high as Ku-band and as low as P-band, using phase measurements to retrieve
bio-geophysical parameters, or looking for extreme accuracies, the coherent interaction with the propagating medium
(atmosphere, ionosphere) must be taken into account. However, models so far are mostly designed for
telecommunication satellites and are not always suited to remote sensing configurations. This activity shall review and
analyse the phase-related effects affecting the propagation of microwave remote sensing signals, for geometries
typical of Earth Observation missions. Both the atmosphere and the ionosphere shall be studied. First, a review of the
available measurements shall be conducted. Then a detailed propagation model shall be proposed, which will rely as
little as possible on statistical assumptions and on simplifying geometric considerations. As an example, this model
shall be able to simulate the effects of tropospheric (ionospheric) scintillations on a Ku-band (P-band) SAR or on an
active occultation measurement. This tool will be used as a benchmark for the assessment of the performance of error
mitigation techniques developed in the future.
Deliverables:
Coherent propagation model through atmosphere / ionosphere. Implemeted software.
Current TRL:
-
Target TRL:
Software:
Algorithm
Application/Mission: BIOMASS, ACCURATE, by 2015
Open source
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
TRL5 by 2011
18 months
Dossier0 Ref.: T-8197, T-8212
N/A
TRP Reference:
T107-030EE
TD:
TD07
Title:
ESA manual towards a new scattering statistics database for different terrain
types
Objectives
The goal of the activity is to have harmonised guidelines in order to enable the gradual construction of a
scattering database.
Description
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TRP Work Plan 2008-2010
Description of Activities
Very often terrain scattering statistics used in the fields of remote sensing, telecommunications and navigation
applications rely on data assembled in the 1970's. At that time, the possible means to characterise in-situ parameters
was at a far lower technical maturity as is currently the case. Also, the understanding of the geophysical parameters
under investigation, such as snow, was more limited at that time. In the following period (1980 - present) far more
effort has been spent on assembling either spaceborne or airborne data. A difficulty herein is in the fact that in-situ
parameterisation is either difficult or impossible (none collocated measurements). Therefore, the proposed activity will
investigate the ground-based instruments and required in-situ parameters in order to build up a future scattering
statistics database. One of these instruments could be the ESA X- to Ku-band ground-based scatterometer currently
under development. Instruments covering other frequency ranges will have to be identified and campaign logistics will
also have to be described in this manual.
Deliverables:
Current TRL:
-
Target TRL:
Application/Mission: GMES
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Software:
Prototype
Application
Need/Date:
Contract Duration:
TRL5 by 2011
6 months
Dossier0 Ref.: T-8153
N/A
TRP Reference:
T107-031EE
TD:
TD07
Title:
Capability of atmospheric parameter retrieval and modelling for wide-swath
spaceborne atmospheric radars
Objectives
The aim of the proposed activity is to investigate the retrieval accuracy and capability of wide swath
atmospheric radars in arriving to horizontal wind profiles
Description
The capability of microwaves to penetrate cloud and rain has placed the weather radar in an unchallenged position for
remotely surveying the atmosphere. Although visible and infrared instruments on satellites can detect and track
storms, only microwave observations can reveal the internal structure of the storm. The current techniques allow the
detection of significant updraft/downdraft revealing convective-type clouds. Furthermore with the recent advancements
in radar and its related processing algorithms, investigations are required to assess and develop new ideas, theories
and technologies to be implemented in future atmospheric radars. One of the new ideas - and to be further expored in
this activity - is to assess the potential for a W-band radar (94 GHz) with wide swath to determine horizontal wind
profiles. A recently concluded GSP activity (Extreme Weather Events) has arrived to a preliminary set of instrument
requirements that will be used as a starting point in this activity. Effect of multiple scattering and depolarisation
(particularly in ice clouds) on determination of the wind vector using both doppler and polarimetric techniques will be
investigated.
Deliverables:
Current TRL:
-
Target TRL:
Application/Mission: Post-EPS, 2018
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Software:
Prototype
Application
Need/Date:
Contract Duration:
TRL5 by 2012
18 months
Dossier0 Ref.: T-7769
N/A
TRP Reference:
T107-032EE
TD:
TD07
Title:
Potential and characterisation of geophysical parameter retrieval using a passive
interferometer
Objectives
The activity intends to quantify retrieval accuracies for a passive interferometer and compare these with
more conventional mechanically scanning radiometers.
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TRP Work Plan 2008-2010
Description of Activities
Description
This activity would firstly look into the effect on the incidence angle dependency of the desired product (fixed for both
MIMR and EGPM). Some preliminary studies have shown that the incidence angle would not need to be a fixed
parameter. Especially the lower frequencies may benefit from an interferometer solution for a conical scanning
radiometer assembly such as EGPM/MIMR type radiometers. This activity would also be of interest to post-EPS.
Clear advantage of the interferometer solution is there will be no need of large scanning reflectors (+2 m) and the
entire payload would be less bulky. The study would look into which frequency band(s) is/are likely to be integrated on
a passive interferometer. Achievable radiometric resolution and accuracy using this technology will be assessed
including a comparison with user requirements. Accuracy of geophysical parameter retrieval will be assessed.
Deliverables:
Current TRL:
-
Target TRL:
Application/Mission: Post-EPS, 2018
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Software:
Prototype
Application
Need/Date:
Contract Duration:
TRL5 by 2012
18 months
Dossier0 Ref.: T-8154
N/A
TRP Reference:
T108-033SM
Title:
Analysis of Normalised Differential Spectral Attenuation (NDSA) Technique for
Inter-Satellite Atmospheric Profiling
TD:
TD08
Objectives
Modelling the impacts of tropospheric scintillation on atmospheric sounding by inter-satellite links
Description
The capability and performance of atmospheric sounding with intersatellite microwave links can be strongly affected
by the presence of scintillation caused by atmospheric turbulence. The existing models have a wide spread of
predicted behaviours and the relations to actual data, mainly derived from high-resolution radiosondes, requires
revision too. Improved models, tailored to the intersatellite will be developed and validated with available radio
propagation experimental data. Retrieval performance will be evaluated.
Deliverables:
Study Report
Current TRL:
-
Target TRL:
Application/Mission: GMES 4, 2015
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Software:
Prototype
Application
Need/Date:
Contract Duration:
TRL5 by 2011
18 months
Dossier0 Ref.: T-7769
N/A
TRP Reference:
T116-034PI
Title:
Long Life Scanning Mechanism - Contactless Power and Data Transmission
TD:
TD15
Objectives
For the post-EPS mission in preparation, a long operational life requirement approaching 10 years per
satellite is considered as a goal.
Description
For the post-EPS mission in preparation, a long operational life requirement approaching 10 years per satellite is
considered as a goal. Mechanically scanned MW radiometers require a rotating mechanism together with power and
data transmission across the rotating interface with the corresponding life-time. The long-life rotating mechanism has
been the subject of past and on-going development activities such as the Ball-bearing Active Preload (BAP) device
and lead-lubricated ball-bearing life-test. The objective of the proposed activity is to develop a contactless/inductive
power and data transmission device across such a rotating interface. Such a device exists for terrestrial applications
which needs to be adapted to the space environment. A breadboard operatable in vacuum environment shall be built
and tested, and shall be subjected to an accelerated life-test.
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TRP Work Plan 2008-2010
Description of Activities
Deliverables:
Breadboard, life-test result
TRL 1
Current TRL:
Target TRL:
Application/Mission: Post-EPS, 2018
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
TRL5 by 2012
Application
Need/Date:
Contract Duration:
18 months
Dossier0 Ref.: T-8226
N/A
1-02 - Optical Payloads
TRP Reference:
T101-035ED
TD:
TD01
Title:
New Techniques for efficient multi-spectral data compression
Objectives
Research and development of new techniques for efficient multi-spectral data compression
Description
Future Earth Observation missions with high data rate instruments will have a need for efficient multi-spectral
compression to reduce the amount of data to transfer. The actual techniques (based on transforms) are very efficient
in terms of compression, but quite demanding in terms of computing resource and also not robust enough to cope
with not highly correlated bands. New techniques based on predictors, like the DSC (Distributed Source Coding) are
very promising in terms of robustness and lower complexity. The new technique shall be robust, in order to be able to
perform intra-band compression even when the correlation is not very high (e.g., in case of slight misregistration).
Moreover it shall be efficient and not complex, in order to be implemented on-board in a real time context.
Deliverables:
Algorithm specification, prototype implementation and performance characterisation
TRL 1
Current TRL:
Target TRL:
Application/Mission: All EO missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
TRL5 by 2011
18 months
Dossier0 Ref.: T-8331
N/A
TRP Reference:
T103-04FP
TD:
TD16
Title:
Lightweight large aperture deployable telescope for lidar applications
Objectives
Description
Large aperture telescopes can unfortunately drastically increase mission costs if large fairing launch vehicles are
required. Deployable telescopes will provide the required performance enhancement while maintaining volume
requirements compatible with small fairing launchers. It is proposed to carry out the research and development of
deployable telescopes with large collecting area and at first optimised for future Earth Observation lidar applications.
Deliverables:
- Technology review report
- Reduced scale / critical component breadboard
- Development plan and cost estimate
Current TRL:
0
Application/Mission:
Future Lidar; SCI exploration
misions
Target TRL:
TRL 2
Application
Need/Date:
Contract Duration:
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TRL5 by 2012
18 months
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TRP Work Plan 2008-2010
Description of Activities
SW Clause :
N/A
Dossier0 Ref.: T-419
Consistency with Harmonisation
Roadmap and Conclusions:
TRP Reference:
T107-027EE
TD:
TD07
Title:
Atmospheric Corrections for Fluorescence Signal Retrieval
Objectives
The objective is to develop the algorithms for deriving bottom-of-atmosphere radiances and fluorescence
signal from satellite observations.
Description
This follow-on TRP activity would further define and implement an atmospheric correction and cloud screening
scheme for both the estimation of the fluorescence signal emitted at BOA (Bottom-Of-Atmosphere) and the
determination of BOA reflectances for the FLEX instruments covering the VNIR (Visible and Near-Infrared) domain.
The study will also reflect on algorithm implications which are due to the fact that the mission is implemented as an in
orbit demonstration mission.
Deliverables:
ATBDs and prototype S/W
Current TRL:
-
Target TRL:
Application/Mission: FLEX, by 2015
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Software:
Prototype
Application
Need/Date:
Contract Duration:
TRL5 by 2011
12 months
Dossier0 Ref.: T-7770
N/A
TRP Reference:
T108-036SM
TD:
TD08
Title:
Sensitivity study on the influence of a target spectral signature in the unfiltering
process for broadband radiometers
Objectives
The objective of this study is to understand the impact of the lack of information on the full spectral
signature of a terrestrial target on the accuracy of the integrated shortwave / total radiance from a
broadband radiometer measurements.
Description
A broadband radiometer performs measurements in two channels, in the shortwave (sun reflected light) and in the
total spectrum (sun reflected + emitted). Perfectly flat spectral responses are not possible. This means that the
sensitivity in certain regions of the electromagnetic spectrum is higher and that to convert its measurements into
physically meaningful measurements (top of atmosphere radiances), scene-dependant calibration coefficients are
needed to account for the spectral shape of the scene signature. This is the so-called unfiltering process. Such
spectral shape requires additional measurements than the ones performed. This study will aim at designing at an
algorithm enabling the unfiltering of the measurements, identifying requirements for data coming from other payloads
and from auxiliary data (numerical weather prediction model), and finally, quantify the radiometric impact of the
unfiltering process on the final products.
Deliverables:
Study Report
Current TRL:
TRL 1
Target TRL:
Application/Mission: GMES 4, 2015
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
TRL5 by 2011
18 months
Dossier0 Ref.: T-7769
N/A
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TRP Work Plan 2008-2010
Description of Activities
TRP Reference:
T116-037MM
Title:
Ultra narrow linewidth phase locked laser for beam splitting
TD:
TD17
Objectives
The provision of an optical ultra precise frequency beam splitting and re-combiantion control for the cold
atom sensor system. The phase error between the beam splitters must be less then 1mRad to achieve the
highest rotation resolution from the sensor.
Description
In this application (cold atom interferometers) the prepared atoms must be split and recombined optically in a very
precise and controlled manner to observe the interference pattern caused, for example by a rotation of the frame
containing the sensor. This can be done by the realisation of Raman Lasers whose function are to split and later
recombine the atoms in the atom interferometer. The interferometer functions like any interferometer where now the
atoms are controlled (split and re-combined) by light. Because the shift required is so small the laser frequency/phase
needs to be very controlled and precise.
Deliverables:
Semiconductor Raman laser for beam splitting and re-combination either for Rb or Cs with ultra low phase error
between sources by using ultra precise microwave equipment coinciding with either the Rb or Cs ground state
splitting.
TRL 3
Current TRL:
TRL 2
Application/Mission:
Earth Gravity Post-GRACE type
missions, by 2018
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.:
T-8194, T-8186, T-8187,
T-8189
TD:
TD17
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
TRL5 by 2012
24 months
N/A
TRP Reference:
T116-038MM
Title:
Red-enhanced L3CCD and gain stability evaluation
Objectives
Development of a breadboard demonstrator and a detailed understanding of the underlying physics of the
ageing (gain degradation) of its L3 register, providing a reliable behaviour prediction model.
Description
Good sensitivity in the long wavelength range requires a thick photo-active layer with a large depletion depth. This is
achieved by a thick Si epi-layer in high-resistivity material. Implementation of a charge-amplifying L3 register with
corresponding high-voltages is not straight-forward but has been developed at E2V and can be considered mature.
The Lidar-specific design will strongly benefit from the devices developed under a current contract targeting the UV
region for Earth-care. A minor re-design will be needed to improve the linarity at low signals. However, a more
systematic and thorough investigation of the ageing process is urgently needed to reliably establish gain degradation
as a function of operating parameters & establish proper burn-in procedures. This is only superficially addressed at
present, but is critical for radiometry.
Deliverables:
The deliverables shall consist in a bread-board of a red-enhanced lidar detector and a validated ageing model to
reliably predict its performance during its lifetime.
Current TRL:
TRL 1
Target TRL:
Application/Mission: Lidar Missions, 2015
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRP Reference:
T116-039MM
TRL 3
Application
Need/Date:
Contract Duration:
TRL5 by 2011
24 months
Dossier0 Ref.: T-7886
Technologies for Optical Remote Passive Instruments, Roadmap
Ref A2
TD:
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TD17
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TRP Work Plan 2008-2010
Description of Activities
Title:
Solar-blind UV Lidar Detector
Objectives
Pre-development of a breadboard to address the UV spectral range which is becoming increasingly in
demand for various Lidar instruments and being extended towards ~250nm (e.g. Post-EPS)
Description
While the Roadmap refers to Diamond, more recent results indicate that AlN is capable of the same high performance
levels with the advantage of greatly eased manufacturability. Diamond only maintains its advantage for extreme
thermal requirements…
Deliverables:
Technology demonstrator breadboard
Current TRL:
TRL 1
Application/Mission: Post-EPS, 2018
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
TRL 3
Application
Need/Date:
Contract Duration:
TRL5 by 2012
24 months
Dossier0 Ref.: T-7886
Technologies for Optical Remote Passive Instruments, Roadmap
Ref. D8
TRP Reference:
T116-040MM
TD:
TD17
Title:
Low dark current 2D TIR CMT detectors based on p/n technology
Objectives
Development of a breadboard to a higher maturity level (~EQM) targeting the concrete needs of TRAQ
Description
Earth observation missions are placing more demanding requirements on long wave TIR performance, in terms of
both spectral and imaging response. The majority of MCT PV arrays are currently manufactured using n on p
technology where the n-type region is created by ion implantation into a p-type epitaxial substrate. Reversing this
structure using an n-type substrate with p-type implantation has the possibility to reduce dark current and/or increase
detector operating temperature, both desirable improvements. This activity aims to develop a high maturity
demonstrator.
Deliverables:
Technology demonstrator breadboard
Current TRL:
TRL 2
Target TRL:
Application/Mission: TRAQ and others, by 2015
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
TRL5 by 2011
24 months
Dossier0 Ref.: T-8176
Technologies for Optical Remote Passive Instruments, Roadmap
Aim C
TRP Reference:
T116-041MM
TD:
TD17
Title:
Mercury cadmium telluride avalanche photodiode detector with >2 um cut-off
wavelength.
Objectives
Development and characterisation of a mercury cadmium telluride (MCT) single avalanche photodiode
(APD) detector for use in satellite LIDAR missions to monitor greenhouse gases.
Description
Photon counting detectors in the SWIR waveband have direct application in the areas of LIDAR missions for
greenhouse gas monitoring. This activity will aim at developing a large area single MCT APD and supporting
electronics to demonstrate this capability.
Deliverables:
Technology demonstrator breadboard
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Description of Activities
TRL 2
Current TRL:
Target TRL:
TRL 4
Application/Mission: A-SCOPE, by 2015
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
TRL5 by 2011
18 months
Dossier0 Ref.: T-7886, T-8187
Technologies for Optical Remote Passive Instruments, Roadmap
Ref. C6
TRP Reference:
T116-042MM
TD:
TD17
Title:
Development of an adhesive-free bonding technique for optical components
through substrate metallisation and hard soldering
Objectives
Development of a method for bonding of different optical substrates and fibres to mechanical structures
(optical benches, mirror mounts) without the use of (potentially outgassing) adhesives to reduce molecular
contamination criticality in high fluence laser systems in vacuum environment.
Description
The method that shall be developed is based on metallisation of different optical substrates and hard soldering to a
metal structure.
Deliverables:
Technology demonstrator, e.g. laser diode (stack) module
TRL 3
Current TRL:
TRL 1
Application/Mission:
Future LIDARs and altimeters, by
2015
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-8186
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
TRL5 by 2012
24 months
N/A
TRP Reference:
T116-043MM
TD:
TD17
Title:
Laser Source for Atmospheric CO2 and Methane Monitoring
Objectives
This activity shall complement ongoing TRP activities on the development of source (laser + FC or fibre
laser) and receiver technology in the 2.05 ?m domain by exploring the feasibility and performance of a
Holmium solid-state laser source at 2.05 ?m for spaceborne DIAL measurements of CO2 and methane.
In particular the development shall demonstrate both the extremely challenging spectral performance as
well as the pulse energy levels of the transmitter required for the measurements.
Description
The measurement of atmospheric greenhouse gases from space represents a technical challenge in terms of laser
transmitter and receiver technology. Previous studies have identified the spectral bands around 1.57 ?m and 2.05 ?m
as the best candidates for active sensing of CO2 and methane. For the generation of laser radiation at any of the
considered frequencies in the targeted bands there is either the possibility of frequency conversion (FC) of an
“established” laser source, e.g. Nd:YAG, to the target wavelength or the option of direct generation (DG) from a
suitable laser material. While the FC approach in general benefits from a certain flexibility with respect to the choice of
target wavelength, the DG approach shows potential for a lower overall system complexity and increased wall-plug
efficiency. In the 2 ?m spectral domain powerful Holmium-lasers have been demonstrated suitable for (terrestrial)
atmospheric water vapour DIAL. Such a laser source offers the potential of DG generation of laser radiation at 2.05
?m for CO2 and methane spaceborne monitoring. This activity shall complement ongoing TRP activities on the
development of source (laser + FC or fibre laser) and receiver technology in the 2.05 ?m domain by exploring the
feasibility and performance of a Holmium solid-state laser source at 2.05 ?m for spaceborne DIAL measurements of
CO2 and methane. In particular the development shall demonstrate both the extremely challenging spectral
performance as well as the pulse. The implementation of this activity is conditional on the selection of the A-SCOPE
mission.
Deliverables:
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Description of Activities
Breadboard of critical transmitter unit
Current TRL:
TRL 2
Target TRL:
TRL 3
Application/Mission: A-SCOPE, by 2015
SW Clause :
Contract Duration:
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
TRL5 by 2011
20 months
Dossier0 Ref.:
T-8186, T-8187, T-8188,
T-8189
TD:
TD17
N/A
TRP Reference:
T116-044MM
Title:
High-Stability Laser with Fibre Amplifier for Interferometric Earth Gravity
Measurements
Objectives
This activity aims at an early instrument pre-development of a high-stability solid-state or fibre laser source
with fibre booster amplifier that is suitable for the purposes of the LDI mission.
Description
The Directorate of Earth Observation is currently in the process of defining a follow-up mission to GOCE, that offers
both higher spatial resolution and measurement accuracy in the mapping of the Earth’s gravity field. A previous GSP
study (“Laser Doppler Interferometry Mission for Earth Gravity” [LDI]) has shown the principal feasibility of such
undertaking based on optical interferometry between two satellites in 10 km distant formation flight. As a first
development step the ongoing TRP activity “Laser Interferometry High-Precision Tracking for LEO” is to demonstrate
the measurement principle with reduced performance requirements in a laboratory setup. The final
mission-representative measurement precision relies crucially on the availability of an extremely long-term stable laser
source, the specifications of which are close to but a bit more relaxed than those of the lasers for LISA. This activity
aims at an early instrument pre-development of a high-stability solid-state or fibre laser source with fibre booster
amplifier that is suitable for the purposes of the LDI mission.
Deliverables:
Demonstrator breadboard of the highly stable laser source
Current TRL:
TRL 2
Target TRL:
TRL 3
Satellite-to-satellite interferometry
Application/Mission: missions for Earth gravity
mapping, by 2018
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
TRL5 by 2012
20 months
Dossier0 Ref.: T-8186, T-8188, T-8189
N/A
TRP Reference:
T116-045MM
TD:
TD17
Title:
Back-thinned InGaAs array for visible-SWIR imaging
Objectives
Development of a thinned, back-illuminated InGaAs array for single-detector imaging in the visible and
SWIR wavebands.
Description
Spectral imaging in the visible and SWIR wavebands has a number of applications in Earth observation and planetary
spectroscopy and is traditionally achieved with two or more detectors. A thinned, back-illuminated InGaAs array offers
the possibility to have a detector that has high sensitivity from 400 to 1700 nm or even 2500 nm with moderate
cooling. InGaAs material is sensitive to wavelengths in both the visible and NIR but arrays are fabricated on an InP
substrate which is opaque to wavelengths below about 900 nm. Thinning the InP layer and illuminating from the back
surface allows the shorter wavelengths to reach the InGaAs array without affecting the NIR sensitivity. This activity will
aim to develop a fully functional array of moderate size to demonstrate this capability.
Deliverables:
Technology demonstrator breadboard
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Description of Activities
Current TRL:
TRL 1
Application/Mission: TRAQ, by 2015
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
TRL 3
TRL5 by 2011
Application
Need/Date:
Contract Duration:
24 months
Dossier0 Ref.: T-8173, T-8184
Technologies for Optical Remote Passive Instruments, Roadmap
Ref. C4
TRP Reference:
T116-046MM
TD:
TD17
Title:
Pulsed Laser Source at 1.57 micro-meters for Atmospheric Greenhouse Gas
Monitoring
Objectives
This activity shall complement ongoing TRP activities on the development of source and receiver
technology in the 2.05 micro-m domain by exploring the feasibility and performance of a solid-state or
fibre-based laser source at 1.57 micro-m for spaceborne DIAL measurements of CO2 and methane. In
particular the development shall demonstrate both the extremely challenging spectral performance as well
as the pulse energy levels of the transmitter required for the measurements
Description
The measurement of atmospheric greenhouse gases from space represents a technical challenge in terms of laser
transmitter and receiver technology. Previous studies have identified the spectral bands around 1.57 ?m and 2.05 ?m
as the best candidates for active sensing of CO2 and methane. While the 2.05 ?m band appears to offer some
advantages from a spectroscopic point of view, the 1.57 ?m band could largely benefit from the heritage of laser
technology at 1.55 ?m developed for the terrestrial telecom market. At this point in time the definitive selection of
either spectral band cannot be made as the trade off comprises a number of performance characteristics of laser
source and receiver which are currently only vaguely known. This activity shall complement ongoing TRP activities on
the development of source and receiver technology in the 2.05 ?m domain by exploring the feasibility and
performance of a solid-state or fibre-based laser source at 1.57 ?m for spaceborne DIAL measurements of CO2 and
methane. In particular the development shall demonstrate both the extremely challenging spectral performance as
well as the pulse energy levels of the transmitter required for the measurements. The implementation of this activity is
conditional on the selection of the A-SCOPE mission.
Deliverables:
Breadboard of critical transmitter unit
Current TRL:
TRL 1
Target TRL:
Application/Mission: A-SCOPE, by 2015
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
TRL5 by 2011
Application
Need/Date:
Contract Duration:
18 months
Dossier0 Ref.:
T-8186, T-8187, T-8188,
T-8189
TD:
TD16
N/A
TRP Reference:
T116-047MM
Title:
High efficiency volume Bragg gratings (VBG) for spectrometry
Objectives
Identify the possible uses of volume Bragg gratings (VBG) for TRAQ and FLEX missions (high efficiency
filters, chirped VBG for beam dispersion etc…) and assess the expected performances. Design of VBG
with Photo-Thermo-Refractive (PTR) glass. Procure and test VBG made of PTR in representative
environment.
Description
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Description of Activities
Volume Bragg grating (or Volume Phase grating) is a well known technology for spectral filtering, spectral dispersion
etc… Its main advantages are high peak diffraction efficiency, polarisation effects lower than for bulk gratings, low
level ghosts and scattered light etc…
A number of materials can be used for recording permanent holograms (LiNbO3, crystals, photosensitive glasses and
bulk photopolymers). Nowadays for large holograms, a sandwich glass/polymer/glass is used, but a photosensitive
glass named PTR and manufactured in the USA have shown properties making the VBG an interesting alternative in
space applications to bulk dispersive elements as reflection diffraction gratings, prisms, grisms for the visible and Near
InfraRed.
On a PTR substrate, holograms with spatial frequencies of 10 000 mm-1 can be recorded, the phase pattern can not
be erased by any type of optical or ionizing radiation and heating up to 400 C are tolerated. Furthermore the substrate
can be polished as any ordinary optical glass. Some possible applications are high resolution spectroscopy, spectral
beam combining, tuneable narrow band filter, beam steering, slitless spectrometry and imaging spectrometry.
It is of great interest to assess the relevance of this technology for space applications. For this, the possible
applications in the missions FLEX and TRAQ will be identified. Then, those devices will be designed and their
performances will be assessed with respect to the requirements of FLEX and TRAQ missions. Finally representative
samples of VBGs made of PTR will be procured and tested.
Deliverables:
Test results and VBGs samples
TRL 2
Current TRL:
Target TRL:
TRL 3
Application/Mission: TRAQ, FLEX by 2015
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
TRL5 by 2011
18 months
Dossier0 Ref.: T-8172, T-8183
N/A
TRP Reference:
T116-048MM
TD:
TD16
Title:
High-performance low-straylight gratings for compact high resolution optical
spectroscopy: Immersed grating technology for compact high resolution optical
spectroscopy in the near-infrared
Objectives
Study and exploration of high resolution grating technologies for future EO missions. Short list selection of
a few realistic high resolution grating technologies. Breadboarding of a promising approach.
Description
Spectrometers equipped with conventional diffraction gratings have a spectral resolution inversely proportional to the
telescope aperture and the angular slit width. To increase the spectral resolution while maintaining the instrument
dimensions, immersed gratings for instance have been proposed in the literature. Other techniques, based on new
optical structures and materials (meta-materials, photonic crystal structures etc.), might also contribute to a spectral
resolution improvement in future space borne spectrometers. The activity shall therefore initially investigate all
imaginable materials and techniques to achieve an increase in spectral resolution and to reduce the level of straylight
generated. Samples shall be produced and tested to assess the suitability of the materials and technologies. The most
promising approach shall then be selected for the detailed design and the production of a full-size grating (> 100 mm
diameter). Optical performance and environmental tests shall be executed to assess the performance in space.
Deliverables:
Full-size grating
TRL 4
Current TRL:
TRL 1
Application/Mission:
FLEX, TRAQ, Sentinel 4, Sentinel
Contract Duration:
5 by 2015
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
TRL5 by 2011
18 months
Dossier0 Ref.: T-8172
N/A
TRP Reference:
T116-049MM
Title:
Micro Optics Filtering Technology
TD:
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TD16
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TRP Work Plan 2008-2010
Description of Activities
Objectives
Demonstrate the feasibility of micro optics filtering technology to be used for on-board spectral calibration
of DIAL systems.
Description
DIAL systems can be used to map the density of atmospheric molecular species. In a DIAL system, typically the
selected “on” and “off” absorption lines are very close to each other (within <1nm) to ensure the same scattering
properties (scattering by the same molecular specie). To control the exact central wavelength position of the emitted
laser lines, onboard spectral calibration might be required.
Micro optics filters, like optical fiber devices, can be used to perform filtering and de-multiplexing of optical signal. The
major advantages of these devices are being very compact and lightweight. High resolution tunable filters with very
narrow bandwidths can be manufactured on optical fibers and offer, at least, identical optical performances as
standard optical filters. These devices can be used for onboard DIAL spectral calibration. Since they could be included
in the DIAL transmitter path the normal coupling problems, associated with these types of single mode devices, are
not critical. Specific fiber based interferometers, FBG devices or embedded FP within the fiber can be considered as
potential technical solutions. Currently, on another ESA activity, optical fiber filters are being developed to
demonstrate the feasibility of tunable, narrow band and thermal stable optical filters based on fiber technology.
This activity shall include:
• Study of micro optics filters based on fiber devices
• Assess the use micro optical filtering on the on-board spectral calibration of DIAL space systems
• Manufacturing and testing of a representative breadboard based on micro optics devices, for the spectral calibration
of a DIAL system. The implementation of this activity is conditional on the selection of the A-SCOPE mission.
Deliverables:
Micro optics filtering breadboard
TRL 3
Current TRL:
TRL 2
Application/Mission:
A-SCOPE, SPACEWAVES, by
2015
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-8188
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
TRL5 by 2011
18 months
N/A
TRP Reference:
T116-050MM
TD:
Title:
Optical filtering for onboard LIDAR calibration
TD16
Objectives
Study and demonstration of optical filtering technology for onboard LIDAR calibration
Description
LIDAR instruments require accurate spectral and radiometric calibration of the emitted laser line. This is particularly
critical for DIAL(Differential absorption LIDAR) systems where several wavelengths are used (with “on” and “off” lines
very close to each other) and because the measurement relies on differential absorption techniques (requiring
accurate knowledge of the laser power for each line). On ground, DIAL systems usually use specific gas cells to
perform calibration. Calibration systems using gas cells can be bulky and requires the use of pressurized containers.
One alternative to gas cells could be to use high stable and tuneable optical filters. Possible solutions are Fabry-Perot
etalons (with capacitive or thermal control and stabilization) or micro-optics technology (fiber embedded devices).
The activity shall include:
• Study techniques for in-flight optical calibration (determination of radiometric and spectral properties of emitted laser
lines) of future space DIAL systems (A-SCOPE or SPACEWAVES)
• Review optical filtering technologies (including macro and micro optics)
• Propose possible configurations for the optical calibration sub-system and perform system level trade-offs (including
using the receiver optical filtering sub-system)
• Demonstrate the selected concept and technologies feasibility by designing, manufacturing and testing a
representative optical calibration sub-system breadboard.The implementation of this activity is conditional on the
selection of the A-SCOPE mission.
Deliverables:
Lidar optical calibration sub-system breadboard.
Current TRL:
TRL 2
Target TRL:
TRL 4
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Application
Need/Date:
TRL5 by 2011
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TRP Work Plan 2008-2010
Description of Activities
Application/Mission:
A-SCOPE, SPACEWAVES, by
2015
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-8188
Consistency with Harmonisation
Roadmap and Conclusions:
20 months
N/A
TRP Reference:
T116-051MM
TD:
Title:
Large Aperture Telescope Technology
TD16
Objectives
Develop lightweight telescope technology for LIDAR applications. Manufacture representative breadboard
for functional and environmental testing.
Description
The effective aperture of a telescope is a key design parameter in LIDAR instruments. The aperture size of the
telescope defines the amount of backscattered laser energy collected by the telescope making it a fundamental
parameter in the determination of the signal to noise ratio (SNR) of the instrument. In order to increase the LIDAR
SNR, the aperture of the LIDAR telescope needs to be maximized. This allows the relaxation on the power of the laser
transmitter that might be also limited by technology or eye safe considerations. In addition the spacecraft total power
consumption is also reduced. The use of large aperture telescopes for space applications is however limited for
several technological reasons. The first limit is the space available for the payload inside the launch fairing, which for
medium-sized launchers can be less than 2 m in diameter. Secondly, since the payload mass drives the launch costs,
the extreme restrictions on the payload mass budget demand the use of very lightweight materials and innovative
design techniques. A recently concluded ESA activity studied large aperture telescopes using deployable mechanisms
and thin deformable primary mirror. It was demonstrated that a LIDAR telescope could have >9m2 aperture with an
area density < 16kg/m2. This previous activity focused on the demonstration of the actuator performances and on the
electrostatic locking mechanism required for the thin mirror survival during launch. A second activity is going to start to
demonstrate critical technologies for the future development of a deployable large aperture telescope.
This activity shall make use of the lightweight telescope technologies developed and demonstrated on the past
activities, and combine these developments on a representative breadboard. The breadboard shall be used to
demonstrate the feasibility to achieve large aperture and lightweight mirrors, with the required optical performance and
be able to withstand vibration and thermal testing.
The activity shall include:
• Review of deployable and lightweight telescope technologies
• Develop lightweight telescope technology for LIDAR applications
• Design and manufacture of a representative breadboard (curved spherical/parabolic mirror)
• Perform optical and environmental testing
Deliverables:
Representative breadboard of a large aperture telescope for LIDAR applications
Current TRL:
TRL 2
Target TRL:
Application/Mission: SPACEWAVES, LIDARs, 2015
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 4
Application
Need/Date:
Contract Duration:
TRL5 by 2011
24 months
Dossier0 Ref.: T-341, T-371
N/A
TRP Reference:
T116-052SF
TD:
TD17
Title:
Critical Technology for future imaging spectrometers in the UV to SWIR range
and Fourier Transform Spectrometers (FTS)
Objectives
To study Criticial Technologies for future imaging spectrometers in the UV to SWIR range and Fourier
Transform Spectrometers (FTS)
Description
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Description of Activities
In the on-going phase 0 studies for the 6 candidate missions new technology requirements might be formulated. In the
case of TRAQ, this might be for pushbroom imaging spectrometers covering the range from UV to SWIR
wavelengths. This includes technologies for detectors and calibration aspects. In addition, the Fourier Transform
Spectrometer and the multi-view polarisation-resolving radaiometer development might require further technology
developments. This activity would target the new technology requirements formulated in the studies. The
implementation of this activity is conditional on the selection of the TRAQ mission.
Deliverables:
Study reports. Breadboards.
Current TRL:
TRL2
Target TRL:
Application/Mission: TRAQ, Post-EPS, by 2015
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL4
Application
Need/Date:
Contract Duration:
TRL5 by 2011
24 months
Dossier0 Ref.: T-8174
N/A
TRP Reference:
T116-053SF
Title:
Critical Technology Activities for high spectral resolution fluorescence imaging
spectrometer
TD:
TD16
Objectives
To study Critical Technologies and breadbording of critical units and components of high spectral
resolutions fluorescence imaging spectrometers
Description
For a high resolution fluoresence imaging spectrometers, covering the oxygen A- and B lines with a sub-nanometer
resolution critical technology areas need to be defined, solution analysed and breadboarded. This includes
technologies for optical spectrometer, detectors and calibration aspects.
Deliverables:
Study reports & Breadboards
Current TRL:
TRL 2
Target TRL:
Application/Mission: FLEX, by 2015
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 4
Application
Need/Date:
Contract Duration:
TRL5 by 2011
24 months
Dossier0 Ref.: T-8184
N/A
TRP Reference:
T116-054SF
Title:
VLWIR Detector breadboarding for an Infrared Limb sounder
TD:
TD16
Objectives
VLWIR Detector breadboarding for an Infrared Limb sounder based on the outcome of the MTG IR
detector activities.
Description
Based on previous activities detector demonstrator shall be build concentrating on the proper size and critical
functionality (on-chip binning and low noise performance).
Deliverables:
Detector demonstrator. Reports
Current TRL:
TRL 2
Target TRL:
Application/Mission: PREMIER, by 2015
N/A
SW Clause :
TRL 4
Application
Need/Date:
Contract Duration:
TRL5 by 2011
24 months
Dossier0 Ref.: T-8181
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Description of Activities
Consistency with Harmonisation
Roadmap and Conclusions:
N/A
TRP Reference:
T120-055MC
TD:
Title:
Advanced Laser Instrument Thermal Design
TD21
Objectives
The objective is to develop an integrated, optimised thermal design concept for future (high-power)
laser-based instruments
Description
Solid-state laser instruments are very demanding with respect to thermal control. On one side the actual laser diodes
have to be thermally controlled fullfilling stringent requirements; e.g. high thermal flux densities, high temperature
stability and uniformity (over lifetime), increased dissipation over lifetime. On the other side, the optical medium needs
to be also thermally controlled with requirements on temperature stability and uniformity, while - at the same time being a quite fragile optical element. Current thermal designs are based on a 'box-level' approach, where heat pipes
(or potentially in the future loop heat pipes) are attached on the outside of the actual laser-box, i.e. quite away from
the actually to be thermally controlled items. Therefore such an approach results in rather low radiator temperatures
due to a number of thermal resistances in the heat path resulting - especiallly in LEO - in large radiators which
complicates the accommodation of such instruments.
The activity shall - based on one of the two currently existing laser design (i.e. ADM or ATLID) - critically review the
current thermal design. All
potential areas for improvement of the thermal design shall be clearly identified, taking into account advanced thermal
control tools. Based
on this, an advanced new thermal design concept shall be proposed resulting in reduced temperature drops, high
temperature stability and uniformity as well as temperature controllability. This activity shall be supported by adequate
thermal modelling to predict the performance of the new concept.
A demonstrator of the selected concept shall then be built and fully tested. Based on these activities, thermal design
guidelines and recommendations shall be issued for future laser designs.The implementation of this activity is
conditional on the selection of the A-SCOPE mission.
Deliverables:
Laser thermal control demonstrator
Current TRL:
TRL 2
Target TRL:
Application/Mission: A-SCOPE, by 2015
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 4
Application
Need/Date:
Contract Duration:
TRL5 by 2011
24 months
Dossier0 Ref.: T-8338
N/A
TRP Reference:
T124-056QM
Title:
Optical Components materials and process development and validation for high
power space borne lasers
TD:
TD25
Objectives
To understand and control the mechanisms responsible for laser-induced contamination and
laser-induced damage, paying particular attention to the wavelength dependency, laser chemistry, and
surface interactions responsible for these effects.To standardise the testing and validation procedures for
materials used for high power lasers in space.
Description
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Description of Activities
High power space borne lasers are currently being developed for several ESA missions (e.g. Aeolus, Earth-Care, and
their follow-on, Bepi Colombo). Experience with Aeolus is showing that the risk of laser induced deposition of
contaminants on optical elements (especially multi-layers) is placing new constraints on the materials and processes
which can be used for the satellite and payload. For example, out-gassing of materials routinely used for conformal
coatings and screw locking are known to induce contamination on the laser optics, even though these materials have
widespread acceptance for space use. Suppliers are often only qualified for processing specific materials, and do not
have alternatives readily available. In support of future missions utilising high power lasers, there is a need to
a) Understand the physics of the processes occurring in the contamination deposition and degradation, as well as the
causes for reduced damage threshold;
b) Establish the criteria for materials and process selection, screening and testing
c) Develop optical coatings which are more insensitive to laser induced contamination, especially in the UV, and which
exhibit high damage threshold in representative laser environmental conditions and optical configuration.
Deliverables:
i) Guidelines and standard test procedures for the selection and validation of materials and processes used for high
power laser missions, including a preliminary high power laser materials/optics database
ii) Optical coatings/optical assemblies with improved laser damage thresholds for a high number of laser shots,
particularly at 355nm, robust to laser-induced contamination via suitable choice of processes and materials
iii) Models for laser-induced contamination and laser-induced damage, validated by test, that can be easily applied to
current models used by the Agency.
Current TRL:
TRL 1
Target TRL:
Application/Mission: Laser based instruments, 2015
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
TRL5 by 2011
Application
Need/Date:
Contract Duration:
24 months
Dossier0 Ref.: T-8189, T-8186, T-419
Lidar Component Harmonization Dossier 2006
1-03 - Platforms/others
TRP Reference:
T101-057ED
TD:
TD01
Title:
SpaceFibre Very High Speed Link Technology Demonstrator
Objectives
Development of a SpaceFibre link capable to transfer up to 2 Gbps using FPGA and
Serialiser/Deserialiser components which are already available as radiation tolerant form. This to
demonstrate the feasibility of SpaceFibre to be used as very high speed link on board of satellites. Further
the SpaceFibre CODEC shall be developed and made available as ESA IP-core for distribution and reuse
in other projects
Description
SpaceWire with its maximum data rate of 160Mbps is the most powerful data link directly available for space
applications today. A number of optical and microwave earth observation instruments produce data at significantly
higher rates. At the moment the fall back solution is the use commercial data link components. These components
have to undergo a specific space qualification program including radiation testing. This is not only expensive but also
always carries the risk of failure. In order to address the recurrent need of very high speed data links the SpaceFibre
concept has been developed. It is an extension to SpaceWire and targets data rates up to 10 Gbps over optical fibre
as well as copper as physical medium. During this activity SpaceFibre CODECS shall be developed based on
components available in radiation tolerant technology in order to demonstrate the feasibility of a very high speed data
link and to evaluate the performance. An IP-core of the SpaceFibre CODEC shall be developed and documented to
allow reuse in other projects.
Deliverables:
SpaceFibre link demonstrator and SpaceFibre IP-core
Current TRL:
TRL 1
Application/Mission: All EO missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
TRL 3
Application
Need/Date:
Contract Duration:
TRL5 by 2011
15 months
Dossier0 Ref.: T-8328
On-board Paylaod Data Processing - B8.1
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Description of Activities
TRP Reference:
T105-058EC
TD:
TD05
Title:
On-board autonomous dynamic planning for operational observation wrt AOCS
constraints
Objectives
The objective is to develop and demonstrate on-board autonomous dynamic planning taking the AOCS
constraints into account.
Description
Higher agility allows now several possible scenes combinations for a pre-defined operational observation scenario.
On-board precise navigation allied with real-time processing of observed environmental conditions (e.g. clouds) or
target features (activity) would allow to maximise the observation sequences return, relying on real-time on-board
observation planification. This means that on-board sensing and optimisation algorithms shall be designed to plan
dynamically observation scenarii wrt AOCS constraints on agility, availability, safety and coping with transient
behaviours as well as spacecraft constraints such as payload illumination, thermal conditions whereas ensuring the
best observation return... All these new algorithms (from environmental conditions and scene features detection and
interpretation to optimisation and planning algorithms) shall be defined, designed and tuned as well as their interests
and limits checked against detailed simulations.
Deliverables:
Simulation models, demonstration platforms
Current TRL:
TRL 2
Target TRL:
Application/Mission: All EO missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
TRL5 by 2011
15 months
Dossier0 Ref.: T-8339
N/A
TRP Reference:
T105-068EC
TD:
TD05
Title:
Modern attitude control of EO satellites with large flexible elements
Objectives
To review state- of-the-art methods to achieve robust optimal control of satellites with large flexible
elementa such as BIOMASS and CoreH2O , with inputs from phase A activities, setup of simulation
framework, model definition, analyses.
Description
Based on the following inputs: models of the dynamics (of increasing detail, along the Phase A) of the BIOMASS and
COREH20 satellites, including flexible appendages (e.g. stiffness and damping matrices, with associated statistics),
the following tasks shall be performed: review of state-of-the-art (attitude) control methods to achieve the robust
optimal control of the spacecraft, set-up of simulation framework, of reasonably wide applicability for LEO flexible
satellites carrying large antennas and large solar arrays, definition of relevant models for sensors (incl. possibly
sensors on flexible elements) and actuators, analyses of dynamics models available, identification of possible
generalizations, application of selected design methods to specific cases of interest (particularly with reference to
BIOMASS), simulations to analyse performance, envelope and margins, to assess robustness with respect to
dynamic parameters, derivation of conclusions and (detailed) recommendations
Deliverables:
The following reports are required: analyses, review of methods, simulation models, preferred (detailed) algorithms for
attitude control of e.g. BIOMASS
Current TRL:
TRL 2
Target TRL:
Application/Mission: Biomass and H20
N/A
SW Clause :
TRL 4
Application
Need/Date:
Contract Duration:
TRL 5 2011
12 months
Dossier0 Ref.:
Consistency with Harmonisation
Roadmap and Conclusions:
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Description of Activities
TRP Reference:
T106-059ET
TD:
TD06
Title:
Advanced Techniques for High Data Rate Links for Earth Exploration Satellites
Objectives
The objective of this activity is two folded; on the one hand to identify, compare and propose advanced
coding and modulation schemes appropriate for high data rate telemetry links and to study and analyse
the adequacy and architectural impacts of implementing on-board pre-distortion techniques for high order
modulation schemes.
And on the other hand to provide analysis, modelling and simulations of mitigation techniques for High
Data Rate Telemetry communications systems based on dual polarisation and to cancel the interference
from other satellites operating in the same band.
Description
In order to better exploit the available bandwidth in the X-band, the implementation of a dual polarised system has
been proposed. One of the major objectives of the activity is to provide the analysis, modelling and simulation of a
High Data Rate Telemetry downlink architecture based upon the use of dual polarisation when using an isoflux
antenna.
In addition, a second scenario shall be investigated which considers the interference experienced amongst different
EO missions using different modulation schemes and operating in the X-band. The activity will identify a number of
realistic interference scenarios, assess the impact of the interference in terms of bit error rate degradation and
investigate effective restoration and mitigation methods that will prevent unacceptable communications link
degradation. The activity shall consider the operational aspects as well as the impact to the on-board and ground
segments (in terms of complexity). The activity shall propose an architectural design of the receiver, analysing
impacts in terms of acquisition, synchronisation, speed of the DSP, etc.
The other major objective of the activity is to provide a revision of the latest coding techniques; in particular those
proposed in the frame of CCSDS, like LDPC and SCCC and identify the most suitable codes for the high data rate
applications. Trade-offs shall be provided in terms of implementation, flexibility, complexity, performance and
compatibility with existing ESA standards.
The activity shall investigate pre-distortion techniques adequate for high rate telemetry links; in particular for the EO
scenario and high order modulation schemes, such as 8PSK, 16APSK. The activity shall consider static pre-distortion
as well as dynamic pre-distortion to compensate for the amplifier non-linearity characteristics changing over voltage,
temperature and ageing, propose the architecture and evaluate the complexity.
Deliverables:
Technical Notes, simulation software and mathematical models.
Current TRL:
TRL 1
Target TRL:
Application/Mission: All future EO missions
Operational SW
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 2
Application
Need/Date:
Contract Duration:
TRL5 by 2011
12 months
Dossier0 Ref.: T-8332
N/A
TRP Reference:
T106-067EE
TD:
TD06
Title:
Channel modelling for design of EO Ka band data downlink systems
Objectives
To develop propagation models for the design of the 26 GHz high data rate downlink system. The major
focus shall be on models combining the dynamic of the atmopsheric channel with the orbital patterns and
to assess the accuracy of advanced fade mitigation techniques in this configuration. Design of dual
polarizations systems shall be also included.
Description
Current propagation models for the design of data downlink systems are all almost derived for GEO SatCom systems.
Therefore they can be applied mainly for link budget analysis but the analysis of channel dinamical properties (fade
slope, fade duration) and the implememtation of fade mitigation techniques (e.g. site diversity, time diversity,
nowcasting, Adaptive coding and modulation) need to be improved to take into account the interaction between
atmopsheric components (gases, clouds and rain) and link dynamic during the passage over the station. This study is
aimed to start from the identification of key system aspects carried out from the findings of the current activity and to
adapt or develop new models to support system analysis (including the simulation and trade-offs).
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Description of Activities
Deliverables:
Final Report and prototype SW
Current TRL:
TRL 2
Target TRL:
Application/Mission: EO Missions
TBD
SW Clause :
TRL 4
Application
Need/Date:
Contract Duration:
TRL 5 2011
12 months
Dossier0 Ref.:
Consistency with Harmonisation
Roadmap and Conclusions:
TRP Reference:
T107-060EE
TD:
TD07
Title:
Innovative planar highly directive antenna based on artificial surfaces
Objectives
To demonstrate the use of quasi-periodic printed multilayer planar structures fed in-plane to obtain highy
directive shaped beams, with optional scanning capability, for Ka-band data downlink antennas.
Description
To provide an efficient, low-mass and low-cost solution for data downlink antennas with optional beam
switching/scanning capabilities. Such antenna is required for Ka-band data downlink in future missions.
Quasi-periodic planar structures obtained by multiple dielectric layers with printed metallic shape of suitable geometry
are known to be able to produce highy directive shaped beams when fed in-plane. A theoretical model has been
recently developed leading to a very effective design procedure and showing the possibility to operate the antenna in
dual polarisation. This solution will be applied to demonstrate the feasibility of simple, low-mass, low-cost and
high-gain Ka-band data downlink antenna concept with optional beam switching/scanning capability for.
Deliverables:
Validated design procedure and proof-of-concept design
Current TRL:
TRL 1
Target TRL:
Application/Mission: All future EO misions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 2
Application
Need/Date:
Contract Duration:
TRL5 by 2012
12 months
Dossier0 Ref.: T-8333
N/A
TRP Reference:
T107-061EE
Title:
Ka-band payload data downlink antennas definition for Earth Observation
TD:
TD07
Objectives
This activity shall identify and define suitable antennas designs and technologies for electronic steerable
Ka-band (25.5-27 GHz) antennas able to meet the data downlink requirements of future EO missions. The
activity shall include preliminary critical breadboarding and the antenna design shall be sufficient to enable
a follow-on demonstrator development activity.
Description
Current data downlinks at X-band are becoming an increasing constraint on the volume of data that can be handled.
The frequency band allocated to telemetry at Ka-band, 25.5-27.0 GHz, provides the capacity for downlinking at the
high data rates necessary to advance the usefulness of future EO missions. Consequently there is a definite need for
the design and development of suitable data downlink antennas operating in this band and which should also be
electronically steerable to meet the anticipated gain requirements for increased data rates.
Deliverables:
Advanced antenna designs/development sufficient for continuation to demonstrator activity
Current TRL:
TRL 1
Target TRL:
Application/Mission: All future EO missions
N/A
SW Clause :
TRL 3
Application
Need/Date:
Contract Duration:
TRL5 by 2011
9 months
Dossier0 Ref.: T-8333
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Description of Activities
Consistency with Harmonisation
Roadmap and Conclusions:
N/A
TRP Reference:
T118-062MP
TD:
TD19
Title:
Development of a Highly Throtteable Low Power Hall Effect Thruster for Earth
Observation.
Objectives
The objective of the activity will be to initiate the development of a highly throtteable, low power Hall Effect
Thruster designed to comply with the recent Earth Observation mission requirements. The activity will be
initiated only if the A-SCOPE mission is selected and its system definition results in electric propulsion
being retained.
Description
ESA founded studies have already identified Electric Propulsion as enable technology for future EO Missions due to
its high fuel mass efficiency and its high accuracy thrust capability. Those studies have highlighted the potential
payload advantages of using Electric Propulsion systems compared with Chemical Propulsion systems, gained by
reducing altitude and/or to increase the mission lifetime.
A LIDAR is the most promising payload that could use those advantages due to the direct link between
power-aperture product and altitude and performances.
As example, in the WALES mission with a high power LIDAR, baselined at 450 km with Chemical Propulsion, the use
of Electric Propulsion systems to perform drag compensation would allow an altitude reduction of 100km without an
increase of the total power consumption (assuming constant measurements performances). The most important
possible benefit was found to be the simplification of the LIDAR and the possible reduction in the aperture size and
mass of the payload which opens the possibility to use cheaper launchers.
The same could potentially be applied to A-SCOPE, one of the six candidates Earth Explorer missions, which is using
the same measurement principle as WALES and is currently baselined at 450km.
Taking WALES as reference to define future needed thrust requirements a range between 2mN - 15mN is identified.
ESA has initiated the development of a 100W-class HET in 2005, but this thruster seems to be able to fulfil just a
fraction of the required applications.
Within the proposed project the Contractor will design and build a low-power, highly throtteable, HET prototype
capable to satisfy the envisaged thrust range required. The prototype will undergo a functional test campaign in order
to modify the thruster design in preparation of an Engineering Model definition.
Moreover, being the successful implementation of a low-power HET into a flight ready propulsion system dependent
on a number of additional elements (Power Supply Unit and suitable propellant feed system) and although hardware
development of these system elements is not required within this program, the Contractor shall also prepare
preliminary specifications that maybe used to plan development activities for these equipments. The implementation of
this activity is conditional on the selection of the A-SCOPE mission.
Deliverables:
Study Report
Current TRL:
TRL 3
Target TRL:
TRL 4
Application/Mission: A-SCOPE, by 2015
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
TRL5 by 2011
18 months
Dossier0 Ref.: T-8336
I2 (EP harmonisation)
TRP Reference:
T118-063MP
Title:
High Efficiency Inert Gas thruster
TD:
TD19
Objectives
Proof of Concept and Characterisation of a low power / high efficiency inert gas Resistojet
Description
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Description of Activities
There is increasing interest in the use of very low thrust inert gas thrusters for pointing and stationkeeping applications
for sensitive optical spacecraft, and also for several missions requiring accurate formation flying. The use of an inert
gas is often mandatory to prevent deterioation of the optical surfaces of the on-board instruments. This activity builds
on the experience of micro- and milli-Netwon class thrusters typically using Nitrogen (Isp ~70s) and combines it with
resistojet technologies (such as capillary heaters) to improve the performance of such thrusters.
Deliverables:
Proof of Concept Bread Board Model thruster, test reports
TRL 2
Current TRL:
Target TRL:
Future Earth observation
Application/Mission: spacecraft with fine pointing
requirements, 2018
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
TRL5 by 2012
12 months
Dossier0 Ref.: T-8336
N/A
TRP Reference:
T122-064QC
TD:
TD23
Title:
Radiation Evaluation of DDR-2/DDR-3 Memories for future high throughput Solid
State Recorders (1Gbit/2Gbit)
Objectives
This activity aims at evaluating radiation effects in commercially available state-of-the-art DDR memories.
Description
In support of future Spacecraft Solid State Recorder, state-of-the-art DDR-2/DDR-3 memories are required as current
SDRAM are becoming obsolete. As commercially available memories have no radiation testing history the objective of
this activity will be to radiation characterize current available DDR memories against TID and SEE effects in order to
identify candidate types for flight. Basic radiation characterization of various types of DDR memories shall be covered
during heavy ion, proton and Co-60 campaigns. These tests shall be carried out on a dedicated DDR memory test
system capable of performing Static and Dynamic (at max. speed) tests. Also an error mapping and error analysis
capabilities shall be developed for full identification of observed events. With DDR memories having a short life time everything around the radiation characterization shall be optimized for a fast turn around time.
Deliverables:
Test set-up, Test results
Current TRL:
TRL 1
Target TRL:
Application/Mission: All EO missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
TRL5 by 2012
24 months
Dossier0 Ref.: T-8329
N/A
TRP Reference:
T125-065GR
TD:
TD26
Title:
Open Rich Client Platform (RCP) for user service tools
Objectives
Assess progress and perspectives of Reach Client Platform environments and demonstrate their feasibility
and benefits for EO Ground Segment user interfaces.
Description
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Description of Activities
The modularity offered by the features and plug-ins architecture of an RCP allows delivering highly specialised
applications, instead of old-fashioned monolithic “core” applications. Reusing pieces of software between projects is
made easier: dependencies between plug-ins in an RCP environment are explicitly defined and enforced, making it
easier to safely pick and choose only those plug-ins that a particular application needs rather than forcing everyone to
use a monolithic “one size fits all” program. A plug-in can be either UI- or non-UI- based (a Catalogue GUI, a map
module, a HMA catalogue interface module, an orbit propagator, a product viewer,...).
The activity shall study the trends on open RCP environments for advanced user interface generation and
components creation and sharing. A prototype shall demonstrate and verify capabilities for specific cases like: search
on ESA catalogues, multiple layers 3D map display, product access and visualisation, possible cooperation with 3rd
party tools from relevant application domains. The objective is to identify an environment permitting in future the
convergence of different interfaces.
Deliverables:
Documented functional prototype.
Current TRL:
-
Target TRL:
Application/Mission: All EO missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Prototype
Application
Need/Date:
Contract Duration:
TRL5 by 2011
18 months
Dossier0 Ref.: T-553
N/A
TRP Reference:
T125-066GR
Title:
Support to topology
TD:
TD26
Objectives
Obtain an update on status, perspectives and capabilities on this topic.
Description
Individual features or shapes can be extracted from Earth Observation images. However their understanding as
specific objects is in many cases (particularly for the complex ones) possible only through the identification of relations
between neighbour objects, e.g., a nuclear plant identified by the proximity of specific components. Therefore, in order
to automate the identification of specific objects, it is essential to identify the single objects, but also their topological
hierarchies and relations, as well as the matching of this topology against pre-defined models.
The proposed activity shall analyse the state of the art and the perspectives of all theoretical and implementation
aspects for to the identification of image objects through topology information. These aspects shall include related
methodologies (object / feature extraction, geometry and topology information identification), models, tools (model
creation and matching vs. data) and supporting technologies (databases and management systems for storage,
search and retrieval of objects / features, geometry, topology and models).
A few representative cases shall be identified and related environment(s) and algorithm(s) shall be implemented in
order to demonstrate feasibility and capabilities.
Deliverables:
Technical report with asessement and ranking of the alternatives; algorithm(s) demonstrating techniques and
capabilities on selected cases.
Current TRL:
-
Target TRL:
Application/Mission: All EO missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Algorithm
Application
Need/Date:
Contract Duration:
TRL5 by 2011
18 months
Dossier0 Ref.: T-1569
N/A
3 - Human Spaceflight and Exploration Preparation
3-01 - Robotics Assistance technologies
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Description of Activities
TRP Reference:
T309-001GD
Title:
MMI for Exploration Missions
TD:
TD09
Objectives
To develop an algorithm for integrating visual and numeric data into a display, To prototype operations
with rovers and cameras
Description
ESA's current generation of mission control infrastructure provides facilities for displaying alphanumeric and numerical
data. However, there is no experience with payload-type data or controlling rovers by integrating images and other
data or developing a plan using image data. Planetary rovers may combine the provision of extensive numerical and
location data with image data gathered by multi-spectral devices and cameras. This study shall show how such data
can be extracted from telemetry packets and integrated into images; data can also be combined from other sources
(planning systems, prediction models, other rover instruments e.g. for distance measurement). The study will develop
a source of image data and numerical representative data. Prototype displays of graphical image data will be
developed to display the images and integrate state based numerical data and show planned paths and predictions of
paths.
Deliverables:
Source code for models, and infrastructure changes, Validation simulator and test cases, User Manual, Prototype
S/W, including test harnesses, data and procedures, and associated documentation
Current TRL:
TRL 1
Target TRL:
Application/Mission: Exploration Missions (>=2013)
Operational SW
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3-TRL 4
Application
Need/Date:
Contract Duration:
TRL5 by 2010
12 months
Dossier0 Ref.: T-8417
N/A
TRP Reference:
T310-003GF
TD:
TD10
Title:
Radio tracking of a landed spacecraft: determination of the spacecraft position
and of the planet's ephemeris and orientation in space
Objectives
In this study the usage of radiometric tracking data acquired from a spacecraft landed on a distant planet
shall be analysed. The objective is to use this tracking data to determine the position of the spacecraft on
the surface of the planet and to improve the knowledge of the planet's ephemerides and it's orientation
and rotation in space.
Description
When a spacecraft is delivered to a distant planet then it is important to specify its location on the surface of the
planet. One means to determine the location of the spacecraft is to use the Doppler shift in the radio communication
link between the lander and the ground station on Earth or between the lander and a relay satellite in orbit around the
planet. The usage of such a technique is directly applicable to the Exo Mars and the Rosetta mission as well as for
any other future ESA mission that involves landing on a solar system object. Apart from this direct operational
application the radio signal could furthermore be utilised to improve the knowledge of some planetary properties. Long
term Doppler measurements can be used to determine the orientation and rotation of the planet in space. Range
measurements between the landed spacecraft and the ground station on Earth contain information about the
ephemeris of the planet, which can therefore be improved by exploiting these measurements. For instance doing
ranging with Exo Mars when landed on the surface of Mars will significantly improve the ephemerides of Mars, which
is of benefit to all subsequent Mars missions. In fact, accurate planetary ephemerides are essential to reduce the risk
of planetary mission failures and to cope with increasing navigation demands of future planetary missions. Goal of this
study is to analyse on a case by case basis what accuracy of the estimated parameters can be expected under
different scenarios In order to do so a prototype software shall be developed that allows to determine the
aforementioned parameters from radiometric tracking data of a landed spacecraft. Re-usage of infrastructure software
modules that are already availabe within ESOC Flight Dynamics is foreseen in order to simplify and guide the
prototype software development.
Deliverables:
Deliverables are the final report, which shall cover the following: a description of the developed mathematical
algorithms, a description of the software and the tests that have been performed as well as results of the case studies.
Further deliverables are the prototype software itself including related documentation and scripts.
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Description of Activities
TRL 3
Current TRL:
0
Application/Mission:
Autonomous Robotic Systems
(>=2013)
Contract Duration:
SW Clause :
Operational SW
Dossier0 Ref.: T-7715
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
TRL5 by 2010
12 months
N/A
TRP Reference:
T313-004MM
Title:
Dexterous Robot Hand
TD:
TD13
Objectives
The goal of this activity is to produce a space robot gripper comparable to human-hands in terms of size,
strength and manipulation capabilities, to enable the handling of objects which can currently only be
handled by Astronauts in space suit. With such a hand a robot can also handle soft objects, e.g. removal
of multi-layer thermal insulation can be removed for access to equipmenmt (and placed back), which at
the moment is a task which consumes much EVA time).
Description
The activity shall produce a proof-of-concept demonstrator of a space robot hand. The hand will be tested in a
representative application.
The development shall start from the latest DLR hand, shall accommodate latest robust tactile sensors and shall
produce a system that can accommodate real space mission requirements and constraints.
Deliverables:
Proof-of-concept demonstrator of a space robot hand.
Current TRL:
TRL 2
Target TRL:
TRL 3
Lunar Orbital Hub Habitat,
Autonomous Robotic
Application/Mission:
Systems,Crew Assistants,System
Maintenance (2015)
SW Clause :
Operational SW
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
TRL5 by 2011-2012
21 months
Dossier0 Ref.: T-939, T-871, T-8429
"Automation and Robotics" 1st semester 2007 consistent with
activity A1 "Dexterous Robot Hand"
TRP Reference:
T313-005MM
Title:
Human Hand Exoskeleton
TD:
TD13
Objectives
The goal of this activity is to produce a human hand exoskeleton. This device is a sort of semi-rigid glove
that when worn by a human operator allows him to command a dexterous robot hand and receive haptic
feedback from it. The human hand exoskelton subject of this development is intended to be used both
in-orbit and on-ground. With such an exoskeleton hand a robot hand can be controlled in a very intuitive
way with a minimal amount of training, as has been demonstrated for controlling a robot arm with an
exoskeleton arm.
Description
The activity shall produce a proof-of-concept demonstrator of a human hand exoskeleton to be used both in-orbit and
on-ground, to control remote dexterous robot hands. The demonstrator shall be designed to smoothly integrate with
ESA human arm exoskeleton.
The control of a robot hand by the Human Hand Exoskeleton will be tested in a representative application, integrated
with the Exoskeleton arm.
Deliverables:
a proof-of-concept demonstrator of a human hand exoskeleton
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Description of Activities
Current TRL:
TRL 1
Target TRL:
TRL 3
Lunar Orbital Hub Habitat,
Autonomous Robotic
Application/Mission:
Systems,Crew Assistants,System
Maintenance (2015)
SW Clause :
Operational SW
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
TRL5 by 2011-2012
21 months
Dossier0 Ref.: T-939, T-871, T-8429
"Automation and Robotics" 1st semester 2007 consistent with
activity A2 "Human Hand Exoskeleton"
TRP Reference:
T313-006MM
TD:
Title:
Autonomous Controller
TD13
Objectives
The objective of this activity is to implement a general-purpose autonomous controller for autonomy level
E4 (Goal-oriented mission re-planning).
Description
In the course of many years ESA has developed a robust robot control system capable to operate on multiple robot
arms and to implement an autonomy level E3 (Event-based autonomous operations execution of on-board operations
control procedures) as per ECSS-E-70-11.
The activity shall produce a proof-of-concept demonstrator of autonomous controller for space robotics,l building on
the previous ESA developments (e.g. RT Operating Systems, Robot Control Software, Autonomous planning and
scheduling) to implement goal-oriented autonomy.
Deliverables:
a proof-of-concept demonstrator
Current TRL:
TRL 1
Target TRL:
TRL 2
Lunar Orbital Hub Habitat,
Autonomous Robotic
Application/Mission:
Systems,Crew Assistants,System
Maintenance (2015)
SW Clause :
Operational SW
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
TRL5 by 2011-2012
24 months
Dossier0 Ref.: T-939, T-8429, T-8430, T-8433
"Automation and Robotics" 1st semester 2007 consistent with
activity B1 "Autonomous Controller"
TRP Reference:
T313-007MM
TD:
Title:
Heavy Duty Planetary Chassis
TD13
Objectives
Exploration and exploitation of the Moon and in future of Mars, indisputably requires surface locomotion
means. The goal of this activity is to realise a general-purpose heavy-duty chassis, derived from the
ExoMars one, capable to constitute the body of a planetary robotic assistant (“centaur”configuration).
Description
The activity shall produce a proof-of-concept demonstrator of a heavy duty locomotion chassis capable to constitute
the body of a planetary robotic assistant (“centaur”configuration). Particular focus is required on the stability of the
platform, which must be kept high without limiting the usability of the robotic assistant.
Deliverables:
a proof-of-concept demonstrator of a heavy duty locomotion chassis
Current TRL:
TRL 1
Target TRL:
TRL 2
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Application
Need/Date:
TRL5 by 2011-2012
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TRP Work Plan 2008-2010
Description of Activities
Lunar Orbital Hub Habitat,
Autonomous Robotic
Application/Mission:
Systems,Crew Assistants,System
Maintenance (2015)
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Contract Duration:
12 months
Dossier0 Ref.: T-8429
"Automation and Robotics" 1st semester 2007 consistent with
activity C1 "Heavy Duty Planetary Chassis"
TRP Reference:
T313-009MM
TD:
Title:
Motion Control Chip
TD13
Objectives
The subject activity shall implement a motion control chip for Dependable space robotics applications
(Dependable Processing allows to do complex processing of science data onboard the spacecraft; using
standard commercial components arranged in a unique architecture, along with special software to detect
and correct radiation induced errors, this technology will allow to build computers that are more capable
than current day spaceborne computer systems). The controller based on the ESA proven LEON-3
architecture shall include all the peripherals needed to acquire common motion sensors (position, speed,
torque) process the control algorithm (specified with software), to provide signals to the power drives
(half or full bridge with PWM) and to communicate with a top level controller.
Description
The activity shall produce a technology demonstrator of a motion control chip for robotics applications. LEON-3
architecture shall include all the peripherals needed to acquire common motion sensors (position, speed, torque)
process the control algorithm (specified with software and logic code), to provide signals to the power drives (half or
full bridge with PWM) and to communicate with a top level controller.
Deliverables:
Technology demonstrator of a motion control chip for robotics applications
Current TRL:
TRL 1
Target TRL:
TRL 2
Lunar Orbital Hub Habitat,
Autonomous Robotic
Application/Mission:
Systems,Crew Assistants,System
Maintenance (2015)
SW Clause :
Operational SW
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
TRL5 by 2011-2012
27 months
Dossier0 Ref.: T-939, T-8429, T-8430, T-8433
"Automation and Robotics" 1st semester 2007 consistent with
activity A5 "Motion Control Chip"
3-02 - Life and Physical Sciences
TRP Reference:
T314-010MM
TD:
TD14
Title:
Continuous Physiological and Medical Monitoring (non-invasive)
Objectives
The objective of the activity is to demonstrate the feasibility of continuous, non invasive and automated
measurement of physiological and medical data with the help of a validated demonstrator.
Description
Continuous non-invasive monitoring of the main physiological/medical parameters is a precondition for a safe long
term exposure of human subjects to unusual conditions. This shall be applied to bedrest, centrifugation, isolation (eg
Concordia) and finally long term exposure under spaceflight conditions. The main parameters of interest will be
defined within the activity and concepts for the most important ones will be established. This will include inter alia
blood pressure as one of the key parameters to monitor in human physiology. For the demonstration of practical
feasibility the cuff-less blood pressure measurement is selected as the first concept to be demonstrated in practical
terms.
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Description of Activities
Current available techniques range from invasive direct measurement to widespread non-invasive, indirect
assessments: the arm- or wrist-cuff-based methods. The latter are well adapted to single measurements. They are
also used for longer-term monitoring , however have drawbacks as the inflation of the cuff every 30 minutes is a sure
disturbance to the sleep quality and moreover those techniques do not provide information about the status of the
vasculature parameters (such as arterial/venous compliance, arterial stiffness …). Those parameters are of increasing
importance to the cardiovascular diagnostics. Combined with the more classical cardiovascular parameters (ECG,
heart rate …) they would be of interest for space applications in assessing the status of cardiovascular de-conditioning
and measuring more accurately the efficiency of cardiovascular countermeasures. Several non-invasive/non obtrusive
measurement principles are reported in the specialised literature, and preliminary assessments show that a couple of
them are of high potential interest (tonometry-based, ultrasound-based, pulse transit time).
The main tasks in the present activity are: A) Review and recommend physiological parameters to be measured non
invasively; B) Refine the specifications and propose concepts;C) confirm the /signals and parameters of interest for
assessing the compliance of the vascular system (including: pulsed waveform, pulsed transit time, FFT of the arterial
waveform …); E) Assess the available solutions for cuff-less blood pressure monitoring (based on applicability to
space situations) and confirm or update the selected measurement principles (up to two); F) For the selected
principle(s) build a demonstrator and demonstrate its performance in vivo.
Deliverables:
Validated breadboard
TRL 3-TRL 4
Current TRL:
TRL 2
Application/Mission:
Human Exploration preparation /
Human Phsysiology (2015)
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-8422
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
TRL5 by 2012
24 months
N/A
TRP Reference:
T314-011MM
TD:
TD14
Title:
Integrated Countermeasures with biofeedback and actuators
Objectives
The aim of the activity is the development of an integrated system for countermeasures in the
neuro-sensory domain including the use of advanced bio-feedback system integrating physiological
signals into the loop.
Description
After prolonged interplanetary trips, the human neuron-muscular-skeletal system suffers severe deconditioning and
impairment of the corresponding functions. In particular, the loss of neuron-sensory control and motor skills can be
problematic and shall be counteracted efficiently. Integrated countermeasure systems shall be developed to allow
astronauts being fit as soon as possible after landing (be it on earth or at their destination, e.g. Moon/Mars). Two
parallel activities ( ESA Contracts 20766 and 20767) have been started to develop and test technology concepts for
integrated countermeasure systems to counteract the above-mentioned deleterious effects of prolonged microgravity
exposure. Building on them, the present activity is aimed at pursuing the initial development work as follows:
A)Developing an integrated system based on the outcomes of the previous activities; B) Develop integrated
biofeedback systems, e.g. integration of human physiological responses into the biofeedback loops, aimed at
optimising the musculo-tendinous responses; C) Assess, Develop and integrate into the Integrated Countermeasure
Stimulators new non-electromechanical actuators for the countermeasure systems, e.g. electro-active polymers,
distributed somato-sensory stimulators, usage of shape memory allow materials… : D)Characterize and when
possible evaluate the above-developed technologies on human beings.The next step (out of the present activity)
should be to develop a TRL6 integrated system.
The present activity can in addition have applications in the medical field, to rehabilitate or prevent the impairment of
the functions controlling the human voluntary movements or balance (elderly, post-stroke rehabilitation …)
Deliverables:
Technology Demonstrator and validated data
Current TRL:
TRL 2
Target TRL:
TRL 3-TRL 4
Application
Need/Date:
Human Exploration preparation /
Preparation for long duration
Application/Mission:
Contract Duration:
human missions in flight validation
0 (2013-2015)
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Description of Activities
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Dossier0 Ref.: T-8424
N/A
TRP Reference:
T314-012MM
TD:
Title:
X-ray based analytical and imaging devices
TD14
Objectives
Develop a consistent concept for the multidisciplinary application of x-ray based analytical and imaging
methods in the context of exploration.
Build and validate as a first step a technology demonstrator for a x-ray based analytical device for human
physiology, with imaging capabilities and integrated shielding.
Description
X-ray as non-destructive analytical method has a wide range of application ranging from the use in human physiology
to the imaging of the integrity of metallic structures. Within this range of application common building
blocks/subsystems have to be identified and integrated into a consistent concept for multidisciplinary application of
X-ray in the frame of space exploration.
As a first demonstrator in this context an application in human physiology is envisaged. Preparing for manned space
exploration will require a very good understanding of the dynamics of the space-flight related physiological
deconditioning (muscle, bone, motor control, cardio-vascular) a good assessment of the efficiency of the
countermeasures developed. To achieve this goal, accurate analytical and medical imaging methods will be required
in space. Even if known as one of the best analytical and imaging medical modalities, X-ray based analytical and
imaging technologies have not been used in space so far, mostly because the equipment was bulky, required power
levels hardly compatible with what a spacecraft could provide (in the KW range or more), and was producing quite
high levels of radiation. The advent of new technology for x-ray tubes now enable the use of analytical devices like
the peripheral quantitative computed tomography which not only would provide a very accurate analysis of the
dynamics of the bone structure changes but would also allow the analysis (and possibly imaging) of peripheral
bone/muscle systems and other types of soft tissues (like changes in bone marrow composition) with low doses of
x-rays (less than the dose received for one chest x-ray, or one round-trip between US East and West coast). By their
accuracy, these technologies would provide essential inputs to the better understanding of above-mentioned
dynamics of the spaceflight related physiological deconditioning and an accurate assessment of the effectiveness of
the countermeasures developed. However they are not available for being ready to use in space.
The purpose of the present activity is to:
A)confirm the leading requirements and parameters for building a space-compatible x-ray based human analytical
system for non-invasive analysis and possibly imaging of subsystems of the human body , including bone-muscle
system;
B)Identify the constrains for using a x-ray based analytical and imaging system in a space environment and derive the
design drivers for such a system (including: physical: power, energy, cooling, radiation operational and processing
constraints, including human safety (shielding));
C)refine the specifications of a space-compatible analytical x-ray based system, with imaging capabilities;
D)establish the technology concept and evaluate and test the critical technologies available on the market (including:
production and collimation of dual-energy soft x-ray, x-ray shielding, power, thermal aspects).
This includes proposing a preliminary design for a breadboard; Build and evaluate a demonstrator of a low-dose, high
accuracy x-ray based system with analytical and imaging capabilities.
Deliverables:
Validated Demonstrator
TRL 4
Current TRL:
TRL 2
Application/Mission:
Human Exploration preparation /
Moon/Mars Missions (2015)
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-8422, T309, T-8425
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
TRL 6 in 2012
24 months
N/A
TRP Reference:
T314-013MM
TD:
TD14
Title:
Non-stochastic detectors of bio-markers for space applications
Objectives
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Description of Activities
Develop concepts for single molecule detection based on nanotechnology methods.
Description
Space biology, be it autonomous exploration- oriented or manned, will have to make use of the recent developments
in the fields of nano bio-sensors, potentially able to detect bio- organic molecules by counting them, and not by
proceeding from a stochastic approach as is the case with traditional biological analysis. A wealth of developments
exist in that field (e.g. Euronanoforum 2005, or to-come Euronanoforum 2007). Nano-based bio-sensors have high
potential because they can be accommodated into very small size and weight, have potential for high
autonomy/automation and for extremely low power and reagents consumption. Most importantly, they also open the
field of detection by molecule counting, instead of stochastic detection, thus making it possible to address the
understanding of mechanisms of molecular signaling – a key to the understanding e.g. of the transmission of
neuromuscular signals or to the cell signaling mechanisms. This mode of determination will also be useful in the
extra-terrestrial biology, enabling the detection of bio-markers which might be present in so small amounts that
stochastic detection is hardly applicable. As this field of activity is evolving very rapidly the activity will include the
organisation of a workshop to review, evaluate and recommend / prioritise candidate technology concepts, amongst
the basic principles of nanobiosensing reported and/or concepts already proven.
Deliverables:
Identification of new and critical technologies
TRL 2
Current TRL:
TRL 1
Application/Mission:
Physical Science / On orbit and in
situ analysis (2017-2018)
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-8420
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
TRL5/6 in 2015
12 months
N/A
TRP Reference:
T314-014MM
TD:
Title:
Imaging of wave scattering in solids
TD14
Objectives
The objective of this activity is to achieve a non invasive diagnostic setup for the detection of
inhomogenities in solid materials, such as mixed phase materials, propagating cracks in alloys,
delaminating effects in composites etc. The contractor shall design, build and test a technology
demonstrator for various applications showing the feasibility and reliability of this measurement technique
for e.g fatigue detection in metals.
Description
Imaging of an elastic nonlinear wave-scattering source in solids is an imaging method for locating isolated nonlinear
scattering source(s) in solids. It relies on extracting the nonlinear response of a solid by modulation of a high by a
low-frequency wave, and employing moving-window, synchronous detection. The resulting image consists of
nonlinear wave reflection profiles with remarkable sensitivity to isolated elastic nonlinear sources, like cracks. In
creating the image, one can distinguish between a nonlinear scattering source(s) and other wave scatterers in the
material. By assembling a technology demonstrator and performing tests on various materials, like alloys, composites
and inhomogeneous materials, the feasibility and sensitivity of this technique shall be demonstrated.
Deliverables:
Technology Demonstrator, Test Data
TRL 2
Current TRL:
TRL 1
Application/Mission:
Physical Science / Long duration
Contract Duration:
missions (Moon/Mars) (2014-2015)
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
TRL 5/6 in 2011
18 months
Dossier0 Ref.: T309, T-8425
N/A
TRP Reference:
T314-015MM
TD:
Title:
Time Resolved Correlation Spectroscopy and Total Internal reflection Scattering
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TRP Work Plan 2008-2010
Description of Activities
Objectives
Breadboarding of a combined miniaturised setup for time resolved correlation spectroscopy and total
reflection internal scattering as a diagnostic tools for in situ investigation on foams, gels glasses and
emulsions.
Description
The present techniques that are used for the study of turbid media like colloidal glasses and gels, foams and
emulsions are all based on Diffusive Wave Spectroscopy , which allows the determination of the structural
modifications of the sample by measuring the time correlation of radiation diffused in the multiple scattering regimes.
There is another technique for investigating temporally heterogeneous dynamics, which is termed time-resolved
correlation (TRC). TRC is applied to data obtained by diffusing wave spectroscopy probing the slow dynamics of a
strongly aggregated colloidal gel. Other examples of TRC data, collected for different jammed materials in single and
multiple scattering, are provided to demonstrate the wide range of applicability of this method. In all cases there is
evidence that the slow dynamics results from a series of discrete steps rather than from a continuous motion,
suggesting temporal heterogeneities to be a general feature of slow dynamics in jammed systems. A novel technique
that is complementary to DWS is Total Internal Reflection Scattering (TIRS). From the detection of light reflected by
the surface above the total internal reflection angle (a region that is prohibited in geometrical optics), it is possible to
reconstruct spatial information of the sample (the two dimensional spatial Fourier) like traditional single scattering
techniques. Since the set-up of TIRS is very similar to DWS in reflection, it is believed that the combination of the two
techniques may be easily implemented in future microgravity experiments on foams, gels, glasses and emulsions.
Deliverables:
Breadboard and Test Results
Current TRL:
-
Target TRL:
Algorithm
Physical Science / Exploration
Application/Mission: Preparation / Study of Complex
Plasmas (2013-2014)
SW Clause :
Contract Duration:
Operational SW
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
TRL 5 in 2010
12 months
Dossier0 Ref.: T-8427
N/A
TRP Reference:
T314-016MM
TD:
Title:
Invasive Physiological Monitoring
TD14
Objectives
To develop an implantable device for monitoring several physiological parameters in mice.
Description
Scientific data generated during long term exposure of mice to reduced gravity (micro-g, Moon- and Mars-Gravity)
are considered as a valuable input for the planning of long term missions of human beings. The planned implantable
sensors to be used on-board FOTON in a mouse facility will allow to follow crucial phsyiological data on-line. The data
set contains body core temperature, heart rate, ECG and blood pressure and will be transferred by telemetry. This
allows a continuous monitoring of the physiological status of the animal. This will be of particular importance in future
oriented experiments e.g. drug testing in the context of countermeasures. The application of these tiny sensors to man
(implantation) on long term missions may be an interesting option to blood withdrawal in regular intervals, also seeing
the fact, that in the future this implants may equipped with tiny biochemical sensors. Ethical and personal (crew)
acceptance still has to be discussed. The concept has already been developed under ESA contract 19033 most of the
effort in this activity will be devoted to the development of the ASIC and its testing in the implant.
Deliverables:
Demonstrators of implants and receivers.
Current TRL:
TRL 2
Target TRL:
TRL 4
Human Exploration preparation /
Application/Mission: FOTON experiments with mice
(2014-2015)
SW Clause :
N/A
Application
Need/Date:
Contract Duration:
TRL 6 in 2011
18 months
Dossier0 Ref.: T-8422
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Description of Activities
Consistency with Harmonisation
Roadmap and Conclusions:
N/A
TRP Reference:
T314-017MM
TD:
Title:
Computer aided medical diagnostics and surgery
TD14
Objectives
The aim of this activity is to develop a demonstrator for Augmented Reality (AR) based assistance to high
precision echographical examination tasks and the extension of the technology towards assistance during
surgeries.
Description
A main challenge during human planetary exploration will be the diagnostics of the physical health of the astronauts
and the treatment of medical problems. A variety of diagnostic/treatment tools will be used for this, which usually
needs experts or long training. Experts and time are limited in space: therefore an - Augmented Reality (AR) based assistance tool shall guide the astronauts through various (medical) examination or treatment tasks. In the present
project a first step in the direction of such a multi-purpose guidance tool will be taken by the development of an
Augmented Reality based guide to high precision echography diagnostic: The astronaut will see in the interactive
mode the guidance information superimposed over his real view of the probe. As this technology shall also be used for
treatment - for example during surgical acts - an integrated concept for AR based assistance during surgeries will be
included in the project. The main tasks of the present activity will therefore be as follows: a)Review of critical
technologies of an Augmented Reality based assistance to high precision echography; b)Demonstration of critical
technologies (e.g.: superimposing the guidance information, calculating correct guidance information); c)Evaluation
and test (one possibility is Concordia); d)Assessment of extension towards a model surgical act.
Deliverables:
Technology Demonstrator, Verification Data
Current TRL:
-
Target TRL:
Algorithm/Protot Application
ype
Need/Date:
Human Exploration preparation /
Moon and Mars missions,
Application/Mission:
preparation/verification in ISS
context (2015)
SW Clause :
Operational SW
Consistency with Harmonisation
Roadmap and Conclusions:
Contract Duration:
TRL6 by 2012
24 months
Dossier0 Ref.: T-8423
N/A
TRP Reference:
T314-018MM
TD:
Title:
In-situ, continuous biochemical analyzer
TD14
Objectives
Develop on-line analysis of cell culture by-products. This includes the development of add-on
technologies required to prepare the human samples for immunobiochemical analysis and standardisation
of processes including test kits.
Description
Technologies for immuno biomedical analysis developed so far (I-BA 2, ESA Contract 19391) focused primarily on
monitoring blood or urine parameters. However, preparing for exploration, will require in addition to focus the attention
on the metabolism of drugs by the human body, hence cell cultures will have to be used for that purpose, especially in
microgravity conditions. For the future it would be of interest to have technologies that would allow to measure the
instantaneous reactions of a cell population to a given drug, whithout having to fix (kill) the cells for that purpose, as it
is traditionally done today. Methods enabling on-line analysis of cell-produced chemicals to follow-up the cell reactions
to drugs concentrations in a continuous way is of high interest for the future. Building on the technologies for
bio-chemical analysis developed within previous TRP activities, the proposed activitiy is aimed towards the adaptation
of the microgravity-compatible technologies to a continuous monitoring of the cell development cycles and cell
reaction to drugs on-line in the the living cell culture. Building on this previous development, the main tasks of the
present activity would be: A) Confirm the classes of bio-markers and parameters to measure; B) Define interfaces
with cell culture systems (generic, specific);C) Confirm the methods for sampling fluids and sample conditioning; D)
Specify, Build and validate a breadboard.
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Description of Activities
Deliverables:
Validated Breadboard
Current TRL:
TRL 2
Target TRL:
TRL 3
Application/Mission: Human Exploration (2013-2014)
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
TRL5 by 2010
24 months
Dossier0 Ref.: T-8420
N/A
3-03 - Human Exploration Technologies
TRP Reference:
T304-019EE
TD:
TD04
Title:
Physics models for biological effects of radiation and shielding
Objectives
Development and validation of new physics models for biological effects of very high energy cosmic ray
heavy ions encountered in interplanetary space and lunar/planetary surfaces, including shielding aspects.
Description
Improved heavy ion hadronic physics modelling has been identified as a key development requirement by the space
radiation effects and shielding community e.g. in the independent external review of the Geant4 collaboration in 2007.
This is especially important for future Exploration missions beyond the Earth's magnetosphere, where unattenuated
fluxes of highly damaging very energetic cosmic rays are encountered. The present activity will start with an analysis
of Geant4 and other Monte Carlo codes capable of hadronic physics simulation (e.g. FLUKA, PHITS, RQMD),
including analysis of relevant theoretical models, analytical codes (e.g. US HZETRN code), and experimental data.
Methods of implementing and interfacing the best models into the Geant4 formework shall be developed. The
resulting software will be thoroughly validated by comparisons to experimental data (exisiting or produced in the
activity) and to other codes. The resulting codes will be applied to realistic cases dealing with human effects.
Emphasis shall be put on the usability of the codes both in terms of computing speed and availability through widely
accepted engineering interfaces (e.g. Spenvis).
Deliverables:
New models of heavy ion hadronic physics interactions for shielding and human effects analyses for future manned
missions; engineering implementations and interfaces for these models. Experimental work where necessary.
Reports.
Current TRL:
TRL 1
Target TRL:
TRL 3
Application
Need/Date:
Human exploration - habitat / All
manned projects beyond ISS, in
particular to lunar/interplanetary
environments and EVA, shielded
Application/Mission:
Contract Duration:
vehicles and habitats (2020) /
Technology demonstration
possible in earlier Demo mission or
onboard ISS (2015-2017)
SW Clause :
Open Source
Consistency with Harmonisation
Roadmap and Conclusions:
TRL5/6 by 2012
24 months
Dossier0 Ref.: T-7780 ,T-309
2006a Rad. Effects Tools
TRP Reference:
T304-020EE
TD:
TD04
Title:
Radiation shielding by ISRU and/or innovative composites for EVA, vehicles and
habitats
Objectives
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Description of Activities
Development of lightweight radiation shielding for vehicles, EVA and use of ISRU material for habitat
shielding, including storm shelters.
Description
The use of alternating layers of high and low atomic weight structures may allow lighter radiation shielding to be
created. This study would design, fabricate and test such a material with the aid of detailed simulation and irradiation.
It would also investigate the shielding properties of lunar and Martian surface materials, including secondary radiation
production for solar and GCR energetic particle populations. Radiation on planetary surfaces arises from secondary
interactions with atmosphere and planetary surface and habitation structures. Severe solar particle events may require
a heavily shielded refuge for crew. The design of this needs to be made and guidelines for its use created.
Deliverables:
Design, sample material and test results, reports.
Current TRL:
TRL 1
Target TRL:
TRL 3
Application
Need/Date:
Human exploration - habitat / All
manned missions, incl. Surface
EVA and ISS, Exploration (2020) /
Application/Mission:
Contract Duration:
Technology demonstration
possible in earlier Demo mission or
onboard ISS (2015-2017)
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
TRL5/6 by 2012
24 months
Dossier0 Ref.: T-7780, T-7791, T-654, T-309
2006a Rad. Effects Tools
TRP Reference:
T308-021SW
Title:
Crew Information System
TD:
TD08
Objectives
To refine the requirements baseline of Mission Execution Crew Assistant (MECA) by conducting field and
in-orbit test & assessments .
Description
The objective of MECA (Mission Execution Crew Asistant) is to empower the cognitive capacities of human-machine
teams during lunar/planetary exploration missions in order to cope autonoumously with unexpected, complex and
potentially hazardous situations. Best practicies of Usability Engineering calls for iterative assessment of real products
in operational contexts even in the R&D phase.
Therefore, during the course of the proposed study the following tasks are foreseen, to refine the MECA requirements
baseline by conducting field and in-orbit test & assessments:
- Prepare, test and evaluate MECA concepts and data-sets in a representative analogue terrestrial setting involving
team collaboration.
- Define and conduct inorbit test of a sub-set of MECA concepts, focussing on decision making.
- Adapt MECA capability and architecture to the inorbit crew transportation scenario.
Deliverables:
MECA requirements baseline v2. MECA operational PoC demonstrator, ( > 2 configurations). MECA technical
specification, incl a CSTS configuration. Evaluation reports from terrestial and inorbit assessments.
Current TRL:
Algorithm - S/W Target TRL:
Prototype - S/W Application
on commercial
Need/Date:
H/W
Human exploration - life support
(2020) / Technology demonstration
Application/Mission:
Contract Duration:
possible in earlier Demo mission or
onboard ISS (2015-2017)
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
TRL5 by 2012
48 months
Dossier0 Ref.: T-8417
N/A
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Description of Activities
TRP Reference:
T319-022MC
Title:
Window design for Manned Spacecraft
TD:
TD20
Objectives
To establish a feasible structural integrity approach for critical pressurized windows in manned spaceflight
application.
Description
European experience in designing and manufacturing pressurized glass windows for human spaceflight
applications(spacecraft and payloads) is limited. The fact that small cracks tend to grow as a function of time, rather
than pressure cycles, and the sensitivity to brittle failure due to stress concentration, makes safe design for long
lifetime challenging. Currently pressurized glass of payloads is designed to relatively low stress, and definition of
acceptance criteria for defects can be problematic.
The study should address:
* detailed definition of design criteria and specification for candidate materials for pressurized windows;
* development of inspection methods, proof test methods, other acceptance test methods and criteria for acceptance
of detected defects;
* determination of relevant strength, fracture toughness and crack growth parameters of candidate materials
applicable environments;
* analysis, design and test of breadboard pressurized window, candidate materials include: fused silica, MgF2 (TBC),
sapphire (TBC).
This activity will specifically focus on the structural integrity aspects of windows /viewports in payloads/experiments
and habitats. Detailed aspects related to materials, manufacturing processes etc for windows shall be covered in a
separate study!!
Deliverables:
Design criteria and procurement specification; development of acceptance test program; materials properties testing
results; breadboard design & test results report.
Current TRL:
TRL 2
Target TRL:
TRL 4
Application
Need/Date:
Human exploration - habitat / all
payloads and modules using
windows/viewports (2020) /
Application/Mission:
Contract Duration:
Technology demonstration
possible in earlier Demo mission or
onboard ISS (2015-2017)
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
TRL5/6 >=2015
18 months
Dossier0 Ref.: T-309
N/A
TRP Reference:
T319-023MC
TD:
TD20
Title:
Flexible window concept for inflatable and expandable habitat modules
Objectives
Review possible flexible window concepts for application in inflatable or expandable habitat modules and
perform basic proof-of-concept testing.
Description
The current flexible habitat module concepts rely on rigid windows to be integrated in them. It has been demonstrated
difficult for assembly (hard/soft interfaces) and not efficient in terms of packaging (rigid part with the soft assembly).
The proposed activity will review alternative window concepts for integration into inflatable or expandable habitat
modules (windows made of flexible transparent material, or rigidized after deployment). The study shall be concluded
with basic proof-of-concept testing on samples.
Deliverables:
Design files, test reports for Proof-of-concept tests, Development plan
Current TRL:
TRL 1
Target TRL:
TRL 3
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Application
Need/Date:
TRL5/6 >=2015
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Description of Activities
Human exploration - habitat / all
inflatable modules/habitats etc
Application/Mission: (2020) / Technology demonstration Contract Duration:
possible in earlier Demo mission or
onboard ISS (2015-2017)
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
18 months
Dossier0 Ref.: T-309
N/A
TRP Reference:
T319-024MC
Title:
Hypervelocity Impacts on Expandable Protections for Space Vehicles
TD:
TD20
Objectives
To explore the ballistic performances of advanced space debris and meteoroids protections for manned
pressurised modules.
Description
This exploratory work shall, as a minimum, address the effect of spacing on the performances of promising
configurations; the effect of thickness and characteristics of the first and the last layer of the protection on its ballistic
performances.; the performances of promising configurations under oblique impacts.; the evaluation of up range and
down range ejectas; the measure of momentum transfer under impacts and a comparison of this momentum transfer
with the performances of protection with stiff metallic components. Testing will be performed for selected
configurations.
Deliverables:
Ballistic Limit Equations suitable for Risk Analysis. Test reports.
Current TRL:
TRL 2
Target TRL:
TRL 4
Application
Need/Date:
Human exploration - habitat /
Human Exploration Missions
Application/Mission: (2020) / Technology demonstration Contract Duration:
possible in earlier Demo mission or
onboard ISS (2015-2017)
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
TRL5 by 2012-2013
24 months
Dossier0 Ref.: T-309
co-ordinated through Network of Centres Space Debris
Coordination Group (NoC SDCG)).
TRP Reference:
T321-025MC
TD:
TD22
Title:
Characterisation of a Nitrogen recycling unit for water recovery
Objectives
Study of static mass balances and hydrodynamics of a nitrifying process.
Description
Nitrogen recycling is a well known difficulty in the ECLSS domain and so far technologies are mainly aiming to a N
complete removal. Unfortunately, the only known technology is energy costly and bi-phasic. Alternative approaches
would require a specific pre-treatment of Nitrogen. Preliminary trade-off has allowed to identify the nitrification as a
very promising pre-treatment, but this possibility needs to be confirmed by a higher level of process characterisation
(mass balance, oxygen needs, volumetric mass transfer coefficient KLa,..). This characterisation will allow to issue
recommendations for a preliminary design.
Deliverables:
mass balances, Test reports. Recommendations for a prelimary design.
Current TRL:
TRL 2
Target TRL:
TRL 3
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Application
Need/Date:
TRL5/6 by 2015
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Description of Activities
Human exploration - life support /
Preparation for Exploration (2020)
Application/Mission: / Technology demonstration
Contract Duration:
possible in earlier Demo mission or
onboard ISS (2015-2017)
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
30 months
Dossier0 Ref.: T-7785
N/A
TRP Reference:
T321-026MC
Title:
Microbial pathogen identification in water
TD:
TD22
Objectives
Study and selection of technologies for automatic and fast identification of pathogen in water.
Description
The need to close the water loop on board considerably increases the microbial risk. This risk has been recently
confirmed by the modification of the ISS Medical Operation Requirement Document, which now requires to identify
potential pathogens in water. The proposed activity will exploit the experience of terrestrial industry to develop a
system for continuous monitoring of microbial contamination in the water on board manned spacecraft. The basic idea
is to take advantage of gene based techniques and to study the implementation of all the steps versus space
applications requirements. Within this study it is proposed to review, select and test potential technologies for a fast
and automatic identification of pathogens in water.
Deliverables:
trade-off, tests document
Current TRL:
TRL 2
Target TRL:
TRL 3
Application
Need/Date:
Human exploration - life support /
Preparation for Exploration (2020)
Application/Mission: / Technology demonstration
Contract Duration:
possible in earlier Demo mission or
onboard ISS (2015-2017)
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
TRL5/6 by 2012
24 months
Dossier0 Ref.: T-7782
N/A
TRP Reference:
T321-027MC
Title:
Removal of specific chemical contaminants in water
TD:
TD22
Objectives
To study, test and select best-suited technology, establishment of a technology development plan.
Description
In order to increase water loop closure in future planetary habitats, a condensate, urine and grey water recovery unit is
being defined (C 19857). This unit combines nitrification and advanced filtration techniques. Heavy metals originating
from condensate (leaching from heat exchanger, piping) will certainly accumulate in the recovery unit and become
toxic for the nitrification. Today, minerals (including heavy metals) are absorbed in ORU multi-filtration beds. Part of
the minerals, which could be further used in other LSS elements (i.e. food production unit) are consequently wasted.
In order to allow maximum recycling, it is necesary to develop a new technique for specific removal of heavy metals
(Zn, Cu, Ag, Ni, Na).
Deliverables:
trade-off, tests documentation, development plan
Current TRL:
TRL 1
Target TRL:
TRL 2
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Application
Need/Date:
TRL5/6 by 2012
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Description of Activities
Human exploration - life support /
Preparation for Exploration (2020)
Application/Mission: / Technology demonstration
Contract Duration:
possible in earlier Demo mission or
onboard ISS (2015-2017)
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
24 months
Dossier0 Ref.: T-7785
N/A
TRP Reference:
T321-028MC
Title:
Extraction of specific chemical contaminants in the Air
TD:
TD22
Objectives
To review and study existing techniques wrt targeted contaminants, perform preliminary tests, select
best-suited extraction technology, establish a development plan.
Description
The LSS for a future planetary habitat shall allow maximum recovery of consumables from the wastes generated by
the crew in order to increase water and gas loops closure. Such a LSS will be composed of several interlinked
sub-systems, from waste treatment to food production. To date, all waste treatment systems under development
mainly generate CO2 and gaseous contaminants, the nature of which depends on the selected waste treatment
technique. Currently, photo-oxidation processes are used to transform volatile organics into re-usable CO2. However,
such processes are not able to cope with contaminants such as NOx, SOx, H2S, skatole, furans, phenols and other
conjugated organics. These gaseous contaminants need to be removed in order to allow re-use of the produced CO2
in a closed life support systems.
Deliverables:
trade-off, tests documentation, development plan
Current TRL:
TRL 1
Target TRL:
TRL 2
Application
Need/Date:
Human exploration - life support /
Preparation for Exploration (2020)
Application/Mission: / Technology demonstration
Contract Duration:
possible in earlier Demo mission or
onboard ISS (2015-2017)
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
TRL5/6 by 2012
30 months
Dossier0 Ref.: T-7786
N/A
TRP Reference:
T321-029MC
TD:
TD22
Title:
Preliminary definition of on-line chemical water quality analysis equipment
Objectives
To study and test analytical methods to monitor water quality and select the best-suited methods for
on-line application.
Description
Today, aboard ISS, monitoring of the quality of recovered water is mainly performed using on-line pH and
electroconductivity measurement. Contamination by organics is not monitored. Electroconductivity is a lump
parameter, which indicates the amount of minerals present in the water but does not allow understanding the origin of
any mineral contamination. As mission duration increases, water loop closure shall also be increased by considering
recycling of urine and hygiene water. In order to better monitor the quality of recovered water and to be able to
determine the origin of contamination, the development of an on-line analytical system is necessary. Preliminary
attention will be paid to , NH4, NO3, Na, K, P and generic technologies. this study will include bibliography review,
preliminary tests of analytical techniques, selection of the best suited techniques for on-line application.
Deliverables:
trade-off, tests documentation
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Current TRL:
TRL 1
Target TRL:
TRL 2
Application
Need/Date:
Human exploration - life support /
Preparation for Exploration (2020)
Application/Mission: / Technology demonstration
Contract Duration:
possible in earlier Demo mission or
onboard ISS (2015-2017)
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
TRL5/6 by 2012
18 months
Dossier0 Ref.: T-7782
N/A
3-04 - Autonomous Robotic Exploration missions
TRP Reference:
T316-030MM
TD:
Title:
Miniaturized Imaging Lidar system (Ph.1)
TD16
Objectives
The objective of this activity is to design, manufacture and test a miniaturized Imaging Lidar system. Novel
and advanced technologies shall be developed and implemented in order to minimize the system mass
and power consumption.
Description
The missions of the Exploration Programme foresee several RVD (Rendezvous and Docking), landing and rover
navigation operations where Imaging Lidar instruments shall play a key role. Typically Imaging Lidars rely on scanning
mechanisms that are still bulky and rather heavy, which is not favourable for space missions. On-going ESA activities
focus on the development of Imaging Lidar sensors that will implement detector arrays. However the number of pixels
of these arrays is not sufficient to cover the total field of view with the required high spatial resolution. For this reason
a scanner mechanism is still needed (with relaxed scanning performance when compared with a single detector
system). In order to miniaturize an Imaging Lidar system novel technologies, including miniaturized scanners (such as
Micro-Opto-Electro-Mechanical Systems - MOEMs) and high performance detector arrays (such as APD arrays), have
to be developed and implemented. During this activity novel and advanced technologies shall be studied and
implemented with the objective to develop a miniaturized Imaging Lidar sensor. The following tasks shall be
performed: 1)Review novel technologies in view of its utilization in a miniaturized Imaging Lidar system focussing on
one specific GN&C application (rendezvous and docking, landing or rover navigation) 2)Execute precursor
experiments and development tasks to assess and increase the readiness level of novel and advanced
technologies.3)Design, manufacture and test a miniaturized Imaging Lidar breadboard.
Deliverables:
Miniaturized Imaging Lidar breadboard
Current TRL:
TRL 2
Target TRL:
Application/Mission: NEXT, MSR (>2016)
SW Clause :
Application
Need/Date:
Contract Duration:
TRL5 by 2013
20 months
T-7719; T-7745;
EDL(Autonomous)
Navigation Systems;
EDL: Autonomous Landing
GNC Technology
Dossier0 Ref.:
Development; Autonomous
RDV Navigation System inc.
Sensors; RDV: Autonomous
Rendezvous GNC
Technology Development
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 4
N/A
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Description of Activities
4 - Space Transportation
4-01 - Launchers oriented Technologies
TRP Reference:
MPC-846
TD:
TD24
Title:
Acquisition and Evaluation of Cryo-Solid Propulsion: Additional Testing
Objectives
The objective is to evaluate and demonstrate the Cryogenic Solid Propellants (CSP) concept.
Description
Conventional solid rocket propellants have specific impulses that are low compared to cryogenic liquids. Cryogenic
Solid Propellants (CSP), defined as frozen propellants that normally are liquids or gases, compare very favourably
with conventional ones. The goal of this activity is to establish a firm evaluation of CSP in terms of applicability,
performance, operability and cost. It is also necessary to establish the theoretical and experimental foundations of
CSP-grain design, production, integration, handling, ignition, combustion etc and rapidly provide the knowledge base
of a prototype demonstrator version of a CSP-motor. Experimental work carried out as part of this activity shall include
investigations of strand burner and tests with sub-scale motors. This CCN will continue the experimental work.
Deliverables:
Test data
Current TRL:
TRL 2
Target TRL:
Application/Mission: Future launchers
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 2-3
Application
Need/Date:
Contract Duration:
For TRL5 by 2020
18 months
Dossier0 Ref.: -
N/A
TRP Reference:
T409-002GI
TD:
TD09
Title:
Assessment of the suitability of ESOC Ground Segment infrastructure S/W for its
use in the launcher field.
Objectives
1. To assess the suitability and identify the limitations of ESOC Ground Segment infrastructure s/w
(Mission Control System, Simulator) for use in the launcher field;
2. To perform a gap analysis in terms of requirements (functional, performances, operational, quality,
safety, etc.) and in terms of system architecture;
3. To sketch the concept of s/w infrastructure product line for launcher Ground Segment infrastructure
identifying commonality and specifics between the spacecraft and the launcher domains.
Description
ESOC Ground Segment infrastructure s/w application (SCOS-2000 and SIMULUS) demonstrated its versatility to fulfil
the requirements of the various ESA Missions but also to fulfil the requirements of 3rd party spacecraft operators like
DLR, EUMETSAT, RADARSAT and Arabsat.
SCOS-2000 also demonstrated its suitably as a kernel for implementing a Payload Operations and Programming
Centre (SMOS mission) but also for implementing an EGSE system for a satellite (Herschel Plank) or for a launcher
like VEGA. While SCOS-2000 was initially selected to be part of VEGA Control Centre Bench (BCV), during the
Project design phase, the choice was revisited and the decision was made to remove SCOS-2000 from the
architecture.
While no justification was provided at the PDR to substantiate this choice, it is clear that VEGA commanding,
monitoring and acquisition real-time performance requirements were very challenging for SCOS-2000 (Commanding
request < 250 ms, monitoring reaction < 50ms, Single/multiple acquisition < 250/500 ms).
To date, no studies have been performed to determine the suitability and limitations of the Ground Segment
infrastructure s/w to fulfil the specific needs of launchers.
Therefore, the activity shall assess the suitability of ESOC Ground Segment infrastructure s/w for its use in the
launcher domain (EGSE, Control Bench, Mission Control system) identifying the necessary addition to develop
suitable product line of applications for launchers.
The approach shall consist in:
1. Performing a requirements gap analysis (functional, performances, operational, quality, safety, etc.) between the
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Description of Activities
various launchers applications and the current ESOC Ground Segment s/w infrastructure.
2. Describing a high level system architecture for a launcher Ground Segment infrastructure s/w by identify
commonalities and specificities between the satellite and the launcher domain.
3. Proposing follow up studies activities to further analyse the more uncertain technical areas.
Deliverables:
1. Technological analysis, requirements and Use Cases
2. High level architectural design
N/A
Current TRL:
N/A
Application/Mission:
All launchers, re-entry vehicles
(Mission Date: 2020)
Contract Duration:
SW Clause :
Operational SW
Dossier0 Ref.: T-120
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
For TRL5: 2014
12 months
N/A
TRP Reference:
T415-003PV
TD:
TD15
Title:
Study for an on-board contamination measurement for launchers
Objectives
Several assumptions and rough analyses are carried out during the launcher design phases and mission
analysis to estimate the level of contaminants (molecular and particulate) originated by the launcher that
may deposit on the Payload. Due to the stringent cleanliness requirements sometimes imposed by the P/L
(e.g. optical sensors) it is important to have a feedback on data from real missions.
Description
It is proposed to initiate a feasibility study as well as a preliminary design for an On-board Cleanliness Measurement
System (OCMS). The OCMS will be able to send by LV TLM the actual levels of molecular and particulate
contamination accumulated , based on sensors to be located as much as possible closed to the P/L location. The
OCMS shall have its own battery (already certified by safety) and shall not have any redundancies expect for what it is
functionally needed. Moreover the maximum use of off-the-shelf equipment and qualified H/W shall be sought.
Deliverables:
1) Research on similar equipments for non-European Launchers.
2) Feasibility study.
3) Preliminary architecture.
4) List of possible Bidders for the system development
TRL 3
Current TRL:
TRL 2
Application/Mission:
Identified need for Vega. (Mission
Date: 2020)
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-855
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
For TRL5: 2014
6 months
N/A
TRP Reference:
T417-004MP
TD:
TD18
Title:
Launcher stage separation and plume interaction validation
Objectives
The objective of this activity is to enhance our tools for stage separation load assessment by performing
dedicated experimentation in suitable facilities and address flight extrapolation and scaling.
The broader scope is to
1. to address the absence of a suitable validation database
2. to provide an initial evaluation of current software.
3. to support to post-flight analysis for current and future launchers.
Description
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Stage separation shows itself to be an area of risk in relation to past, current and future launch vehicles. The process
of stage separation at high Mach numbers involves complex flow interactions and multi-body motion and, thus, the
process is not fully verifiable on ground.
Therefore; in order to mitigate against risk, approaches to stage separation are traditionally conservative and
non-optimal from a cost and performance perspective. Improving the current state of the art for stage separation
should therefore focus on a combination of ground based wind tunnel testing and simulation. Tests are a pre-requisite
in order that numerical tools can be properly validated before application to flight scale. Currently, such problems may
be modeled but the validity of the results (in the absence of a thorough knowledge of the true flow physics) is
questionable.
During the course of the activity it is foreseen:
• The contractor shall review available data on stage separation from past experimentation ( e.g. A4) and define a
strategy for validation experimentation including flight extrapolation and scaling with the objective to enhance present
day knowledge as well as taking into account recent lessons learned from the VEGA working group on stage
separation.
• The contractor shall define in agreement with the agency the windtunnel model(s) for aerodynamic testing in transand supersonic facilities representative of a selection of stage separation approaches (including both current and
potential future configurations).
• The contractor shall perform sub-scale wind-tunnel testing with variation of the major aerodynamic and geometrical
parameters in order to construct a database against which numerical tools shall be validated.
• The contractor shall perform CFD activities in order to evaluate them w.r.t the generated experimental database
(including parametric variations).
• The contractor shall perform CFD activities to investigate the sensitivity of the CFD results w.r.t extrapolation to a
flight representative scale and boundary conditions.
• An assessment of the uncertainties introduced due to parameters that are not possible to fully reproduce on ground
shall be included.
• Where windtunnel results are obtained in relation to current/historic configurations the contractor shall ensure that a
comparison with post flight data is possible.
• Based on the results obtained, a synthesis and recommendations for future work shall be given.
Deliverables:
Wind tunnel test data, CFD Solutions, Technical notes,
Test Articles, Test Data
TRL 3
Current TRL:
TRL 2
Application/Mission:
All staged launch vehicles (Mission
Contract Duration:
Date: 2020)
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
For TRL5: 2014
18 months
Dossier0 Ref.: T-7900, T8095
Consistent (A18)
TRP Reference:
T417-005MP
TD:
TD18
Title:
Launcher base flows and shock interaction regions improved load
characterization
Objectives
The objective of this TRP is to enhance the tools ( facilities, instrumentation and CFD modelling )
simulating the heat flux and pressure loads for Ariane and Vega launchers. Priority is given to revisiting
base flow regions and regions with strong pressure gradients (SWBLI) as these are the regions which are
usually strongly over dimensioned. In addition present day facilities have been improved and more
knowledge has been obtained as to the influence of the hot plume onto base flow regions thereby allowing
a more accurate assessment of the design loads. The outcome of the study should be improved modelling
of loads at e.g. regions around the batimoteur of A5 or around the DAAR/DAAV regions reducing the
required TPS mass and therefore optimize the complete launcher as well as saving recurrent cost. ( as an
example: today 600kg Prozial is used in A5 base region which most likely can be reduced)
Description
As part of the harmonization of the Aerothermodynamics tools, the need to improve the means (experimental and
numerical tools) to assess the environmental loads for launchers became a priority. In particular the tools used to
define the maximum pressure and heat flux loads in base flow regions such as those encountered on Ariane 5 are a
priority.
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The present TRP deals with enhancements of the methods used to define the pressure and heat flux loads taking into
account the influence of the hot plume. The phenomena to be addressed in the context of this TRP are unsteady
pressure and heat flux loads around launcher base regions where plume entrainment, recirculating unsteady flows
and afterburning determine the level of the convective heat fluxes and maximum pressure loads. These loads define
the general specifications who drive the design of the Structural, thermal protection and venting holes.
Previous studies concentrated mainly on buffeting unsteady pressure loads driving the gimballing actuator forces on
the Vulcain as well as on the nozzle start up transient side loads. Here the focus is on radiative and convective heat
loads and on pressure loads in base regions but also in regions where strong shock interactions occur such as
around the upper and lower A5 EPC attachement bars ( DAAV and DAAR). .
The contractor shall perform the following activities :
• Review of present day tools used for A5 and Vega launcher loads;
• Analysis and prioritization of uncertainties for heating and pressure loads.
• Definition of generic configuration or use of existing windtunnel models representing the phenomenon and region of
interest.
• Feasibility of addressing influence of hot plume in existing facilities e.g. (Onera S3, or DLR KOLN ) or retrofitting
facilities such as the TNO propulsion stand to obtain basic data on hot plume base flow interaction
• Instrumentation developments, and windtunnel testing ;
• Analysis of data and numerical rebuilding including flight extrapolation and scaling
• Uncertainty analysis and consolidation of new approach for follow up application for A5 and Vega launchers
• Synthesis and recommendations
Deliverables:
Software / manuals / technical reports and numerical data from validation
TRL 6
Current TRL:
TRL 4
Application/Mission:
Launcher load optimization
(Mission Date: 2020)
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-7900, T8095
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
For TRL5: 2014
24 months
Consistent (A11)
TRP Reference:
T418-006MP
Title:
Experimental Investigation of Rotordynamic Fluid Forces on Cavitating Helical
Inducers
TD:
TD15
Objectives
The main purpose of the proposed activity is the experimental characterization of the unsteady fluid forces
and moments acting on turbopump inducers as a consequence of their whirl motion under
cavitating/noncavitating conditions, with special emphasis on the onset and development of lateral
rotordynamic instabilities.
Description
The most critical rotordynamic instability in turbopumps is the development of self-sustained lateral motions (whirl) of
the impeller under the action of destabilizing forces. These forces can be of mechanical origin (internal damping and
hysteresis of the rotor and of the shaft, anisotropy of the rotor and bearing stiffness, dynamic unbalance, direct contact
of the static and rotating parts, system nonlinearities, etc.) or of fluid dynamic origin (flow asymmetries, cavitation,
journal bearing or seal forces, leakage and recirculation flows, rotor/stator interactions, non-stationary phenomena).
Because of their greater complexity, rotordynamic forces of fluid mechanical origin have so far received less attention
in the open literature than mechanically induced rotordynamic forces, despite of their well recognized potential for
promoting rotordynamic instabilities of high performance turbopumps and for significantly modifying, in conjunction
with cavitation, the dynamic properties of the impeller, and therefore the critical speeds of the whole machine. A
significant amount of work has also been developed for analyzing the various forms of flow instabilities in pumps by
theoretical and/or numerical means.
A consistent body of systematic experimental information on unsteady rotordynamic fluid forces and, among them,
cavitation forces in high performance turbopumps is, at the same time, vital for future propulsion applications to
reusable launchers and, at present, almost completely lacking in the open literature. Practically nothing is known on
the interactions of cavitation-induced instabilities, in particular rotating cavitation, and lateral rotordynamic impeller
forces. There is, therefore, a great need for further work in the this area, particularly in Europe, since earlier openly
published efforts have mostly been developed in the United States and recently, with rapidly increasing success, in
Japan.
Current trend towards supercritical operation of turbopumps for liquid propellant feed systems imposes careful
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reconsideration of the contributions of rotordynamic fluid forces on cavitating impellers in determining the dynamic
properties of the rotors. Simple overestimation of these forces with reference to noncavitating operation works well in
subcritical pumps but is clearly no longer acceptable in supercritical machines, since it would lead to unrealistically low
values of the critical speeds and to drastic overestimates of the stability margins at design conditions, where
significant cavitation is commonly accepted. Nowadays experimentation still plays an essential role for progress in this
technology field because the extreme complexity and imperfect understanding of the relevant unsteady fluid dynamic
phenomena prevents the possibility of relying on theoretical or numerical predictions alone. Operational and economic
limitations clearly indicate that detailed, highly-instrumented experiments can only be effectively carried out on
turbopumps operating under fluid dynamic and thermal cavitation similarity. Ultimately, the proposed activity will
provide the designers of high performance turbopumps with a systematic set of experimental data on the impeller fluid
forces resulting from its position or whirl motion with respect to the pump casing. This information, expressed in terms
of properly nondimensional flow-induced rotordynamic coefficients under fluid dynamic and thermal cavitation
similarity, will allow realistic estimates of these forces in full-scale turbomachines to be deduced from model data or
from the direct measurement of the impeller position and whirl motion in full-scale turbopumps. Even more importantly,
it will provide corrections of the machine’s critical speeds to account for the presence, nature, and dynamic behavior of
the entrained fluid, thereby effectively contributing to identify the operational regimes that are likely to develop into
dangerous and potentially destructive rotordynamic instabilities. The availability of a systematic set of experimental
data on rotordynamic fluid forces on whirling impellers represents an important step for the reduction of the
development costs of advanced turbopumps for space applications.
Deliverables:
Technical notes, test data file(s)
TRL 3
Current TRL:
TRL 2
Application/Mission:
All launchers with liquid propulsion
Contract Duration:
(Mission Date: 2020)
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
For TRL5: 2014
24 months
Dossier0 Ref.: T-7899
N/A
TRP Reference:
T418-007MP
TD:
Title:
European medium thrust engine concept
TD19
Objectives
The aim of this activity is to develop the needed propulsion technologies enabling the implementation of a
medium thrust engine suitable for space transportation purposes that encompass launcher, transfer
vehicle, planetary transfer and descent/ landing applications.
Description
Launcher system studies suggest the usage of a medium thrust engine for small launcher upper stage and for heavy
launcher in dual launch configuration, orbit transfer vehicles need thrust levels in the same range. Planetary transfer
studies, carried out with the objective to meet Mars and Lunar mission requirements, come to the same conclusion.
The following cases can be mentioned in support to the above assessment: the Vega launcher upper stage engine
(currently purchased abroad), the ATV propulsion design, the several ESA CDF system studies for transfer to Mars
and Moon and entry/landing and ascent on the planet surface, ESA GSP activities done in the frame of the design and
technology investigation for the propulsion systems to satisfy MSR (Mars Sample Return) mission requirements.
The activities will span from the analysis of requirements, to the performance of architectural studies, the design of
fluid dynamic aspects of a prototype for demonstration of the technologies to implement a medium thrust (3 – 8KN)
engine.
To reach this goal, Industry will capitalise on the work previously done in Europe in this area. It will be of paramount
importance to have a clear view of this already at industry proposal level, where the bidder shall provide full evidence
of the past work and clear understanding of the current availability and validity of the relevant results. Also, in the
Industry Proposal, the data available from past ESA survey studies shall be analysed and used for full justification of
the proposed engine concept solution.
The main tasks to be performed can be summarised as follows:
Task1: to define engine requirements according to a reasonable envelope of the main listed mission requirements
Task2: to design the chamber material to allow long duration firing
Task3: to design the nozzle extension for long duration firing
Task4: to develop the pulse mode firing concept at all parts level
Task5: to perform the injector head design for multi start and long duration firing
Task6: to design a valve able to feed the engine in pulse mode firing and in steady state firing
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Description of Activities
Task7: to prepare the technology development test plan based on the achievements reached in the design phase and
outline the complete engine development phase
As a general rule during the activities, it will be recommended to maximise the usage of existing H/W (where
applicable) while it will be acceptable to design new equipment where the need is demonstrated.
Deliverables:
Industry background data, engine parts preliminary design report, engine preliminary design report, prototype
technology development test plan, engine development plan
TRL 3
Current TRL:
TRL 1
Application/Mission:
Future Vega/Ariane upper stages,
Exploration (Mission Date: 2020)
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-8324
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
For TRL5: 2014
12 months
N/A
TRP Reference:
T418-008MP
TD:
TD15
Title:
Dynamic Characterization of Cavitating Turbopumps and Inducers for POGO
Suppression
Objectives
The objective of the present proposal consists in experimentally characterizing the dynamic transfer
matrices of typical cavitating inducers for rocket propellant feed turbopumps operating under fluid dynamic
and thermal cavitation similarity, in order to investigate the influence of the frequency and amplitude of the
excitation, the potential impact of thermal cavitation effects, the system-independence of the results and
the intensity of the ensuing forces on the rotors.
Description
The term POGO refers to the out of phase motion of the ends of a liquid rocket, which can build to a dangerous
magnitude due to propulsion system feed-back caused by self-excited pressure oscillation in the propellant feed lines.
Since the development of the Titan II launcher for the Gemini programme, POGO instability has been one of the major
concerns in the design of modern rockets.
As the inception and control of POGO oscillations is largely affected by the multiphase behavior of fluids in the feed
system, and thus by the cavitating response of propellant turbopumps. The fatigue failure of an inducer blade due to
fluid dynamic instabilities of the Japanese LE-7 liquid hydrogen turbopump and the consequent catastrophic loss of
the first H-2 launch in November 1999 dramatically confirmed that cavitation-induced instabilities represent the
dominant fluid mechanical phenomena that adversely affect the dynamic stability and safety of propellant feed
turbopumps.
Several important aspects of the dynamics transfer matrices of cavitating turbopumps still require further investigation,
namely: a) the behavior at higher reduced frequencies, relevant to a number of critical turbopump instabilities; b) the
influence of thermal effects, which is known to be quite significant in steady operation and is likely to be of comparable
importance also in dynamic conditions; c) the independence on the pump’s boundary conditions, which is essential for
the practical value of measured transfer matrices and has not yet been verified by previous experiments; and d) the
magnitude of the fluid forces induced on the pump rotors, whose knowledge contributes to the most efficient structural
design of the machine.
Currently, these extremely complex aspects can only be realistically addressed by means of detailed forced vibration
experiments on turbopumps in fluid dynamic and thermal cavitation similarity. However very little specific
experimentation has been so far performed in Europe related to these issues, which have been accounted for by
increasing design margins in an empirical and not necessarily efficient way.
The experiments will be carried out by harmonically perturbing the inlet/outlet flow of the machine by means of suitably
designed flow fluctuators. Thermal cavitation effects will be investigated by adjusting the liquid temperature as
necessary for adequately scaling the pump prototype operating at design conditions (flow coefficient and cavitation
number) with the given propellant (LH2, LOX, hydrazine, UMMH or NTO). System-independence will be verified by
modifying the dynamics of the suction/discharge lines of the pump by means of suitable additional components
(resistances, capacitances or inertances) and, as far as possible, by comparison with the data available in the
literature. The ultimate objective of the activity consists in providing pump designers and manufacturers with a wider
experimental database on the dynamic response of cavitating turbopumps to inlet line pressure oscillations, and on
the related unsteady impeller forces, to be used for improving the capability of controlling, suppressing or possibly
surviving dangerous POGO instabilities of liquid propellant rocket propulsion systems.
Deliverables:
Technical notes, test data file(s)
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Description of Activities
TRL 3
Current TRL:
TRL 2
Application/Mission:
Launch vehicles. (Mission Date:
2020)
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-7899
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
For TRL5: 2014
24 months
N/A
TRP Reference:
T418-009MP
Title:
Technology feasibility of cryogenic PMD elements
TD:
TD19
Objectives
The design and development of a complete cryogenic PMD for large upper stages like Ariane 5 is a very
complex task requiring noticeable funding and long schedule. Objective of this study is to start this
process by a design and pre-development work on selected PMD elements to investigate the preferred
conceptual approach and verify its feasibility.
A survey of European industrial experience and knowledge together with worldwide background will have
to be coupled with maximum usage of existing data.
Description
Re-ignitable Launcher Upper stage cryogenic propulsion systems need Propellant Management Devices (PMD) of a
different concept with respect to more traditional non re-ignitable systems. Definition and development of such PMDs
is an enabling technology to allow implementation of advanced launcher upper stage propulsion. Previous ESA and
industrial studies largely agree on this need and plenty of technical data is available to support initiation of
experimental activities on such devices. The European industry has performed initial activities both in the field of
fluid-dynamics and thermal. Preliminary definition work is available.
However, a cryogenic PMD is a complex device whose definition is very much correlated to system and propellant
tank design aspects; the activities will initially focus on the definition of a number of possible cryogenic PMD concept
candidates, their preliminary design and analysis followed by trade studies, also in relation to ESA programs strategic
needs, to select a preferred concept.
Detailed design of demonstrator elements of the selected concept will be performed and manufacturing and functional
testing will be performed.
In particular, the foreseen work can be summarised in the following tasks:
Task1: to analyse mission applications in relation to PMD functions and streamline a list of representative
requirements.
Task2: identify attractive PMD concepts and perform preliminary design definition
Task3: select preferred concept based on trade parameters agreed with ESA
Task4: perform detailed design of functionally representative PMD parts and manufacture. Consider as a minimum the
following aspects: screens, capillary devices, start basket, venting, cooling coils.
Task5: define a test plan for the PMD parts and demonstrate their coverage of the technology demonstration needs.
Task6: perform test plan and post process test data.
Task7: assess further cryogenic PMD technology development roadmap.
Deliverables:
Survey of European and worldwide state of art, Cryogenic PMD mission needs, Cryogenic PMD concepts trade
studies and selection, preliminary design of representative parts, parts test plan, parts test results, technology
development roadmap.
TRL 3
Current TRL:
TRL 1
Application/Mission:
Re-ignitable cryogenic stages,
(Mission Date: 2020)
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-7568
Consistency with Harmonisation
Roadmap and Conclusions:
TRP Reference:
T418-010MP
Target TRL:
Application
Need/Date:
For TRL5: 2014
24 months
Consistent
TD:
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Description of Activities
Title:
Simulation models for Solid Rocket Motor’s (SRM’s) Ignition Transient (IT)
Objectives
The present activity shall be devoted to achieve the following two objectives:
• to increase the knowledge of the more relevant phenomena involved in the SRM ignition transient (IT),
their interactions and their dependencies from the main design parameters (igniter configuration and
operation, propellant grain geometry, pressurization level, pressurizing gas typology etc.);
• to develop and /or validate a simulation model able to reproduce the SRM IT behaviour for a large variety
of SRM configurations. This simulation model shall to be characterized by high reliability, flexibility and low
computational time.
The expected outcomes, with respect to the previous objectives, are:
i) to provide general and specific indications to address the SRM design process toward the achievement
of proper ignition IT behaviour;
ii) to develop a computer code to be used to analyze and predict the SRM IT.
Description
The ignition transient phase of a Solid Rocket Motor (SRM) generates a number of issues and behaviours on the
launcher that might be detrimental to its performances and may eventually lead to the loss of the mission.
A good understanding of the phenomena associated to the ignition transient is essential and the development of a
simple, reliable tool capable to reproduce these ignition transient phenomena is requested as an important support to
current and future applications of SRMs.
The ballistic behaviour of a SRM during the Ignition Transient (IT) phase mainly generates the following issues:
i) Thrust imbalance (dual booster configuration).
ii) Rate of increase and oscillations of propulsive thrust.
iii) Stage separation procedure and timing.
iv) Structural integrity and deformation of propellant grain.
v) Payload integrity (frequency and amplitude of induced oscillations).
vi) Others.
In order to prevent possible problem, a good level of detail in the IT reconstruction is mandatory.
By looking at the evolution of the internal pressure during the IT, different motor configurations lead to different
pressure evolution typology. Even if the propagation phenomena could be more or less significant in characterizing
the IT evolution (for example, by pressure oscillation with significant frequency and amplitude), an efficient, robust and
reliable unsteady gasdynamical model is considered as a mandatory requirement to simulate the IT phase. In order to
fulfil the requirement of reasonable computing times, a quasi 1D unsteady model shall be adopted to approach the
problem. More complex, and time consuming, 3D models could be proposed for the preignition gasdynamical
simulation and/or for validation purposes.
Due to its great influence on the IT behaviour, also others phenomena shall be modeled, such as the propellant
surface heating and ignition, the propellant combustion, the igniter operation etc. To simulate these phenomena the
support of specific sub-models is required.
The total activity could be partitioned in the following work packages:
• Basic gasdynamic model and sub-models’ formulation and discussion.
• Computer code development.
• Model and computer code validation.
Deliverables:
Technical notes, computer models.
TRL 3
Current TRL:
TRL 2
Application/Mission:
SRM for Launch vehicles. (Mission
Contract Duration:
Date: 2020)
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
For TRL5: 2014
24 months
Dossier0 Ref.: no ref.
N/A
TRP Reference:
T418-034MP
TD:
Title:
Experimental Investigation of Key Technologies for a Turbine Based Combined
Airbreather-Rocket Engine
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Description of Activities
Objectives
The largest component of the program is the precooler development. This will involve manufacture of
approximately 65 precooler modules, which assemble into 3 drums (21 modules per drum). The complete
pre-cooler will then be installed upstream of a jet-engine to simulate realistic operational conditions
including the effectiveness of the frost control. The investigation of oxidiser cooling of the chamber
consists of oxidation trials on coated copper coupons in appropriate atmospheres, followed by the
manufacture of a small chamber with cooling channels, tested under combustion conditions with air
cooling plus hydrogen film cooling in airbreathing mode, and lox cooling in the rocket mode. The
investigation of nozzle stability consists of design, procurement and cold flow testing of small adapting
nozzles based on analysis of previous test work, followed by procurement of a larger scale model for hot
firing at higher flows proving the stability of a highly expanded nozzle at surface atmospheric back
pressure.
Description
The experimental investigation of key technologies for a turbine based combined air-breather-rocket engine cover
demonstration of pre-cooled engine with frost control, thrust chamber and nozzle concept, variable air intake
geometry, and implementation and functional operation issues of achieved developments in aerospace programmes.
Specifically the following need to be addressed:
- Demonstration of pre-cooled engine with frost control (REL) air intake:
The largest component of the program is the precooler development. This will involve manufacture of approximately
65 precooler modules, which assemble into 3 drums (21 modules per drum). The complete pre-cooler will then be
installed upstream of a jet-engine to simulate realistic operational conditions including the effectiveness of the frost
control.
- Thrust chamber and nozzle concept (EADS-Astrium + Bristol university):
The thrust chamber must be cooled by the oxidiser, high pressure air during airbreathing and liquid oxygen during
rocket modes. The thrust chamber activities are targeted at demonstrating liquid oxygen and air cooling of a copper
liner and the operation of a suitable atmospheric compensating nozzle.
A hybrid airbreathing and rocket engine must operate over the whole range of back pressure, from the Earths surface
to space. The engine performance is therefore very dependent on the expansion ratio of the nozzle. There is strong
motivation to find an adaptive nozzle design which can compensate for atmospheric back pressure.
This activity involves use of earlier in-house work at Reaction Engines and shall involve potential manufacturers of the
eventual prototype system.
- Air intake (GDL):
The program shall demonstrate the recovery over the Mach range 0 - 5. There is also a requirement to accommodate
wide flow variations with limited variable geometry in an axisymmetric intake.
- Implementation and operational issues of developments in aerospace programme (REL):
The exact breakdown of these activities depends on the results to be achieved and emerging system requirements by
ESA and BNSC against specific aspects of the program.
Phase I essentially covers experiments to gain confidence on concepts of initial elements in particular demonstration
of pre-cooled engines with frost control, thrust chamber and nozzle concept.
In Phase II experiments will be performed with more representative hardware, e.g. air intake and will address system
implementation and operational issues.
Deliverables:
Technical reports, database of experimental results, hardware (oxidation trials test specimens, test combustor and
injector, cold flow nozlle, hot chamber)
Current TRL:
TRL 2
Target TRL:
Application/Mission: TRL7 (Mission Date: 2020)
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3-TRL 4
Application
Need/Date:
Contract Duration:
TRL5 by 2017
24months
Dossier0 Ref.: T-8260
European Space Technology Harmonisation – Technical Dossier :
Aerothermodynamics Tools
TRP Reference:
T419-011MC
TD:
Title:
Delamination assessment tool for composite structures
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TRP Work Plan 2008-2010
Description of Activities
Objectives
To develop a comprehensive damage tolerance verification logic for highly loaded composite launcher
structures, addressing both numerical methodologies as well as material-, subcomponent- and component
testing. This shall include advanced numerical tools/methodologies to model the onset and propagation of
delaminations in CFRP structures subjected to high loads, as well as methodologies for the definition and
execution of model calibration and verification tests.
Description
Several problems related to delamination have been encountered during the VEGA development as well as for
Ariane-5 structures, underlining the need for the development of consolidated design verification methodologies
addressing the effect of delaminations.
The use of advanced composite structures in launchers requires a thorough understanding of the inelastic response of
composites under general loading conditions. One of the most relevant mechanisms that contribute to the loss of
stiffness and to the structural collapse of composite structures is delamination. Besides degrading the structural
integrity of composites, delamination is also difficult to detect using traditional non-destructive inspection methods.
The majority of the analytical and experimental investigations of delamination have been focused on the study of
delamination growth under quasi-static loads, and use simplified and limited numerical tools such as the virtual crack
closure technique- often without adequate verification by test. In addition, under cyclic loading, delaminations may
grow up to a critical size for loads well below the critical load for quasi-static loading. Currently, the applied design and
verification methodologies barely consider the possibility of interlaminar crack growth under static and dynamic
loading, being more oriented to prevent fatigue damage by assuring that a stress or strain threshold for delamination
onset is not exceeded. It is hence proposed to develop a more comprehensive verification logic, addressing both
numerical methodologies as well as material-, subcomponent- and component testing.
The currently applied design and verification methodologies for highly loaded composite structures barely considers
the possibility of interlaminar crack growth under static and dynamic loading, being more oriented to prevent fatigue
damage by assuring that a stress or strain threshold for delamination onset is not exceeded. It is hence proposed to
develop a more comprehensive verification logic, addressing both numerical methodologies as well as material-,
subcomponent- and component testing. The new design verification methodologies to be developed will address both
delamination initiation and growth under quasi-static and cyclic loads of large highly loaded launcher structures, and
should include aspect such as interface cohesive finite elements, able to predict both delamination onset and
delamination growth. Methodologies for model correlation by test will be included, including both material coupon tests
as well as design representative sub-component or component tests.
The workplan will include the development of an overall verification approach, numerical modelling and relevant tests.
A number of case-studies will be defined and addressed in detail. A limited demonstrator test program will be
performed and numerical predictions will be compared with the experimental results and design guidelines will be
proposed.
In the framework of the development of virtual tools, damage tolerance verification methods addressing the prediction
of delamination onset and growth under fatigue loading emerges as one of the most important topics to assess the
integrity of highly loaded launcher structures.
Deliverables:
Verification (analysis/test) methodology, documents, test results and coupons
Current TRL:
TRL 2
Target TRL:
TRL 4
Application
Need/Date:
all large and highly loaded
Application/Mission: launcher structures (Mission Date: Contract Duration:
2020)
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
For TRL5: 2014
24 months
Dossier0 Ref.:
T-8116, T-8138, T-8289,
T-8318, T-579, T-7763
TD:
TD20
N/A
TRP Reference:
T419-012MC
Title:
Fracture Control/Damage Tolerance methods for highly loaded launcher
components
Objectives
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Description of Activities
Establishment of advanced fracture/damage tolerance tools and methodologies for highly loaded launcher
structures such as engine components, tanks, skirts etc. Such methods shall make use of recent
advances in stochastic analysis and defect propagation retardation models.
Description
Classic damage tolerance methodologies based on linear elastic fracture mechanics (without taking into account the
potentially beneficial effects of the interaction of loads with variable amplitude) are in many case not considered
feasible for a number of launcher structural components such and nozzles, engine parts, highly loaded components
etc. without resulting in much too heavy components. More advanced methodologies are available that can help to
make damage tolerance approach for such items feasible, and thus improve the reliability and safety of such
components. The study shall build upon e.g. experience with retardation models developed for the ESACRACK
software (NASGRO module), and stochastic methodologies developed for e.g. aeroengines and Space Shuttle
(DARWIN and NESSUS software). Also a probabilistic version of the ESACRACK software is available for such
application.
Classic damage tolerance methodologies are currently applied for the verification of most launcher structures and
other subsystems. However, for a number of components such and nozzles, engine parts, highly loaded structural
parts etc. the classical linear approach can often not be applied or will result in much too heavy components if applied.
More advanced methodologies such as retardation methods and the application of stochastic tools have been
developed, e.g. for application in aeroengines, and could be used for launchers as well. This study will address two
areas namely:
a) Feasibility on the applicability of retardation models (strip-yield model of ESACRACK software) for ELV/RLV and
transfer vehicle structures. Well defined high loads early or at regular intervals in the fatigue load spectrum of the
structural items can reduce the growth of cracks in the rest of the fatigue life. Examples of such loads are proof loads,
highest loads during launch, etc.
The risk to overestimate the beneficial effects of such overloads must however be reduced to acceptable level. As
such the development will address methodologies for definition of load spectra, and the approach to be followed to
apply safety factors, scatter factors etc. in the verification has to be critically assessed and modified if necessary.
b) Application of stochastic damage tolerance methodologies, specifically relevant for nozzles, engine parts etc.
The study shall explore the stochastic nature of the most important parameters of the damage tolerance evaluation,
like mechanical (incl. thermo-mechanical) loading, and initial flaws present in the structural parts. It shall be
investigated whether the distribution of initial flaws should be based on the characteristics of the non-destructive
inspection method, or on e.g. known flaw distribution inherent to the material and manufacturing process
(complemented or not by NDI). The reliability target needs to be investigated as well, e.g. by application of the
methodology to proven reference concepts (similar what is e.g. done in aeroengine practice).
Deliverables:
Analysis & verification methodologies, documents, software, test coupons as relevant
TRL 4
Current TRL:
TRL 3
Application/Mission:
All space transportation vehicles
(Mission Date: 2020)
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-8318, T-7763
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
For TRL5: 2014
18 months
N/A
TRP Reference:
T419-013MC
TD:
TD20
Title:
Structural integrity of pressurized structures: Advanced non-linear methodology
Objectives
To improve non-linear fracture mechanics models for application in damage tolerance evaluation of
pressurized launcher structures including welded structures and other high performance applications
where LEFM is too conservative or inadequate.
Description
Pressurized structures, such as launcher tanks, booster cases and pressure vessels are generally optimized for mass
and therefore operate at relatively high stresses. Application of the traditionally applied Linear Elastic Fracture
Mechanics (LEFM) for safe life evaluation is in some cases inadequate for such applications: depending on the
situation it may be both too conservative (resulting in mass penalty) or potentially unsafe. The need for more
advanced, non-linear or Elastic-Plastic Fracture Mechanics (EPFM) is therefore recognized, and will be reflected in
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Description of Activities
e.g. the next version of the ECSS fracture control standard (ECSS-E-32-01). EPFM methodology has been applied
successfully on e.g. a number of European launcher structures, based on the results of the Structural Integrity of
Launchers Study performed by ESA in the 1990s.
Meanwhile, EPFM methodologies have evolved, e.g. in European (SINTAP, FITNET) and American studies. The need
to evaluate the suitability and potential of the improved methods for highly loaded space (pressurized) structures, and
to provide guidelines and better integration with the existing software tools used for damage tolerance verification on
ESA projects (ESACRACK, FRAMES-2) is identified.
In general, current damage tolerance analysis methods relies on LEFM for safe life evaluation. For high performance
structures, including pressure vessels, for the next generation of RLV or ELV structures such evaluation may be too
restrictive or even inadequate. Damage tolerance evaluation, which may take into account material plasticity becomes
necessary.
This activity will include several tasks:
• Establishment of advanced methods for analysis of crack extension and strength under static load (e.g. R6, SINTAP,
strip yield), including development of relevant new J-integral solutions for structural details containing surface cracks;
• Assessment tools for void creation, extension and strength under static load (e.g. Gurson models);
• Establishment of advanced methods for analysis of fatigue crack and void growth in plastic conditions, incl.
investigation and improvement of existing models;
• implementation in damage tolerance analysis and database software tools (ESACRACK, FRAMES2), or to
link/integrate them with suitable existing non-linear fracture mechanics software, as appropriate.
Guidelines on how to implement more advanced finite element analysis in case simplified analysis using the standard
software tools is considered inadequate.
• These tasks will include tests on cracked samples of representative materials (e.g. Al2219, Al-Li, D6AC steel,
Inconel, titanium) to verify the analytical models, where necessary.
Deliverables:
Documentation, software modules and test results
TRL 4
Current TRL:
TRL 2
Application/Mission:
FLPP, manned vehicles (Mission
Date: 2020)
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-8318, T-7763
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
For TRL5: 2014
24 months
N/A
TRP Reference:
T420-014MC
TD:
TD21
Title:
Development of nano-structured cryogenic foam insulations
Objectives
To assess the potential of advanced nano-structured foam insulations and to pre-develop an insulation
system for cryogenic tanks of launchers and potential long-term missions.
Description
New advanced nano-structured foam materials based on PU and PI have been developed in recent years. At the
same time previous materials selected as promising candidates for such applications became unavailable due to the
lack of sufficient industrial interest. The newly developed materials are expected to be good candidates for the
insulation of large cryogenic tanks of future launchers. Further, new advanced insulation systems will be required for
long-term missions to the Moon or Mars.
:Within this activity newly developed nano-structured materials shall be screened and assessed in view of their
suitability for cryogenic tank insulations. Relevant screening tests shall be performed in the applicable temperature
range. Relevant aspects concerning integration, cryo-pumping and sealing shall be investigated.
Deliverables:
Screening, test and study reports, test samples
Current TRL:
TRL 1
Target TRL:
TRL 3
ELV, RLV, Long-term missions
Application/Mission: using cryogenic propellants (e.g.
CSTS) (Mission Date: 2017)
Application
Need/Date:
Contract Duration:
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Description of Activities
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Dossier0 Ref.: T-8275
N/A
TRP Reference:
T423-015MC
TD:
TD24
Title:
Passive / Active oxidation of CMC structural materials
Objectives
The objective of the proposed activity is to characterize CMC materials for oxidation behavior by
identifying a series of test conditions (representative, as much as possible, of flight environments),
identifying adequate measurement techniques, material erosion rates and the triggering of passive to
active oxidation. In addition a dedicated test campaign on samples representative of- and subjected to
environments relevant for space transportation systems shall be performed. The expected output will be:
o To achieve a better understanding of the critical parameters under which transition from passive to
active oxidation occurs;
o To characterize CMC materials for oxidation behavior;
o To improve the tools (measurement techniques and physical models) addressing the passive to active
transition (PAT) phenomena;
Description
The application of ceramic matrix composites (CMC's) for hot structures and thermal protection systems for space
transportation vehicles is a necessity for mass and performance reasons. Large efforts have been made during the
last fifteen years to mature the technology readiness of CMC materials and flight worthy structures have been
developed and tested successfully. However, the behavior of such CMC materials under critical thermo-mechanical
environments requires further investigation. In particular, the application of CMC materials in reusable space
transportation systems requires the deep knowledge of the passive to active oxidation boundaries of such materials.
The results will be directly applicable to FLPP and manned vehicles.
The activity shall include:
Selection of existing hot-structures and TPS CMC materials with their respective Oxidation Protection Systems.
Identification of a series of test conditions (representative, if possible, of flight environments), identification of adequate
measurement techniques, material erosion rates and the triggering of passive to active oxidation and performance of a
dedicated test campaign on samples in the area of interest for space transportation systems environments.
Extrapolation of test conditions to typical flight conditions and evaluation of operational/ lifetime constraints based on
the tested materials. Identification of technology developments needed to improve the oxidation protection of CMC
materials.
Deliverables:
documentation and test samples
Current TRL:
TRL 2
Target TRL:
TRL 3
all future re-entry vehicles using
Application/Mission: CMC materials for TPS (Mission
Date: 2017)
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
Dossier0 Ref.:
For TRL5: 2012
18 months
T-8116, T-8138, T-8289,
T-8318, T-579, T-7763
N/A
4-02 - Human Space Flight oriented Technologies
TRP Reference:
T401-016ED
TD:
Title:
Safety oriented reference architecture
TD01
Objectives
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TRP Work Plan 2008-2010
Description of Activities
To provide a reference architecture for systems where Safety is the driving requirement and especially for
man rated systems with the possibility of scaling down the system for other high availability system like for
robotics mission. This architecture shall be based on technologies update (higher miniaturisation as
compared to ATV or DMSR like, problem of the components obsolescence), and include the specifications
of the key building blocks and their interfaces, with special attention to the computer as being the most
complex and then costly element (typically 50 % of the hardware) for a Safety oriented Fault tolerant Data
system. In addition the analysis shall be performed in the perspective of recurrent production and within
an overall system assessment of the whole platform avionics. This reference architecture shall then
foster the definition, design and development of a suite of compatible building blocks.
Description
If most of the space systems fall into the category of “reliable” oriented systems where emphasis is given to
guarantee an operational life time over a given period of time (mission dependent, typically 15 years for a telecom
satellite) although tolerating episodic interruption of services for the purpose of reconfiguration for example, there is a
category of systems where no interruption of service is allowed as it could have catastrophic consequences, and in
particular for man tended systems. ATV is to-day the best example of such system but is built upon a technology that
is to day obsolete (like the 3 chips ERC32 microprocessor out of production…).
The activity shall provide reference to the development of safety critical system (i.e. where human safety is a concern)
as a first priority but shall also be a useful reference for systems having high requirement for high availability as it can
be the case of autonomous robotics mission by performing a down scaling of the requirements applicable to man
rated systems.
(including previous related studies)
Phase 1 :The activity shall start from an evaluation of the state of technology both in the domain of space
transportation and launcher (ATV, Ariane-5…) and in other domains where safety issues are of prime importance like
Aeronautics, Automotive, nuclear plants...
It will then specify the functional and performance requirements extracted from prospective use cases on CLV and
ELV evolution for launcher and other space transportation scenarios (space tug, Moon or Mars lander…) with a
particular attention to characterise for each case the availability defined by the need to maintain a continuity of
services even in the presence of failures that can vary from “tolerance 0” i.e. when no outage is tolerated in the most
stringent cases (as ATV) up to cases where some outage can be tolerated as long as it does not exceed some
limited TBD time value.
The contractor shall perform the architecture trade-off in relation with some perspective on the underlying technology
for implementation (e.g. migration from 0.25 µ rad tolerant process to 0.13 µ or 90 n, possible use of COTS.. ) and to
conclude by the identification of the main building blocks (H/W and S/W) as necessary to build the system core.
In a second step, the contractor shall issue his specification of the architecture, namely the buildings blocks and their
interfaces (H/W-H/W, H/W-S/W, S/W-S/W) as well as providing the models corresponding to their specifications.
This step shall be concluded by a PDR prior to make available the requirements for the different activities involved in
the design and development of the main building blocks e.g. :
• the computer and the main I/O and peripheral such as the internal interfaces (buses, networks) both at platform
level and “in the box”(inter-modules) or external (TM-TC),
• highly resilient data storage that can be used as safeguard that can provide a data storage service able to tolerate
specific events or failures (as power down)without loosing any bit of critical data (e.g. on board data bases, software
back-up, recovery points…),
• dedicated co-processor or embedded sensor that can be required by a given mission definition
Emphasis shall also be given on the provision of a modular architecture allowing system extension in order not to
block the evolution of the system with time (technology upgrade) .
At the end of Phase 1, the “architect” contractor shall release a consolidated preliminary specification of requirements
for the design and pre-development of the main building blocks as well as specifying the building blocks interfaces.
Phase 2
In a second step, the ”architect” contractor shall follow-on the individual building block design and development
phases, supporting the analysis of any simulation, validation, test analysis.
He shall lately support the integration of the different building blocks breadboards, to be performed under parallel
activities, into a reference test bench.
At the end of the activity, the contractor shall provide an updated specification of the main system building block and a
roadmap for their implementation up to the flight model .
Deliverables:
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Description of Activities
- Specifications of requirements of reference architecture (functions, specification of main building blocks and their
interfaces (H/W-S/W, H/W-H/W, S/W-S/W)),
- Models of the building blocks and interfaces,
- Technology and architecture trade-off for the FT computer and release of initial set of performance requirements,
- Specifications of requirements for the Use cases “test applications”,
- Test review and analysis of the delivered building blocks (module, unit level),
- Technical follow-on of the integration activities (model based up to reference architecture test bench integration).
Current TRL:
TRL 2
Application/Mission:
Human Space Flight (Mission
Date: 2020)
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
TRL 4
Application
Need/Date:
Contract Duration:
For TRL5: 2014
18 months
Dossier0 Ref.: T-8308
Consistent (Avionics/Embedded item A4 , and Computer data
system item B1)
TRP Reference:
T405-017EC
Title:
Robust Skip-entry Guidance and Control Techniques
TD:
TD05
Objectives
To study the most effective, robust and accurate guidance and control strategies guaranteeing "anytime
return" from the surface of the Moon to the same Earth landing site(s);
- To develop and validate the most promising skip-entry guidance algorithms on a dedicated high fidelity
simulation environment against various reentry scenarios including perturbation in initial entry conditions,
vehicle mass and aerodynamic properties and atmospheric density;
- To demonstrate their real-time closed loop performance on a tailored reentry real-time test bench.
The expected results are the delivery of validated robust skip-entry guidance components (TRL: 3)
general enough to be applicable to similar CSTS vehicle concepts with different vehicle characteristics.
Description
One important aspect of manned space exploration is the safety of the crew. It is required to provide safety
considerations at all stages of flight: during launch, in flight and during re-entry. In particular, future lunar manned
mission architectures require that the crew vehicle return safely (abort mission conditions) at anytime from the lunar
surface to the same terrestrial landing site(s). Such a requirement is also applicable for ascent aborts or emergency
returns from orbit. In order for the crew vehicle entry trajectories from lunar return or LEO to use the same landing
site(s), it is necessary to extend the downrange capability (> 10,000 km) of the re-entry vehicle. This can be obtained
by using a skip-entry guidance on the lunar return trajectories. The skip-entry lunar return technique provides an
approach for returning crew to a single landing site, for ease and minimal cost of recovery, post-landing safety, and
reusability of the spacecraft, anytime during a lunar month. The Russians for their abortive manned lunar program
perfected this technique in the 1960's. While skip-entry promises tremendous operational capabilities it creates
technical challenges for the thermal protection system as well as guidance and control. Therefore, robust re-entry
guidance and control algorithms are not only desirable but also compulsory.
The activity starts with an analysis of the mission and system requirements and constraints of past and future lunar
manned mission architectures, such as Apollo, CEV and CSTS, and translation into the navigation, guidance and
control chain requirements (Task 1). An analysis and trade-off of candidate skip-entry guidance and control strategies
are carried out leading to the selection of the most promising algorithm(s) satisfying the entry range requirements
(Task 2). Subsequently, a standardized entry flight profile allowing to target the same range-to landing site trajectory
for all return scenarios so that the crew and vehicle experience the same heating and loads during each lunar return
entry flight is defined (Task 3). The detailed design of the most promising skip-entry guidance and control algorithms
are performed and their performance robustness tested on a dedicated high fidelity simulation environment. Monte
Carlo simulations are used to disperse the environment (atmosphere and winds), vehicle systems (navigation, vehicle
thrust, control system), and vehicle state (position and velocity) to ensure that the vehicle achieves the desired landing
site with the proper reserves of consumables. The simulations will also used to size the vehicle thermal protection
system that protects the vehicle from the intense heat of entry; to ensure excessive accelerations and dynamic
pressure limits are not exceeded; and to size the vehicle engines and control system accordingly (Task 4). Finally, to
achieve TRL 3 embedded software prototypes of the selected skip-entry guidance and control algorithms are
produced using industrial automatic code generation tool and their real-time closed loop performance demonstrated
on a tailored reentry real-time test bench (Task 5).
Deliverables:
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Description of Activities
ESA will be provided with validated robust skip-entry guidance and control algorithms and associated embedded
software, including technical documentation, as well as Monte Carlo simulation and real-time closed loop performance
test reports using a CSTS-like vehicle as the main test case. Moreover upgraded version of an existing high fidelity
reentry functional engineering simulator (Reentry-FES) and real-time test bench (Reentry-RT) will be delivered at the
end of the activity.
Current TRL:
TRL 1
Target TRL:
CSTS, RV requiring extended
Application/Mission: downrange, Space Exploration
(Mission Date: 2020)
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
For TRL5: 2014
12 months
Dossier0 Ref.: T-8300
N/A
TRP Reference:
T417-018MP
TD:
TD18
Title:
Planetary Probe Standard model testing in High enthalpy facilities
Objectives
Background: (including previous related studies)Planetary probe model testing in high enthalpy facilities
such as F4 ( lessons learned from MSRo) in air and Co2 as well as recent experimentation on similar
probes at Tsagi revealed the need to enhance our knowledge for a series of critical issues for planetary
probe design such as
- existence of supersonic wake closure
- wake shear layer transitional flow
- shoulder heating
- influence of sting on base flow
and this in air as well as in Co2 environments.
Objectives of the study and expected results: Creation of an experimental data base using 2 types of
standard models and testing in different high enthalpy facilities for the study of critical aerothermodynamic
phenomena such as
- base heating,
- sholder overheating including boundary layer transition as well
- data on hypersonic stability and trimming.
The 2 standard models shall be tested in different hypersonic facilities in air as well as in Co2. The
purpose is to use where possible existing models; attention shall be placed on appropriate instrumentation
and provision of free stream condition shall be made.
The first standard model shall be an axisymmetric blunt cone simulating a ballistic entry (the existing 70
degree planetary blunt cone) and the second standard model shall be the Apollo like (EXOMARS) shape
configuration (simulating a 20 degree trimmed reentry) .
The outcome shall be experimental data on pressures, heat flux, flow field densities as well as nozzle free
stream characterization. CFD workshop type of validation exercises shall be performed and conclusion
drawn on uncertainties associated with above listed critical phenomena.
Description
The contractor shall perform the following activities :
- Review of past experiments on planetary probes and capsules, analysis, quantification and prioritization of critical
phenomena
- Definition of 2 type of instrumented standard models, taking into account availability of existing models and
proposing new ones pending budget constraints. 1 to study ballistic planetary probe phenomena and a second one
simulating trimmed capsule Apollo type phenomena
- Execution of appropriate hypersonic test campaigns in Air and Co2
- CFD validation workshops
- Analysis of data, conclusion on remaining uncertainties associated with the critical aerothermodynamic phenomena
listed above including assessment on flight extrapolation.
- Consolidation of lessons learned, synthesis and recommendation
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Description of Activities
Deliverables:
Wind tunnel test data, CFD Solutions, Technical notes,
Test Articles, Test Data
Current TRL:
TRL 2
Target TRL:
TRL 3
planetary probes, sample return,
Application/Mission: human space flight, exploration
vehicles. (Mission Date: 2020)
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
For TRL5: 2014
24 months
Dossier0 Ref.: T-7904
Consistent (B4)
TRP Reference:
T418-034MP
TD:
TD19
Title:
Solid Modulated Propulsion for Space Exploration
Objectives
The main objective of the proposed TRP activity is to demonstrate thrust modulation capacities (based on
solid propulsion technology) for ascent and possibly accurate and soft landing.
The activity is expected to demonstrate the technology feasibility of thrust modulation in solid propulsion
motors for application to missions on other planets.
Description
Among the intrusive measurement techniques for in-flight experimentation in entry vehicles, classical instruments such
as thermocouples of various type and heat flux sensors are extensively used. They are easy to procure and relatively
cheap, but it has been recognised that they could fail to provide accurate aerothermodynamic data unless an
extensive characterization activity of their transfer functions is carried out prior to in-flight experimentation.
It is to be noted that each sensor reading available to the experimenters for post-test rebuilding activities is only the
final output of a measurement chain significantly affected by the properties of the material on which the sensor is
integrated, the adopted integration technique and obviously the characteristics of the sensor itself.
In specific cases such as thermocouples in pyrolizing ablative materials it has been seen in the U.S. that not only the
integration of sensor heads but also the layout of the whole sensor has an impact on the final sensor reading.
Although each Thermal Protection System material (ceramic, metallic, ablative) features different properties (thus
requiring different One of the major limitations of solid propulsion has been so far the impossibility to modulate the
thrust according to the mission needs. For planetary applications to ascent and eventually even descent and landing
where the need of high thrust (typical of solid propulsion) is coupled to the requirement of thrust modulation, the
introduction of a modulation capability on solid rocket engines will provide an important add-on with respect to the
currently available propulsion technologies. Preliminary assessment to introduce such capability has been performed
by industry, but a dedicated R&D activity is needed to bring the TRL level to the point to decide about the capability for
this propulsion technology to compete with others currently available.
The proposed TRP activity shall include:
- mission requirements establishment, for the definition of a representative thrust modulation profile and behaviour;
- trade-offs on candidate thrust modulation techniques for solid propulsion;
- motor design;
- development of breadboard(s);
- testing activities for thrust, performance, and modulation ratio capacities demonstration;
- technology development plan for future activities.
Deliverables:
Technology design report; test report; technology development plan.
Current TRL:
TRL 2
Target TRL:
TRL 3
Relevant missions: AURORA
Application/Mission: missions, ExoMars >2013,
Precursor missions, MSR 2020.
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
Dossier0 Ref.:
For TRL5: 2012
18 months
Flight Test and Measurement
techniques 17-C-II
Consistent
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Description of Activities
TRP Reference:
T420-019MC
TD:
TD21
Title:
Development of a European ablative material for heatshields of sample return
missions
Objectives
To develop, test and characterise a European ablative heatshield material for the Earth entry capsule of
sample return missions (e.g. Mars, comets, asteroids), able to cope with the stringent environment (typical
peak heat fluxes of 15-20MW/m2 and heat loads up to 200MJ/m2) while conforming to the mass budget.
The development shall take into account a potential later application of the material for human return
missions (CSTS).
Description
The Earth return from extraterrestrial bodies (e.g. Mars or comets) involves a hyperbolic entry with velocities of
typically above 12km/s and resulting peak heat fluxes of 15-20MW/m2. In a previous activity a screening of existing
European ablators to assess their suitability for a sample return mission was performed. Unfortunately, it turned out
that none of the materials is suitable to sustain the very high heat fluxes while coping with the stringent mass
requirements. The work to be performed within this activity shall be based on a stepwise approach:
• Trade-off concerning new development or modification of an existing material,
• Identification of necessary development steps,
• Iterative material development supported by adequate sample tests,
• Development and assessment of advanced ablative heatshield concepts
• Characterisation testing including plasma wind tunnel testing at appropriate flux levels,
• In addition to the development of the material, approaches shall be developed to advance the design, testing,
validation and verification process for such materials e.g. shock tubes and wind tunnels.
Deliverables:
Material samples, documentation
TRL 4
Current TRL:
TRL 2
Application/Mission:
MSR, CSTS
(Mission Date: 2020)
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-8283
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
For TRL5: 2014
18 months
N/A
4-03 - Generic Space Transportation Technologies
TRP Reference:
T403-03MC.B
TD:
TD18
Title:
Improvement of the gas-surface interaction models, to account for the coupling
pyrolisis-catalysis. Integration of models into a CFD code. Validation.
Objectives
The objective of this activity if to continue the development inititated in the "Multidisciplinary Modeling of
Fluid Structure Interaction" TRP activity, aiming at improving the gas-surface interaction models.
Description
Planetary entry capsules, such as Huygens, are most of the time equipped with thick ablative heat shields to cope with
the high temperature dissociated flow surrounding the vehicle during its entry. The design and verification of the shield
requires the analysis of the interaction between the flow field and the TPS material. In particular, models for ablation
and hypersonic flows have been developed in some groups. The dissociation of the flow in the shock layer is
accompanied with the transport of atomic species to the surface, where they recombine and release their
recombination energy directly to the vehicle: This process, called catalycity, increases the thermal loads on the
vehicle. It exists together with the ablation of the TPS material. The interaction between the two processes needs to
be further analysed to assess the thermal environment and the design margins available.
Deliverables:
Models. Computational modules. Test cases selection/simulation. Results analysis + conclusion/recommendation.
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Description of Activities
Prototype
Current TRL:
Target TRL:
Beta Version
Application
Need/Date:
All Space Transportation, re-entry
Application/Mission: and entry vehicles (Mission Date: Contract Duration:
2017)
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
SW Operational >
2011
16 months
Dossier0 Ref.: T-8091
Consistent (B27)
TRP Reference:
T405-001EC
Title:
On-line System Identification Technology
TD:
TD05
Objectives
To specify the requirements and design drivers for on-line reentry vehicle model identification systems
To select the most promising on-line system identification techniques for re-entry vehicles according To
performance robustness against parametric and dynamic uncertainties, aerodynamic coefficients
estimation accuracy, real-time implementation, etc.
To develop and benchmark the selected on-line reentry vehicle model identification systems
Description
Within the IXV demonstrator project, gathering of flight data and processing them via system identification techniques
is fundamental (i) for vehicle performance assessment, (ii) for stability and control evaluation, (iii) for future European
re-entry vehicle development. With respect to the first two points, vehicle system identification techniques are to be
investigated for the development of more accurate flight validated reentry vehicle dynamical models. Accurate
modeling validation and verification is one of the most expensive activities for reentry vehicles. Special flight test
techniques to adequately excite the system in combination with system identification techniques allow reconstructing
accurately the vehicle dynamics experienced during flight. Main elements of the mathematical model to be
reconstructed are the control and stability derivatives, FLAP/RCS control efficiency, closed-loop flying qualities
properties, etc. that determine how well the vehicle responds to desired commands. These needs have already been
recognized within the IXV project and will be addressed via the so-called Vehicle Model Identification (VMI)
experiment, which is conceived as an off-line post-flight system identification experiment with special focus on the
post-processing of the in-flight data for determining the vehicle aerodynamic coefficients and associated derivatives.
The next step, to specifically address point (iii) above, is to develop on-line system identification techniques which
would allow decreasing the need with respect to GNC robustness, so that systems margins and uncertainties can be
further adapted at the increase of global performance and confidence.
The activity starts with the specification of the functional, performance, operational, etc. requirements and design
drivers for on-line reentry vehicle model identification systems (aerodynamic coefficients and derivatives, vehicle MCI
parameters, etc.) (Task 1). The on-line reentry vehicle model identification system architecture: minimal sensors suite
characteristics, excitation profiles, algorithms, etc., is then defined and analysed (Task 2). An analysis and trade-off of
candidate on-line system identification techniques are carried out leading to the selection of the most promising one(s)
(Task 3). Subsequently, the detailed design of the selected on-line system identification algorithm(s) are performed,
performance metrics defined, and performance robustness against parametric and dynamic uncertainties evaluated
on a dedicated high fidelity simulation environment using IXV as a reference test case (Task 4). Finally, a functional
prototype of the baseline on-line reentry vehicle model identification system will be developed and validated at a later
stage using IXV in-flight measurement data (Task 5).
Deliverables:
ESA will be provided with on-line system identification components for reentry vehicles, including technical
documentations, as well as performance and benchmark simulation test reports using IXV as the main reference test
case.
TRL 2
Current TRL:
TRL 1
Application/Mission:
RTVD, CSTS, RLV (Mission Date:
Contract Duration:
2017)
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
For TRL5: 2012
18 months
Dossier0 Ref.: T-8300
N/A
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Description of Activities
TRP Reference:
T405-020EC
Title:
Robust Flight Control System Design, Verification and Validation Framework
TD:
TD05
Objectives
To develop an enhanced robust flight control system design framework, including methodology, algorithms
and tools, for uncertain non-linear time-varying safety critical systems such as Expendable Launch Vehicle
(Ariane, Vega Evolution) or Re-entry vehicles (IXV, CSTS, RLV). The framework shall reduce significantly
the Design, Validation & Verification (DV&V) effort, shall comply with high level missionization
requirements and shall ensure enhanced dependability by design.
The expected result is a DV&V framework for robust launcher GNC development that makes use of the
latest advances in robust multivariable control technology. The framework will be developed is such a way
that it fits well with the current industrial DV&V process and common design practices as well as being
applicable for re-entry vehicles.
Description
Currently well established gain scheduling control laws based on eigenstructure assignment, filtering, LQG, and/or
H-infinity are already flying (Ariane). However, the compromise between robustness and launcher performance
seemingly almost to be achieved is a result of a tedious trade-off between rigid mode control and attenuation needs
for bending modes. For future launcher applications such as Vega Evolution, but still applicable for the current Vega
(see Vega SCDR Board Report), GNC missionization is a key requirement that can definitively be improved by
advanced control design methods.
To address and improve the goal of increasing vehicle performance, safety, reliability and efficiency, a more powerful
design process needs to be developed. Significant results have been obtained in robustness modeling, robustness
analysis and robust control synthesis with associated validation and verification technologies for the development of
complex nonlinear and time varying flight control systems. In a small explorative study (see previous related study) it
has been shown that the above mentioned robust GNC missionization requirement can be met by novel robust
multivariable control technologies. By means of specially developed uncertainty management models with appropriate
techniques and tools it has been shown how the design process can be simplified and made more accurate by
systematic and guaranteed model coverage for the control design and control analysis and verification. However the
technology readiness level of the technology is still at a level between one and two (method verified on a single axis
launcher vehicle) and not yet applied to full scale of launcher GNC system.
In the light of the above consideration, the aim of the proposed activity is to develop a DV&V framework for robust
launcher GNC development. The framework shall increase the TRL of this technology and consist of industrially
applicable modelling, design analysis, validation and verification tools for complex evolving launcher GNC systems.
Special attention shall be given such that these tools fit well in the current industrial DV&V process and common
design practices. Emphasis will be given to the development of advanced control concepts and tools to increase the
launcher performance level at increased level of confidence while simplifying and making the developmental process
more rigorous and systematic. Having such an infrastructure in place minimum effort for retuning, analysis and
verification shall be demonstrated. Specific tasks to be performed include:
- Development of generic modelling tools for the systematic incorporation of launcher model uncertainties at various
system and subsystems level. Demonstration of these tools on a fully industrial VEGA launcher system via the
development of multi-purpose uncertainty models;
- Development of a suite of theoretically well founded analysis and worst-case analysis tools allowing to measure
various performance and robustness measure related to launcher flight control systems architectures;
- Further development of a suite of theoretical robust gain scheduling control concepts suitable for the specificity of the
launcher problem; Detailed design and development of novel control laws using the newly developed control methods;
- Development and model validation of a simulation software tool for the analysis and robustness performance
assessment of robust launcher flight control systems for representative industrial uncertainty scenarios in order to
demonstrate how the infrastructure can respond to rapid design changes;
- Real-time simulation and analysis for the model and performance validation of the robust G&C algorithms (real-time
software prototype);
- Industrial implementation and comparison with the current industrial solution
Deliverables:
ESA will be provided with a validated Robust Flight Control System Design, Validation and Verification Framework:
methodology, algorithms and tools, including technical documentations and associated ECSS-040 software
documentations. Benchmark performance metrics and test reports will also be provided.
Current TRL:
TRL 1
Target TRL:
Ariane 5 Evolution, Vega
Application/Mission: Evolution,CSTS, RTVD, RLV
(Mission Date: 2020)
SW Clause :
N/A
TRL 3
Application
Need/Date:
Contract Duration:
For TRL5: 2014
18 months
Dossier0 Ref.: T-8303
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Description of Activities
Consistency with Harmonisation
Roadmap and Conclusions:
N/A
TRP Reference:
T405-021EC
TD:
TD05
Title:
Hybrid Navigation (HiNAV) System Architecture Consolidation
Objectives
To consolidate the HiNAV functional, performance, safety and operational requirements for satisfying AR5
Evolution, Vega Evolution and Crew Space Transportation System (CSTS) navigation needs;
To consolidate the HiNAV mechanical and electrical architecture, including the selection of European IMU
and GNSS equipments selection, GNSS antennae accommodation, etc., while ensuring its compatibility
with Galileo positioning system;
To generate the HiNAV industrial file for the development of a Flight Model, including specifications,
development, verification & validation approach, programmatic, cost, industrial organisation, etc.
The expected results are a demonstration of the HiNAV technical and economical benefits for future
European launchers and Space Transportation System such as CSTS. With regard to the later the HiNAV
system could be considered as an ESA under-taking to the CSTS programme (international cooperation).
Description
The emergence of composite terrestrial missions (launcher, reusable space transportation system, earth re-entry with
precision landing) featuring a succession of different phases (ascent, orbital, re-entry, TAEM and landing) calls for
hybrid navigation solutions combining different navigation means into a sensor suite (IMU, GNSS, DGNSS, air data
sensor, radar altimeter, etc.). Hybridisation has become in recent years a technology in itself and has been identified
by Eurospace as a strategic technology for the European Space Industry. In this respect, the Agency has initiated
since fall’05 the design, development and real-time testing of a robust multi-mission hybrid navigator (HiNAV)
breadboard. Phase I results, recently completed, have demonstrated that the selected ultra-tight aided navigation
solution fulfilled the hybrid navigation system functional and performance requirements for a wide spectrum of mission
reference scenarios and vehicles: A5 GEO (launch), ATV (orbital/far rendezvous), EVEREST (re-entry and TAEM)
and Phoenix (landing). Phase II, to be completed in 4Q07, will develop a breadboard of the hybrid navigation system
and will demonstrate its real-time closed loop performances on a dedicated COTS avionics test bench (dSPACE,
SPIRENT II and LEON boards).
The activity starts with a detailed analysis of AR5, Vega, CSTS mission profiles, operations, system, electrical and
avionics architectures, etc., leading to a consolidation of the multi-mission HiNAV functional, performance, safety and
operational requirements (Task 1). The existing hybrid navigation chain design is then reviewed and consolidated (if
necessary) for each application cases, with the identification of hardware and software resources impacts (Task 2).
Similar analyses are made on Processing and FDIR design as well as HiNAV electrical and mechanical
implementation issues onboard AR5 and Vega (Task 3). Based on the European IMU, GNSS equipments selection
results, GNSS antenna accommodation and multi-path analyses, compatibility with Galileo positioning system
analyses, and HiNAV breadboard activity results, the multi-mission HiNAV system architecture, including electrical
and mechanical detailed design, is consolidated (Task 4). Upon acceptance of the upgraded HiNAV functional
engineering simulator and real-time closed loop test bench, the demonstration of the multi-mission capability of the
HiNAV is simulated (functional and real-time) for AR5, Vega and their evolutions as well as CSTS with representative
reference scenarios, and test reports produced accordingly (Task 5). Finally, the complete industrial file for the
development of the HiNAV Flight Model is elaborated, including the development, verification and validation approach,
as well as the programmatic file (Task 6).
Deliverables:
ESA will be provided with the multi-mission Hybrid Navigation (HiNAV) system industrial file for the development of a
Flight Model as well as real-time performances and mission instantiation demonstration test reports for representative
AR5 Evolution, Vega Evolution and CSTS mission scenarios. Moreover upgraded version of the HiNAV functional
engineering simulator (HiNAV-FES) and real-time test bench (HiNAV-RT) will be delivered at the end of the activity.
Current TRL:
TRL 3
Target TRL:
Ariane 5 Evolution, Vega
Application/Mission: Evolution, CSTS,RTVD, RLV
(Mission Date: 2020)
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 4
Application
Need/Date:
Contract Duration:
For TRL5: 2014
6 months
Dossier0 Ref.: T-8302
N/A
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Description of Activities
TRP Reference:
T405-022EC
TD:
TD05
Title:
Advanced Reentry Flying Qualities Analysis Framework
Objectives
To develop an advanced Flying Qualities Analysis framework for re-entry vehicles, including methodology,
advanced modelling, algorithms and SW tools, for the analysis and determination of safe and reliable
controllable operating envelope of re-entry vehicles while overcoming the traditional flying qualities
analysis process shortcomings;
To assess the benefits of the advanced Flying Qualities analysis framework with respect to the traditional
flying qualities analysis process using IXV as reference test case.
The expected result is a new approach for flying qualities analysis of re-entry vehicles that takes into
account dynamics coupling and uncertainties (aerodynamics parameters, flight conditions, etc.) and
makes use of the latest advances in robust multivariable control technology.
Description
Flying qualities of a re-entry vehicle reflect the desired closed loop system properties and stability properties
determined by the vehicle shape, controls and control systems. Traditionally the trim and stability analysis are
executed loop at the time in a single variable setting, i.e. longitudinal and lateral motions are assumed to be
decoupled, whereas re-entry dynamics is high angle of attack and inertia roll coupling may appear in case of roll
reversal manoeuvers. Therefore, dynamics coupling needs to be addressed carefully. Further, many vehicle
characteristics, such as aerodynamics coefficients are not well known especially in the transonic regime. As a result
the definition of worst cases accounting for uncertainties on aerodynamic parameters and/or flight conditions is time
consuming and difficult. To improve the traditional flying qualities analysis process, concepts from multivariable control
theory and uncertainty modeling could be used to determine worst case parameter sensitivities on the vehicle multi
axis flight mechanics enabling the determination of safe and reliable controllable operating envelope of the re-entry
vehicle.
- The activity starts with a critical analysis of the traditional Flying Qualities analysis process for re-entry vehicles and
the identification of the shortcomings accordingly. The analysis shall lead to the formulation of relevant selection
criteria and performance metrics used for the selection of the most promising solutions fro improving the traditional
process (Task 1). The advanced Flying Qualities Analysis framework is then defined and specified as well as the
respective candidate techniques and software toolsets for modelling and worst case flying qualities analysis (Task 2).
The framework, including methodology, advanced modelling, algorithms and SW tools, is then developed according to
ECSS-040 tailored to small project (Task 3). The advanced reentry Flying Qualities Analysis framework is then tested
and benchmarked against the traditional process using IXV as a reference test case, leading to the desired TRL 2
(Task 4). Finally, major findings are synthesized and lessons-learnt reported (Task 5).
Deliverables:
ESA will be provided with an advanced Flying Qualities Analysis Framework: methodology, algorithms and tools,
including technical documentations and associated ECSS-040 software documentations. Benchmark performance
metrics and test reports will also be provided as well as critical assessment and follow-on activities.
TRL 2
Current TRL:
TRL 1
Application/Mission:
CSTS, RLV, RTVD (Mission Date:
Contract Duration:
2017)
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
For TRL5: 2012
12 months
Dossier0 Ref.: T-8300
N/A
TRP Reference:
T406-023EE
Title:
Re-entry Vehicle Communications Technology
TD:
TD06
Objectives
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To consolidate and extend the electromagnetic interaction model for the prediction of antenna radiation
pattern in the presence of engine plumes and of plasma, e.g. during atmospheric re-entry, based on the
models initially developed;
To define, develop and demonstrate robust communication architecture and technologies for the
monitoring, command and control system providing non-interfering, continuous, communication under all
flight conditions with special attention to the blackout phase.
The expected results are the development of a robust communication system and an antenna radiation
pattern prediction tool for re-entry vehicles. For the later two main classes of vehicles will be considered:
ballistic re-entry vehicles (e.g. ARD) and unpowered lifting vehicles (e.g. IXV).
Description
During flight trajectories, re-entry vehicles can generate electron densities with plasma frequencies exceeding the RF
transmission frequency, leading to communication blackouts. Communication is restored when plasma frequencies
decrease, due mostly to the deceleration to lower vehicle velocities and increase in collision frequency of electrons
with neutral particles due to the higher density of the plasma at lower altitudes. The ARD RF link during re-entry
produced much higher signal than expected during the plasma phase leading to the conclusion that an RF link could
be maintained if the antenna positioning is selected in a suitable way. To meet public safety concerns, it is necessary
to maintain communications for telemetry and vehicle control as well as navigation and tracking of vehicle during the
so-called blackout phase.
The proposed activity will define the communications architecture required for future missions, inc. IXV and CSTS.
The design drivers are communications via the TDRSS data relay satellite constellation and possible communications
via Artemis or a small GEO platform providing data relay capabilities. There is a communications relay package
proposed for the ARTES-11 small GEO activity. The communication link outages that can be expected during re-entry
and determine the most efficient means of getting high priority TM to the ground during entry, descent and landing
onto the Earths surface will be considered. The telecommand link shall also be considered as part of the baseline
architecture. This will involve a direct Earth to vehicle communications link using direct sequence spread spectrum
modulation or other resilient types of communications systems. The study will also consider the need for a
telecommand to be relayed to the re-entry vehicle during the re-entry phase (90-45km from Earth), when direct
Ground to Vehicle communications links are not possible due to plasma effects. A baseline architecture shall be
proposed in order to maintain telecommand capability with a high degree of reliability during critical mission phases.
On the other hand, post-mortem modelling of the ARD TT&C antenna pattern has demonstrated the possibility to
predict with good accuracy the effects of the plasma sheath generated during re-entry in the Earth atmosphere on the
RF link. These models are to be consolidated and extended to cover the case of engine plumes, also including the
presence of metallic particles, made suitable for more general vehicle geometries and antenna types, and
implemented as a component for the European Antenna Modelling Library to offer an effective prediction and design
tool for future missions. The tool will be validated with existing ARD data as well as with other data made available by
the Agency, e.g. from future re-entry experiments (e.g. EXPERT, IXV).
Deliverables:
ESA will be provided with the definition and detailed design of a robust communication system for re-entry vehicle,
including associated technical documentations. In addition a validated antenna radiation pattern analysis tool will be
delivered at the end of the activity.
TRL 3
Current TRL:
TRL 2
Application/Mission:
CSTS, RTVD, RLV (Mission Date:
Contract Duration:
2017)
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
For TRL5: 2012
12 months
Dossier0 Ref.: T-8059
Consistent with “TT&C transponders and Payload Data
Transmitters” Technical Dossier
TRP Reference:
T417-024MP
Title:
Damping derivatives assessment for hypersonic re-entry vehicles exhibiting
high angle of attack
TD:
TD18
Objectives
Background :
(including previous related studies)During the atmospheric entry or re-entry of flight vehicles, one critical
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issue is the dynamic stability of the vehicle in the transonic and supersonic regimes. Aerodynamic stability
is a function of the aero-shell shape. Static stability is highest in the hypersonic region and decreases with
decreasing Mach number. Since dynamic stability also decreases at lower speeds, space vehicles can
become unstable in the low supersonic to subsonic flight regime. This situation often requires the solution
of parachute deployment in the supersonic regime avoiding any risk of loss of the vehicle. Deploying a
parachute at supersonic speeds requires a much more robust parachute design and a highly performant
deployment system. The additional robustness requirement for the deployment system and parachute
design leads to additional mass requirements for the system. If the dynamic stability of a vehicle can be
determined accurately through ground testing, some of the constraints on the parachute deployment
system could be relaxed.
Measurements of static stability parameters are routinely performed in wind tunnels in all speed regimes.
In contrast, measurement of dynamic stability parameters, the so-called dynamic derivatives, is not a
well-developed capability in Europe.
In fact, there are only a few facilities capable of measuring the dynamic stability of flight vehicle
configurations over limited flight environment conditions.
Two types of facilities have been used for this type of testing in the past:
1) free-flight ballistics range and
2) free-to-tumble/forced-oscillation configurations in transonic / supersonic wind tunnels.
In the past ESA studied dynamic derivatives for ballistic configurations such as EXPERT and Huygens in
respectively facilities at VKI (S1) and at FOI (T1500 and S4).
The present TRP addresses not the ballistic planetary shape like configurations rather focuses on CSTS
and IXV shapes exhibiting large angle of attacks in the transonic domain.
These lifting body configurations, having a quite large base area and a limited number of control surfaces,
perform an autonomous flight in the supersonic-transonic regimes with an angle of attack larger than 45°.
For GNC the static and dynamic aerodynamic coefficients are required.
With a re-entry vehicle flying at high angle of attack in supersonic-transonic speeds, the knowledge of the
dynamic derivatives become more and more significant.
Considering that for the above configurations of interest(CTST, IXV) , no data are available in the
literature, it is proposed through the present TRP to define a working plan to improve the tools ( CFD,
WTT) for the prediction of the dynamic derivatives
Objectives of the study and expected results :The objectives of the present study is to improve the
dynamic derivatives characterisation and in particular the pitch damping for CSTS and IXV type of
configurations exhibiting large angles of attach in the transonic domain.
The tools to be improved are both the experimental techniques as well as the numerically unsteady tools
addressing mainly Reynolds effects required for flight extrapolation and in situ windtunnel sting support
influences.
For high angle of attack application, the dynamic derivatives are found to depend strongly on non-linear
effects induced by flow field separation, vortex breakdown, wake flow dynamics etc and cannot be
predicted properly by means of presently used empirical methods.
It is well known that flow separation is dependent on Reynolds number, thus one of the key points of this
study will be to reproduce as close as possible the flight Reynolds number.
Basically, the damping derivatives of interest are as follow : Cmq, Cnr, Clp, Cnp, Clr .Through the present
TRP, a deep analysis will be performed with emphasis on the Cmq.i.e. the pitch damping.
Description
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The contractor shall address the following activities :
Review of existing European wind tunnel capabilities and numerical expertise associated with transonic dynamic
derivative assessment for high angle of attack blunt body configurations.
Selection of 2 configurations: e.g. one associated with the latest CSTS shape and one using an existing IXV model
Selection of windtunnels ( blow down, continuous or ballistic ) and sting support technique ( base sting, free to tumble,
magnetic suspension..)
Performance of test campaigns, post-processing of the time histories and numerical rebuilding activities.
Analysis data, uncertainty assessment and flight extrapolation. The numerical results will be assessed with emphasis
on the sensitivity of the main parameters involved in the damping derivatives like computational strategy effect,
turbulent modelling effect, mesh effect, post-processing of the time history employed, etc
Synthesis to be carried out, highlighting the main lessons learned and drawing recommendations for further activities.
Deliverables:
Technical Notes
Test Articles
Test Data
TRL 3
Current TRL:
TRL 2
Application/Mission:
All re-entry and entry vehicles
(Mission Date: 2017)
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-7904
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
For TRL5: 2012
24 months
N/A
TRP Reference:
T417-025MP
TD:
TD18
Title:
Development of an innovative validation strategy of gas-surface interaction
modelling for re-entry applications.
Objectives
Background :
(including previous related studies)Various modeling tools have been developed in the past decades
within Europe to address the gas-surface interaction phenomena occurring at the interface between
Thermal Protection System (TPS) materials and the aerodynamic flowfield in re-entry conditions. The
practical interest in the thorough understanding and control of these phenomena (such as catalysis and
oxidation) is associated to their impact on the design and sizing of the TPS.
In fact, considering for instance catalysis, it is well known that the catalytic reactions occurring at the
interface between the flowfield and the solid domain are exothermic, thus lead to an increase of the heat
flux and consequently of the thermal load which the TPS has to sustain.
A detailed understanding of the catalytic mechanisms and a full confidence on the associated modeling
tools would enable the precise determination of the induced thermal loads and the optimal sizing of the
TPS, avoiding excessive margins which would translate into additional vehicle mass.
The aerothermodynamic community has been striving in the past years to understand on one hand the
basic physics driving the gas-surface interaction phenomena and on the other to collect ready-to-use
information for project applications; various models (ranging from state-to-state basic model to
semi-empirical curve fitting tools) have been developed or are still being consolidated, but so far none of
them has undergone an extensive and successful validation campaign to prove its suitability and reliability
for project applications.
Indeed, the experimental activities have demonstrated that the collection of data on gas surface
interaction phenomena is an extremely difficult task due to the severe environmental conditions in which
the phenomena take place, the location at which the measure should be taken (interface between two
domains) and the need of a high enthalpy but pure flow field to avoid any pollution. Only the development
of an innovative testing strategy could enable the overcoming of these difficulties; the strategy should be
based on innovative test set-ups, advanced measurement techniques and potentially technologies
transferred from different domains.
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In the last years, Europe has matured an improved knowledge of the ground facilities performances and
on the use of conventional measurement techniques and has benefited form the cross-fertilization among
different research institutes and fields of expertise, creating the necessary background to develop an
innovative validation strategy for gas surface interaction tools, with the aim of gaining the sought
confidence and to serve at best re-entry project applications.
Objectives of the study and expected results :The objective of the proposed activity is to develop an
innovative validation strategy of gas-surface interaction modelling, on the basis of the theoretical,
numerical and experimental work carried out during the past decades and exploring possible synergies
with technologies developed for different applications for test purposes.
The activity shall result in the validation of the gas-surface interaction modelling tools through the
definition of an innovative test approach (including test set-up and test conditions modulation), the
identification of the most suitable measurement techniques (conventional and/or innovative) and the
selection of the test cases.
Description
The proposed activity shall include the following tasks:
Identification of the gas-surface interaction phenomena of interest for re-entry application including as a minimum
catalysis and oxidation for ceramic and metallic Thermal Protection System in typical re-entry ranges.
Extensive survey of the currently available modelling approaches for the selected phenomena, classification and
selection. After having established a number of modelling categories, the Contractor shall provide an exhaustive
description of each modelling approach highlighting in particular the underlying physical rationale, the driving
parameters, the targeted applications and the potential weak areas. The Contractor shall moreover propose a set of
modelling approaches for further validation to be approved by the Agency.
Extensive survey and classification of the gas-surface interaction experimental on-ground activities carried out in the
last decades. For each test category, the Contractor shall detail the test philosophy and objectives, the underlying
assumptions, the test facility’s advantages and limitations, the test article features and the selected measurement
techniques with associated impact on the test results.
Definition of the innovative validation strategy. Based on the outcome of the previous tasks and on the exploration of
measurement technologies developed for domains other than re-entry, the Contractor shall propose an innovative
modelling approach for gas-surface interaction modelling, specifying the test objectives, the test procedure (including
test article and set-up), the associated measurement techniques and the test cases definition philosophy.
The Contractor shall be able to prove the innovation and at the same time the engineering consistency of the
proposed validation approach for the Agency approval. Ideally the Contractor shall also be able to establish a link a
priori between the proposed approach and the reviewed experimental results for post test elaboration. In case in-flight
data are available for validation purposes the Contractor shall ensure that the validation strategy adequately accounts
for them.
Validation Campaign preparation, execution, discussion of the results. The Contractor shall prepare the experimental
activity as per agreed validation plan, execute the tests and discuss the results addressing in particular the
achievement of the validation objectives. This phase shall include all the necessary rebuilding activities.
Conclusion and recommendations. The Contractor shall conclude on the suitability of the adopted validation approach
and on the validation status of the selected gas-surface interaction tools for the Agency approval.
Deliverables:
Technical Notes
Test Article
Test Data
TRL 5
Current TRL:
TRL 3
Application/Mission:
All re-entry and entry vehicles
(Mission Date: 2017)
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-7898
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
For TRL5: 2012
24 months
Consistent (B26)
TRP Reference:
T417-026MP
TD:
Title:
Definition and validation of transfer functions for intrusive measurement
techniques in re-entry and entry environments
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Objectives
The objectives of the proposed TRP activity are:
• To define (for a set of intrusive measurement techniques in entry and re-entry applications) a generic
transfer function formulation embedding dedicated “application-dependent” parameters to account for
material and integration techniques properties.
• To validate this approach through dedicated basic experiments on adequately selected material/sensor
combinations (e.g. thermocouples/heat flux sensors and ablative/metallic/ceramic materials) enabling in
addition the set-up of an engineering database for the “application-dependent” parameters.
• To draw conclusions on the impact of “application-dependent” parameters on the experimental results
and to issue recommendations on engineering practices to mitigate this impact.
Description
Among the intrusive measurement techniques for in-flight experimentation in entry vehicles, classical instruments such
as thermocouples of various type and heat flux sensors are extensively used. They are easy to procure and relatively
cheap, but it has been recognised that they could fail to provide accurate aerothermodynamic data unless an
extensive characterization activity of their transfer functions is carried out prior to in-flight experimentation.
It is to be noted that each sensor reading available to the experimenters for post-test rebuilding activities is only the
final output of a measurement chain significantly affected by the properties of the material on which the sensor is
integrated, the adopted integration technique and obviously the characteristics of the sensor itself.
In specific cases such as thermocouples in pyrolizing ablative materials it has been seen in the U.S. that not only the
integration of sensor heads but also the layout of the whole sensor has an impact on the final sensor reading.
Although each Thermal Protection System material (ceramic, metallic, ablative) features different properties (thus
requiring different integration techniques), it is considered possible to identify for each sensor of interest (e.g.
thermocouples, heat flux sensors) a generic transfer function formulation containing within well confined parameters
the dependency onto materials and associated integration techniques.
A set of basic experiments on selected materials/sensors would allow to determine the quantitative impact of the
dependency parameters on the final sensor reading and to identify engineering ways to mitigate this impact. The
proposed TRP activity shall include:
A survey of the intrusive measurement techniques of interest (including as a minimum thermocouples and calorimeter
probes) for on-going and future re-entry and entry applications. The Contractor shall then down select a set of
intrusive measurement techniques and associate to each of them (in a database format) the typical application in
which it is used, the type of material on which it is integrated and the most frequently applied integration techniques.
The Contractor shall detail as well the environmental constraint that each equipment can survive and the parameters
driving the measurement accuracy.
• Definition of the generic transfer function formulation. For each selected measurement technique the Contractor shall
study and define a suitable generic transfer function in which the “application-dependent” quantities are isolated by the
independent parameters; the Contractor shall dedicate significant effort to the modelling of these
application-dependant parameters, identifying the most suitable mathematical structure to describe further
sub-dependencies (e.g. on the material, on the integration technique on the sensor layout, etc.) in view of dedicated
basic experiments to be carried out later in the course of the activity.
• Preparation and execution of the transfer functions validation phase. On the basis of the outcome of the previous
task, the Contractor shall establish a validation approach for the transfer functions, preparing for each measurement
technique a test matrix covering adequately different material categories, integration techniques, measurement ranges
and test duration. Following the Agency approval the Contractor shall carry out at suitable premises the agreed
experimental activities, shall report the obtained results in a database format and shall analyse the data vis-à-vis the
validation objectives. In case available experimental data could serve the validation purposes, the Contractor shall
include them in the validation plan.
• Post-test assessment. The Contractor shall correlate the obtained experimental data with the mathematical
formulation of the transfer functions and in particular of the “application-dependent” parameters and shall complete the
engineering database accordingly. On the basis of the correlation, the Contractor shall assess the achievement of the
validation objectives and establish the quantitative impact of the “application-dependent” parameters on the
measurement output.
• Conclusions and recommendations. As a final task the Contractor shall conclude on the work carried out and shall
issue recommendations for engineering best practice in the integration of intrusive measurement techniques.
Relevance / Applications: Intrusive measurement techniques could fail to provide accurate aerothermodynamic data
unless an extensive modelling and characterization activity of their transfer functions is carried out prior to in-flight
experimentation; the general approach developed within this activity provides sufficient flexibility in the transfer
function modelling to adapt to different applications such as re-entry and entry vehicles instrumented thermal
protection systems but also future launch vehicles components operating in severe environments.
Moreover, the set of basic experiments carried out within the present activity could serve as an engineering database
for the abovementioned project applications.
Deliverables:
Technical Notes
Test Articles
Test Data
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Current TRL:
TRL 2
Target TRL:
TRL 3
All re-entry and entry vehicles to
be instrumented with classical
sensors; future launch vehicles
Application/Mission:
components operating in severe
environments. (Mission Date:
2017)
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
For TRL5: 2012
18 months
Dossier0 Ref.: T-7903
Consistent (B27)
TRP Reference:
T418-027MP
TD:
TD18
Title:
Aerodynamics of down load systems: parachutes
Objectives
The present TRP will enhance the PADSA capabilities by augmenting its data base with new windtunnel
experiments simulating as a priority supersonic deployment scenario’s. The experiments will be performed
taking into account past experimentation, lessons learned and focus on the upcoming DLS agency needs.
These basic experiments will be used to update PASDA for the supersonic DLS design and analysis.
Priority shall be put on improvements associated with supersonic deployment. This new experimental data
base shall be used to enhance the Agency PASDA tool.
Description
The performance of Down Load Systems (DLS) especially the deployment of supersonic parachutes have recently
shown to be inadequately mastered (lessons learned Genesis). Note that even subsonic deployment is still today
without risk (lessons learned USV). The expertise on supersonic parachute deployment resides mainly (with the
exception for Huygens ) in Russia and in the US. The Agency invested in the past in the PASDA tool development;
PASDA stands for Parachute System Analysis and Design tool and contains mainly engineering routines for subsonic
parachute operation and deployment. It was used for post flight analysis of the ARD
The contractor shall perform the following activities :
- Review state of the art in parachute design and analysis and address the limitations and short coming of the Agency
PASDA tool especially for the supersonic regime.
- Propose experimental strategy taking into account agency needs, select appropriate wind tunnel models for transand supersonic windtunnel testing.
- Improve PASDA tool by enhancing engineering routines for supersonic DLS deployment and perform validation
exercise using present new experimental data base.
- Apply updated tool to some agency defined test cases such as e.g. EXPERT and Huygens.
- Provide synthesis and recommendations to expand PASDA tool to include other type of decelerators such as
ballutes, inflatable systems or other types of drag chutes.
Deliverables:
Wind tunnel test data, CFD Solutions, Technical notes,
Test Articles, Test Data, updated PASDA
Current TRL:
TRL 2
Target TRL:
TRL 3
All earth reentry vehicles,
Application/Mission: planetary probes (Mission Date:
2017)
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
For TRL5: 2012
24 months
Dossier0 Ref.: T-7906
Consistent (Add 3)
TRP Reference:
T418-028MP
TD:
TD19
Title:
Extra light nozzle extension for upper stage engine and in space propulsion
Objectives
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Existing European technology currently employ a 3D multi-weave fabric called GuipexÒ, which thickness
range can be as low as 0.8 mm for different C-SiC applications in operation or in development.
This material is applied on aeronautic engines components or thermal protection systems (IXV windward
TPS). It is therefore a promising technology to use in the design of even lighter nozzle extensions. A proof
of concept C-C nozzle has been manufactured to check the capability of GuipexÒ to design large bell
shape components (diameter: inlet 0.4 m, outlet 1.1 m, Length 1.1m, wall thickness 1.5 mm) and resulted
in a 6.2 kg weight of the component, representing more than 30% mass saving compared to the same part
that if it had been made with RL10 B-2 technology.
The objective of the activity is mature the technology from the current TRL2 to TRL3 before it can be
considered for such technology demonstration programs such as FLPP.
Description
One of the design criteria for upper stage propulsion and in-space propulsion is the reduction of the mass of
components whilst achieving high performance.
Generally for rocket engines very high nozzle expansion ratio’s are required to achieve high Isp’s . Therefore this
study is to evaluate the potential advantages of developing such an extra-light weight nozzle extension and to bring
the technology to a level of maturity such that it can be considered for future launch vehicle programs.
The current state of the art is the RL10 B-2 C-C NE ( RL10 B-2 engine Carbon-Carbon Nozzle Extension). This has
proven to be very efficient and the right solution to that extent thanks to the high temperature resistance and low
density of Carbon-Carbon.
However, the 3D technology currently utilized in the design of such very large nozzle extensions has a limitation of a
minimum 2.3 mm wall thickness which limits the weight reduction potential for future projects.
Threfore, the proposed activity is as follows:
• Perform an assessment / trade-off of potential applications of the extra-light weight nozzle.
• Define a generic nozzle extension with relevant singular areas such as attachment flange, integrated stiffener, aft
stiffener, wall construction and wall thickness (use of existing tooling to concentrate the effort on the technology only)
• Manufacture one generic extra light Carbon-Carbon nozzle
• Material characterization on coupons from part or plates
• Perform preliminary margin evaluation for generic sizing loads
Investigate potential application and full scale demo firing testing options for next technology maturation phase
(TRL3/4 – TRL7)
Deliverables:
Extra-light weight nozzle hardware, design and development data package as output of activity.
Current TRL:
TRL 2
Target TRL:
TRL 3
Application
Need/Date:
Application/Mission: All launchers (Mission Date: 2020) Contract Duration:
N/A
SW Clause :
Dossier0 Ref.: T-472
Consistency with Harmonisation
Roadmap and Conclusions:
For TRL5: 2014
12 months
N/A
TRP Reference:
T418-029MP
TD:
TD19
Title:
Battleship chamber for unsteady combustion process analysis
Objectives
The proposed study aims at studying the feasibility, designing, manufacturing and operating of a simplified
test rig, in the form of a battleship combustion chamber, to provide relevant test cases for the tuning of the
predictive models.
At the same time, this test facility could provide an excellent test bed for assessing, even with empirical
methods, devices or design features likely to damp or even eliminate the non desirable phenomena
(dampers, specific injection features,…)
Description
The problem of combustion instabilities, Low Frequency or High Frequency, has always been a major hazard in the
development of launcher or spacecraft engines. There is currently no other way than extensive and consequently
expensive testing to verify that the design is on the safe side. Moreover, the conservatory measures to mitigate the
risk are costly in terms of engine performance (high delta Pressure of the injector and consequently increased
turbopumps power requirements, etc,…). The current design and validation tools are essentially empirical and the
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recovery actions in case of problems often palliative (treating the effects and not the causes).
On the field of High Frequency combustion instabilities, specific studies, including also ESTEC, have been triggered
by the accident of the Aestus Ariane 5 third stage engine, during flight 510, but it was never possible to fully
understand and describe the chain of events leading to the failure.The efforts aiming at improving the capacities to
design more robust engines, taking those phenomena into account, are hindered by the absence of tools due in part
to the lack of basic validation experiments.
The activity will start with a comprehensive literature survey of the existing background and worldwide. Then a
preliminary study will be initiated and the main parameters traded off. The following list gives an example of the main
open choices:
• propellant combination
• size and shape of the chamber
• Conceptual study of the devices used to adapt the sensitivity to instabilities (volume of injection domes, pressure
losses,…)
• possible excitation devices
• instrumentation needs
The design should be driven by the goal to maximize the chances to encounter instabilities but also by possibilities to
counter them.
Then the detailed design should be performed and the material manufactured.
Eventually, the tests facility will be commissioned with the first run in tests.
After, the test bench and articles will be available for subsequent validation tests cases performance.
Deliverables:
Literature survey
Feasibility and Preliminary design File.
Detailed design
Bench Commissioning Tests report
TRL 3
Current TRL:
TRL 1
Application/Mission:
All launchers with liquid propulsion
Contract Duration:
(Mission Date: 2020)
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
For TRL5: 2014
24 months
Dossier0 Ref.: T-7899
N/A
TRP Reference:
T418-030MP
Title:
Innovative PED bladder technology
TD:
TD19
Objectives
To demonstrate feasibility an innovative propellant expulsion device (PED) concept compatible with
hydrazine and nitrogen tetroxide propellants and suitable for demanding mission requirements such as LV
upper stage bi-propellant storable propulsion systems, Small-medium Bi-propellant spacecraft, Space
exploration missions, Orbit transfer vehicles.
The activities shall focus on PED technologies including selection of base materials, functional and
environmental testing and manufacturing at material sample level.
Description
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Description of Activities
In the area of satellite applications, European Industry accumulated appreciable experience in the development of
bi-propellant compatible diaphragm materials for propellant tanks. Material formulation and manufacturing
technologies were investigated and initial works performed on diaphragm design and manufacturing.
All the activities shall be addressed to the identification of suitable material and its development testing to verify its
usability on a wide range of space missions.
To this end, the following main tasks shall be carried out:
Task1: definition of high level requirements
Task2: survey of candidate materials
Task3: sample candidate material manufacturing
Task4: laboratory level testing of candidate materials
Task5: material trades and selection, assessment of space mission applicability
Task6: definition of material development test specification
Task7: material development test program
Task8: preliminary manufacturing plan at diaphragm/bladder level
Deliverables:
Documentation relevant to the identified tasks.
Candidate materials formulation, chemical composition, compounds chemical characteristics and procurement frame
and any other details necessary to allow material technology transfer were needed.
Material manufacturing file including main manufacturing process steps and specifications.
Current TRL:
TRL 1
Target TRL:
TRL 3
LV upper stage bi-propellant
storable propulsion systems,
Application/Mission: Small-medium Bi-propellant
spacecraft, Space exploration
missions, Orbit transfer vehicles.
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
For TRL5: 2014
12 months
Dossier0 Ref.: no ref.
Consistent
TRP Reference:
T420-031MC
TD:
TD21
Title:
Material characterization of European ODS material candidate, Kanthal APMT, for
application in metallic TPS
Objectives
To produce ODS sheet and foil from Kanthal APMT and characterize material properties relevant to
application in metallic TPS.
Description
Metallic TPS is being studied in the context of the FLPP-1 M&S activities by Dutch Space. The driving requirements
initially led to ODS materials from Plansee, PM1000 and PM2000, being identified as baseline for the tile
demonstrator. However, with the withdrawal by Plansee from the space business, a search for another supplier was
started, because only an ODS material is foreseen to be capable of repeated cycling to peak temperature levels.
While Kanthal APMT was identified as an option, further study is required to confirm its suitability, especially it has to
be verified that it can be produced in a form which can be used for the tile, while retaining the desired characteristics.
The driving requirements for metallic TPS and the analysis of the requirements by Dutch Space is included in:
TPS Tile Technology Development Based on ODS Material Architecture Concept, Trade-off and Design Report,
M&S-DS-TR-006
A first evaluation of Kanthal APMT is included in:
Roadmap for development of metallic TPS tiles using super-alloys as alternative to ODS materials, M&S-DS-ME-004
It concludes that presently too little is known about Kanthal APMT and that super-alloys will be used for IXV metallic
TPS, as replacement for PM1000 and PM2000. The TRP activity has the objective to fill the gaps in the
characterization of Kanthal APMT and identify the route to raise the technology maturity level to make it a competitive
choice in a post-IXV perspective, offering the advantages of ODS material for high-temperature applications.
The activity will include:
• To establish the manufacturing route of Kanthal APMT sheet material (0.25 and 0.5 mm thick) and foil (0.075 mm
thick) and identify any associated limitations (e.g. size, thickness, heat treatment or grain-size)
• To produce TBD samples of Kanthal APMT sheet material
• To define a test plan to perform material characterization (e.g. elasticity, yield strength, creep, tensile strength and
thermo-physical properties), collecting necessary data to evaluate the suitability of Kanthal APMT for use in metallic
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Description of Activities
TPS, i.e. over the temperature range from RT to 1400 deg C.
• To perform testing according to test plan
• To compile a test report, including conclusions on the potential for improvement of the material characteristics by
adaptation of the manufacturing route.
Deliverables:
Tested samples plus a corresponding set of reference samples, test reports, Final report
TRL 4
Current TRL:
TRL 2
Application/Mission:
All entry vehicles (Mission Date:
2017)
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-575
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
For TRL5: 2012
9 months
N/A
TRP Reference:
T420-032MC
TD:
TD21
Title:
Development of lightweight flight sensors and measurement techniques for
planetary entry probes and vehicles
Objectives
To develop measurement techniques and relevant lightweight sensors to assess the interaction between
aerothermodynamic flow and the response of the TPS. This shall include as a minimum the following
parameters: temperature, pressure, heat flux, erosion, gas composition.
Description
The heatshield represents an essential component of any planetary entry probe or vehicle, and can consume a
considerable fraction of the available probe/vehicle mass. The sizing of the thermal protection system involves rather
large margins stemming from the uncertainties in deriving the heat fluxes and the interaction between the
aerothermodynamics and the response behavior of the TPS. Reducing these uncertainties requires in-flight data from
previous missions. Unfortunately, such data is very limited since the heatshield instrumentation is usually either
omitted or extremely reduced due to the strict mass limitations. It is therefore essential to develop lightweight
techniques and sensors to assess the interaction between the aerothermodynamic flow and the TPS.
During the course of the activity following tasks shall be performed:
• Review of existing sensors and assessment of mass reduction potential
• Investigation of alternative measurement techniques and concepts
• Screening and trade-off
• Iterative design development
• Breadboard design, manufacturing and test
Deliverables:
Concept description and trade-off, development and test reports, breadboards and demonstration samples
Current TRL:
TRL 2
Target TRL:
TRL 4
Application
Need/Date:
Planetary exploration missions e.g
Application/Mission: MRS, CSTS, RLV / IXV (Mission
Contract Duration:
Date: 2020)
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
For TRL5: 2014
18 months
Dossier0 Ref.: T-8282
N/A
TRP Reference:
T420-033MC
Title:
Zero Boil Off propulsion system feasibility demonstration
TD:
TD21
Objectives
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Description of Activities
The aim of this activity is to analyse the applicability of ZBO concepts to both space transportation and
exploration missions. To reach this goal propulsion and system analysis will provide design and
technology needs based on a number of identified mission typologies. On the above grounds, capability of
long term cryogens storage and management without cryogens losses will be demonstrated and impacts
on cryogenic propulsion system design aspects evaluated.
Description
The idea of this activity is to realise a design where the heat losses of a cryogenic storage tank are compensated by
the cooling power produced with an active cooling system. In practice, especially for large tanks, there is always a
non-avoidable heat input into the cryogens which needs conditioning of the cryogens to avoid creation of large
temperature gradients.
To study this issue and define a baseline for the ZBO, the following tasks are foreseen:
• Task1: Identification and specification of mission typology in relation to ZBO aspects. In particular: analysis of
mission duration boundaries in relation to ZBO needs, assessment of propulsion and system impacts on upper stage
and interplanetary missions.
• Task2: Definition of main functional and design propulsion requirements for upper stage and interplanetary missions.
• Task3: flow down of propulsion specifications at tank and thermal control hardware to define ZBO requirements.
• Task4: architectural studies of tankage and thermal control hardware for different cryogenic propellants (O2, H2,
Cryogenic Hydrocarbons); identification of critical aspects regarding propulsion functionality and thermal control.
• Task 5: Establishment of a thermal and fluid dynamic model of the whole propulsion system including engine,
tankage and thermal control hardware representative of the different mission phases identified.
• Task6: Scaling down of the cryogenic tank design to a representative breadboard for testing using LN2.
• Task7: Manufacturing of breadboard, testing and correlation with thermal and fluid dynamic models.
• Task8: Updating of mathematical models for large tanks for different propellants.
• Task9: Preparation of technology development roadmap including analyses of flight experimentation at breadboard
level.
Deliverables:
ZBO mission needs, conceptual design report of ZBO propulsion system architecture, thermal and fluid dynamic
model for mission representative and breadboard versions of the propulsion system including correlation with test
results, breadboard model design report, breadboard model test results, breadboard hardware.
Current TRL:
TRL 1
Target TRL:
Application/Mission: (Mission Date: 2020)
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
For TRL5: 2014
24 months
Dossier0 Ref.: T-8275
Consistent
5 - Telecommunications
5 - Telecommunications
TRP Reference:
03/ETM-001
TD:
Title:
SAW Filter Development
TD06
Objectives
The objective of this activity (CCN) is to continue the original SAW filter development by extending the
device working frequency and test it on a breadboard.
Description
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Description of Activities
Surface Accoustic Wave (SAW) quartz resonators are often used in Voltage Controlled Oscillator (VCO) with
demanding phase noise requirements. However, the use of SAW resonator based VCOs (SAWR-VCO) has so far
mainly been limited to frequencies below 1 GHz for very high Q (Quality factor) applications. The use of SAW
resonators at higher frequencies and on other materials has been demonstrated in the MATOPS program for the use
in low-loss impedance element filters (IEF). For both SAW-IEF and SAWR-VCO the main goal in design of the
resonators is to achieve high resonator Q-values (and therefore low energy dissipation per cycle).
In 2006 an activity was started aiming at investigating and improving SAW resonator technology for use in VCOs in
the 1-2.5 GHz range. The expected space applications of low-phase noise VCOs are in navigation and communication
systems operating in this frequency range. The results are applicable for narrowband low-loss filters and SAW notch
filters.
The new CCN shall aim at extending the working frequency of the developed resonator device and test it on a
breadboard including a LO (Local Oscillator). The breadboarding shall include design, development and testing.
Deliverables:
Breadboard
TRL 4
Current TRL:
TRL 2-TRL 3
Application/Mission:
Navigation and communication
systems
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: -
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
TRL5 >2012
18 months
-
TRP Reference:
T504-001EE
Title:
Slot Region radiation environment
TD:
TD04
Objectives
Investigate radiation environment at the altitude range of future low and medium altitude constellations
where environment is harsh but poorly characterised
Description
The altitudes of future telecom constellations is characterised by the outer edge of the proton radiation belt and the
variable "slot" region . As seen by Globalstar, where many anomalies are attributed to the environment, this
environment can be extremely problematic. The proton environment gives rise to many degradation and single event
effects not encountered at GEO and the electron environment can be harsh and dynamic, giving rise to internal
charging and high doses. Models of the environment specific to these regions will be developed allowing these effects
to be analysed efficiently.
Deliverables:
Calculation models and tools.
TRL 3
Current TRL:
TRL 1
Application/Mission:
Low-medium altitude comms
constellations (>2010)
Contract Duration:
SW Clause :
Operational SW
Dossier0 Ref.: T-9
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
Study
results
applicable by 2010
24 months
N/A
TRP Reference:
T506-002ET
TD:
TD06
Title:
Modelling and Design of Optimized Waveguide Components utilizing 3D
Manufacturing Techniques
Objectives
Objective is the analysis, EM modelling and demonstration of novel waveguide resonator and iris
geometries using sophisticated shaping strategies to achieve cost-competitive high performance
waveguide filters with up to 30% reduced dissipation losses.
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Description of Activities
Description
3D manufacturing techniques such as selective laser melting offers new freedom for the RF-designer to employ
optimised geometries to improve RF performance without significant impact on production cost.
In this activity optimum resonator and iris shapes shall be developed and investigated. For this purpose dedicated
highly efficient EM software shall be developed for accurate and fast computation of the losses of the optimum
resonator and coupling apertures. A Ku-band OMUX channel filter with optimum resonator and coupling aperture shall
be designed, modelled and analysed to demonstrate the RF performance improvements achievable. The resonator
and iris shapes investigated shall be realisable without the constraints of conventional milling techniques but adapted
to 3D manufacturing techniques. Electrical, mechanical and thermal performance as well as production costs including
prototyping, assembly and tuning shall be evaluated in detail and compared to standard designs using conventionally
employed manufacturing techniques. The predicted RF performance improvements of the optimized resonators and
coupling structures shall be verified on Ku-band demonstrators.
MOTIVATION:
3D manufacturing techniques are very cost competitive but also provide new freedom for the RF designer. Very
complex geometries can be fabricated without much impact on cost. Furthermore significant cost savings can be
expected since separately assembled components with mechanical and thermal functions are now integral part of the
hardware. With this approach of single part hardware, the number of contact interfaces is minimized resulting in
improved Q and PIM. In addition advanced resonator geometries and iris shapes for further Q improvements can now
be realised and cumulative Q improvements of up to 30% can be expected.
Deliverables:
Efficient and accurate software capable to analyse a 3D waveguide filters with advanced geometries including the
accurate modelling of losses;
Breadboards of optimum shaped Ku-band resonators and coupling structures to demonstrate achievable RF
performance improvements;
Current TRL:
TRL 1
Target TRL:
Application/Mission: All missions (>2017)
Operational SW
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
TRL5 by 2014
24 months
Dossier0 Ref.: T-7929, T-7909
Consistent
TRP Reference:
T506-003ET
TD:
TD06
Title:
Study of high order modes and fringing fields in Multipactor effect
Objectives
The aim of this activity is the study of RF breakdown (Multipactor effect) in large gaps where high order
modes and fringing fields are considered. The product Frequency-gap is directly linked to high power RF
hardware with large gaps (OMUX, Filters, OMT, antennas, etc …) and future high frequency applications.
It is expected that many telecommunication components can enhance their power capabilities by
addressing the Multipactor effect considering these two effects.
Description
The product Frequency-gap is an important parameter to predict Multipactor effect. The RF breakdown threshold can
be calculated from this ratio in easy geometries. However, the model fails when the gap is large and the travelling
electrons change direction several times before they collide with the inner walls of the waveguide due to the change in
polarity of the RF electric field.Thus, in irises and corrugated elements, the Multipactor parallel-plate approach is valid
only for a certain range of gap width to gap length ratios (up to 1). For larger ratios the voltage necessary to induce
multipactor increases significantly. If the ratio gap width to gap length is increased, more electrons tend to accelerate
along curved paths rather than along the straight-line path between the walls. The resonance condition within the gap
is no longer valid. The longer effective path length shifts the operating location to larger values of the f x d product.
Higher field gradients across the gap are thus necessary as the multipactor diagram shows. Furthermore, many of the
electrons are accelerated in a direction completely away from the gap region and are no longer available for the
breakdown. It is expected that for gap width-length ratios between 1.2 and 6, there is an exponential function of the
voltage increase factor and gap width-length ratio, leading to dramatic power increase factors between 4 and 49. This
activity will investigate the importance fxd product (gap height and high frequencies) in the prediction of Multipactor
effect and the effect of the fringing fields in the threshold.
Deliverables:
Any hardware produced: test samples with irises.
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Description of Activities
Current TRL:
TRL 1
Target TRL:
Application/Mission: All missions (>2010)
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
Study
results
applicable by 2009
24 months
Dossier0 Ref.: T-7929, T-7909, T-7919
Consistent with "RF Power measuring and modelling"
(TEC-ETM/2007.30/DRG/drg, Activity 3B2)
TRP Reference:
T506-004ET
TD:
TD06
Title:
Widely-tunable MEMS LC tank for Wideband Oscillators
Objectives
The objectives are to develop, manufacture, and test a MEMS LC tank featuring a wide tunability while
maintaining a stable Q-factor.
Description
There is a need for Local Oscillator with a large tuning range. However, in practise, resonators with large tunability
tend to offer degraded performance due to the decrease of the Q-factor with tuning. This translates into degraded
phase noise of the LO. The MEMS LC tank is a resonator which can have a large tuning range while maintaining a
fairly high Q-factor.
In a first phase, after reviewing state of the art achievements in the field and assessing all applications where a
wideband oscillator is of prime interest, MEMS varactor with large capacitance control as well as MEMS inductance
with high resonant frequency shall be investigated. In a second phase, those two element shall be integrated into a
single MEMS tank circuit which shall then be evaluated in an oscillator with a wide tuning range.
Deliverables:
Breadboard of wideband oscillator.
Current TRL:
TRL 2
Target TRL:
Application/Mission: All missions (>2015)
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 4
Application
Need/Date:
Contract Duration:
Dossier0 Ref.:
TRL5 by 2011
24 months
T-7928, T-7918, T-7908,
T-7746
Consistent (MEMS Component Technology Board (CTB) Dossier)
TRP Reference:
T506-005ET
TD:
TD06
Title:
High-Q MEMS resonator for high-performance oscillators
Objectives
Develop, manufacture, and test MEMS based mechanical resonators; to highly improve degree of
integration, reduce of cost, mass and size of payload.
Description
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Description of Activities
Laboratory demonstrations have shown that MEMS resonators may become an interesting alternative to crystal
resonators both in oscillators and filters. Already today, very high Q-values comparable to those of good crystal
resonators have been demonstrated for the MEMS resonators. Important advantages of the MEMS resonators are
foreseen in their extremely small size and integration compatibility with silicon process. In comparison to crystal
resonator, cost reduction is expected at lower frequencies (from 10 MHz) whereas better performance is expected at
higher frequencies (from 100 MHz). One more important aspect is that the MEMS fundamental mode frequency can
be much higher than that of the crystal. Demonstrations have been done (mostly US) for devices from 10 MHz to 500
MHz. However, it is evident that technological challenges remain in several areas, such as temperature
compensation, packaging, long term stability, and phase noise.
The activity aims at developing MEMS resonators, MEMS test structures for e.g. coupling characterisation, and RF
oscillator demonstrators. The design frequencies shall be selected in the 10 MHz to 500 MHz range and designs
optimised for the best achievable RF performance.
In the beginning of the activity, the available MEMS technologies and process shall be investigated and their
properties evaluated in the light of the MEMS resonator performance. Then, the MEMS resonators and the RF
oscillator shall be designed, manufactured and tested. The test shall address the critical parameters such as the
frequency stability, long term stability, phase noise, Q and resonator coupling properties.
The performance, size, and mass of the MEMS oscillators will be evaluated and compared with those of a crystal
oscillator.
Deliverables:
MEMS resonators, oscillator breadboards.
Current TRL:
TRL 2
Target TRL:
Application/Mission: All missions (>2015)
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 4
Application
Need/Date:
Contract Duration:
TRL5 by 2011
24 months
Dossier0 Ref.: T-7908, T-7928
Consistent
TRP Reference:
T506-006ET
TD:
Title:
Efficient Techniques for On-Board Processing
TD06
Objectives
The study shall review, analyse and assess efficient algorithms and processing techniques for improving
power consumption and integration (i.e. mass) efficiency of telecom OBPs.
Appropriate design and optimization methods shall be identified and tailored to comply with typical
payload performance specifications.
Description
Several architectures and algorithms have been recently introduced to decrease the computational burning of
elementary digital processing elements such as Finite Impulse Response (FIRs) filters and Fast Fourier Transforms
(FFTs). As well as new techniques allow reducing oversampling ratios in polyphase filter banks.
Jointly such techniques could prove themselves highly effective in reducing ( potentially up to 20-30%) the complexity
(ASICs area and Power) or in extending the performances (increased processed bandwidth and number of beams) of
On-Board Digital Processors for telecommunication satellite systems.
Full exploitation of these techniques requires a design flow change (from round-off of the ideal filter/BFN coefficients
to filter/BFN design based on constrained architecture and coefficients space). Typically the design is further
complicated by the combinatorial nature of the filter/BFN coefficient space (e.g. Sum-Of-Power-Of-Two - SOPOT,
Canonical-Signed-Digit - CSD, etc.) and requires the adoption of appropriate search and optimization methods.
Tasks to be carried out shall include:
• Standard arithmetic with reduced multiplication/addition complexity for filtering and beamforming (e.g. multiplier-less
SOPOT, CSD, etc.)
• Non-standard arithmetic for signal processing (e.g. residue number system – RNS et alii)
• “FFT-like” and reduced oversampling techniques in polyphase filter banks.
• Analysis and assessment of coefficient round-off and finite arithmetic errors
• Integrated design of Multi-Channel Demultiplexing and Beamforming based on constrained (for efficiency) digital
arithmetic.
• Pros and Cons assessment with respect to benchmarking OBP scenarios (narrowband and broadband).
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Description of Activities
Deliverables:
Reports, models and technology roadmap.
Current TRL:
TRL 1
Target TRL:
Application/Mission: All missions (>2014)
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
TRL5 by 2011
12 months
Dossier0 Ref.: T-7913
Consistent
TRP Reference:
T506-007ET
TD:
TD06
Title:
Reconfigurable multi-mission payload feasibility study
Objectives
To study the architecture of a reconfigurable payload with flexible allocation of resources ( bandwidth,
power, coverage) to different missions (i.e. broadcasting, multibeam access, high speed point to point,…)
during the life of the satellite. Reconfigurable payload building-blocks shall be identified and trade-offs on
the most suitable technologies carried out.
Description
Prior R&D work has demonstrated an important capacity gain (15%-20%) granted by flexible power and bandwidth
allocation in addition to a factor 2 spare in DC power in the case of a realistic unbalance traffic demand distribution
over the coverage in a multibeam payload application
In case multiple missions are hosted on board the same spacecraft, a high gain is expected by flexible and dynamic
sharing of power and frequency resources
This activity will study the architecture of a reconfigurable payload with flexible allocation of resources ( bandwidth,
power, coverage) to different missions (i.e. broadcasting, multibeam access, high speed point to point,…) during the
life of the satellite. Reconfigurable payload building-blocks will be identified and trade-offs on the most suitable
technologies carried out.
Deliverables:
Reports, models and technology roadmap.
Current TRL:
TRL 1
Target TRL:
Application/Mission: All missions (>2014)
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
TRL5 by 2011
12 months
Dossier0 Ref.: T-7746
Consistent
TRP Reference:
T506-008ET
TD:
TD06
Title:
Payload/system evaluation of beam hopping techniques
Objectives
• Definition, simulation and evaluation of an advanced Ka band multibeam payload using beam hopping
techniques.
• Identification of key equipment for further development under ARTES 5 programme.
Description
This activity will be focusing on payload aspects related to beam hopping will represent the follow up of an ongoing
ARTES 1 beam hopping system activity. Beam hopping represents an efficient solution to flexible resource allocation
in multi-beam networks that has large impacts on the space and ground systems.
The proposed activity shall continue this work with a detailed evaluation, simulation and evaluation of an advanced
payload implementing beam hopping tecniques.
In particular, different beam hopping payload architectures using advanced antenna and RF front end concepts (
DRA, FAFR, ….) and advanced technologies available in the near future ( high temperature electronics, GaN,
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Description of Activities
mini-TWTs, highly integrated BFNs, next generation digital processors using deep sub micron technology, optical
processors,…) shall be proposed. The payload performance will be compared to more conventional payloads.
After a first analysis and trade-off between the different options, payload computer models shall be generated for
simulation and assessment of the system performance obtained and perform a comparison with non beam hopping
payload solutions.
The payload models and payload/system simulations shall consider representative physical layers(i.e. modified
DVB-S2/RCS) , and shall include the effects of the main payload impairments ( i.e. non linear distortions,
interference,….)
As a result of this activity, a development plan shall be proposed for the breadboarding of the key building blocks of a
beam hopping payload .
Deliverables:
Beam hopping payload/system model and reports.
Current TRL:
TRL 1
Target TRL:
Application/Mission: All missions (>2015)
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
TRL5 by 2012
12 months
Dossier0 Ref.: T-7746
Consistent
TRP Reference:
T506-009ET
Title:
Benefits of the introduction of GaN technology on an L- band GEO mobile
payload
TD:
TD06
Objectives
The objective of this activity is the assessment of the benefits of the introduction of GaN SSPA technology
on an L band GEO mobile payload. With this purpose, a first basic iteration shall be done of the payload
architecture definition, preliminary design, accommodation and payload/system assessment of an
advanced INMARSAT XL payload using GaN SSPA technology, and compare the results with the current
implementation based on GaAs SSPA technology.
Description
The study aims to define a set of possible payload architectures to take advantage of GaN SSPA technology and
determine a preliminary sizing estimate and accommodation. The work is organized in to two tasks.
Task 1
INMARSAT shall be taken as a reference payload baseline with which to compare the new architectures. The
contractor shall begin by identifying potential payload architectures introducing GaN SSPA technology.
The following levels of architectural changes shall be considered;
1. Simple replacement of the current GaAs based SSPAs by GaN versions, possibly with higher RF output power
capabilities and with commandable bias point of the transistors to achieve extra RF power flexibility.
2. A MPA-less implementation, based on a set of redunded GaN SSPAs, with the implementation of power flexibllity
based on the combination of commandable SSPA bias to increase/decrease the output power capabilities of each
SSPA and the adjustment of input power at carrier level by BFN in the digital processor.
3. A solution MPA less, but without implementation of SSPA redundancy and the use of a “cold” redundancy approach
based on bias control and BFN carrier level control.
For each of the identified architectures, the full potentiality of GaN technology shall be identified and evaluated.
Further, for each of the proposed architectures, a methodology for the sizing and assessment of the payload shall be
proposed. At the first meeting at ESTEC three will be chosen for further study.
Task 2
For each of the three payload architectures identified at the end of Task 1, ASTRIUM will do a first iteration of payload
definition and preliminary sizing and accommodation. The objective of this exercise is the assessment and
quantification of the potential for improvement at payload/system level of the different identified GaN based payload
architectures. The work will be done according to the methodology agreed at the end of phase 1.
For each of the payload concepts, the following outputs will be provided and compared against the current
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Description of Activities
performance of INMARSAT XL payload.
• Payload architecture and block diagram
• RF budgets
• Payload capacity estimation
• Payload flexibility assessment
• Preliminary accommodation
• Mass and DC consumption/dissipation budgets
• Hardware matrix
• Estimation of comparative recurrent costs with current INMARSAT XL
• Conclusions and recommendations for future work
Deliverables:
D1: Payload architecture preselection (set of meeting power point slides). D2: Final Report
N/A
Current TRL:
Target TRL:
Application/Mission: L-Band Mobile Geo Payloads
N/A
SW Clause :
N/A
Application
Need/Date:
Contract Duration:
2009
6 months
Dossier0 Ref.:
Consistency with Harmonisation
Roadmap and Conclusions:
TRP Reference:
T507-009EE
TD:
TD07
Title:
RF MEMS based reconfigurable telecommunication dual reflector antenna
Objectives
The objective of this activity is to investigate the feasibility of using MEMS switches for programmable
contoured beams in Ku- and Ka-band dual-reflector telecom antennas.
Included in this activity are the following actions:
• Identification of possible telecom applications that may benefit from the use of MEMS-based
reflect-arrays
• Analysis of performance improvement that can be realised by using programmable MEMS controlled
reflect-array sub reflectors over traditional solution
• Design and critical bread boarding of representative MEMS-based reflect-array prototype
Description
Most commercial communication satellites today have a 15 to 18 years life time in orbit. This means that by adding the
duration of the system definition study, the coverage of the satellite antenna must be frozen around 20 years before
the end of the mission. It is obvious that during such a long period the traffic demand, e.g. multimedia, TV broadcast
or phone, evolve drastically.
Therefore, a very attractive solution for satellite operators is to have an antenna that is able to change its coverage in
flight. Of course the extra cost that is involved in such a solution should be reasonable. For this reason, it is proposed
in this study to perform the coverage reconfigurablity by modifying the sub-reflector characteristics while keeping
unchanged the lightweight main reflector technology.
To achieve the reconfigurability of the subreflector, this study will perform the design and develop a MEMS controlled
reflect-array. One of the critical issues of using MEMS switches is the reliability and the power handling, but it is
foreseen that for the typical applications referred to in this activity the power per MEMS element will not exceed 1-2 W.
Final performances will have to be demonstrated by test with a partial sub reflector demonstrator and analyses at
antenna level.
Deliverables:
Ku-band Subreflector Reflectarray breadboard with active RF MEMS.
TRL 3
Current TRL:
TRL 2
Application/Mission:
Fixed Satellite Services (FSS),
DBS missions (2015)
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-7907
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
TRL5 by 2012
18 months
Consistent- Array Antennas - 2005
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Description of Activities
TRP Reference:
T507-010EE
Title:
Self focussing retroreflective Tx Rx antennas for Mobile Terminal Applications
TD:
TD07
Objectives
The objective is to develop self-focusing terminal antennas for Mobile Applications
Description
To date, satisfactory designs that combine Tx/Rx function, low profile and low cost are not available. Low profile
designs exist based on array technology (patch or waveguide), with a combination of electrical and mechanical
scanning in elevation and azimuth respectively, but these do not have a sufficiently low cost potential so as to enable
mass market appeal. Low cost products based on reflector technology exist but these are necessarily high profile
designs and suitable mainly for larger vehicles. Fully active planar array are under development but mainly in receive
mode only. Innovative design is therefore mandatory to satisfy the market requirement for low profile and low cost
product that can be conveniently integrated into smaller vehicles. It is considered of major interest to investigate
innovative antenna concepts to overcome the above mentionned limitations.
As an example, some companies in Europe have developed high performances receive antennas, for broadband
communications via geo satellites, based on cryoelectronic components. Using superconducting circuits, quantum
electronic components and cryocooled semiconductor amplifiers practically noiseless RF front ends may be designed.
As a consequence of this extremelly low noise temperature, for a given G/T requirement, the receive antennas based
on cryocooled aperture incorporating superconducting structures can be the smallest possible. This promising
technology may offer extremelly important advantages also in transmit. In particular, the Microwave Phase
Conjugation allows novel methods of handling propagating signals. Recently, phase conjugation elements sufficiently
small to be used in planar arrays through the use of high temperature superconductors have been developed.
Beside superconductive devices, Direction Of Arrival can be obtained through RF closed loop, information from on
board computer and attitude sensors.
This activity will investigate different antenna concepts allowing to range finding of several satellites at once and
assess the technical feasibility and cost issues. Ability to handle dual polarisation shall be considered. The use of
these techniques may allow the system to self-focus, potentially onto several satellites at once, offering simultaneous
ranging of these satellites. This is a significant advantage as from the received signal the antenna is able to send back
the signal in the same direction. The need for extra information comming from GPS is then avoided and this results in
faster setup times and reduced complexity. Also, distortions to the phase conjugation surfaces or in the propagation
path can be automatically corrected.
Deliverables:
Study Report, limited supporting prototype hardware.
Current TRL:
TRL 1
Target TRL:
Application/Mission: Mobile Telecom (2015-2017)
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 2
Application
Need/Date:
Contract Duration:
TRL5 by 2013
12 months
Dossier0 Ref.: T-7923, T-7910
N/A
TRP Reference:
T507-011EE
TD:
TD07
Title:
Circular polarisation dual-optics proof-of-concept
Objectives
To obtain proof-of-concept experimental demonstration of critical antenna elements for dual-optics CP
antennas.
Description
The circular polarisation equivalent of "dual gridded"reflector antennas will enable the reduction of mass, enveloppe
and cost of the antenna farm for many future Ku and Ka band missions.
The availability of space-wave circular polarisation filters to improve polarisation purity for circular polarisation
coverages and allow the implementation of dual-optics solutions (the CP equivalent of dual-gridded reflector
antennas) is a longstanding unsatisfied need for telecommunications missions. Recent development finally made a
viable concept available. This activity is aimed at an experimental demonstration in Ku or Ka band.
Deliverables:
Proof-of-concept demonstrator.
Current TRL:
TRL 1
Target TRL:
TRL 2
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Application
Need/Date:
TRL5 >2014
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Description of Activities
Fixed Satellite Services (FSS),
Application/Mission: Broadband Satellite Service (BSS), Contract Duration:
(2017)
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
18 months
Dossier0 Ref.: T-7907
Consistent- Reflector Antennas - 2004
TRP Reference:
T507-012EE
TD:
TD07
Title:
Assessment of propagation modelling risk for Satcom system design
Objectives
To identify the risk and the error budget associated to paths radiowave propagation models at Ku, Ka and
Q/V bands. The identification of variations on daily, seasonal and long-term (e.g. El-nino) periods on a
global scal is another objective of this actvity.
Description
The use of prediction risk/error during system design would permit a more realistic trade-offs between different
options/architectures (e.g. availability target, coverage area, EIRP levels and margins). The identification of all various
contributions to the overall error budget of prediction models shall permit to identify and control the risk associated to
prediction. The assessment of variability and its temporal scale is also useful for planning services and costs. This
activity shall make use of long-term Numerical Weather Prediction and Earth observation databases to identify the
error covariance matrix.
Deliverables:
Final report, Models and proposals for ITU-R recommendations.
Current TRL:
TRL 2
Target TRL:
TRL 3
Fixed Satellite Services (FSS) for
Application/Mission: Interactive Broadband Services
(2014)
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
TRL5 by 2011
12 months
Dossier0 Ref.: T-8252
N/A
TRP Reference:
T507-013EE
TD:
TD07
Title:
Combination of tropospheric and local environment propagation effects for MSS
above 10Ghz
Objectives
Consolidate propagation models that combine effectively local envinroment and tropospheric effects using
data from measurement campaigns, climatological databases and existing models developed for fixed and
mobile services.
Description
Mobile Satellite Systems at L and S bands are mainly affected by free-space loss and propagation effects in the local
environment. Future systems that require larger bandwidth will use higher frequency bands such as Ka/Ku, where the
tropospheric effects also plays a role. The activity aims to consolidate the physical principles to combine mobile and
atmospheric effects at frequencies above 10Ghz based on existing models for MSS and FSS and data from
narrowband and wideband mobile measurement campaigns at Ku and Ka bands from previous ESA contracts. Effects
of multipath and shadowing together with gaseous and rain attenuation including the dynamics of the user terminal
and atmosphere shall be considered.
Deliverables:
Report, protoype software (consolidated calculation model).
Current TRL:
TRL 2
Target TRL:
TRL 3
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Application
Need/Date:
TRL5 by 2012
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TRP Work Plan 2008-2010
Description of Activities
Application/Mission:
Ku/Ka band mobile comms &
broadcasting (2015)
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-8251, T-7923
Consistency with Harmonisation
Roadmap and Conclusions:
12 months
Consistent (EEP propagation dossier)
TRP Reference:
T507-014EE
TD:
TD07
Title:
Advanced propagation tool for satellite ATM & aeronautical communications
Objectives
Develop a tool for propagation analysis of aeronautical communications and air traffic management by
satellite.
Description
The activity aims to develop an operational software raytracing tool for the study of signal propagation on ATM
satellite communication in all phases of flight focused in L band (unless requirements and air interface is redefined
before the activity is started). The tool shall be able to include 3D models of most commercial airplanes, and digital
elevation maps for approaching phases shall be included. The characteristics for broadband communications for
in-flight entertainment, internet and multimedia shall be also considered, due to its analogy regarding propagation,
however keeping the focus on ATM.
Deliverables:
Software, report.
Prototype (alpha Application
version)
Need/Date:
Current TRL:
Algorithm
Application/Mission:
All telecommuntication missions
(>2013-2014)
Contract Duration:
SW Clause :
Operational SW
Dossier0 Ref.: T-8256
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
SW Operational by
2013
18 months
Consistent (EEP propagation dossier)
TRP Reference:
T507-015EE
Title:
Compact Low-mass global antennas
TD:
TD07
Objectives
The objective of this activity is to design, manufacture and test a breadboard model of a light and compact
C-band antenna, with dual polarisation (linear or circular), able to provide global reception/transmission for
telecommunications from geostationary orbit. Efforts shall be focused on overall volume reduction while
complying with RF performances over the required frequency bandwidth.
Description
There have been studies aiming at reducing the volume of global coverage antennas either for navigation or for
telecommunication bands . At C-band and below, this type of horn is very bulky for implementation on the earth deck
of a large satellite and it becomes a major concern for small satellites (2-3 tons). Although a reduction in volume has
been achieved, so far the bandwidth performance has been very low (around 1%). It is therefore required to
investigate ways of expanding the bandwidth. The preliminary specifications for this transmit/receive antenna would
be the following: frequency band: C-band; mass < 0.8 Kg; radiating element height < 2.5 wavelengths; gain higher
than 16.5dBi within theta = ± 9º; bandwidth around 2-3 %. Other telecommunications frequency bands (L, S) could
also benefit from this activity. Receive only might also be considered for some applications.
Deliverables:
EM of antenna.
TRL 4
Current TRL:
TRL 2
Application/Mission:
Fixed Satellite Services (FSS,
>2015)
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-7746
Target TRL:
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Application
Need/Date:
TRL5 >2012
18 months
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TRP Work Plan 2008-2010
Description of Activities
Consistency with Harmonisation
Roadmap and Conclusions:
Consistent- Reflector Antennas - 2004
TRP Reference:
T516-016MM
TD:
TD17
Title:
Interchip-Optical Communciations and Photonic PCBs for next gereration OBP
Objectives
To investigate the potential benefits of using chip to chip optical communications in a photonic or
electro-photonic PCB for the next generation OBP (On-Board Payload).
Description
Next generation OBP are very power demanding as they are designed to handle aggregate traffic of several Tbps. In
this activity the effort will be to stuidy and lenerage to space the systematic investment undetraken by the commercial
computing industry in implementing optical communications at the IC and PCB level inorder to achieve power
efficient processors of ultra-high capacity and speed. A trade-off of the variosu optical communcaitions techniques
shall be perfromed together and a comparison to the electrical equivalent shall be made. The most suitable
technologies shall be identified and a technology roadmap shall be prepared. Aprelimnary design of a represntative
photonic PCB with selected IC-IC optical Communciations and optical interfaces to other PCBS ahall be prepared
supported with simulation results.
Deliverables:
A deyailed Technical Report on Applications and Technologies Trade-off analysis and a Preliminary design with
simulation results of a photonic PCB with inter-chip optical ommuniciations and optical intercafes to other PCBs
designed according to the requrieemnts of the NG OBP.
TRL 2
Current TRL:
TRL 1
Application/Mission:
Next Generation Payload (NGP,
>2015)
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
Contract Duration:
TRL5 >2012
12 months
Dossier0 Ref.: T-7913
Not linked to the Harmonisation Roadmap. Related to ARTES 5
activity on "Inter-board Opticalcommunications
TRP Reference:
T516-017MM
TD:
Title:
Electro-Photonic ADC
TD17
Objectives
To study the impact of a high frequency electro-photonic ADC on a telecommunications payload and
demonstrate experimentally the concept of subsampling at a frequency adapetd to the requirement such a
payload.
Description
Recent advancments in phtonic micrwave devices have enabled the use of ultra-low jitter laser pulse sources for high
quality sampling of high frequnecy of RF signals up to 20 GHz, using principles of subsampling such an
electro-photonic ADC coul dperfrom sampling directly at the carrier frequency of incoming signals in satellite
communication paylaods. The activity shall study the impact that this device has in the architecture of sat-com
payloads and demonstrate its operation at a frequency up to Ka band adapted to the needs of such payloads.
Deliverables:
A Technical Reprot on assessment of the impact of electro-photonic ADC on satellite payload and a demonstartor of
an electro-photonic ADC operating at a frequency requried by such a payload.
Current TRL:
TRL 2
Target TRL:
Application/Mission: Future Digital Paylaods (2015)
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
Study
applicable
results
>2009,
12 months
Dossier0 Ref.: T-7746
Not linked to the Harmonisation Roadmap. Related to ARTES 5
activity "Hybrid ADC/DAC with optical interconnects
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TRP Work Plan 2008-2010
Description of Activities
TRP Reference:
T516-018MM
Title:
Opto-microwave based front-end for a multi-beam large direct radiating array
antenna
TD:
TD16
Objectives
To design, manufacture and test a proof-of-concept demonstrator of an innovative opto-microwave based
front-end for a large direct radiating array antenna with multiple beams, with the main target to
demonstrate (a) the expected mass / volume / power consumption savings and (b) the enhanced
performance (e.g. capability to generate additional beams without increasing complexity) compared to a
pure-microwave or a digital beam-forming implementation options.
Description
Recent accomplishments (in the ESA ITI program) in microphotonic device fabrication (Buttler matrices) pave the way
for considering constructing large feed array antennas using optical BFN. In this activity, the Contractor shall carry out
the design of an optical assembly suited to be included in the front-end of a very large transmitter direct radiating
array, taking into account the end-to-end system level requirements of a broadband multi-beam communications
mission in Ka-band (e.g. multimedia via satellite, HD-TV). In particular, it shall include:
• The passive beam-former network (with optical architectures to reduce the number of input ports and the BFN
complexity).
• Frequency up-converters (from I.F. to microwave downlink frequency in Ka-band)
• Fast optical switches able to provide very fast beam-hopping (if required).
Options for integrating various functionalities into a single device, or even a single chip shall be assessed. RF
performances (e.g. C/I+N, RF gain, directivity degradation due to fabrication tolerances) shall be validated by
manufacturing and testing a representative proof-of-concept demonstrator of a fully operational opto-microwave based
front-end for a multi-beam large DRA antenna with optimised opto-electronic interfacing to the payload.
Deliverables:
A representative proof-of-concept demonstrator of an opto-microwave based front-end for a multi-beam large DRA
antenna.
Current TRL:
TRL 2
Target TRL:
Application/Mission: Future missions (>2015)
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
TRL5 >2012-2013
24 months
Dossier0 Ref.: T-7746, T-7926
N/A
TRP Reference:
T518-019MP
TD:
TD19
Title:
Electronic pressure regulator for Small GEO Electric and-cold gas propulsion
system applications
Objectives
Objective if this activity is a the design from a BB to an EM level of an Electronic Pressure Regulator
based on proportional valve for Small GEO Electric propulsion system and cold gas system
Description
Small GEO Propulsion system will be based on Electric propulsion system and a cold gas system. Do to the wide
range of mass flow rate demand from 1 g/sec for a 0.25 N Xenon cold gas thruster to 0.5 mg/sec for an a ion engine,
this range is prohibitive for a mechanical pressure regulator. Electronic bang-bang regulator might not be able to
operate successfully. It is proposed the development and manufacturing of a pressure regulator based of a
proportional valve realised with new technologies (e.g. piezo) in closed loop with suitable transducers (pressure or
mass flow) able to cope with this large range of mass flow requirement
Deliverables:
Electronic Pressure Regulator at EM level and test data.
Current TRL:
TRL 3
Target TRL:
Application/Mission: Small GEO (2012)
N/A
SW Clause :
TRL 4
Application
Need/Date:
Contract Duration:
TRL5 by 2010
18 months
Dossier0 Ref.: T-7979
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Description of Activities
Consistency with Harmonisation
Roadmap and Conclusions:
N/A
TRP Reference:
T520-020MC
TD:
TD21
Title:
High conductive CFRP sandwich technologies for platforms
Objectives
Development of CFRP spacecraft panel structures using conductive CFRP fibers in order to reduce mass,
where conductive fibers are need for thermal reasons. The design shall show clear mass benefits with
limited cost and impact.
Description
Design/ manufacturing and qualification of demonstrator radiative panel using high conductive CFRP. Material
screening and selection. Manufacturing of samples as well as a demonstrator breadboard.
Deliverables:
Breadboards/demonstrators. Synthesis report.
TRL 2
Current TRL:
Target TRL:
TRL 4
Application/Mission: Telecom platforms (2013)
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
TRL5 by 2011
24 months
Dossier0 Ref.: T-7937
Composite materials harmonisation
6 - Navigation
6 - Navigation
TRP Reference:
T604-001EE
Title:
Highly miniaturized active MEO radiation monitor Ph.A-B
TD:
TD04
Objectives
Development of highly miniaturized active radiation monitor
Description
Using advances in ASIC technologies and detector technologies from non-space sectors (HEP), develop a very small
(<20g, 2cm3) device with pulse height analysis capability, built-in storage and communications, to allow monitoring of
radiation environments at various locations in a s/c and/or on multiple s/c. The activity will establish the basic
technology for ASIC implementation and validate the principles through irradiation and simulation.
Deliverables:
prototype highly-miniaturized active radiation monitor
Current TRL:
TRL 1
Target TRL:
TRL 3
Application/Mission: Galileo Evolutions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRP Reference:
T604-002EE
Application
Need/Date:
Contract Duration:
18 months
Dossier0 Ref.: T-8374
2005a rad monitors
TD:
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TD04
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TRP Work Plan 2008-2010
Description of Activities
Title:
Energetic electron shielding, charging and radiation effects and reduction of
margins
Objectives
Development and application of new radiation shielding models. New physics models with related
easy-to-use engineering interfaces to treat radiation shielding, deep charging and dose effects problems
specific to the MEO environment will be developed. Use methods will be developed to produce optimised
shielding schemes, including material composites. The role of dose enhancement close to a target device
due to high Z (atomic number) in packaging and chip construction materials shall be addressed in
explaining the discrepancies observed in orbit (GIOVE-A). Detailed analysis of sources of error and
margins in radiation environments and effects evaluation processes will be performed, and models and
methods to reduce margins will be developed.
Description
The activity will develop new physics models and rapid methods for assessing in particular the electron and secondary
gamma shielding, charging, dose enhancement and other effects issues, relevant for the MEO environment and for
the specific materials and geometries used in Navigation spacecraft. Engineering interfaces to widely used industrial
tools, such as e.g. SPENVIS and FASTRAD will also be developed. The new models and tools will be extensively
validated by comparisons with (exisiting and/or produced) experimental data, and compared to a range of other
methods. The developed models will be used to development of new shielding methods which may include layered
shielding and denser packing of existing mass within spacecraft. Potential gains to be made by simulation of physics
of particle tracks to reduce/validate margins in sector methods, and to compute accurately the effects of spot
shielding. Radiation transport modelling shall be performed to investigate how to optimise shielding using alternating
high and low atomic weight materials. Sample material composites shall be fabricated and tested. Experimentally,
GIOVE-A measurements indicate that heavily shielded RADFETs receive a much higher dose than expected. One
possibility is that the heavy flux of electrons is interacting with local high-Z (atomic number) materials to generate a
shower of photons and secondary electrons, enhancing the dose. If true, this could give rise to needs for additional
shielding, higher margins and better dose calculation methods. The activity will investigate this phenomena and model
the GIOVE-A and B geometries down to device level, for both measurement devices and electronic components and
establish rules and methods and new dose models. Furthermore, radiation environment and effects evaluation
processes for projects are subject to uncertainties and statistical variations which are accounted for through margins.
However, the establishment of margins is highly problematic in many projects, in particular those encountering
high-flux electron environments. They are not always rationally established and can lead to significant over-design and
cost (too high margins) or high risk (too low margins). A complete analysis of sources of margins in calculation of
environment (modelling methods, data analysis, instrumental issues) and effects (shielding, dose, SEE) will be
performed. The output of the activity will be substantially improved environment and effects models, tools and
methods for applying margins in satellite designs.
Deliverables:
Updated physics models; software and methods; improved engineering interfaces; validation and analyses; material
design, sample materials, test recommendations and results; margin practices and recommendations
Current TRL:
TRL 1
Target TRL:
TRL 3
Application
Need/Date:
Galileo; other mission categories
encountering high-flux electron
environments (e.g. Telecom,
Application/Mission:
Contract Duration:
missions to outer planets). Margins
reduction is furthemore benefiting
all missions.
SW Clause :
Operational SW
Consistency with Harmonisation
Roadmap and Conclusions:
TRL5 > 2010
12 months
Dossier0 Ref.: T-8374
Rad Effects (2006a); radiation test facilities and engineering tools
(1st. sem 2006) consistent with activities E1: ensure access to
validated tools, D2: coordinated radiation effects, C1: enhanced
capabilities of tools
TRP Reference:
T604-003EE
TD:
TD04
Title:
Dose enhancement in high electron environment as source of under-prediction
Objectives
To investigate the role of dose enhancement close to a target device due to high Z in packaging and chip
construction materials in explaining the discrepancies observed in orbit (GIOVE-A)
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TRP Work Plan 2008-2010
Description of Activities
Description
GIOVE-A measurements indicate that heavily shielded RADFETs receive a much higher dose than expected. One
possibility is that the heavy flux of electrons is interacting with local high-Z materials to generate a shower of photons
and secondary electrons, enhancing the dose. If true, this could give rise to needs for additional shielding, higher
margins and better dose calculation methods. This activity will investigate the phenomena and model the GIOVE-A
and B geometries down to device level, for both measurement devices and electronic components and establish rules
and methods and new dose models.
Deliverables:
Rule, margins, models, methods, test recommendations
TRL 1
Current TRL:
Target TRL:
Application/Mission: Galileo
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
2010
12 months
Dossier0 Ref.: T-8374
N/A
TRP Reference:
T606-004ET
TD:
TD06
Title:
Innovative algorithms for multi-system Precise Point Positioning
Objectives
Improvement of PPP performance (using GPS plus Galileo, and advanced algorithms) in terms of
initialisation time, accuracy, and integrity.
Description
PPP using GPS is an existing technique, offering decimetre-level real-time navigation. PPP offers world-wide
coverage, requiring only precise orbits to be transmitted to the user. However, one of the main limitations today is the
initialisation time (up to 30 minutes). If the initialisation time can be reduced, the number of PPP-users might increase
significantly. PPP might become one of the commercial services of Galileo. Within this task, a study shall be
performed of new algorithms to enable enhanced multi-constellation PPP (GPS+GLONASS+GALILEO/GIOVE). The
bidder shall use the new available signals and the expected lower latency of IGS products. The reduction of the
initialisation time of PPP shall be addressed.
Deliverables:
A technical document reporting of the improved PPP performances achievable with Galileo and associated innovative
algorithms, plus simulation software.
TRL 1
Current TRL:
Target TRL:
Application/Mission:
SW Clause :
TRL 3
Application
Need/Date:
Contract Duration:
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
12 months
Dossier0 Ref.: T-8161
N/A
TRP Reference:
T606-005ET
Title:
Peer2peer positioning
TD:
Objectives
* Development of peer2peer algorithms and processing techniques
Demonstration of the benefits of the peer2peer concept
TD06
*
Description
Traditionally, navigation systems (e.g. GPS, DGPS, EGNOS, Galileo) are using a one-way flow of information (i.e.
from the system to the users). The concept of peer2peer positioning addresses the exchange of information between
users, hereby improving navigation performance. In addition, ranging between users might be considered. Especially
in difficult environments (e.g. indoor, interference, multipath), peer2peer positioning is expected to be beneficial.
In this activity, the peer2peeer algorithms shall be developped, and the concept shall be demonstrated.
Deliverables:
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TRP Work Plan 2008-2010
Description of Activities
Design, development and performance report for the peer2peer navigation system concept. Software simulation tool.
TRL 1
Current TRL:
Target TRL:
Application/Mission:
Application
Need/Date:
Contract Duration:
Operational SW
SW Clause :
TRL 3
Consistency with Harmonisation
Roadmap and Conclusions:
12 months
Dossier0 Ref.: T-8372, T-8055, T-8052
N/A
TRP Reference:
T606-006ET
TD:
TD06
Title:
Real time ODTS Algorithms for navigation satellites
Objectives
Development of innovative real time ODTS algorithms (Kalman filtering, neural networks, etc.) using
paralel processing. The activity will allow to analyse the improvements of orbit and clock predictions and at
the same time develop suitable innovative algorithms.
Description
Currently the ODTS algorithms in Galileo and EGNOS are based on batch least squares algorithms. This means that
real time estimation will never be possible, and only predictions can be used.
Recent developments however have shown that statistical techniques for the process noise makes Kalman Filtering
possible for GNSS. This is used in GPS today.
Also other techniques like neural networks improve the accuracy of ODTS. At the same time the real-time character of
the current and future algorithm can be improved by using recently developed paralellisation techniques like OpenMP.
The expected improvement with this new technique compared to current Galileo budget, should be in the order of
10-50cm over 1 hour (range level orbit and clock).
Deliverables:
“Representative” proof-of-concept demonstrator of an integrated optical-quantum ISL
Technology Data Package
Summary Report
Modelization tools (mathematical/numerical computer models)
TRL 1
Current TRL:
Target TRL:
Application/Mission:
SW Clause :
TRL 3
Application
Need/Date:
Contract Duration:
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
12 months
Dossier0 Ref.: T-8161
N/A
TRP Reference:
T606-007ET
TD:
TD06
Title:
Design and pre-development of Techniques and Technologies for Payload
Autonomous integrity monitoring
Objectives
The objective of this activity is to study the techniques and the technologies that could be introduced at
Payload level to allow monitoring the integrity of the emitted signal directly measuring the signal at the
payload RF output. The satellite will be able to qualify autonomously the signal transmitted identifying
more promptly and more accurately some specific failure modes reducing the probability of failure of the
satellite leading to a drastic simplification of the Ground Integrity monitoring system.
Description
Integrity monitoring is currently provided with the usage of very complex Ground infrastructure which is not only very
expensive but also affected by all the propagation/geometric/network effects and so sometimes very inaccurate.
Proper calibrated equipment can be included on board to measure the signal at the RF output of the payload providing
instantaneous and accurate detection of specific failure modes. The satellite failure probability can be drastically
reduced if not made negligible thus reducing the need for a complex ground infrastructure.
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Deliverables:
Technical Notes analysing in details payload feared events and models, possible algorithm to detect them, a concept
architecture for the monitoring, performance of the algorithm, analysis of the improved reliability, simulation and
source code. Breadboard implementation of critical software and/or hardware elements.
TRL 1
Current TRL:
Target TRL:
TRL 3
Application/Mission:
Contract Duration:
N/A
SW Clause :
Application
Need/Date:
Consistency with Harmonisation
Roadmap and Conclusions:
13 months
Dossier0 Ref.: T-8047
N/A
TRP Reference:
T606-008ET
TD:
TD06
Title:
Advanced signal-in-space Techniques (Mod, Cod, Message)
Objectives
This activity is focused on the introduction of state of the art tele-communication techniques (Modulation,
Coding, Message, etc) in to the navigation domain to improve the performance of the Navigation signals
for those types of users and Services for which the current signal design is not optimised or to achieve a
more efficient use of the available RF resources to be exploited for future radionavigation system design.
Description
Communication techniques can be introduced in the Navigation domain to improve the performances. Easyness of the
generation/reception of the signal, reduction of the intrasystem interference, higher orthogonality of the spreading
sequences, efficiency of the message encoding mechanism to achieve higher data rate or lower BER, robustness of
the signal tracking, higher efficiency in the exploitation of the available bandwidth, robustness to hostile RF
environment, jamming and anti spoofing capability etc. are areas for possible improvement. Use of multilevel codes,
structurally banlimited or compact signals, multiobjective optimisation of the spreading sequence and of the pulse
shape, turbo codes, are just example of possible ways to achieve these improvements, whose applicability or the real
advantages have to be proven and studied in detail. The impact on the receiver and payload design must also be
taken into account for the feasibility.
Deliverables:
Technical Notes including simulation models and source code
Current TRL:
Target TRL:
Application/Mission:
SW Clause :
Application
Need/Date:
Contract Duration:
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
12 months
Dossier0 Ref.: T-8372
N/A
TRP Reference:
T606-009ET
TD:
Title:
Autonomous on-board timing reference
TD06
Objectives
The objective of this activity is to develop and validate techniques for the implementation of autonomous
on-board timing references.
Description
The on-board timing reference of GNSS systems is a key driver of the navigation and integrity performances. The
today solution is to embark Atomic Clocks whose performance and integrity are monitored on ground, via the OD&TS
process. This puts significant constrains on both the reliability and performance of the on-board clocks and on the
operation and control of navigation and integrity. Several methods (e.g. phase comparison, three-corner-hat…) offer
the possibility to monitor directly on-board the performance of the timing system, and to implement some switching
strategies in case of failure, with no effect on the phase coherence. The aim of this activity is to investigate such
methods and to implement and validate at breadboard level an autonomous on-board timing reference.
Deliverables:
1BB
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TRL 2
Current TRL:
Target TRL:
Application/Mission:
SW Clause :
TRL 4
Application
Need/Date:
Contract Duration:
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
2010
24months
Dossier0 Ref.: T-8046
N/A
TRP Reference:
T607-010EE
TD:
TD07
Title:
Assessment techniques of tropospheric effects for local augmentation systems
Objectives
To develop channel models and channel assessment techniques to support the reduction of error
introduced by the troposphere by means of local augmention systems and external sensors. To model
spatial and temporal correlation of troposperic delay for development of synthetic time series generators.
To define covariance elements and distribution of the error of models for GNSS users receivers.
Description
The accuracy of tropospheric excess path length estimation in a GNSS receiver can be increased by using an
estimate of current or short-term evolution of atmospheric conditions. This information can be provided by ground or
space based sensors and numerical weather prediction systems (like ECMWF for a global scale or HIRLAM/MM5 for
regional scale). The models and algorithms to process this type of information and convert it into a message for local
augmentation systems need to be develped. The modelling of the spatial and temporal correlation properties of
tropospheric effects is also relevant for the development of channel models to be used by system simulation tools.
Deliverables:
Report, prototype software.
Current TRL:
TRL 1
Target TRL:
Application/Mission: EGNOS & Galileo evolutions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
12 months
Dossier0 Ref.: T-8033
N/A
TRP Reference:
T612-011MM
TD:
TD12
Title:
Demonstration of optical clocks based on cryogenic resonators
Objectives
To design and breadboard a cryogenic resonator optical clock, that is ready for ground station operation
and has the following Allan deviation requirements:
· 1E-14 @ 1 second
· 1E-15 @ 100 seconds
· 1E-16 @ 10000 seconds
Description
A new generation of atomic standards, based on optical atomic clocks, is expected to outperform microwave
frequency standards by two to three orders of magnitude in both short- and long-term stabilities. Optical clock
technology is however at an initial stage, and some work will be required until this technology reaches a level of
maturity that leads to the full achievement of the high potential of optical clocks for applications both on ground and in
space.
Cryogenic resonators can be used as stand alone optical clocks (if the optical cavity is well designed, cryocooled and
properly stabilised) or local oscillator stages for optical atomic clocks. The development of improved optical cryogenic
resonators is twofold. On one hand, an optical clock of excellent performance can be available at lower cost, volume
and size than that of a complete optical atomic clock, which makes this technology a very promising one for on-board
optical clocks. On the other hand, improved cryogenic resonators can be used as local oscillators in state of the art
optical atomic clocks.
The advent of optical clocks will open the field to an outburst of new applications and mission returns. In the case of
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Description of Activities
GNSS systems, the use of optical clocks will provide the means for more stable and more performing systems, and
will minimise the rate of frequency corrections.
The specifications generated as part of the feasibility study to be completed in 3Q2007 will be used as input to this
activity. The breadboard produced as part of this activity shall be ready for ground station use and comply to the
following Allan deviation requirement:
- 1E-14 @ 1 second
- 1E-15 @ 100 seconds
- 1E-16 @ 10000 seconds.
The optical cryogenic resonator shall be developed based on a design phase in which the following is carefully
assessed:
- Industrialisation
- Cost
- Size
- Maintenance
- Operation
- Required operational environment
- Monitoring and control
- Synthesis of frequencies
- Regeneration to microwave frequencies
Deliverables:
– Breadboard of an optical clock based on cryogenic resonator technology
– Documentation (Design, Integration, Tests, Manuals)
TRL 1
Current TRL:
Application/Mission:
SW Clause :
Target TRL:
TRL 3
Application
Need/Date:
Contract Duration:
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
2014
36 months
Dossier0 Ref.: T-8381
YES (Harmonisation of ground Frequeny and Time activities,
2006)
TRP Reference:
T612-013GS
Title:
Optical cavity cryo resonator breadboard for ground optical clocks
TD:
TD12
Objectives
This study pursues the design, breadboarding and testing of an optical cavity resonator of high finesse, a
laser source, servo electronics to lock the laser to the cavity, vibration isolation and tilt control means. This
equipment will be used to:
Confirm design feasibility
Optimise all interfaces (Electrical, Mechanical, Thermal, Monitoring & Control)
Validate integration procedures
This equipment shall be designed to operate as a cryogenic resonator, even though cryogenic stages will
be designed and built as part of a subsequent phase. It shall also be possible to use the equipment
developed within this activity as LO stage in a full optical atomic clock.
Description
A new generation of atomic standards, based on optical atomic clocks, is expected to outperform microwave
frequency standards by two to three orders of magnitude in both short- and long-term stabilities. Optical clock
technology is however at an initial stage, and some work will be required until this technology reaches a level of
maturity that leads to the full achievement of the high potential of optical clocks for applications both on ground and in
space.
Cryogenic resonators can be used as stand alone optical clocks (if the optical cavity is well designed, cryocooled and
properly stabilised) or local oscillator stages for optical atomic clocks. The development of improved optical cryogenic
resonators is twofold. On one hand, an optical clock of excellent performance can be available at lower cost, volume
and size than that of a complete optical atomic clock. On the other hand, improved cryogenic resonators can be used
as local oscillators in state of the art optical atomic clocks.
The advent of optical clocks will open the field to an outburst of new applications and mission returns. In the case of
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Description of Activities
GNSS systems, the use of optical clocks will provide the means for more stable and more performing systems, and
will minimise the rate of frequency corrections.
The specifications generated as part of the feasibility study will be used as input to this activity. The breadboard
produced as part of this activity shall be meant for ground station use and comply to the following Allan deviation
requirements:
- 1E-14 @ 1 second
- 1E-15 @ 100 seconds
- 1E-16 @ 10000 seconds.
The optical cryogenic resonator shall be developed based on a design phase in which the following is assessed:
- Stability performance (Allan deviation and phase noise)
- Operating temperature
- Sustaining electronics
- Vibration isolation
- Sensitivity to external perturbations
- Power consumption
- Size
- Materials, processes and parts
- Environmental conditions
- Reliability, operation and maintenance
- Definition of interfaces (electrical, thermal, mechanical)
- Transportability
- Expected final manufacturing costs
The breadboard shall be then manufactured and tested accordingly.
Deliverables:
– Breadboard of a cryogenic resonator
– Documentation (Design, Integration, Tests, Manuals)
TRL 1
Current TRL:
Application/Mission:
SW Clause :
Target TRL:
TRL 3
Application
Need/Date:
Contract Duration:
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
2014
18 months
Dossier0 Ref.: T-8381
YES (Harmonisation of ground Frequeny and Time activities,
2006)
TRP Reference:
T616-012MM
Title:
Applications of optical-quantum links to GNSS
TD:
TD16
Objectives
The objective of this activity is to investigate the potential of optical-quantum links for next generation
navigation systems, to assess the achievable performances and to design an optical-quantum terminal
(i.e., optical terminal with an integrated quantum transceiver, as part of a complete optical-quantum
intersatellite link and/or space-ground link). This combined optical-quantum terminal shall improve the
knowledge of the satellite’s orbit and its on-board time reference, compared to an approach based
exclusively on ground-space measurements or using RF intersatellite links. It shall also offer the possibility
for implementing a secure scheme for distributing cryptographic keys to/from the satellite on demand. The
performances of the proposed design of an optical-quantum terminal shall be verified and validated by
means of a laboratory proof-of-concept demonstrator, which shall integrate multiple functionalities (e.g.,
quantum key distribution, quantum clock synchronization, optical metrology, full-duplex bidirectional high
speed communications link).
Description
ESA and several European National Agencies have maintained the effort, after the successful SILEX experiment, in
developing the next generation of optical terminals with reduced mass, size and power consumption, and increased
data transmission rate (e.g. LOLA program in France, LEO TerraSAR-X in Germany). In contrast to optical (classical)
communications, quantum communications offer some unique features like security (i.e., Quantum Key Distribution
provides means for two parties to exchange with complete security an enciphering key, meaning that the presence of
an eavesdropper will always be detected), improvement of the estimation of a physical parameter (i.e., Quantum
Metrology), etc. Such quantum protocols rely on the foundations of Quantum Physics.
In this context, ESA has conducted several R&D studies within the ESA’s General Studies Programme (contract
numbers: 16358/02/NL/SFe, 16441/02/NL/SFe, 17766/03/NL/PM, 18805/04/NL/HE). In these studies novel concepts
for space communication systems based on the principles of Quantum Physics have been identified and investigated,
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Description of Activities
and proof-of-concept experiments utilizing available space infrastructure (e.g., ESA’s Optical Ground Station) have
been carried out (i.e. free-space distribution of entanglement and single photons over 144 km atmospheric path). This
achievement paves the way towards a future space-based Quantum Key Distribution demonstration.
The improvement of the estimation of the orbit parameters and the on-board clock is of paramount importance in next
generation navigation systems. The combination of (classical) optical communications and quantum communications
can enhance the knowledge of these critical physical parameters, by integrating a quantum transceiver in an optical
terminal (i.e., an optical-quantum terminal), and implementing optical-quantum intersatellite links (ISLs) and
space-ground links in the satellite constellation.
This activity shall start with an assessment of the potential of optical-quantum ISLs and space-ground links for next
generation navigation systems, to complement ground-space measurements for orbit and time synchronization.
The benefits and drawbacks of optical-quantum links compared to a navigation system with only ground-space
measurements or also with RF ISLs shall be critically assessed (e.g., potential complexity reduction for disseminating
a clock reference in space = towards a single clock in space, improvement of clock synchronization accuracy between
ground and space clocks). The impact on overall architecture shall be outlined and the requirements for the
optical-quantum link and terminal derived.
The design of an integrated optical-quantum terminal shall be carried out. This terminal shall encompass multiple
functionalities:
• distribution of quantum keys for confidential data encryption (including remote control access to satellite)
• synchronization of on-board clocks by means of a quantum channel (including the quantum protocol)
• high speed optical communications for time / orbit information transfer
• high precision optical (classical) metrology
Particular attention shall be paid to the accommodation of the quantum subsystems as part of the optical (classical)
terminal. Technical solutions in the optical bench to fulfil isolation requirements (between quantum and classical
channels) shall be investigated in depth. Impact of moving targets shall be assessed and solutions to correct the
effects of relative motions proposed.
To evaluate the predicted performances (i.e., position accuracy, time synchronization, key rate), a laboratory
proof-of-concept demonstrator of an optical-quantum link (i.e. end-to-end including relative motion effects) shall be
developed and tested using as much as possible off-the-shelf technology and breadboards available at the
Contractor’s premises.
Experimental validation of the predicted performances in a scenario “representative” of a space-ground link (e.g.,
inter-island experiment) is out of the scope of the present activity and will be executed in a follow-on contract.
This activity shall include:
• assessment of the potential applications of optical-quantum ISLs and space-ground links for next generation
navigation systems
• consolidation of optical-quantum link requirements (for both ISL and space-ground links)
• design of a multi-functional optical-quantum terminal
• development of a laboratory proof-of-concept demonstrator of an optical-quantum link (including two “representative”
optical-quantum terminals)
• performance validation of the proof-of-concept demonstrator (including testing)
• appraisal and recommendations
Deliverables:
Proof-of-concept demonstrator of an integrated optical-quantum link, Modelization tools (mathematical/numerical
computer models)
TRL 1-TRL 2
Current TRL:
Target TRL:
Application/Mission:
SW Clause :
TRL 3
Application
Need/Date:
Contract Duration:
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
2020
18 months
Dossier0 Ref.: T-8161, T-8045
Technology harmonization roadmap for “Optical Communications
for Space”
TRP Reference:
T616-013ET
TD:
Title:
Advanced receiver architectures
TD06
Objectives
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Description of Activities
This activity proposes to study optimisation of the receiver processing architecture via tighter integration
between the navigation and the signal processing, and exploitation of large amount of redundant
information available with multiple constellation, frequency, signals, in order to improve in general
acquisition and tracking performance, robustness against hostile RF environment etc.. The activity also
includes the design and prototyping of a channel monitor for multipath estimation and mitigation in GNSS
receivers.
Description
New architecture/design of the receiver processing chain can contribute in improving the performance. Recent
increases in the computational power of computers and digital signal processors have made possible novel signal
tracking techniques in GNSS receivers, so that both the Signal processing and the Navigation processing can be
optimised or even combined in to one single estimation algorithm. Such techniques as Direct Correlators Output
Processing (DCOP) or Vector Delay Lock Loop, channel estimators replace individual traditional tracking loops with a
single Kalman Filter, which jointly processes the received signals while exploiting their correlated noises. Potential
benefits of these new tracking techniques include an order-of-magnitude improvement in positional accuracy in
environments of jamming and high dynamics. More over exploitation of the signal, frequency constellation diversity
can also be a means to achieve higher performance.
Deliverables:
Technical Notes describing the architecture of a receiver, models of the environment and of the signals effects, SW
implementation of Rx, simulation/analysis of perfromance and comparison with existing receiver architecture.
Deliverables are SW source code and Techinical reports with results
TRL 3
Current TRL:
TRL 1
Application/Mission:
Navigation and communication
systems
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-8052
Target TRL:
Application
Need/Date:
TRL5 >2014
12 months
Consistency with Harmonisation
Roadmap and Conclusions:
TRP Reference:
T616-014ET
TD:
TD26
Title:
Enhancement of GALILEO system robustness exploiting Signal-of Opportunity
Objectives
This activity aims at identifying way to exploit Signal-of-Opportunity (SoO) coming from other not known
a-priori sources in order to supplement GNSS system when it works in difficult environments (such as
urban canyon or inside buildings) as well as when unintentional and intentional interferences, human
errors and natural phenomena effect GNSS performance.
There have been several studies aimed at identifying ways to exploit Signal-of-Opportunity coming from
terrestrial and space based signals (such as such as TV broadcasting antenna, mobile towers and
satellites) but all of these studies assumed known the location of the SoO emitters and consequently they
only have proved the feasibility to use SoO as navigation signals. The new idea behind this activity,
instead, is to develop a system concept and architecture able to automatically recognise SoO that are
present into the environment (it means that the receiver has to be able to recognise the bit pattern and
modulation technique for instance) and calculate the locations of their emitters exploiting GNSS systems
when these provide adequate performance. After this first stage thanks to which the SoO emitters
locations is known, the receiver should be able to calibrate the obtained System-of-Opportunity and so
exploit SoO for positioning when it turns to work under conditions of GNSS denial and in difficult
environment.
This activity it is very important because the utilization of the Signal-of-Opportunity in the performance of
position, navigation and timing, guaranteeing and improving GNSS services, actually enhances the
robustness of the overall GNSS system.
Description
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The activity has to provide a proof of concept of the feasibility of exploiting Signal-of-Opportunity coming from other
not known a-priori sources to supplement GNSS systems when they work in difficult environments (such as urban
canyon or inside buildings) or under the influence of unintentional or intentional interferences.
The activity shall involve a preliminary study phase aimed at investigating all available technologies capable to provide
potential
SoO
followed
by
a
development
phase
that
shall
be
carried
out:
- identifying and specifying the most promising Signal-of-Opportunity by mean of simulations at system level.
- providing simulated-based validation of the system concept
assessing
the
performance
enhancement.
- developing a preliminary architectural design of the user receiver
Deliverables:
Technical Notes describing all available technologies capable to provide potential SoO as well as the proof-of-concept
of the system feasibility. The technical notes shall also include detailed description of the used simulation models and
accordingly results.
TRL 3
Current TRL:
TRL 1
Application/Mission:
Galileo/Navigation and
Communications Systems
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-8376
Target TRL:
Application
Need/Date:
TRL5 >2015
18 months
Consistency with Harmonisation
Roadmap and Conclusions:
TRP Reference:
T616-015ET
TD:
TD06
Title:
GaN Power stage based on European technology for Navigation SSPA in L-Band
Objectives
Develop a L-band power stage based on European GaN technology with output power in the range of
120-150W capable of power flexibility.
Description
The objective of this activity shall be to investigate very high power amplifiers based on solid state European GaN
technology.
Unlike the amplifiers available today, GaN technology shall offer the possibility to build such HPA with only one power
module at the output. On its own this shall improve efficiency, ease of manufacture and price.
This activity shall also investigate the possibility to implement power flexibility and design techniques for increasing
efficiency in presence of digitally modulated signals and their implications in case of navigation application (e.g group
delay and gain flatness, stability etc..).
Finally the activity shall consider careful Multipactor related design.
Deliverables:
HPA breadboard and design documentation.
TRL 3
Current TRL:
TRL 1
Application/Mission:
Galileo/Navigation and
communication systems
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-8046
Target TRL:
Application
Need/Date:
TRL5 >2015
24 months
Consistency with Harmonisation
Roadmap and Conclusions:
TRP Reference:
T616-016GS
TD:
TD12
Title:
Development, integration and test of critical ground optical clocks elements
Objectives
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Description of Activities
This activity aims at the breadboarding of a ground optical clock based on a cryogenic resonator. The
clock will perform at a stability of 1E-14/sqrt(Tau) or better up to 10000 seconds. This breadboard will be
used to:
- Confirm design feasibility
- Optimise all interfaces (Electrical, Mechanical, Thermal, Monitoring & Control)
- Validate integration procedures
Cryogenic stages will be designed and built as part of this activity. The cryogenic resonator will be
available as part of a parallel TRP activity.
Description
In parallel to a TRP activity dealing with the design and development of a cryogenic resonator, this activity pursues the
design and development of missing optical clock elements and the integration and test of a full optical clock.
More in detail, the design shall at least consider the following aspects:
- specifications for the cryogenic stage
- optical incoupling control unit
- modulation detection unit
- tilt stabilisation system
- specifications and characterisation of frequency comb
- analog servo circuit boards
- monitoring & control
- signal recovery and relock routines
- integration of all subsystems (resonator, detection package, cryogenics, frequency comb)
A complete breadboard shall be manufactured and tested accordingly.
Deliverables:
– Full optical clock breadboard
– Test report
– Final report
TRL 2
Current TRL:
TRL 1
Application/Mission:
Ground Systems/Frequency
Standards
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-8361
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
TRL5 by 2016
18 months
Consistent (Demonstration of single ion optical clock Roadmap)
7 - Generic Technology and Techniques
7-01 - On-board Data Systems
TRP Reference:
T701-001ED
TD:
Title:
PowerLink : Two- wire Power and Data Link
TD01
Objectives
To define a harness efficient solution for interfacing smart sensors. This can be achieved by combining on
the same wires, a data communication channel and the power supply lines. This concept is different from
the PLC (Power line Carrier) where an existing power distribution network is used to convey data as well.
Powerlinks are point to point links specifically designed for the dual purpose of providing a two-wire only
interface. It applies to secondary power distribution (from the control-unit to the (smart sensor).
Description
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Description of Activities
This aims at defining the requirements in terms of voltage range, current supply range (hence power) and in terms of
data communication throughput. This first step will be followed by a reduced scale demonstrator based on commercial
technology.
Deliverables:
Reduced scale breadboard and concept demonstrator
TRL 1
Current TRL:
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
TRL 3
Application
Need/Date:
Contract Duration:
2012
18 months
Dossier0 Ref.: T-8382
Consistent “Computer and Data System” (2nd semester 2006)
D2.1
TRP Reference:
T701-002ED
TD:
TD01
Title:
Demonstration test bed for a secure TMTC system - step 1/Securing space
communications – Cryptographic line replaceable units
Objectives
The objective is to a set up the foundation of lines of products embodying cryptographic logic that can be
used to build up security solutions, enable evolutions in security techniques with limited impact on the
environment and prepare cross vendor compatibility.
Description
Cryptography provides primitives that are at the base of several security functions. A significant part of known
cryptographic techniques relies on the difficulty to resolve mathematical problems. The domain of cryptography is in
permanent evolution and not exempt from mutations and breakthrough susceptible to reduce investment in security
implementations to nil. A strategy is to be devised to isolate infrastructures, systems, equipment parts and security
controls from the details of used cryptographic techniques.
In order to define a line of security products it is proposed to identify groups of security functions that can evolve
separately from each other taking into account interface security, interdependencies and maintainability aspects. The
number of interface is minimized and validated from security standpoint to reduce costs through economies in
production of equipment.
The results of this activity are expected to be trustworthy in the sense that sufficient credible evidence is provided for
one to believe that the results of this activity can be used to build-up security solutions. Therefore information
assurance techniques to ensure that the result of the activity is secure may be needed to be used from the start of
activity.
The activity will identify and define a set of cryptographic line replaceable units (LRU), each of those units consisting in
a group of one or several security functions supported by cryptographic logic with an interface that can economically
support a wide range of applications.Ultimately a set of one or several of those line replaceable units will be identified
as critical to build up security solutions using cryptography. Those critical components can be assigned priority for
secure development (e.g. IP cores) and implementation in possible pilot follow-on activities. The scope of this activity
includes both security engineering and assurance aspects. The activity will produce implementation independent
documents that can serve as a basis for the design, development of security products by industry and possible
evaluation of security solutions by accredited organizations.
Deliverables:
security requirement/objective analysis, correspondence, dependencies, assumptions, external functional
specification, interfaces, high level design, and information assurance.
TRL 2
Current TRL:
Application/Mission:
SW Clause :
Target TRL:
TRL 5
Application
Need/Date:
Contract Duration:
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
2011
18 months
Dossier0 Ref.: T-7805
Consistent (“Computer and Data System” (2nd semester 2006) –
activity A9 “Secured TM-TC building blocks” step 2)
TRP Reference:
T701-003ED
TD:
Title:
Demonstration test bed for efficient on board sensor networks - STEP 1
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Description of Activities
Objectives
To evaluate solutions for sensor buses
Description
The activity shall provide an evaluation of sub-bus (sensor bus - e.g. I2C, LIN 2.1, 1-wire) technologies which are
currently used or planned for automotive/avionics industry and assess their suitability to space. Following an analysis
of missions requirements (Science,EO, Navigation, Exploration), solutions providing efficient implementation of the I/O
required for the monitoring, command and control of the platform and payload equipment shall be selected,
considering lessons learnt from other domains (e.g. aeronautics, automotive). A breadboard hardware demonstrator
shall be implemented, to assess performances and suitability of the selected technologies.
Deliverables:
Breadboard implementation of the busses.
TRL 2
Current TRL:
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
TRL 4
Application
Need/Date:
Contract Duration:
2012
12 months
Dossier0 Ref.: T-8383
Consistent with harmonisation roadmap and conclusion (Second
semester 2006 – Computer and Data system A2.1)
TRP Reference:
T701-004ED
TD:
TD01
Title:
Techniques for radiation effects mitigation in ASICs and FPGAs
Objectives
The objective of this activity is to describe in a single document the available mitigation methods against
radiation effects. This document shall enable the designers of microelectronic circuits to check the
adequacy of their methodology for radiation hardening, and to complement their design techniques where
necessary.
Description
Microelectronic circuits for space applications are required to tolerate radiation effects in the space environment.
Available microelectronic technologies with radiation tolerant capabilities are already applying a number of different
mitigation techniques. While this relieves the designer of integrated circuits from applying the same methods himself,
the designer is always challenged for a number of issues: --The choice of the most suitable technology (foundry,
process, and cell library). --The identification of critical parts of the circuit with respect to radiation effects (including,
but not limited to SEL, SEU, SET, and TDI) --The application of high level design techniques against radiation effects
such as triple modular redundancy (TMR), checksums, or memory scraping. --The design for synthesis and testability
of redundant circuits. --In full custom design: the application of low level design techniques against radiation effects
such as the adjustment of layout design rules to prevent single-event latchup (SEL) or enclosed layout transistors to
prevent leakage current. This activity shall describe in detail the available technology choices and mitigation
techniques for --Digital ASICs –FPGAs --Mixed-Signal and Analogue ASICs.
Such a document is frequently requested from companies which have not developed circuits for space applications
before, in both, new and old ESA member countries.
Deliverables:
“Techniques for Radiation Effects Mitigation in ASICs and FPGAs” document
N/A
Current TRL:
N/A
Application/Mission:
reliable space IC design, all
missions
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-7804
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
2010
12 months
Consistent (activity: B1, in µE Dossier - Sem 1 2007 (mapping))
TRP Reference:
T701-005ED
TD:
Title:
High capacity, high speed IC test system for automatic fault injection and
analysis (FT-UNSHADES2)
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Description of Activities
Objectives
Provide space industry (and projects) with a tool not available today to analyze the robustness against
SEUs of digital integrated circuits (both ASICs and FPGAs) that have been protected with design
techniques, totally or partially. The new tool based in fault injection will allow the tests to be done on the
chip: A) before manufacturing the chip, in order to ensure that the protection logic inserted by the designer
is good enough and acting as expected (it is correctly designed) B) and/or to investigate anomalous
behaviors that are suspected to be caused by radiation (after chip irradiation campaigns, or after in-flight
anomalies)
Description
This activity proposes the development of a mature tool to analyze the robustness of digital designs against radiation.
The tool is based on Fault Injection and is composed of a reconfigurable board and SW CAD tool. The activity is
based on the experience from the work already performed on FT-UNSHADES, which is a new system for SEU
injection, analysis and diagnostics over post synthesis netlists, to automatically diagnose IC weak point w.r.t.
radiation-induced bit-flips. The FT-UNSHADES has been developed since 2003 under ESA contract (Small study on
corporate budget: contract C17540). Both HW and CAD of the FT-UNSHADES tool have already been developed and
are being used: they prove the concept of fault injection using partial reconfiguration of the Xilinx SRAM-based
FPGAs, and several designs have been used to verify the complete flow for both ASICs and FPGAs. The task
breakdown is as follows: Phase I: - Feasibility study of the new FT-UNSHADES2 system based on the
FT-UNSHADES experience- Definition of reconfigurable board architecture, the control FPGA architecture and the
CAD tool architecture- Detail design of all the parts: board, FPGA design and the CAD tool- FT-UNSHADES2
integration and verificationPhase II: - Use of the tool for a test case- Final Generation of Application Notes on how to
efficiently use the system
Deliverables:
The deliverable includes: (1) - Reconfigurable prototyping board based on state-of-the-art commercial
reprogrammable FPGAs (2) - CAD tools to: - assist in the design flow of integrating the Module Under Test (MUT)
into the reconfigurable prototyping board - perform Single Event Upset campaigns and assist in the analysis of the
results (3) – Documentation of the development and User Manuals and White Papers on how to use the tool
Current TRL:
TRL 2
Target TRL:
TRL 4
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
2010
12 months
Dossier0 Ref.: T-7804
Consistent (activity: B7, in µE Dossier - Sem 1 2007 (mapping))
TRP Reference:
T701-006ED
TD:
TD01
Title:
Asynchronous design in space IC (Phase1): Methods, tools, design
Objectives
investigate, enable and demonstrate the use of asynchronous, clock-less design techniques for digital
ASIC in space.Phase 1 includes analysis/simulations, establishment of a design flow, and design of a
demonstrator chip to be manufactured and tested (performance, radiation) in a second phase.
Description
Phase I: Survey and feasibility study on the use of asynchronous design techniques for digital space ASIC's; Survey
of the state of the art (scientific publications, status in industry); Investigate (analysis, simulations) environmental
effects (radiation and temperature) ; Define a methodology to port existing (synchronous) designs
Deliverables:
Technology survey report
- Environmental effects analysis/simulation report and models
- Design flow documentation and dedicated scripts and software
Current TRL:
TRL 1
Application/Mission: All missions
N/A
SW Clause :
Target TRL:
TRL 3
Application
Need/Date:
Contract Duration:
2014
12 months
Dossier0 Ref.: T-7801, T-7799
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Description of Activities
Consistency with Harmonisation
Roadmap and Conclusions:
Consistent (activity B8, in µE Dossier, Sem 1 2007 (mapping))
TRP Reference:
T701-007ED
TD:
Title:
European DSP Trade-off and Definition Study
TD01
Objectives
Definition of a detailed set of requirements for the implementation of the next generation of European DSP
Description
Based on the recommendations of the Round Table on the Next Generation European DSP a set of detailed
requirements for the implementation have to be defined. These requirements shall be specific enough to start the
implementation of the DSP ASIC and the related development environment in follow-on activities. Dependent on the
selected baseline this can comprise an architectural design and / or first prototyping and test of critical areas on
FPGA. It comprises further the selection of a suitable ASIC technology.
Deliverables:
Requirements and architectural design for the implementation of the next generation DSP
Current TRL:
TRL 1
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
TRL 2
Application
Need/Date:
Contract Duration:
2011
18 months
Dossier0 Ref.: T-7798
Consistent with "On-board Paylaod Data Processing" (activity
A1.1- Sem 2 2006)
TRP Reference:
T701-008ED
TD:
TD01
Title:
European DSP Application Development Environment and Software Libraries
Objectives
Development of an Application Development Environment and Software Libraries for the Next Generation
European DSP
Description
This activity aims at the development of an Application Development Environment and Software Libraries for the Next
Generation European DSP. It will be based on the requirements obtained from the European DSP Trade-off and
Definition Study. The availability of a comprehensive set of SW development tools is essential to promote the usage of
the new processor. The same holds for a Software library for common functions which allows to develop the SW at a
higher level of abstraction. An integral part of this activity is as well the validation of the developed or adapted tools.
Deliverables:
Application Development Environment and Software Libraries for the Next Generation European DSP
Current TRL:
TRL 1
Application/Mission: All missions
Open source
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
TRL 2
Application
Need/Date:
Contract Duration:
2011
12 months
Dossier0 Ref.: T-7798
Consistent with "On-board Paylaod Data Processing" (activity
A1.5- sem 2 2006)
TRP Reference:
T701-009ED
Title:
SpaceWire Backplane
TD:
TD01
Objectives
Trade-off of SpaceWire Backplane Architectures, specification and selection of suitable connectors.
Description
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Description of Activities
The SpaceWire physical layer as defined in ECSS-E-50-12A is a point to point cable connection. This is most suitable
for the data link between equipments. With the success of SpaceWire it is also used more and more to connect
different boards within the same box. For this type of use typically a connection via the backplane would be used. So
far there is no standardised solution for SpaceWire connections over the backplane defined. In this activity the
different possible architectures of active and passive backplanes shall be traded-off. A suitable, impedance matched
backplane connector shall be found. A SpaceWire Backplane specification shall be defined that can be used as input
for the backplane standardisation work.
Deliverables:
SpaceWire Backplane specification
Current TRL:
TRL 1
Target TRL:
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 2
Application
Need/Date:
Contract Duration:
2011
12 months
Dossier0 Ref.: T-7801
Consistent with "On-board Paylaod Data Processing" (activity B3)
TRP Reference:
T701-010ED
TD:
Title:
SpaceWire Evolutions
TD01
Objectives
Definition, implementation and test of new techniques proposed to be used on SpaceWire like sideband
signalling for interrupt distribution and simplex SpaceWire. Prototyping of the proposed techniques prior to
the formal standardisation.
Description
Some evolutions of the SpaceWire standard have been proposed by the SpaceWire working group. Among the
discussed techniques there is the sideband signalling for interrupt distribution and the introduction of SpaceWire
operating in simplex mode. These new backwards compatible techniques need to be breadboarded prior to their
eventual standardisation. The SpaceWire test setup shall be mainly based on existing SpaceWire equipment which is
upgraded with the enhancements. A full set of functional tests shall be performed, assessing the usefulness and
derive recommendations for improvements.
Deliverables:
SpaceWire test setup for the investigated evolutions, test results and recommendations
Current TRL:
TRL 1
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
TRL 2
Application
Need/Date:
Contract Duration:
2011
12 months
Dossier0 Ref.: T-7801
Consistent with "On-board Paylaod Data Processing" (activity B3)
TRP Reference:
T701-011ED
TD:
Title:
Security architecture for command and control
TD01
Objectives
To determine the impact on the flight DHS architecture of the introduction of security layers.
Description
The majority of ESA spacecraft utilise existing, ESA defined, components or standard IP cores to assemble a robust
TT&C system. The introduction of security on forward and return links may impact the use of existing components or
even invalidate their use. This activity seeks to understand potential impact of the introduction of security on current
and future architectures and developments. Note: this activity will not concern itself with security mechanisms or
algorithms.
Deliverables:
Study report identifying the various levels of security that will likely be used in future ESA spacecraft and how each of
these may impact the flight DHS. The report will identify any changes required to existing components or standards.
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Description of Activities
Current TRL:
TRL 1
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
TRL 2
Application
Need/Date:
Contract Duration:
2010
6 months
Dossier0 Ref.: T-8382
Consistent with "Computer and Data System" (2nd semester 2006,
activity A8)
TRP Reference:
T701-012ED
TD:
TD01
Title:
Space internetworking protocols (Ph.1 of T701-012ED +T701-103ED)
Objectives
To determine the communication requirements for future exploration based missions involving multiple
space-borne and landed elements.
Description
Future exploration missions will rely on cooperative in-flight configurations ìnvolving many space borne and landed
elements with multiple, possibly disjoint, communications paths between them. Communication will most likely rely on
IP connectivity, coupled with delay tolerant mitigation techniques. The communication requirements will impact the
flight (and ground) systems in terms of the protocols used, the resources required and the procedures used for 2-way
communication.
This activity is consistent with the Ph.1 of the combined T701-012ED + T701-103ED developement, and will study the
end-to-end packet level communications requirements of future in-flight scenarios, to determine the most suitable
communication protocols.
Deliverables:
Reports describing the scenarios expected in future exploration missions, the derived communication requirements
and the proposed supporting protocols
Current TRL:
TRL 1
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
TRL 2
Application
Need/Date:
Contract Duration:
2010
6 months
Dossier0 Ref.: T-7727
Consistent with "Computer and Data System” (2nd semester 2006,
D2.5)
TRP Reference:
T701-013ED
TD:
Title:
SOIS interfacing to PUS
TD01
Objectives
To analyse the use of the ESA packet utilisation standard (PUS) in the context of the CCSDS
Recommendations for spacecraft onboard interface services.
Description
The CCSDS (Consultative Committee for Space Data Systems) has developed a standard set communications
services to be applied to the onboard DHS. The main intention of these services is to foster reuse of interfaces and
software across multiple missions. Before applying the approach to ESA spacecraft it will necessary match the
proposed services to those of the ESA packet utilisation standard as used by all ESA missions. This activity will
examine the required harmonisation of the SOIS (Spacecraft Onboard Interface Services) services with those
provided by PUS in order to ensure compatibility.
Deliverables:
Analysis of the packet level end-to-end communication system between ground (SCOS, Spacecraft Control &
Operation System) and flight elements (incorporating C&C, payload and mass storage) covering the use of PUS
services in combination with those provided by SOIS.
The mapping of PUS services onto those provided by SOIS subnetwork and Application support layer service.
Identification of any shortcomings and the proposal of solutions including updates to SOIS draft recommendations.
Current TRL:
TRL 1
Application/Mission: All missions
Target TRL:
TRL 2
Application
Need/Date:
Contract Duration:
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6 months
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Description of Activities
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Dossier0 Ref.: T-8382
Consistent with harmonisation roadmap and conclusion
TRP Reference:
T701-014ED
TD:
Title:
SOIS proof of concept
TD01
Objectives
To prototype the CCSDS SOIS recommendations together with other supporting developments to
provided system validation.
Description
Within the SOIS (Spacecraft Onboard Interface Services) area of the CCSDS (Consultative Committee for Space
Data Systems), a set of draft recommendations have been developed with the internet of standardising the
communication services used within the flight datahandling system. Before transiting to full CCSDS standards, it is
necessary to prototype the recommendations both to validate the protocols and ensure the suitability for adoption by
ESA. The SOIS activity covers hardware and software interfaces and protocols, the use of onboard resources such as
mass memory, and the interfacing with ground services defined by the ESA packet utilisation standard.
Deliverables:
Software modules implementing SOIS services and protocols, integrated with PUS software modules, interfacing via
SpaceWire and Milbus SOIS compliant protocols. Demonstration environment based on the ESA RASTA test bed
capabilities supplemented with the necessary hardware, software and test facilities to demonstrate the complete SOIS
set of recommendations in a representative system.
Set of use cases covering all SOIS services
Analysis reports of each service;
Current TRL:
TRL 1
Application/Mission: All missions
Open Source
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
TRL 3
Application
Need/Date:
Contract Duration:
2010
12 months
Dossier0 Ref.: T-8382
Consistent (Second semester 2006 – Computer and Data system
A2.1)
7-02 - Space System Software
TRP Reference:
T607-08EM
TD:
TD02
Title:
Standardisation and Building Blocks: Standardisation watch and verification
Objectives
The activity aims at guiding, supervising, controlling and verifying the standardisation of the building
blocks.
Description
This is a long term activity all along the standardisation period. It includes the creation and animation of a
standardisation watch group involving industry members who will be in charge of defining what needs to be
standardised, how it is standardised. It takes care of the maintenance of the standard. It steers the open source
implementation, it guarantees the availability of the reference architecture, it decides on the deployment, and is
responsible for organising the maintenance of the building blocks. It also includes the verification of the standards
during their definition in terms of completeness and consistency between each others. This will be done with some
dedicated tasks to verify specific technical aspects such as consistency of interface, completeness of the behaviour
definition, data models, etc.
Deliverables:
System Model of a generic avionic architecture and a decomposition in building blocks.
Current TRL:
TRL 2
Application/Mission: All missions
Target TRL:
TRL 3
Application
Need/Date:
Contract Duration:
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SW
operational
>=2009-2010
12 months
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Description of Activities
SW Clause :
Operational SW
Consistency with Harmonisation
Roadmap and Conclusions:
Dossier0 Ref.: T7667, T7661
Consistent (G1)
TRP Reference:
T702-015SW
TD:
TD02
Title:
Schedulability analysis techniques and tools for cached processors
Objectives
This project addresses how the existence of cache in the processor can and should impact software
design and implementation in order to maximize software and system performance and at the same time
ensure a high level of testability, predictability and analyzability. Further the project shall specify,
implement and verify low level functions (HW or SW) needed in order for the software to manage and
control the cache functionality on LEON processor
Description
- Requirements and recommendations for Software development tools in supporting implementation for cache
processor execution
- Requirements and recommendations on ways to structure application SW using the LEON caches for different
programming languages
- recommendations for the LEON3 cache architecture
- Specified, implemented and validated low level layer Software functions for cache management for LEON processor
- Tools for cache analysis
Deliverables:
Requirements and recommendations
Software layer for cache management
Tools for cache analysis
Current TRL:
Algorithm
Target TRL:
Prototype
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
2010
18 months
Dossier0 Ref.: T7667, T7665
Consistent (E2)
TRP Reference:
T702-016SW
TD:
TD02
Title:
Complexity, cost and change impact based on models
Objectives
The objective of the activity is to try and formalize better the notions of software complexity and/or cost,
and the impact of change of a requirement, taking advantage of the Model Driven approach that itself
formalizes the requirements
Description
The software requirements in English language can be formalized:
- in an advanced way , through knowledge organisation
- in a more usual way, with the Model Driven approach.
This formalism is equivalent to a high level language. On the other hand it is possible today to use software coding
language to asses the complexity and cost of software.
This activity will attempt to use the high level language expressing the requirements by adapting the techniques of
complexity, cost and change impact assessment available for coding languages, or derive new ones.
The activity shall include:
- requirements engineering knowledge organisation
'- selection of system and software modelling language (e.g. SysML, UML)
- definition of metrics for complexity, cost and change management
- prototype tools
Deliverables:
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Description of Activities
- definition of metrics,
- guides on the use of metrics,
- prototype tools
Current TRL:
Algorithm
Target TRL:
Prototype
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
2010
18 months
Dossier0 Ref.: T303, T7660
Consistent (A2)
TRP Reference:
T702-017SW
TD:
TD02
Title:
Development environment for future DSP/multicore
Objectives
Characterize the effects of compilers, cache, buses, MMU on multicore microprocessor.
The multicore microprocessors, like GINA, provide computation power, but it is extremely hard evaluate
the variability on execution time due to effect of cache, MMU, busses etc. The device response
characterization is the first step to understand where put the effort to improve either SW that HW.
Description
The proposal aims at analyzing and characterizing the performances and the behavior of these new products:
- RTEMS for Multiprocessors
- Aonix - ObjectADA for Multiprocessors
- AdaCore - GnatPro for Multiprocessors
- Linux for Multiprocessors / ECOS / etc.
The work to be carried out under this TRP is structured as follows:
1. Consolidate the discussion on the development environment of multicore placed in the proposal.
2. Port and run the ERB test suite on multicore environments
3. Analyse the results and agree on improvements
4. Implement the agreed improvements in the development environment
5.Check, consolidate or define the commercial availability and the maintenance scheme for each elements of the
environment. Update the relevant documentations
Deliverables:
- ERB test suite (source code, executables) with related documentation
- prevalidated selected cross development environment
Current TRL:
Algorithm
Target TRL:
Prototype
Application/Mission: All missions
Open Source
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
2011
18 months
Dossier0 Ref.: T7665, T7753
Consistent (D5)
TRP Reference:
T702-018SW
Title:
Interface Standardisation verification by data modeling
TD:
TD02
Objectives
Following the definition of the reference architecture in CORDET, implement the data modelling
technology to verify the interface to be standardized
Description
- consolidate if needed the reference architecture
- detail the interface requirements
- model the interface
- verify the interface
- integrate into the reference architecture, with the functional view tool, and with vertical transformation to a virtual
machine
Deliverables:
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Description of Activities
- data types in ASN.1
- binary encoding and integration into the virtual machine context and the functional tools context
Current TRL:
TRL 2
Target TRL:
TRL 3
Application/Mission: All missions
Operational SW
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
2012
18 months
Dossier0 Ref.: T7667, T7661
Consistent (G1)
TRP Reference:
T702-019SW
TD:
TD02
Title:
Dependability design/approach for critical flight software
Objectives
The starting TRP on "performance and verification" addresses software and hardware fault models
combination to derive dependability properties. Everything cannot be done in this TRP which needs a
follow on fror example for discrte event controller modelling and generation
Description
1.Evaluation and justification of a unified modelling and specification approach suited for automated analyses, which
are mandated by the development lifecycle of the critical on-board systems, and definition of the System-Level
Integrated Modelling (SLIM) formalism;
2.Development of a tool-set, Integrated Platform for System-Software Co-Engineering – Correctness, Performability
and Safety, implementing the required analysis techniques based on combined use of model checking and numerical
solution algorithms;
3.Demonstration of the approach on a case study and evaluation of the experimental results in terms of scalability and
usability;
4.Evaluation of applicability of the approach and developed technology to the specifics of the critical on-board systems
and software development for the space domain.
Deliverables:
Verification and analysis methods and tools covering such aspects as correctness, safety and dependability in the
context of dynamic system operation, system performance, influence of degraded modes of operation and fault
tolerance measures on the system aspects, effectiveness of the FDIR procedures and automated derivation of
observability requirements for effective diagnosability by FDIR.
Current TRL:
Algorithm
Target TRL:
Prototype
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
2012
18 months
Dossier0 Ref.: T7661
Consistent (H5)
7-03 - Spacecraft Power
TRP Reference:
T703-020EP
TD:
TD03
Title:
Investigations on avoidance of Solar Array thermal/electrical unbalance in power
systems equipped with Maximum Power Point Tracker interface.
Objectives
To define the boundaries of thermal/electrical unbalance in order to use MPPT schemes at their best
performances.
Description
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Description of Activities
A solar array/panel is formed by a number of sections in parallel, which are in turn formed by a number of strings in
parallel. Each string is provided with a series blocking diode, and is formed by a series of solar cells.
It is well known that the temperature dependance of open circuit voltage VoC and maximum power voltage Vmp of a
solar array cell are negative. If a MPPT system forces a solar array panel or section to work at the Vmp, and if, for any
reason, within the same panel or section one SA string transfers less power than the others, it will heat up more, since
more power "stays" locally in the string itself (e.g. it is not removed electrically).
Since the string becomes hotter, it will transfer even less power to the power system, possibly triggering further strings
to reduce their transferred power due to increased thermal differentials in the solar array/panel. The phenomenon
might evolve further until the string is disconnected from the power system due to the presence of the blocking diode.
It highly depends on the in-plane thermal condunctance of the solar array/panel.
Some minor, unexplained power difference during MPPT operation has been observed in Venus Express, that might
be reconducted to the thermal/electrical unbalance phenomenon
hereby described.
It is important to establish the boundaries of this phenomenon especially in relation with critical foreseen applications
such as, Sentinel 3 or Bepi Colombo where the phenomenon might be enhanced due to the high expected thermal
flux on the SA. The activity will will include developing a thermo-electrical model of a solar array, and validate it on the
basis of the test data from at least two different representative solar array/panel coupons subject torepresentative test
conditions to enhance as much as possible the thermal runaway phenomenon.
The model will then be used to identify the boundaries of the problem.
Deliverables:
Thermo-electrical model, reports and technical notes.
Current TRL:
TRL 1
Target TRL:
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 4
Application
Need/Date:
Contract Duration:
2011
12 months
Dossier0 Ref.: T-7814
N/A
TRP Reference:
T703-021EP
TD:
TD03
Title:
High Power Battery - Supercapacitor system study
Objectives
To compare supercapacitors, hybrid systems, high power lithium batteries and their impacts on the power
system, and identify potential applications for such technologies
Description
Future spacecraft may require a battery sustem able to provide bursts of high power (SAR, Lidar, 'agility'). A TRP
activity on "development of supercapacitors for space applications" ended in Dec 2006. Supercapacitors have a large
power density but a poor energy density (5Wh/kg). They can be used in hybrid systems combined with a lithium
battery to optimise the power system for energy and power. However, power conversion and management of such a
hybid may not be simple. High power lithium ion batteries are now available, and to be qualified for Vega TVCs.
An assessment of different technologies available (supercapacitors, hybrid systems, high power lithium ion batteries)
is necessary, together with the assessment of the potential applications of such technologies. The impacts of these
technologies on the power sub-system will need to be addressed also. A trade-off of the different technologies, for the
different applications identified will be performed.
Deliverables:
Report
Current TRL:
TRL 2
Target TRL:
Application/Mission: LIDAR, SAR misions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
2011
12 months
Dossier0 Ref.: T-7810
Consistent with "Battery" roadmap issue 1 revision 3 September
24 2006 (Activity F0 Requirement T-8062)
TRP Reference:
T703-022EP
Title:
Carbon Nanofibres for advanced Lithium-Ion Batteries
TD:
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Description of Activities
Objectives
Improving the rate capability of batteries, improving the low temperature charging capabilities, imnproving
the cycle life.
Description
This activity focuses on (partial) replacement of active carbon in Li-Ion batteries with carbon nanostructures, which , in
preliminary short tests, showed superior cycling behaviour compared with standard carbon materials used in the Li-Ion
batteries investigated so far at ESA. During the course of the activity small Li-ion demontrator cells shall be built and
validated by lab scale testing.
Deliverables:
Test data, selected prototype cells for eventual testing at the ESBTC.
Current TRL:
TRL 2
Target TRL:
TRL 3
Application/Mission: All EO, SCI, COMS S/C
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
2010
9 months
Dossier0 Ref.: T-7810
Consistent, and considering industrial requests as well
TRP Reference:
T703-023EP
Title:
Further Advanced Lithium Cell development
TD:
TD03
Objectives
To evaluate a new battery technology with an energy density > 300 Wh/kg.
Description
The current advanced lithium barrery activity is adressing improvements to lithium-ion in oder to reach 250 Wh/kg.
Other non-lithium-ion technologies such as Li-polysulphide, Li-air) are emerging for terrestrial applications and offer
specific energies in excess of 300 Wh/kg. Battery electrodes are also benefiting from the use of nano-size particles or
nano-caoatings. It is necessary to keep up to date with the latest developments and to evaluate rapidly any new
emerging technology interesting for space use, and keep the leading place of Europe in batteries for space
applications.
The activity will consist of: Evaluation of promising very high specific energy battery systems and their potential
application to space.
Deliverables:
Test Data, battery samples
Current TRL:
TRL 1
Target TRL:
TRL 4
Application/Mission: All S/C platforms
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
2010
18 months
Dossier0 Ref.: T-7810
Consistent with "Battery" roadmap issue 1 revision 3 September
24 2006 (Activity G2. Requirement T-7937. Looking beyond
Li-Ion)
TRP Reference:
T703-024EP
Title:
Development of Next Generation triple junction Cells & SCAs
TD:
TD03
Objectives
To improve the cost-effectiveness of solar cell technology
Description
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Description of Activities
The work performed in previous TRP contracts C15134, C18767 and C20761, has led to subsequent qualification and
use of fully European GaAs based solar cells with state-of-the-art performance (27.5% beginning of life, typically 24%
at end of life). However, a new generations of devices are under development both in Europe and from US
manufacturers and there remains considerable identified scope for cost-effective improvements (ie. the cost of
development is likely to be repaid in performance improvements and cost reductions).
The activity will perform both improvements of triple-junction cells and cells with more than three junctions. This will
include improvement of the components of the device (each triple-junction cell consists of three photovoltaically active
junctions linked electrically by two tunnelling diodes - more than thirty semiconductor layers in total) and optimisation
of the associated processes. For cells with >3 junctions, development of new test methods with illumination spectra
matched to the devices will also be necessary.
Deliverables:
Solar cell manufacturing; characterization/qualification documentation and hardware.
Current TRL:
TRL 2
Target TRL:
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
2012
18 months
Dossier0 Ref.: T-7805
N/A
TRP Reference:
T703-025EP
TD:
TD03
Title:
Manufacturing Technologies of ultra-thin GaAs based solar cells
Objectives
To demonstrate the feasibility of manufacturing ultra-thin solar cells
Description
Whereas the previous activity (T728-02EP) addressed the demonstration of very basic techniques for ultrathin solar
cells and selection of a viable concept in a lab environment, this activity is intended to address the manufacturing
aspects and characterization of the ultra-thin solar cells.
Deliverables:
Characterization and Pre- Qualification of next generation solar cells
Current TRL:
TRL 2
Target TRL:
Application/Mission: all missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
2012
24 months
Dossier0 Ref.: T-7806
N/A
TRP Reference:
T703-026EP
TD:
TD03
Title:
Solar cell development based on nano technology for new materials
Objectives
To improve the solar cell efficiency
Description
In order to increase efficiencies of solar cells beyond 33 % new technologies have to be explored. Amongst these new
technologies and also with good prospects to achieve this goal, are nanotechnologies such as quantum wells and
quantum dots. Previous studies have shown the potential to increase solar cell performance by implementing quantum
wells and quantum dots in solar cell structures.
This activity is a follow up on the TRP activity T604-06EP “Nanotechnology for space solar cells” that investigates the
impact on solar cell efficiencies by nanotechnologies.
The implementation of these technologies into an industrial solar cell manufacturing process is likely to demand
further R&D activities.
The activity focuses on the possibilities to implement promising nanotechnologies in current state-of-the-art space
solar cells. Impacts on industrialised processes shall be analysed.
Deliverables:
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Description of Activities
10 prototype of solar cell
Current TRL:
TRL 2
Target TRL:
Application/Mission: all missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
>2012
18 months
Dossier0 Ref.: T-7806
N/A
7-04 - Spacecraft Environment & Effects
TRP Reference:
T704-027EE
Title:
Highly miniaturised radiation monitoring
TD:
TD04
Objectives
Design, manufacture and test a monolithic radiation detector integrated on a single chip, including energy
deposition discrimination, counting, accumulation and processing. Two possible designs for the
single-chip radiation monitor will be investigated.
Description
Two possible designs for a single-chip monolithic radiation monitor will be evaluated: the first design based on Active
Pixels Sensors and the second on silicon sensors (e.g. silicon micro strips). This radiation monitor will have
capabilities to discriminate between different parts of the LET (energy deposit) spectrum. After having identified the
best technology and architecture, a prototype will be manufactured and tested. The prototype will have standard
interfaces to spacecraft data handling systems so that it can be treated as a source of housekeeping telemetry. Such
a highly-miniaturized radiation detector will be beneficial for all ESA and commercial missions, providing a reliable
real-time monitoring of the radiation environment at specific spacecraft locations. This can be useful for alerts in case
of very intensive radiation fluxes (e.g. during solar storms) to take counter-measures to protect sensitive parts and of
particular importance for astronauts' radiation safety. The very small size (<1 cm3) and weight (<20g) allows placing
many chips at different critical locations or stacking them in a telescopic configuration to extend the energy/spatial
resolution. This single chip detector can be used to correlate in-flight Single Events Effects occurrence with the
measured LET spectrum. The activity will produce a number of prototypes of the monitor chip architecture. Preliminary
characterisation of the prototype will also be carried out in an appropriate radiation environment.
Deliverables:
The activity will produce the selected architecture, relevant detailed design, breadboard, and test results
Current TRL:
TRL 1
Application/Mission: All Missions\
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
TRL 3
Application
Need/Date:
Contract Duration:
2011
12 months
Dossier0 Ref.: T-18
Radiation environment modelling and in orbit measurement (1st
Sem. 2005)-Consistent with activities: Technology for
miniaturisation/highly miniaturised monitor.
TRP Reference:
T704-028EE
TD:
Title:
Reduction of margins in radiation analysis
TD04
Objectives
To perform the detailed analysis of surces of error and margins in radiation environments and effects
evaluation processes. Development of models and methods to reduce margins.
Description
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Description of Activities
Radiation environment and effects evaluation processes for projects are subject to uncertainties and statistical
variations which are accounted for through margins. However, the establishment of margins is highly problematic in
many projects. They are not always rationally established and can lead to significant over-design and cost (too high
margins) or high risk (too low margins). A complete analysis of sources of margins in calculation of environment
(modelling methods, data analysis, instrumental issues) and effects (shielding, dose, SEE) will be performed. The
output of the activity will be substantially improved environment and effects models, tools and methods for applying
margins in satellite designs.
Deliverables:
Software based on updated models and methods
Current TRL:
Algorithm
Application/Mission: All Missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Beta Version
Application
Need/Date:
Contract Duration:
2010
12 months
Dossier0 Ref.: T-10, T-19, T-7765
Radiation test facilities and engineering tools (1st. sem 2006)
consistent with activities E1: ensure access to validated tools, D2:
coordinated radiation effects, C1: enhanced capabilities of tools
TRP Reference:
T704-029EE
TD:
TD04
Title:
Simplified standard MEO/GEO tools for spacecraft charging
Objectives
To develop a tool for the evaluation of surface electrostatic charging that can be used without specialized
training and which guides user in making appropriate choices for GEO/MEO…. application.
Description
A user-friendly tool will be developed using software components from the SPIS (Spacecraft plasma Interaction
Software). It will include standard plasma environment, material property lists, and will alllow 3-d geometrical models
to be created. The tool will allow for a high degree of automisation of parameters needed to make the code run but
which do not reflect real phsical inputs, e.g. mesh resolution, particle weights, time-steps. The code will be
extensively verified using available data. User and data interfaces will also be produced.
Deliverables:
Software for MEO/GEO…. charging calculation and related data and user interfaces
Current TRL:
Algorithm
Target TRL:
Application/Mission: All GEO, MEO, PEO, Jupiter
Open source
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Beta Version
Application
Need/Date:
Contract Duration:
2010
18 months
Dossier0 Ref.: T-8395
Subject not harmonised
TRP Reference:
T704-030EE
TD:
Title:
Update of meteoroid flux model
TD04
Objectives
To update an existing preliminary interplanetary meteoroid model. This shall be done by implementing
identified enhancements and by improving the user interface and computational speed of the model.
Description
The main activities of this study are the development of an enhanced meteoroid population model for interplanetary
space. The model shall be applicable for distances between 0.3 AU and 10 AU from the sun. It shall cover as a
minimum the size range 10E-12 g to 1 g and include the directional and velocity distribution of meteoroids. As a
starting point the IMEM model shall be used, which will be provided by ESA. The activity shall include the validation
and enhancement of the underlying physical model parameters, assumptions and simulation procedures. The
efficiency of the computational algorithms shall be improved. The final model shall be validated against measurements
near Earth (e.g. from meteor observations and impact studies of retrieved hardware) and against other models. A user
friendly interface shall be developed. The model shall allow the calculation of incident fluxes for user specified
meteoroid mass ranges, trajectories (Earth, planetary or interplanetray) and spacecraft surface orientations.
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Description of Activities
Deliverables:
The model software; corresponding software documentation; input and output files of test cases.
Current TRL:
Algorithm
Application/Mission: All missions
Operational SW
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Beta Version
Application
Need/Date:
Contract Duration:
2009
18 months
Dossier0 Ref.: T-17
Subject not harmonised but activity consistent with work plan of
NoC Coordination Group on Space Debris
7-05 - Space System Control
TRP Reference:
T603-04ES
TD:
TD05
Title:
Robust Model Predictive Control (MPC) for Space Constrained Systems
Objectives
The objective is to develop a Robust Model Predictive Control (MPC) control design toolbox suitable to
analyse critical space mission scenarios.
Description
Model Predictive Control (MPC) is a widely used and well accepted controller design method in the process industry.
The most appealing feature of this type of control is its ability to cope with constrained systems. Thanks to the
combination of new research results, increasing processor and FPGA performance capabilities and recent progresses
in embedded MPC technology it has recently been possible to develop MPC controller for fast dynamics applications
such as automotive and aerospace. Finally, as a variety of performance goals such as optimal path planning, obstacle
avoidance and dynamic safety margin can easily be incorporated in the MPC controller, MPC technology is well suited
for space applications requiring a high level of autonomy. The aim of the proposed activity is to evaluate, benchmark
and demonstrate the benefits of robust Model Predictive Control on two yardstick space applications, one of them
being a planetary rover locomotion. The real-time performance (CPU, memory, etc.) of the respective MPC based
wheel-slip and motion planning controllers will be assessed, and a MPC software framework (design methodology,
chain tool, algorithms library, study cases, standard test elements) for the development, validation and verification of
embedded MPC controller for space applications will be developed.
Deliverables:
Robust MPC control design toolbox including benchmark models and documentation (technical data package,
summary report, and abstract).
Current TRL:
Algorithm
Target TRL:
Application/Mission: all
Operational SW
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Beta Version
Application
Need/Date:
Contract Duration:
24 months
Dossier0 Ref.: T-7817
N/A
TRP Reference:
T705-031EC
TD:
Title:
Star Tracker on a chip pre-development (Phase 1)
TD05
Objectives
The objective is to perform a pre-development of a star tracker on a chip and get proof-of-concept.
Description
The Sensor on a chip activity has shown the feasibility of a 75g, 0.2 watt, 30 arcsecond accuracy fully autonomous
star tracker with all functionality implemented on a single chip. Several key unknowns however still exist and can only
be verified by test. These include: Optical quality acheivable, on chip NVM behaviour, radiation behaviour of key
functions, noise cross talk and power management.
Phase 0 of this predevelopment shall concentrate on demonstrating the optical elements including the bonding to the
silicon substrate and environmental testing.
Deliverables:
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TRP Work Plan 2008-2010
Description of Activities
Test optics
Current TRL:
TRL 2
Application/Mission:
micro satellites, telecom, EO,
landers
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
TRL 2
Application
Need/Date:
Contract Duration:
2012
18 months
Dossier0 Ref.: T-7815
Consistent with "AOCS Sensors and Actuators" Oct 05 (Star
Trackers AIM F)
TRP Reference:
T705-032EC
TD:
Title:
Accelerometer for IMU feasibility demonstrator
TD05
Objectives
The objective is to develop a accelerometer demonstrator for a low cost IMU.
Description
The purpose of the activity is to develop an accelerometer demonstrator to be implemented as the accelerometer
component of a low-cost IMU for vehicle applications. This development will rely on the the conclusions from
'Definition of accelerometer needs for an IMU', which aims at defining the technical specification and a preliminary
design for the accelerometer, covering a wide scope of space applications including, but not limited to, landers, rovers,
re-entry vehicles, interplanetary probes, launchers. MEMS technology is expected to be a relevant technology for this
development.
Deliverables:
Elegant breadboard
TRL 2-TRL 3
Current TRL:
Application/Mission: all missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
TRL 4-TRL 5
Application
Need/Date:
Contract Duration:
2010
15 months
Dossier0 Ref.: T-7818
Consistent with "AOCS Sensors and Actuators" Oct 05
(Accelerometers AIM A)
TRP Reference:
T705-033EC
TD:
TD05
Title:
Feasibility of GNSS sensors for AOCS applications in GEO and higher altitudes
Objectives
The objective is to demonstrate the feasibility of GNSS sensors for AOCS applications in GEO and higher
altitudes.
Description
In this study the feasability of Global Navigation Satellite System (GNSS) receivers for the usage of AOCS orbit
sensors in GEO and higher altitudes (lunar transfer) shall be investigated (autonomous orbit control, ephemeris
generation and attitude control). The GNSSs to be considered shall be Galileo, GPS Block 2 and also the new GPS
Block 3. The simulation environment shall be as realistic as possible and use HW-in-the-loop tests where suitable.
Especially the performance improvement when using additionally to the main lobes also the side lobes shall be
investigated as well as single and dual frequency use. The activity shall specify the final AOCS performance as well
as the GNSS sensor, and should provide input for the future definition of the Galileo space service volume users.
Deliverables:
1. Performance results from high accuracy simulation and evaluation
2. AOCS orbit sensor specification (including GNSS sensor)
3. Space Service Volume Requirements
TRL 3-TRL 4
Current TRL:
TRL 2-TRL 3
Application/Mission:
Telecom, Navigation, Earth
Observation
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-7821
Target TRL:
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Application
Need/Date:
2010
18 months
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Description of Activities
Consistency with Harmonisation
Roadmap and Conclusions:
N/A
TRP Reference:
T705-034EC
TD:
TD05
Title:
Active and passive disturbance isolation for high accuracy control systems
Objectives
The objective is to study an optimised solution combining active and passive isolation systems.
Description
Sub microradian line of sight stability together with stringent attitude restitution requirements lead to the need of better
rejection of disturbances. Reaction wheels are still the most efficient actuators for many applications and other
disturbances (cryocoolers for example) cannot be avoided.
In particular, for Earth Observation and Science missions, reaction wheel microvibration perturbation is an obstacle to
stability pointing improvement. Several solutions have been sketched so far such as new units techniques (low noise
magnetic bearing reaction wheel), active and passive microdynamics control, isolators... Considering current maturity
of these solutions, a combination of active and passive solutions seems promising to isolate, damp and/or control the
perturbation: active control of low frequency perturbation (e.g. reaction wheel first harmonics) combined with passive
isolation well above the AOCS control bandwidth. The interaction with the AOCS control loops stability will be
analysed. An alternative solution with active / passive isolators close to the instrument line of sight will also be
considered but this is more specific of each mission.
Most promising solutions shall be breadboarded and tested against representative scenari.
Deliverables:
1) TN
2) simulation models
3) demonstration platforms
TRL 3-TRL 4
Current TRL:
TRL 2
Application/Mission:
SCI/EO missions (with stringent
Contract Duration:
disturbance isolation requirements)
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
TRL5 by 2010-2012
15 months
Dossier0 Ref.: T-8384
N/A
TRP Reference:
T705-035EC
Title:
Versatility of Filtering Techniques in Non-Linear Programming Optimization
TD:
TD05
Objectives
The objective of this study is to explore an alternative theory, mainly studied and promoted by Dundee
University (Pr. Fletcher), which would use advanced filtering techniques for NLP solvers. The idea is to
iteratively evaluate progress during an optimization by checking the development of a set of criteria,
inspired by composite objectives.
Description
In recent years the optimization research community has put major emphasis on the development and implementation
of interior point methods for NLP solvers. However, in the light of practical application cases, for instance trajectory
optimization or launcher design optimization, this trend does not seem to be the best suited method, since the
composition of the set of active inequality constraints is rather static, especially, for qualified initial guesses. Therefore,
alternative methods need to be studied.
The primary task of the study is to determine the characteristics of an NLP solver for space applications based on
filtering techniques. The findings shall be practically demonstrated and illustrated by applying testing of preliminary
solver designs on a number of optimization problems that are representative of typical space applications.The
following tasks would be included:
- Assessment of filtering techniques for space centric NLP optimization evaluation of the individual qualities (theory)
- Use of a preliminary filter implementation to compute a number of space optimization problems
- Description of the basic concept and analysis of benefits
- Prototype the algorithms with the target of obtaining a proper a reliable benchmarking of the benefits obtained
Deliverables:
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TRP Work Plan 2008-2010
Description of Activities
1) TN
2) application to study cases
3) Prototype of filtering algorithms
Current TRL:
TRL 2
Target TRL:
Application/Mission: All
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3-TRL 4
Application
Need/Date:
Contract Duration:
10 months
Dossier0 Ref.: T-7817
N/A
TRP Reference:
T705-036EC
TD:
TD05
Title:
Mathematical Optimisation Methods for Concurrent Early Design of Trajectories,
Propulsion, and Aerothermodynamics
Objectives
The objective of this study is to explore the feasibility and benefit of a co-design and optimisation at an
early stage to increase design efficiency and cut cost. Space Transportation vehicle conceptual design is
today separated from trajectory optimization. Due to the high interaction between trajectory selection and
aerothermodynamics & propulsion subsystems, this process requires much iteration prior to fulfilling the
design requirements. This traditional approach is highly time consuming and does not guarantee the
finding of the optimal solution for the vehicle design.
Description
The tasks of this study will be to
1) Design, and develop the mathematical models for conceptual concurrent design of trajectory, propulsion and aero
disciplines. The mathematical models shall be valid for the commonalities of all addressed discicplines.
2) Obtain key parameters and constraints from the concurrent models of the previous phase as to be inserted into an
appropriate NLP solver.
3) Prototype the algorithms that will lead to early optimal design inside a suitable optimizer
Deliverables:
Application to study cases for a heavy launcher and a re-entry mission, SW prototype of mathematical algorithms
Current TRL:
TRL 2
Target TRL:
Application/Mission: all
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3-TRL 4
Application
Need/Date:
Contract Duration:
10 months
Dossier0 Ref.: T-7816
N/A
TRP Reference:
T705-037EC
Title:
Enhanced LFT Toolbox
TD:
TD05
Objectives
The objective is to develop generic modelling software tools for worst case analysis in order to improve
the Validation & Verification cycle. The tools allow worst case stabilty and performance robustness
analysis for systems in LFT form (Linear Fractional Transform). LFT forms are special model
representations that allow to iclude uncertainty models. Software modules for the generation of LFT
uncertainty models for space systems dynamics reflecting flexible models & sloshing satellites including
subsystems such as actuator, sensor and environmental models. The toolset shall enable the generation
of LFT uncertainty models of variable complexity and granularity depending on the analysis requirements.
The S/W toolset shall contain model validation tools, model manipulation and reduction tools to enable
worst case efficient and reliable worst case V&V analysis.
Description
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TRP Work Plan 2008-2010
Description of Activities
It is proposed to develop LFT libraries for generic space systems that allow to compose and assemble complex
uncertainty models for the purpose of worst case analysis using Mu-type of analyses. The activity shall include at a
minimum the following tasks:
• Perform an analysis of existing LFT modeling tools in order to set up research direction towards efficient LFT
modeling approach
• Perform a critical analysis for an industrial LFT framework that enables to be employed during the entire
development cycle of a space systems.
• Development of S/W LFT libraries for satellite/rendezvous/Launcher/RLV dynamics including all necessary models
(MCI offset, flexible modes, sloshing, actuators nonlinearities, sensors models including noises, Digital effects and
distortions, System and component degradation mechanism to faults, etc) including model validation tools
• Benchmarking of LFT models using Worst Case Analysis using advanced Mu-analysis tools on inustrial appications
and comparision new V&V (verification & validation) process with traditional V&Vprocess
Deliverables:
Generic, reliable and validated LFT uncertainty models for space systems in S/W libraries for LFT models. TN's
describing new approaches for uncertainty modeling principles. Space applications demonstrating efficient worst case
and V&V procedures.
Current TRL:
Target TRL:
Application/Mission: all
Open Source
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Beta Version
Application
Need/Date:
Contract Duration:
12 months
Dossier0 Ref.: T-7817
N/A
TRP Reference:
T705-038EC
TD:
Title:
Maturation of Robust LPV Techniques
TD05
Objectives
Extension of the LPV (Linear Parameter Varying) framework (process methodology, algorithms & tools )
for modeling, analysis and design for safety critical GNC systems applied to satelllites, Launchers, RLV's
and rendezvous missions. Enhance and reduce Validation & Verification effort and increase flexiblity for
nonlinear robustness analyses by providing mature modeling and analysis tools for the validation and
verification for nonlinear control laws. Develop efficient reconfiguarble LPV control strategies for
uncertainties, disturbances and faults including LPV detection as support to robust autonomous GNC
functions. Implementation and numerical issues for on board GNC implementation of the reconfigurable
LPV concept are investigated. LPV design process enhancements for on board autonomous GNC
performance, robusntess and safety.
Description
Further process integration is aimed by demonstrating the implementation aspects of LPV techniques over the entire
design process until implementation of LPV GNC on an onboard computer. Investigated and demonstrated
reconfigurable LPV control in support for autonomous space GNC systems. Adaptive structure and multi rate LPV
control shall be investigated in the face of variable computational resources, on-line changing needs, disturbances
and uncertainty profiles. The variable performance and robustness issues will be addressed in a multi objective
fashion to improve the trade-off in the achievement of simultaneously competing objectives. The validation and
verification procedures for the enhanced version of LPV systems must be refined and improved.
In order to achieve the objectives the activity shall perform:
• Detailed requirement analysis and trade-off analysis for enhanced LPV modeling, analysis, design, validation &
verification strategies
• Development of LPV S/W tools
• Application of the various LPV technology components to industrial GNC problems
• Implementation of LPV concepts in real-time systems
• Validation and Verification by means of software in the loop experiments
• Study synthesis
Deliverables:
The outcome is a robust and fault tolerant LPV GNC development process (methodology, algorithms & tools ) for real
time applications demonstrated on industrial applications. Maturated LPV software with implementation and improved
designs on industrial space applications showing the improved design process, V&V. Increased on board safety.
Current TRL:
TRL 1
Target TRL:
TRL 3
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Application
Need/Date:
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TRP Work Plan 2008-2010
Description of Activities
Application/Mission: all
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Contract Duration:
12 months
Dossier0 Ref.: T-7817
N/A
TRP Reference:
T705-039EC
TD:
Title:
Space MPC-On-a-Chip Building Blocks
TD05
Objectives
Autonomous RVD requires a guidance and control unit that implements the on-board MPC (Model
Predictive Control) GNC flight software for attitude and orbit control during RVD experiments. The MPC
guidance and control unit includes flight management function for mode control, fault tolerance and
trajectory planning and reconfiguration to realize the autonomous RVD function. In MPC the control
actions are calculted on-board and necessitate on-line state estimation, online model generation and fault
detection and isolation functions. This activity is concerned with the set up of a software infrastructure and
building blocks enabling implementation and hardware acceleration of model predictive control MPC
implementations on Field-Programmable Gate Arrays (FPGAs).
FPGA programmable MPC software libraries with underlying components will allow to develop a
methodology for the design of reconfigurable GNC hardware architectures for MPC for future autonomous
space applications.
Description
Model predictive control allows to develop online control solutions for complex nonlinear multivariable systems with
optimality guarantees incorporating physical, safety and performance constraints making this technique very suitable
for autonomous GNC technologies. To enable the application of MPC for real time applications the limitations imposed
by the computation speed with conventional processors can be overcome by exploiting code parallelisation, pipelining
as well as flexible numerical representation capabilities given with FPGAs solving the constrained nonlinear
optimization problems on line at orders of magnitude faster than it is until now possible. MPC libraries must be
developed to implement online numerical constrained optimization problems, as well as libraries implementing online
MPC support function (plant dynamics updates, state etimators, adaptive filters, detections filters and remodelling
dynamics for reconfiguration needs) within the FPGA architecture. Detailed GNC hardware trade-off study shall be
conducted to establish computational load involved with autonomous GNC applications using latest results from
hardware development and implementation strategies and methodologies of massively parallel constrained
optimization algorithms on FPGAs. The following steps have to be investigated:
• Perform a trade off study for the most suitable hardware dedicated formulations of numerical optimization programs
solving the MPC problem.
• Develop Libraries for MPC implementing customized optimization algorithms and MPC utilities.
• Perform FPGA based MPC software design and coding, software integration and testing
Deliverables:
Software Libraires for automatic generation of hardware description language (VHDL/Verilog/Handel-C)
implementation of MPC based GNC system and TN's describing the MPC implementations
Current TRL:
TRL 1
Target TRL:
Application/Mission: all
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 4
Application
Need/Date:
Contract Duration:
12 months
Dossier0 Ref.: T-7817
N/A
7-06 - RF Payload Systems
TRP Reference:
T603-40ET
TD:
TD06
Title:
Evaluation and validation of electromagnetic software, test facilities and test
standards in Europe to predict and test RF breakdown and passive
intermodulation (PIM)
Objectives
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Description of Activities
Identifying the European needs in terms of prediction/simulation tools to avoid RF breakdown and PIM in
space hardware; evaluate and recommend, among the major existing/available software packages, the
best options.
Description
This activity shall start with a survey among the European Space Industry to identify the European needs in terms of
prediction/simulation tools to avoid RF breakdown and PIM in space hardware. The activity will propose a number of
existing and available software packages best matching these needs and recommend which ones could be the
baseline in Europe for future software developments in the field. The selection shall be done comparing prediction
data using the proposed packages with test results on a number of RF passive devices defined during the first phase
of the study.
To achieve this, the contractor shall also identify test facilities in Europe technically capable to perform high power RF
tests (Power handling, Multipactor and Corona) and passive intermodulation (PIM) on space hardware. A number of
waveguide test samples (golden samples) shall be produced and carried to the different test sites for the evaluation of
their facilities and test procedures. This activity has been proposed in the frame of the “power RF measurements”
document, presented by ESA during the Harmonization meetings in 2004.
Deliverables:
Golden test samples for each frequency band. Documentation.
Current TRL:
N/A
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
N/A
Application
Need/Date:
Contract Duration:
Standard >2012
24 months
Dossier0 Ref.: Consistent with “Power RF measurements” document, presented
by ESA during the Harmonization meetings in 2004.
TRP Reference:
T706-040ET
TD:
TD06
Title:
Cryptographic Pseudo-noise codes and related acquisition techniques for direct
sequence spread spectrum transponders
Objectives
The main objective is to determine cryptographic Pseudo-noise (PN) codes that provide a protection
against the traffic analysis threat. A secondary objective is to improve the anti-jamming protection
provided by current spread spectrum transponders that use linear PN sequences.
Description
The aim of the proposed activity is to evaluate, benchmark and demonstrate the benefits of robust Model Predictive
Control on two yardstick space applications, one of them being a planetary rover locomotion. The real-time
performance (CPU, memory, etc.) of the respective MPC based wheel-slip and motion planning controllers will be
assessed, and a MPC software framework (design methodology, chain tool, algorithms library, study cases, standard
test elements) for the development, validation and verification of embedded MPC controller for space applications will
be developed.
Deliverables:
Technical Notes, Simulation reports and Final Report
Current TRL:
TRL 1
Target TRL:
Application/Mission: EO, Telecom, Galileo
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
2010-2011
12 months
Dossier0 Ref.: T-8379, T-7784
Subject not harmonised so far 2007 Harmo dossier in preparation.
Consistent with “TT&C transponders and Payload Data
Transmitters” Technical Dossier.
TRP Reference:
T706-041ET
TD:
TD06
Title:
Wireless integrated communications and navigation system for formation flying
missions
Objectives
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Description of Activities
To study, specify and simulate the RF wireless technology allowing navigation and high data rate
communications for a formation flying (FF) mission with multiple satellite. The activity will explore existing
standards and technologies from the terrestrial wireless techniques, and define the adaptation to the FF
space missions. The activity also includes performance assessment based on SW simulations
Description
Formation flying (FF) missions are envisaged in different space domains to enable new missions that cannot be
performed by conventional single spacecraft (e.g. interferometer with large baseline or telescopes with large focal
length).
The RF inter-satellite navigation/communication link will exchange data between different spacecraft (distributed
architectures and sensors) and give the possibility to exploit the inherent redundancy inside a formation and the
optimisation of the resources (centralised vs decentralised data processing). This is only possible with inter-satellite
links of Mbps. The RF metrology unit developed by (former) Alcatel Space in the frame of previous ESA activities (
contract 15511/01/NL/EC) does incorporate a communications link at only low bit rate (up to 4 kbps).
Ensuring a reliable inter-satellite navigation/communication link (ISL) at high rate allows the formation to operate
together as one "virtual satellite" and strengthens the ability of multiple small satellites flying in formation to perform
missions traditionally carried out by single, larger satellites. The architecture for each spacecraft could be much
simpler as the ISL opens the possibility to share resources (like memory and bandwidth) between the spacecrafts and
to increase autonomy and reliability.
The scope of the proposed activity is to identify and analyse RF technologies allowing navigation and communications
using a single RF signal, aimed at a formation flying missions with multiple spacecrafts. Secondly, a performance
assessment based on SW is proposed to prepare the future devices allowing easy interactivity between satellites of a
same formation.
A preliminary work breakdown is given below.
1- Selection of the frequency in accordance with regulations of ITU for inter-satellite links.
2- Analysis of the terrestrial wireless techniques for formation flying applications in order to take benefit from the
existing standards and technologies (System-on-chip…)
3- Adaptation of chosen candidate for space formation flying mission in terms of communications and navigation. The
design choice shall be driven by very low power consumption and mass, and allowing components integration.
4- Performance analysis of the proposed system in terms of communications and navigation taking into account
multiple spacecraft formation.
5- Definition of the hardware and software technologies parts (RX and TX)
Deliverables:
Final report including specifications technology trade-off and design performance assessment.
Current TRL:
TRL 1
Target TRL:
Application/Mission: Formation Flying Missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
2010
12 months
Dossier0 Ref.: T-783, T-7747
Consistent with Formation Flying (FF) radiofrequency (RF)
Metrology Technology dossier. Will be harmonised in 2nd
Semester 2007.
TRP Reference:
T706-186ET
Title:
Millimetre-wave measurements at MilliLab
TD:
TD06
Objectives
Support the Millilab test facility by means of a 5years frame contract (2008-2012)
Description
MilliLab was established in 1995 as a joint institute between Technical Research Centre of Finland (VTT) and
Technical University of Helsinki (TKK). A work order contract (no. 11655/95/NL/PB) was awarded in December 1995
to MilliLab, according to which MilliLab has acted as the ESA External Laboratory on Millimetre-Wave Technology. Its
main task has been to establish and maintain a state-of-the-art measurement and characterisation facility for
mm-wave components, circuits, and systems, and to make these services available to European companies and
institutes. During the period 1995-1999 ESA supported MilliLab with an amount of 1 MEUR for upgrading the
measurement facility and for setting up of the measurement services. In addition, significant national support was
provided by Tekes and the parent organisations VTT and TKK.
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Description of Activities
Since the initial period, further development of the facilities and all the investments have been the responsibility of VTT
and TKK. ESA funded activities at MilliLab have consisted largely of the utilisation of the facilities in specific
measurement and modelling tasks, often in connection with other ESA activities. MilliLab has also acted as a
sub-contractor or service-provider in ESA activities. In addition to space-related activities, MilliLab has been actively
involved in many national and international development activities for terrestrial applications, and has provided direct
measurement services to the industry.
Driven by the needs of the future mm-wave instruments for Earth observation, several technology activities are being
carried out and will start in near future for the development of European mm-wave components and subsystems, with
the funding from TRP, GSTP and Earth Observation Directorate. The present procurement aims to set up a
contractual framework for the utilisation of the services and facilities of MilliLab in support of ESA technology
programmes. The development efforts for Schottky devices and modules for frequency conversion and multiplication
at 664 GHz have just started in several European institutes. The first task of MilliLab is foreseen to be the
characterisation and modelling of these components and modules. The independent characterisation and modelling
facility of MilliLab is also foreseen to be utilised in support of the development of other mm-wave components and
modules, like HEMT devices and MMICs for low noise and power amplification, and mm-wave detectors.
Deliverables:
Test report
N/A
Current TRL:
Target TRL:
Application/Mission:
SW Clause :
N/A
Application
Need/Date:
Contract Duration:
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
N/A
60 months
Dossier0 Ref.: N/A
7-07 - Electromagnetics Technology
TRP Reference:
T707-042EE
TD:
TD07
Title:
Electromagnetic field prediction tool for solar panels
Objectives
Objective is to develop a simulation tool for the prediction of electromagnetic fields generated by solar
panels
Description
Many EO and scientific satellites embark magnetometers and electromagnetic sensitive instruments (e.g. bolometers,
sounders) that pose severe constraints on the electromagnetic cleanliness of the entire system. The solar panels (SA)
are known to be one of the main sources of electromagnetic disturbances and unfortunately no simulation tools are
available to assist the engineers in the verification of SA compatibility with the overall system..
As opposed to units like latch valves, thrusters and batteries, the magnetic field generated by solar panels cannot be
measured and easily controlled throughout the entire development phase. The ability to estimate, analytically and/or
numerically, the AC and DC magnetic fields generated by the SA would improve the accuracy and the reliability of the
estimate of the overall magnetic field, avoiding late problems fixing that necessarily call for design and manufacturing
modifications.
Similarly the ability to predict the electric field generated by SA to frequencies up to few MHz is also of paramount
importance to assess the solar panel compatibility with susceptible payloads like sounders.
This activity will entail:
1.- The developement of an INPUT interface (geometry descriptor) able
(i) to define SA sections' layout
(ii) to define sections wiring
(iii) to input SA current waveform (time domain) with various regulation systems
(iv) to account for 3D mutual positioning between SA and S/C structure
2.- The development of a SOLVER able
(i) to compute the current to electromagnetic field transfer function
(ii) to predict the electromagnetic field at any location (3D) within a specified volume
3.- The developement of an OUTPUT interface
4.- Tool validation by measurments on test samples
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Description of Activities
Deliverables:
Simulation tool
User manual and relevant technical notes
Test sample and relevant reports
Current TRL:
Algorithm
Target TRL:
Application/Mission: EO and Science S/C
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Beta Version
Application
Need/Date:
Contract Duration:
2010
24 months
Dossier0 Ref.: T-50
Not included in harmonization but consistent with EMC Dossier
TRP Reference:
T707-043EE
TD:
TD07
Title:
Advanced shielding techniques for spacecraft harness
Objectives
Objective is to study and characterize different methods of shielding and connector types based on
dedicated measurements for representative test cases. Selection criteria and guidelines will constitute the
output of the study.
Description
Today there is still a lack of knowledge and universal agreement on the selection and the effectiveness of various
shielding methods and their implementation to attain built-in EMC compatibility at system level. This is particularly true
when constraints of weight, cost and implementation efforts are accounted.
In a previous ESA study (contract number 14455/00/NL/WK ), a limited number of operative solutions have been
explored and assessed on the basis of measurements of selected test cases. Though correct in the methodology the
approach followed in the abovementioned study has permitted the characterization only of a small number of solutions
over a limited frequency range.
The variety of targets (e.g. magnetic cleanliness, electric cleanliness) presented by different satellites together with the
introduction of new materials call for further analytical and experimental investigations of the shielding techniques
nowadays available.
The results of the study will form a sound and consolidated basis for the selection of the optimal shielding solution
which is not currently available.
The activity consists of:
1.- Analysis of the results from the previous study
2.- Definition of representative test cases of the techniques nowadays available
3.- Analytical proof of concept for shielding efficiency of the selected test cases w.r.t. different shielding targets
4.- Verification by measurements
5.- Definition of selection criteria and guidelines
Deliverables:
Reports with technical findings
Measurement Report
Technical note with guidelines and selection criteria
Test samples
Current TRL:
TRL 1
Target TRL:
Application/Mission: All Spacecraft
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
2011
18 months
Dossier0 Ref.: T-50
Not included in harmonization but consistent with EMC Dossier
TRP Reference:
T707-044EE
TD:
Title:
Reverberating chambers
TD07
Objectives
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Description of Activities
Assess the viability of performing radiated tests in stirred mode chamber at unit and subsystem level
targeting reduction of cost and testing time.
Description
Radiated emissions and, mainly, susceptibility tests constitute an expensive element in the overall qualification of any
satellite. The relevant expensive facilities and the long test time impose a cost burden to EMC development and
testing especially to Small-Medium Enterprises. Despite these costs, such tests are afflicted by inherent large
uncertainties in the results.
A cost effective alternative to an anechoic chamber in the frame of radiated verification is the use of stirred mode
reverberation chamber that is not yet used in the space Industry domain.
The stirred mode chamber is much cheaper in construction than conventional EMC chambers. It requires only basic
EMC instrumentation, less RF power to achieve high field strengths compared to conventional methods used by
Space industry.
It is therefore surely affordable even by Small-Medium Enterprises, which would reach autonomy in EMC testing with
the obvious business benefit.
This activity will entail:
(i) Study of the state-of-the-art of the reverberating chambers techniques
(ii) Study of the viability of performing radiated tests in stirred mode chambers in the space Industry domain,
assessing costs and programmatic implications.
Deliverables:
Technical report with the assessment of applicability to space domain including design specifications
Current TRL:
TRL 1
Target TRL:
Application/Mission: All Spacecraft
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
2012
18 months
Dossier0 Ref.: T-53
Not included in harmonization but consistent with EMC Dossier
TRP Reference:
T707-045EE
TD:
TD07
Title:
Advanced grounding rail concepts for satellite applications
Objectives
Theoretical and experimental study of grounding solutions alternative to flat grounding rails for CFRP
structures.
Description
CFRP S/C honeycomb structures are generally equipped with flat grounding rails to guarantee a common reference
ground. Recent studies (contract 18985/05/NL/JA) have proven that in the high frequency range the conductivity of the
CFRP structure is sufficient to provide the functionality of the grounding rails. Low frequency fault currents can be
routed, if needed, by simpler wires or other solutions (e.g. metallised surfaces or embedded copper meshes).
Technical solutions alternative to flat grounding rails shall be explored in this activity with the objective of achieving
weight reductions and much simpler and more flexible S/C design.
This activity will entail:
1.- Definition of alternative grounding concepts (e.g. wires, conductive surfaces)
2.- Theoretical and/or numerical analysis of new concepts
3.- Design and manufacturing of test samples
4.- Experiments with different concepts on breadboard and demonstrator
Deliverables:
Technical notes with experimental and theoretical findings. Test samples, breadboard and demonstrator. Guidelines
for selection of grounding concept w.r.t. to operational configuration (frequency, power etc.)
Current TRL:
TRL 1
Application/Mission: All Spacecraft
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
TRL 3
Application
Need/Date:
Contract Duration:
2010
18 months
Dossier0 Ref.: T-50
Not included in harmonization but consistent with EMC Dossier
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Description of Activities
TRP Reference:
T707-046EE
TD:
TD07
Title:
Polarimetric (sub)millimeter wave antenna architectures
Objectives
The objective is to demonstrate a novel polarimetric concept that meets the stringent Eatrth Observation
and science requirements and to maintain the European lead. This study shall assess the scientific
impact, determine the topology of potential sub-millimetre wave polarimetry concepts for space and
identify the critical technologies.
Description
Polarisation properties of electromagnetic radiation can reveal important information about the emitting sources.
Examples in astronomy include the polarisation of the cosmic microwave background radiation, and the tracing of
magnetic fields in active galaxies and star-formation regions. Examples in Earth observation include the polarised
scattering by water ice particles in cirrus clouds, which allows determination of the size of these particles and therefore
how they affect the Earth's radiation budget. Submmw polarimetry has opened up a very active new field in science,
and a dedicated post Planck mission is considered.The payload will consist of many feeds in such a polarisation
configuration to retrieve all the relevant (Stokes) field parameters.
The study will identify the applications and/or mission scenarios for which sub-millimetre wave polarimetry technology
offers significant advantages. In particular, as a minimum, the following areas will be investigated: scientific objective
of the applications and/or mission scenarios (scientific products), system requirements, system concept, instrument
topology, technological risk, fabrication issues, critical technologies.
Deliverables:
Scientific products, alternative conceptual designs and performance analysis, critical technology development
roadmap
Current TRL:
TRL 1
Target TRL:
Application/Mission: Enabling ESA Missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 2
Application
Need/Date:
Contract Duration:
2015
18 months
Dossier0 Ref.: T-47
Consistent with "Technologies for (sub) millimeter wave passive
instruments" - 2nd Semester 2006. This activity is included in
Roadmap B1, activity "sub millimeter wave polarimetric concept".
TRP Reference:
T707-047EE
TD:
TD07
Title:
Feasibility of Very Large Effective Receiving Antenna Aperture in Space
Objectives
The objectives are to investigate the feasibility of developing a space-based very large effective aperture
array, to assess the technical benefits, cost aspects and to identify the associated technologies readiness
level.
Description
The continuous development of ultra-light weight deployable structures in space can lead to viable very large
space-based antenna apertures, based on the backside of the Moon as well as exploiting formation flying. The
wide-bandwidth advanced technological developments are useful in a range of applications as already noted in the
frame of the international Square Kilometre Array (Earth based project). Very large antenna systems, free flying with
formation flying focal units as well as satellite cluster are considered. Hybrid solutions further allow expandibility, in
combination with various solutions to realise large apertures with strong requirements on nulling out multiple
interfering sources. Applications include remote sensing and Deep Space communication potential additional to radio
astronomical tasks as well as extended mobile telecommunications capabilties. Candidate applications are
investigated, starting from a General Study result (contract 18378/04/NL/AG) on the subject, trade-offs and baseline
design investigations with critical aspect identification. Feasibility and readiness investigations are to be supported by
a road mapping, technology identification and mission support constraints.
Deliverables:
Study report with preliminary Design Development Plan
Current TRL:
TRL 1
Target TRL:
TRL 2
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Application
Need/Date:
2015
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TRP Work Plan 2008-2010
Description of Activities
Application/Mission: Enabling ESA Missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Contract Duration:
12 months
Dossier0 Ref.: T-7832, T-8399
Not included in harmonization but consistent with EEA array
dossier
TRP Reference:
T707-048EE
TD:
TD07
Title:
Design study for precision microwave radiometer in ESA Ground stations
Objectives
Analysis and preliminary design of precision radiometer for intregration in ranging stations.
Description
Passive radiometric receivers operating in the 20/30, 50 and 90 GHz frequency bands can provide information on the
atmospheric excess path length, but the current technology is not providing sufficient accuracy and stability for the
requirements imposed by ESA's most demanding science and earth observation missions. This study shall address
the technological issues which need to be solved in order to build a microwave radiometers suitable for integration in
ESA ground stations for Science and Earth Observations missions where precise ranging is required.
Deliverables:
Preliminary design of a radiometer for ESA ground stations, including RF front end, Antenna and tracking system.
Current TRL:
TRL 2
Target TRL:
Application/Mission: Science, EO, Nav
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
2009
12 months
Dossier0 Ref.: T-46
Not included in harmonization but consistent with Wave Interaction
Dossier
7-08 - System Design & Verification
TRP Reference:
T708-049SW
TD:
Title:
Space Simulation Reference Architecture
TD08
Objectives
The main objectives of the study are:
• Technological advancement: Bring simulators technology forward from the typically C++ and object
-orientated approaches that were popular in the 1990s to a model driven development approach.
• Decreased complexity. One of the main issues with current simulator development is that the mission
specific developments are highly integrated and complex software systems. A way to simplify their
implementation should be researched.
• Increased reuse: Allow more extensive reuse across missions and throughout mission phases.
• Decreased risk: Due to the high complexity of space simulators and their dependency on the space
elements to be simulated, the development is considered high risk. Reduced risk can be achieved by
increasing generality of models, reuse as well as allowing more flexibility to be put into the development
cycle.
• Reduced cost: If the risk and complexity of simulator development can be reduced, and reuse can be
extended, it is natural that a reduction in cost can be achieved as well.
Description
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Description of Activities
The study will address the entire development lifecycle of a space simulator within the overall space programme
context including:
1) Definition of a Space Simulator Reference Architecture. The architecture shall identify the main components of a
spacecraft simulator and their interfaces and capture them in a formal language.
2) Selection and application of suitable modern methods, such as a model-driven approach, in order to achieve the
study objectives.
3) Provision of rules and guidelines to guide the granularity of the components into which a simulator is broken down.
4) Define migration strategy for legacy models
5) Prove the suitability of the proposed Reference Architecture by selecting one or more reference missions or
infrastructure and making its simulation implementations throughtout the mission life cycle.
6) Analyse previous and current projects to show how the Reference Architecture would meet their needs or any
changes that would be required.
Deliverables:
The expected outputs are:
1. Reference Architecture captured in UML (delivered as XMI) and XML schema definitions targeting the E-40-07
standard.
2. Reference mission and its simulator implimentations
3. Technical notes documenting the space simulator reference architecture.
4. Prototype software, including test harnesses, data and procedures, and associated documentation.
5. Updated Requirement Specification of a full Reference Achitecture framework taking into account the leassons
learned from this study that can be used as starting point for developing an operational version from the prototype.
6. Study final report and presentation, summarising the experience, results and recommendations.
Current TRL:
Algorithm
Target TRL:
Application/Mission: all missions
Operational SW
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRP Reference:
T708-050SW
Title:
Conformance Kit
Prototype
Application
Need/Date:
Contract Duration:
2011
18 months
Dossier0 Ref.: T-7834
Consistent with "System Modelling and Simulation Tools"(B3)
TD:
TD08
Objectives
Develop a conformance kit to establish the conformance of simulation models as well as simulation
environments with the ECSS E40-07 standard.
Description
After the establishment of the portability standard (E40-07) it will be necessary to have the means to verify the
compliance of simulation artefacts with this standard. This enables the certification of suppliers of models and
environments for the space market.
This activity shall establish a test harness and associated environment allowing a standalone verification of this
conformance.
Deliverables:
Validated E40-07 conformance kit
Current TRL:
Algorithm
Application/Mission: all missions
Operational SW
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Beta version
Application
Need/Date:
Contract Duration:
9 months
Dossier0 Ref.: T-7834
Consistent with "System Modelling and Simulation Tools"(B2)
TRP Reference:
T708-051SW
Title:
Automatic generation of database MMI from a domain ontology
TD:
TD08
Objectives
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Description of Activities
The objective is to automate the generation of database editor MMIs resulting from a formal data-model in
order to facilitate the rapid production of user interfaces that mirror the choices of the particular operational
services chosen through the process of tailoring of ground-space interface definitions.
Description
The objective is to automate the generation of database editor MMIs resulting from a formally specified data-model.
The data model is constructed in line with a domain ontology (prepared in an existing approved TRP activity) which
removes ambiguity in terminology and data content. It is refined through the tailoring of E70-41A (packet utilisation
standard). This will enable the automated generation of user interfaces to M+C AIT databases according to project
specific space-ground ICDs.
Deliverables:
Output will be:
- a demonstration of the capability to automate the production of MMI using an existing ontology
- The prototyping of a tool supporting the automatic production of database MMI.
Current TRL:
Algorithm
Target TRL:
Application/Mission: all missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Prototype
Application
Need/Date:
Contract Duration:
12 months
Dossier0 Ref.: T-7292
N/A
TRP Reference:
T708-052SW
TD:
TD08
Title:
Automation of space system test data collecting, processing and reporting
Objectives
The objective is to study the cycle of electrical test reporting from test specification to test report close-out
and to analyse the applicability of methods and tools used in other domains with similar domains to
establish whether a spin-in of such tools could accelerate the application of benefiting from modern IT
technology solutions.
Description
Study will address the life cycle of electrical test reporting from test specification to test reporting as defined by
ECSS-E10 part2 & part3. A mapping will made to similar domains in aerospace, automotive, energy industries.
Candidate tools will be identified procured and evaluated in order to assess their suitability. The roles of a Database of
test results and the associated tools will be proposed that support data analysis (trends, graphical records etc) and
automated test documentation production. Impact on current EGSE architectures and solutions to be assessed.
Deliverables:
Output will be:
- a critical assessment of the current process
- technical note identifying requirements for an IT based end-to-end solution
- set of candidate tools
- a set of mock-ups demonstrating the use of the tools.
- final report containing a set a requirements specification
Current TRL:
Algorithm
Target TRL:
Application/Mission: all missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Prototype
Application
Need/Date:
Contract Duration:
12 months
Dossier0 Ref.: T-7557
N/A
TRP Reference:
T708-053SW
TD:
TD08
Title:
Tools from non-space domains to support space system testing
Objectives
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Description of Activities
Study will address the hardware and software tools employed outside the space domain for complex
electrical system testing to determine the value of spin-in of such technology.
The objective is is to determine how more commercially available solutions can replace the bespoke
solutions currently employed and to determine the extent of commonality achievable with the space
product design and development and verification life cycle.
Description
Analyse of the applicability of the tools assessed will be made to determine extent of applicability to the space
domain. An assessment of selected tools against a specific project's requirements will be performed. The commonality
with the design and development tools will be analysed to establish the level of continuity. The goal is to demonstrate
the (dis)advantages of such an approach from a set of criteria (e.g. financial, commercial, risk) and to propose an
EGSE concept derived from the results.
Deliverables:
Output will be:
- survey report of solutions in comparable domains
- technical note identifying commonalities with spec product design an and development
- trade-off report matching typical project requirements against candidate tool capabilities
- catalogue of candidate tools
- trade-off report demonstrating benefits accrued from such an approach
- prototype adaptations of selected tools
Current TRL:
Target TRL:
Application/Mission: all missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Prototype
Application
Need/Date:
Contract Duration:
12 months
Dossier0 Ref.: T-7292
N/A
TRP Reference:
T708-185SW
TD:
Title:
Autocoding for PUS and satellite database
TD08
Objectives
The purpose of this activity is to enhance the production of OBSW (On Board SW) by automating the
production and verification of the OBSW PUS (Packet Utilisation Standard) services. It is important in
OBSW projects to avoid discrepancies between the source-code, the documentation and the system
model (e.g. the SCOS - Spacecraft Control & Operation System - based S/C databus). Therefore using a
single source for the definition and implementation of these OBSW artefacts will increase the efficiency of
software projects. The activity will build upon recent ECSS work related to the definition of a space system
model (refer to ECSS-E-70-31A, related to Monitoring and Control Data Definition), which contains a PUS
service model.
Description
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Description of Activities
A prototype CASE tool will be developed using a model driven approach based upon the ECSS E-70-31A definitions
to auto-code, auto-document and (optionally) auto-test the PUS services of the on-board data management software.
The ECSS E-70-31A standard introduces the concept of a space system model (SSM) which is used to capture and
share knowledge related to the space system and specifies the monitoring and control data definitions required for
testing and operating the Spacecraft.
Compliant with ECSS-E-70-41A (the PUS), the ECSS-E-70-31A formally introduces the rules to apply to tailor PUS
and identifies the associated mission specific data. Therefore this activity will produce a toolset that implements the
following steps:
1. tailoring of the PUS service as defined in ECSS E-70-31A, including adding mission-specific services and
extensions.
2. definition and population within the SSM of the OBSW-specific parameters (e.g. TM Service 5 event IDs, AOCS
on-board parameters, filtering values, enumerations, etc)
3. consistency verification of the SSM mission data
4. generation and maintenance of OBSW and SSM artefacts: TM/TC interface + datapool source-code, software user
manual, and update the SSM with new OBSW model
5. automatically generate test scripts for unit level white-box validation of the generated source-code
The generated source-code (both C and Ada shall be supported) shall be MISRA-C compliant (for C) and conform to
ESA coding standards (both Ada and C) ensuring that the code is suitable for use with embedded systems.
Deliverables:
- Updated SSM.
- Automatic toolset.
- User manual.
- Case study.
Current TRL:
Algorithm
Target TRL:
Application/Mission: All missions (>2012-2013)
Open source
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Prototype
Application
Need/Date:
Contract Duration:
Prototype by 2010
18 months
Dossier0 Ref.: T-7662
Consistent
7-09 - Mission operation and Ground Data Systems
TRP Reference:
T709-054GI
TD:
TD09
Title:
European Technology Harmonisation on Ground Systems Software - Phase 2 Second set of standard interfaces
Objectives
The main objective is to select 2 main Ground Data Systems Interfaces and produce a set of ICDs to be
delivered to the ECSS as proposed future standards. This shall ensure the coherence of the accepted
roadmap during the European Technology Harmonisation agreements
Description
The following activities have to be performed:
- Collection of Data Systems Information from different European Organizations and Industry
- Assessment of Data System Information against the Harmonisation Reference Architecture
- Consolidation of the Reference Architecture for the selected Subsystems
- Production of the IRD requirements
- Definition of the Interfaces
- Production of the selected ICDs
- Support to the Steering board
Deliverables:
A set of standard interface definition between the modules of the Ground Systems reference Architecture
Current TRL:
TRL 2
Target TRL:
TRL 4
Application
Need/Date:
Application/Mission: Output to become ECSS Standard Contract Duration:
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Description of Activities
Operational SW
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Dossier0 Ref.: T-7840
Consistent with Grfound Segment Subsystem Interfaces (1st
semester 2003)
TRP Reference:
T709-055GI
TD:
Title:
Flight Control Team Multi-Agent System
TD09
Objectives
A new concept of high level spacecraft monitoring is proposed to be validated with agent technology. The
main objectives are: Situation Awareness at Flight Control level, Time saving due to autonomous
monitoring of nominal spacecraft behaviour, Initial assessment of implications of anomalies
Description
Development of a Multi-Agent system where each member of the Flight Control Team has an Agent that acts on his
behalf. He configures his agent to perform the monitoring task he would. The monitoring results of the agent are
available to other agents and to the members of the Flight Control Team. Other agents can then perform an initial
assessment of the implications of the reported anomaly in the subsystems they are responsible for. The FCT
members will take the initial assessment of their Agents and further elaborate based on their knowledge and
experience.
The main benefits of this approach are:
- Distributed monitoring of the Spacecraft Behaviour. Every agent has the expertise of the FCT member that has
configured it.
- Autonomous monitoring of nominal spacecraft behaviour
- Quick communication among members of the FCT when something unexpected happens. The FCT agents can
provide an initial assessment of the implications of the reported anomalies in several subsystems.
- The Flight Control Team members save time by getting the initial assessment by the agents
- Situation Awareness at FCT level
Deliverables:
* Technology assessment report enabling the use of Multi-Agent Systems and the transmition of the knowledge from
the FCT members to the Agents
* Prototype implementing the monitoring & diagnosis via Agent-based FCT
* Operational Assessment of the prototype
* Relevant documentation (requirements, design, validation, software user manuals, software source code, etc.)
* Support during the validation of the prototype with a selected ESA mission
* Final study report and presentation
1
Current TRL:
Application/Mission:
SW Clause :
Target TRL:
3-4
Application
Need/Date:
Contract Duration:
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 6 by 2011,
TRL 9 by 2013
12 months
Dossier0 Ref.: T-120
Not part of harmonisation
TRP Reference:
T709-056GI
TD:
TD09
Title:
Linux and multi-core processor technology for simulators
Objectives
- To develop a light version of a simple simulator that has minimal host performance requirements.
- To develop a high performance simulator that can run efficiently on multi-core processor technology.
Description
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Description of Activities
The activity includes the two main tasks :
1. Development of a light-weight version of a simple simulator that has minimal host performance requirements,
identifying the irreducible residual operating system dependencies. In particular this form of ther similator could run
embedded e.g. in an ERC-32 processor on-board for PROBA-3.
Including following subtasks:
• Analysis of how to communicate with an embedded simulator.
• Definition of new API for serial input/output to and from simulation including starting, stopping, external interaction to
replace user commands normally sent by the MMI.
2. Development of a high performance simulator that can run efficiently on multi-core processor technology. This will
include
• Technological advance: develop an algorithm for a scheduler which can use modern multi-core CPUs effectively.
• Achievement of higher levels of performance and parallelism by improved model construction and annotation
Including following subtasks:
• Survey literature on Discrete Event simulation.
• Analyze the architecture of operational simulators and compare with other industrial simulations where more
aggressive scheduling algorithms have been used
Deliverables:
For both the Linux embedded simulator and the multi-core simulator the following will be expected:
1. Source code for models, and any infrastructure changes
2. Validation simulator and test cases
3. Technical notes and User Manual.
4. Prototype software, including test harnesses, data and procedures, and associated documentation.
A Study final report and presentation, summarizing the experience, results and recommendations. shall also be
delivered
Algorithm
Current TRL:
Target TRL:
Prototype
Application/Mission:
Contract Duration:
Operational SW
SW Clause :
Application
Need/Date:
Consistency with Harmonisation
Roadmap and Conclusions:
SW Operational >
2013
12 months
Dossier0 Ref.: T-7843
Not part of harmonisation
TRP Reference:
T709-057GI
TD:
TD09
Title:
Suitability of emerging service based technologies in ground data systems
Objectives
Assess the suitability of emerging technologies such as Service Component Architecture (SCA) and Data
Distribution Service (DDS) for ground data systems infrastructure applications.
Description
The activity shall assess the limits of Service Component Architecture (SCA) and Data Distribution Service (DDS) in
their applicability to space M&C systems, particularly the possibility of interacting with legacy systems. It shall be
validated whether SCA and/or DDS technology are able to provide the level of performance and flexibility required by
monitoring and control software:
- A detailed analysis of the maximum and minimum requirements concerning this two aspects needs to be performed.
- Evaluation of Pros/Cons of the frameworks implementing the SCA and/or DDS specification based on the specific
needs for M&C.
- This architecture shall be validated against a set of representative scenarios (Use Cases)
Deliverables:
Technological analysis, requirements and Use Cases, Implementation frameworks, design, Proof-Of-Concept
TRL 3-TRL 4
Current TRL:
TRL 1
Application/Mission:
next generation of data systems
development framework.
Contract Duration:
SW Clause :
Operational SW
Dossier0 Ref.: T-7843
Target TRL:
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Application
Need/Date:
TRL 6 by 2011,
TRL 9 by 2013
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Description of Activities
Consistency with Harmonisation
Roadmap and Conclusions:
Not part of harmonisation
7-10 - Flight Dynamics and GNSS
TRP Reference:
T710-058GF
Title:
Interactive Design of Interplanetary Trajectories
TD:
TD10
Objectives
The objective is to develop new working methodologies and s/w tools for a preliminary and interactive
design of interplanetary missions based on the ASTRO-toolbox philosophy. To be covered are: Planetary
swing-bys, asteroid/comet rendez-vous and fly-bys, weak stability boundary transfers, aerocapture and
aerobraking, chemical and low-thrust propulsion, atmospheric entry and landing, planetary ascent and
Lagrangian points.
Description
Starting with the ASTRO Toolbox, trajectory design modules shall be built that the mission analyst can use to quickly
make a first mission design. Trajectories based purely on chemical propulsion (e.g. Rosetta type), low-thrust
trajectories (BepiColombo type), trajectories passing through planetary atmospheres and trajectories around Lagrange
points (e.g. Herschel/Planck) shall be designed to validate the proposed concept.
Deliverables:
Detailed Architectural Design, software (source code)
TRL 1
Current TRL:
Target TRL:
Application/Mission: Sci/Exploration missions
Operational SW
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
2010
18 months
Dossier0 Ref.: T-8435
N/A
TRP Reference:
T710-059GF
TD:
TD10
Title:
GNSS contribution to next generation global ionospheric monitoring
Objectives
To significantly improve on the existing capability of making near-real-time ionospheric models, by
exploiting the growing availability of GNSS data sets
Description
This study will propose new approaches and improvements to existing ionospheric modeling, and produce a prototype
implementation of selected new features.
Improvements are expected in areas of:
- timeliness (models can be available closer to real-time)
- resolution (in position or time)- realism (multi-layer or 3-dimensional modeling)
- accuracy
- modeling techniques (e.g. using additional data or measurement types)
Deliverables:
prototype implementation
Current TRL:
-
Target TRL:
Application/Mission:
SW Clause :
Prototype
Application
Need/Date:
Contract Duration:
Operational SW
Consistency with Harmonisation
Roadmap and Conclusions:
18 months
Dossier0 Ref.: T-7941
N/A
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Description of Activities
7-11 - Space Debris
TRP Reference:
T711-060GR
TD:
Title:
Space Debris Stare and Chase
TD11
Objectives
The objective is to develop a stare and chase mode for the L-band radar at FGAN. It shall allow to follow
a space object once it is detected inside the 3db radar beam. Test campaigns shall be performed where
the radar beam is parked ("stare") until an object passes through the beam, whereupon the radar follows
the object ("chase"). Based on the tracking information rough orbital elements have to be determined.
Description
The primary way to obtain a better knowledge of the near-earth environment are radar measurements. The Research
Establishment for Applied Science (FGAN) carried out a TRP study on Advanced Radar Techniques for Space Debris
Observation (contract nr. 11184, FR in June 2000). In a second TRP study (contract nr. 13261, FR in July 2003) H/W
and S/W upgrades were implemented which further increased the sensitivity of the radar. FGAN operates a powerful
Tracking and Imaging Radar (TIRA) consisting of a 34-m parabolic antenna, a monopulse L-band tracking radar, and
a high resolution Ku-band imaging radar. The L-band radar can detect 2 cm space debris at a range of 1000 km.
Ten 24 beam-park experiments were performed in the years 1999 to 2006. Up to 500 objects were detected during
each measurement campaign. Not even one quarter of these detections can be correlated with catalogued objects.
With a successful stare and chase operation, a couple of minutes of tracking data can be collected which allows a
reliable determination of the orbital plane (i and O) and semimajor axis. It is expected that correlations with known
satellite breakups can be established.
WP 1. Development of stare and chase algorithms
The software to control the radar has to be extended to trigger a chase mode once an object passes the radar beam.
WP 2 Preparation and execution of a multi-hour test campaign
The concept developed in WP1 shall be validated. First it will be tested on objects which are known (i.e. the time and
direction of the passing object can be predicted) but finally it needs to be tested on unknown objects. On average
objects pass the radar beam every 3 minutes triggering the stare and chase mode.
WP 3. Data Processing and Orbit Determination
Output: Detection list with orbital elements, size estimation and rms-errors in range, range rate, azimuth and elevation.
Deliverables:
Algorithms, detection list with orbital elements and their parameters
Current TRL:
N/A
Target TRL:
N/A
Application/Mission: Prototype algorithms in mid 2009
Operational SW
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
Prototype
algorithms in mid
18 months
Dossier0 Ref.: T-1093
N/A
TRP Reference:
T711-061GR
TD:
TD11
Title:
Preliminary design and analysis of new generation space debris cameras
Objectives
The objective of this study is to prepare the improvement and expansion of the application of ESA's
Optical Ground Station for the purpose of space debris observation, space surveillance and astronomical
use through the introduction of a new generation sensors. The study shall identify and specify leading
edge technology, coming with faster processing and higher sensitivity that allows multiple purpose use
and generates experience for future applications (SSA, JWST, space debris research,...) in all three
domains. Finally, the necessary adapations to the camera controller software shall be developed and
tested.
Description
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Description of Activities
ESA owns a 1-meter Zeiss telescope located at the Observatorio del Teide on Tenerife, forming part of the ESA
Optical Ground Station (OGS). One of its most important missions is the regular survey of geostationary altitudes in
which it can detect objects down to 15-cm sizes. This is almost one order of magnitude better than the performance of
the USSTRATCOM space surveillance network (SSN) for this orbit region. It employs a 4096 x 4096 pixel space
debris camera which is reaching its end of live, showing already first signs of instability. With a replacement being
urgently required, there is an opportunity to switch to leading edge technology. New generation HyViSI (Hybrid Visibile
Silicon Imager) sensors for example allow to readout pixels through direct access. This permits to generate subframes
and allows for continuous and fast readout, reducing the background level.
In this study, technologies shall be identified and analysed that satisfy the needs of several application domains in
parallel (e.g. astronomy and space surveillance), allowing them to apply, evaluate and optimise this technology for
their purpose. In a first step the needs of telescope users from all domains shall be analysed and specifications of the
camera shall be drafted. Available products shall evaluated in terms of performance and interface. The specifications
shall be completed and a development and assembly, integration and a validation plan generated. The existing
camera controller software shall be analysed and necessary adoptions specified. The camera controller software shall
be updated according to the specifications and tested in the development environment.
Deliverables:
? Specifications
? Design documentation and camera specifications,
? Technical report on market survey and recommended products
? Development and assembly, integration and validation plan)
Current TRL:
TRL 2
Target TRL:
TRL 3
Application/Mission: TRL 3 by mid 2008
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
TRL 3 by mid 2008
6 months
Dossier0 Ref.: T-1093
N/A
TRP Reference:
T711-062GR
TD:
TD11
Title:
Development and simulation of strategies for the detection and tracking of MEO
objects
Objectives
This study shall develop and analyse observation concepts for the optical detection of dcimetre sized
uncorrelated objects in inclined MEO orbits. The efficiency of the survey strategies shall be demonstrated
through simulation and detection algorithms shall be prototyped. The goal of this study is to provide the
feasibility and performance assessment as a technical fundament for a later implementation of the
techniques into ESA's space debris telescope.
Description
Today, MEO orbits with semi or higher order synchronous periods typically between 20,000 and 26,000km altitude
become more and more important (Galileo, GPS,…). The regular surveillance of this region through a future
autonomous European system is a challenging task and has not been exercised in Europe so far. Critical technologies
comprising observation strategies, correlation and preliminary orbit determination algorithms for such surveillance
activities need to enter the prototyping stage.
In this study, a strategy for the detection of inclined MEO objects needs to be developed. This strategy must take the
performance of preliminary orbit determination algorithms into account in order to guarantee correlation of objects in
separate observations. Existing detection, telescope control and orbit determination algorithms need to be reviewed
and their suitability for MEO observations analysed. The necessary adoptions shall be specified, implemented and
verified. Available simulation techniques shall be used to optimise and validate the survey concept.
Deliverables:
? Technical report on the evaluation of survey strategies
? Prototpye detection algorithms and associated software documentation
? Technical report on necessary upgrade to the telescope and camera control systems
Current TRL:
N/A
Target TRL:
N/A
Application
Need/Date:
Application/Mission: Prototype algorithms in early 2010 Contract Duration:
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Description of Activities
Operational SW
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Dossier0 Ref.: T-1093,T-1102
N/A
7-12 - Ground Station Systems and Networks
TRP Reference:
T712-063GS
TD:
TD12
Title:
Study on the architecture for the next generation of ESA TT&C processors
Objectives
The goal of this study is to explore and breadboard new architectures for the next generation of
multi-mission TT&C processors, in support of future missions, ranging from S- to Ka-band allocations.
Description
The study will define and breadboard the new TT&C processor, which is the central equipment in every ESA tracking
station. The study is needed now because the currently deployed multi-mission TT&C platform is not able to support
additional and more advanced functions. Moreover, problems of maintenance of the related hardware are expected to
come up in the next years. More in detail, the study shall cover the following aspects:
• collect any requirement, in terms of telemetry reception, for future scientific, Earth-observation and Exploration
missions
• collect any requirement, in terms of telecomand transmission, for future scientific, Earth-observation and Exploration
missions
• collect any requirement, in terms of orbit determination (ranging, Doppler, wide-band ranging, delta-DOR,
regenerative ranging, same-beam interferometry, etc), for future scientific, Earth-observation and Exploration missions
• consider interoperability requirements with other Space Agencies working in the same fields, so that cross support
could be granted, once the system under study becomes operational, as per present and projected CCSDS/ECSS
recommendations
• consider recent advancements in terms of automatic reconfiguration of receivers
• consider the performance of state-of-the-art DSP components and processors, including off-the-shelf IP cores, and
related analogue-to-digital conversion components
• define new RF interfaces, to cope with the increased demand of high data rate (telemetry) and larger band (precise
orbit determination)
• consider state-of-the-art design methodology issues
• evaluate and select novel receiver algorithms, more suitable to the expected high integration requirements
• define and consolidate the TT&C processor requirements
• provide high level architectures of the processor, defining interfaces and operation modes
• Detail the hardware and software architectures, so that appropriate feasibility can be evaluated. Detailed analysis of
the needed design is foreseen in a further phase
• argue the cost, operation and maintenance of the new TT&C processor
• Set the specifications of the new TT&C processor
• Produce a breadboard of the new TT&C processor following this specifications
• Make a test plan for the breadboard test
• Validate the breadboard.
Deliverables:
Breadboard of a new TT&C processor
TRL 1
Current TRL:
Target TRL:
Application/Mission:
SW Clause :
TRL 3
Application
Need/Date:
Contract Duration:
Operational SW
Consistency with Harmonisation
Roadmap and Conclusions:
by 2011
12 months
Dossier0 Ref.: T-1227
N/A
TRP Reference:
T712-064GS
TD:
TD12
Title:
New and improved cryocooler technologies for deep space antennas cryogenic
sub system
Objectives
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Description of Activities
New and improved cryocooler technologies for deep space antennas cryogenic sub system
Description
In order to avoid any service interruption in case of cold head failure, it will be considered to implement two cold heads
working in parallel inside the vacuum enclosure. By this the second cold head will still be in operation when the first
cold head fails.
In order to be able to replace the faulty cold head without breaking vacuum and without service interruption, it will be
necessary to implement cold head sleeves to allow rapid substitution of the cold head. During maintenance the cold
head sleeve is exchanged with a spare and no service interruption is required. The double cold head and cold head
sleeve principles are already used in magnetic resonant imaging, where very high reliability is required. Such
concepts have to be adapted to the communication environment, taking into consideration the specific constraints and
interfaces.
The study will also cover the evaluation of Low frequency pulse tube technology. This technology reaches the same
level of performance as Gifford Mc Mahon coolers, which are currently used in ESA ground stations. Pulse Tube
technology does not have any moving part inside the cold head and can theoretically work for an indefinite period of
time without maintenance.
This study will cover:
- the analysis of the redundant cold head and cold head sleeve concepts
- the design of cryocooled dewar prototype with redundant cold head and sleeves
- the design of cryocooled dewar prototype with redundant cold head and pulse tube technology
- the performance assessment of the developed breadboards
- The final aim of the study is to apply the developed concepts to future production units to be deployed in ESA
stations.
Deliverables:
Dewar prototypes with redundant cold head and modular sleeve or pulse tube, Test report
TRL 1
Current TRL:
Target TRL:
Application/Mission:
Application
Need/Date:
Contract Duration:
N/A
SW Clause :
TRL 2
Consistency with Harmonisation
Roadmap and Conclusions:
by 2010
12 months
Dossier0 Ref.: T-1263
N/A
TRP Reference:
T712-065GS
TD:
TD12
Title:
Feasibility and breadboarding of a multiple frequency cryogenic receiver
Objectives
It is expected to upgrade 35 m deep space stations with the K band (25.5-27 GHz) in order to support
mission going to the Lagrange point (Darwin, WFI, FIRI). In order to upgrade deep space station with this
band and fulfil link budget requirement (as shown in 19719/5/F/VS GSP study), it will be necessary to
develop new dual band (X/K) cryogenic receivers. The same techcnology could be used for X/Ka-Band
application.
Description
The X/K cryogenic low noise amplifier will be made of two separate RF circuits, one for K band and one for X band.
Both RF circuits will share the same vacuum dewar enclosure and the same refrigerator. The RF circuits will be made
of input coupler, filters, isolators, HEMT LNA cooled at 15K and post amplifiers at ambient temperature.
This study will cover:
- Feasibility analysis of the dual band cryogenic receiver in X/K- and X/Ka-Band
- Design of the cryogenic receiver in X/K-Band
- Prototype realization
- Performances assessment
The activities of this TRP study shall be continued with the development of the production units with infrastructure
funding and the installation of the units in ESA Ground Stations.
Deliverables:
Dual band cryo receiver demonstrator, Performance assessment report
Current TRL:
TRL 1
Application/Mission:
SW Clause :
Target TRL:
TRL 3
Application
Need/Date:
Contract Duration:
N/A
by 2010
12 months
Dossier0 Ref.: T-1263
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Description of Activities
Consistency with Harmonisation
Roadmap and Conclusions:
N/A
7-13 - Automation, Telepresence & Robotics
TRP Reference:
T713-066MM
Title:
Multi wafer hybrid integration: Robotics IMU I
TD:
TD13
Objectives
The goal of this activity is to develop an integrated micro localisation platform based on inertial platform
(3-axis solid-state gyro + 3 accelerometer) with a digital serial bus interface (e.g. CAN). The platform shall
be specifically designed for use in navigation for robotics applications where mass is extremely critical
and there is a wide spectrum of mechanical noise. The effort of the activity will be on very tight integration
of ESA-developed sensors and interface/processing circuitry aiming to total mass below 200 gr.
Description
The activity shall 1) detail requirements for an IMU in robotics operations 2) define interfaces and architecture 3)
design a Robotics MEMS IMU based on ESA harmonised sensors 4) prepare proof-of-concept demonstrator
Deliverables:
Robotics MEMS IMU proof-of-concept demonstrator
TRL 3
Current TRL:
TRL 1
Application/Mission:
robotics for future planetary
surface missions/ orbital servicing
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
Contract Duration:
2012
18 months
Dossier0 Ref.: T-6,T-876,T-7818
Consistent with first semester 2007 harmonisation on A&R (activity
A4)
7-14 - Life & Physical Sciences Instrumentation
TRP Reference:
T714-067MM
Title:
High Temperature Sensors with self calibrating capabilities
TD:
TD14
Objectives
The objective of this activity is to achieve a fully functional and reliable temperature measurement setup
with self calibrating capabilities for temperatures up to approx. 2500 °C, targeting applications in
propulsion systems and other high temperature applications. With these temperature sensors, an advance
in durability, range and accuracy shall be achieved in comparison with the actual high temperature
thermocouple systems.
Description
It is perceived that reliable thermocouples with self calibrating capabilities, by means of carbon eutectic fixed point
cells for temperature monitoring and control, are important for high temperature applications. These carbon eutectic
materials are at this moment of high interest as temperature standards for temperatures above the silver point.The
system shall consist of
a compact system housing containing electronics, mechanics etc. together with data acquisition and evaluation and
operation units a central processor unit, data acquisition, evaluation and storage unit appropriate interfaces for
real-time optical temperature measurements Thermocouple sensors with calibration cells containing single eutectics
Thermocouples with calibration cells containing multiple eutectics in adjacent compartments
Supporting tools, such as: calibration samples, pyrometers, etc.
Deliverables:
Functional breadboard, test data
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Description of Activities
TRL 2
Current TRL:
Target TRL:
Application/Mission:
SW Clause :
TRL 3
Application
Need/Date:
Contract Duration:
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
18 months
Dossier0 Ref.: T-8266
N/A
7-15 - Mechanisms & Tribology
TRP Reference:
T715-068MM
TD:
TD15
Title:
European Space Tribology Laboratory Technology Application Programme
Objectives
Development of space tribology technologies and associated engineering tools to enable the timely
development of ad-hoc mechanisms for future missions
Description
This activity is dedicated to the tribological evaluation of emerging dry and fluid lubricants, materials, coatings and
tribo components under harsh environment and duty cycle. Elaboration of tribology engineering tools to predict in orbit
behaviour of mechanisms.
Deliverables:
Samples, breadboards, tests reports, technical notes, Tribology handbook updates, tribology softwares
Current TRL:
TRL 1
Target TRL:
Application/Mission: 2010-2012
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
2010-2012
36 months
Dossier0 Ref.: T-7846
N/A
7-16 - Optics
TRP Reference:
T716-070MM
TD:
TD16
Title:
Innovative Technologies for Large Deployable Optical Telescopes
Objectives
The main objective of this activity is to identify and assess suitable advanced technology concepts and
materials that may provide a disruptive breakthrough for very large optical space telescopes (e.g.
deployable membranes)
Description
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TRP Work Plan 2008-2010
Description of Activities
Large aperture telescopes are increasingly required for space projects where sensitivity and resolution are mission
drivers. Current light-weight mirror technologies (25 kg/m2) based on ceramic composites satisfy the needs of
missions in implementation (Herschel/Planck, GAIA). Future missions aiming at the observation of the sky
(science/astrophysics) or of the Earth (GEO-based Earth observation, high-sensitivity lidars and sounders) will require
much larger and/or much lighter mirrors and telescopes. Ultra-thin membrane mirrors with actuators (adaptive optics)
to reach and maintain the WFE after deployment have been identified as potential candidate solutions to reach an
areal mass close to 1 kg/m2. These foldable and light-weight membranes provide focusing based on diffraction. The
principle is based on zone plate Fresnel lenses. Instead of rings, the “photon sieve” diffractive optics uses a large
number of pinholes as diffractive elements.
This activity shall
- review the state-of-the-art of thin membrane mirrors,
- assess the achievable optical performances,
- study the limitations in terms of field-of-view, spectral range, optical throughput, wavefront error, aperture,
- identify the technological manufacturing limitations and the methods for deployment and in-orbit metrology,
- assess the suitability of this new technology for the space environment.
The main functionalities shall be demonstrated in a down-scaled breadboard.
Deliverables:
Study Report + BB of a representative downscaled demonstrator
TRL 3
Current TRL:
TRL 1
Application/Mission:
TRL 5 by 2013, for future science
and EO missions
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-7855
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
TRL 5 by 2013,
24 months
Harmonisation planned for Sem 1 2008
7-17 - OptoElectronics
TRP Reference:
T716-069MM
Title:
Use of the Novel Modelocked Semiconductor Lasers technique in the
Sub-Picosecond Regime for Space Missions
TD:
TD17
Objectives
The present activity addresses the applications of sub-picosecond Mode-Locked-Semiconductor
Lasers-based new metrology concepts for ( future) space missions such optical interferometry and
metrology missions, spectroscopy, optical communications, on-board data processing, etc, and assess
the impact at overall performance and system level.
Description
The novel technology of Modelocked Semiconductor Lasers (MLSCL) is a promising candidate to be used in optical
metrology systems for various space applications, e.g. in the context of optical interferometry or frequency and
distance metrology as well as optical communications and data processing. Recent laboratory demonstrations of
MLSCLs are capable of producing VIS / NIR ultrashort light pulses in the few picoseconds time regime at very high
repetition rates in the MHz domain. These ultrashort light signals can be used in a simple time-of-flight (TOF)
metrology system for the measurement of short and - limited by the achievable optical output power - also long
distances of potentially kilometres with an accuracy on the millimetre level. Due to the MLSCLs compactness and
superior wall plug efficiency they could be integrated into miniature optical systems replacing presently used laser light
sources of large unit dimension. The present activity addresses the development and performance characterisation of
MLSCLs in the sub-picosecond time domain investigating the suitability for space applications.
Deliverables:
Braedboard of a sub-picosecond metrology system based upon MLSCL concept
Current TRL:
TRL 1
Target TRL:
TRL 3
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Application
Need/Date:
2012
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TRP Work Plan 2008-2010
Description of Activities
Optical interferomtry and
metrology missions, spectroscopy,
Application/Mission:
Contract Duration:
optical communications and data
processing/ 2012
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
24 months
Dossier0 Ref.: T-7757
Subject not harmonidsed
7-18 - Aerothermodynamics
TRP Reference:
T717-071MP
TD:
TD18
Title:
Laminar to Turbulent transition in hypersonic flow
Objectives
The objectives of the present activity is to improve bypass transition correlations for hypersonic space
vehicle design.
Description
One of the most critical design drivers for earth reentry or planetary entry vehicle design are the specifications
associated with allowable gap,step, or roughness as well as the assessment of the transitional reattachment heating
for separated flow fields typically encountered on defelcted flaps. The present TRP shall focuss on advances of
transition correlations by performing experiments in hypersonic facilities thereby improving wind tunnel to flight
extrapolation and scaling by advancing the Hot Experimetal Testing Techniques (HET) so as to improve T-wall over
T-recovery effects. In addition special will be given to the measurememts of the unsteady components such as
pressures and temperatures to augment the data base for follow up analysis using advanced methods such as LES or
DNS. Finally,where possible, synergies with potential passenger flight opportunities should be proposed.
In detail :
o The contractor shall assess state of the art of present day by-pass transition correlations.
o The contrator shall analyse present and future planned in flight testing projects and recommend experimetal
activities to improve the data base associated with roughness induced and shear layer transition
o The contractor shall propose a set of roughness induced transition experiments taking into account the wall
temperature effects
o The contractor shall propose shear layer transition experiments talking into account wall temperature effects.
o The contractor shall in addition to the classical windtunnel measurements improve and implement unsteady
pressure and temperature meausrements thereby augmenting the data base for analysis of advanced methods.
o Rebuilding of windtunnel experiments /extrapolation to flight/ recommendation for future.
Deliverables:
technical notes
Current TRL:
TRL 3
Target TRL:
TRL 3
earth reentry vehicles, planetary
Application/Mission: probes, future launchers, debris
analysis .
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
.
24 months
Dossier0 Ref.: T-8315, T-8097
Consistent (Roadmap item B2)
TRP Reference:
T717-072MP
TD:
Title:
Multi-phase aspects in propulsion systems
TD18
Objectives
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TRP Work Plan 2008-2010
Description of Activities
The objectives of the present activity is to improve the understanding of multi-phase phenomena occuring
during transients, start-ups and shut-downs in propulsion systems. This entails waterhammer effects or
pre-combustion where propellants undergo drastic changes due to sudden exposure to near-vacuum
conditions. To allow proper modelling, detailed experiments need to be created for typical multi-phase,
multi-component flow phenomena: waterhammer during priming, flash atomization and vaporization.
Description
The activity shall include:
- evaluation of the liquid front behaviour during waterhammer prior, during and after impact for different operational
conditions
- evaluation of atomization processes in flashing conditions at different conditions
- evaluation of vaporization rates in flashing conditions at different conditions
- extension of correlations for flash atomization
- extension/validation of correlations for flash vaporization
Deliverables:
technical notes
TRL 3
Current TRL:
TRL 2
Application/Mission:
All s/c and upper stages propulsion
Contract Duration:
systems
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
24 months
Dossier0 Ref.: T-7899
Consistent (Roadmap item A4)
7-19 - Propulsion
TRP Reference:
T718-073MP
TD:
TD19
Title:
Assessment of the interaction between spacecraft and electric propulsion
systems
Objectives
The objective of the activity is to create an experimentally validated model for thruster interaction with the
S/C subsystems
Description
Smart-1 with a Hall-effect thruster (HET) on board and an Electric Propulsion Diagnostic Package (EPDP) has
demonstrated the good functioning of electric propulsion for interplanetary missions. Nevertheless, possible interaction
of the backflow of the thruster or even the primary ions in telecommunication satellites could produce some
interactions (erosion, contamination, electromagnetic compatibility issues, etc.). Diagnostics and modelling are the
main tools to assess this issue.This activity should look at all the possible models employed in this work and assess
the design of specific experiments to tackle this issue. Flight data of some spacecraft such as Smart-1, Artemis,
etc.shall be used to demonstrate that the current models have been validated and that the experiments can give a
good insight in the problem. Furthermore several tests will be performed durng this activity in order to fully validate
and assess the use of these models in this specific matter. In deatail, following tasks shall be performed:
o Assessment of the impact of on-ground testing conditions on the main physical properties of EP thrusters compare
to in-flight conditions – specifically on the external environment induced by the EP thrusters (backflow,
back-sputtering…)
o Analytical quantification of this impact and comparison of flight-data to on-ground testing of EP thrusters (Hall effect,
HEMPT, Ion, FEEP)
o Identification of possible diagnostics for performing measurement relevant to the thruster-S/C interaction in a test
facility during on-ground testing
o Selection of a specific set of diagnostics providing a full characterisation main physical parameters of EP thrusters
relevant to thruster-S/C interaction
o Design of an experiment(s) in which the diagnostics will be used and identify the models required to assess this
problem
o A test using diferent thrusters, validation of the identified models with the test data and finally comparing the results
with the flight data available.
Deliverables:
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Description of Activities
Technical Notes
Current TRL:
TRL 1/2
Target TRL:
Application/Mission: All missions with EP systems
Open source
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
2010
24 months
Dossier0 Ref.: T-856
Consistent (Roadmap item G1-G4)
TRP Reference:
T718-074MP
Title:
Development of a Hollow Cathode Thruster
TD:
TD19
Objectives
The objective of this activity is to demonstrate the feasibility of Hollow Cathode Thruster
Description
For small satellite propulsion or large communication satellites with electric propulsion on board, it would be beneficial
to make use of the existing Xenon supply system for an auxiliary AOCS system based on Hollow Cathode Thrusters
(HCT). This would effectively remove the complete chemical propulsion subsystem and replace it with a few additional
Power Supply Units (PSU) and HCT. During the course of this activity a thruster system consisting of the Hollow
Cathode Thruster, Flow Control Unit, Power Supply Unit shall be breadboaded and its performance characterized.
The test shall include direct thrust measurement and plasma characteristics through the use of balances, diagnostic
prrobes, etc. The use of this thruster also as a cold gas shall also be assessed during this activity.
Deliverables:
Breadboard
Current TRL:
TRL 3
Target TRL:
Application/Mission: Telecom platforms
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 4
Application
Need/Date:
Contract Duration:
2012
18 months
Dossier0 Ref.: T-867
Consistent (Roadmap item I5)
TRP Reference:
T718-075MP
TD:
TD19
Title:
Preliminary characterization test campaign of Electric Propulsion technology
with non conventional propellants.
Objectives
The objective of the activity is to perform a characterization test campaign with existing Electric Propulsion
Thrusters (HET, GIE) propelled with non-conventional gaseous propellants.
Description
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TRP Work Plan 2008-2010
Description of Activities
Previous ESA/non-ESA studies assessing the possibility of extending LEO mission’s duration and allowing very low
altitude operations, identified the mass of propellant required to perform drag compensation manoeuvres as the major
limiting factor.
The ESA Ram-EP GSP study proposed an innovative solution to enable those LEO missions: collecting from the
atmosphere the molecules causing the drag and use them to propel Electric Propulsion Thrusters. Indeed Electric
Propulsion thrusters (HET, GIE) have the capability of operating from virtually any gaseous propellant, including
oxygen and nitrogen (although with a lower efficiency). One of the main concerns highlighted by the study was the fact
that the performances of the thrusters used to assess the concept’s feasibility require experimental verification.
As a natural follow-on of the GSP study and in order to assess the feasibility of the concept for future applications, this
TRP activity has the objective of verifying the thruster performance, when the thruster is required to operate with
different propellant. A mixture between the selected propellant and the conventionally used Xe will be also considered.
Earth upper atmosphere for given solar activity shall be examined to obtain information about the densities, pressures,
temperatures and composition for an altitude ranging between 150km and 500km. Since the concept is also
applicable to orbiting manoeuvres around different planet, an investigation of the Martian atmosphere composition will
be also performed in order to assess the feasibility of using its gaseous components as possible propellant.
Following the selection of the propellant, an existing thruster will undergo a preliminary characterization test campaign
(about 300 hrs of operation total). The performance models shall be correlated in accordance with the results of the
test activity and the numerical simulations shall be modified in order to predict long term behaviour.
In the case of modifications required to current thruster’s design, the contractor shall propose a way forward to update
the thruster design in preparation for an EM definition, suitable for operating with selected propellant.
Deliverables:
Technical Notes
TRL 4
Current TRL:
TRL 3
Application/Mission:
Vey low altitude satellites around
Mars and Earth
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-855
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
12 months
Consistent (Roadmap item I5)
TRP Reference:
T718-076MP
Title:
Surface tension PMD for low-fill fraction and horizontal transportation
TD:
TD19
Objectives
The objectives for this activity are as follows - 1. A market assessment detailing the applications and
potential cost savings of this technolgy. 2. A trade-off of all of the different PMD options with downselction
to the most promising candidates.
Description
A surface tension PMD will allow for horizontal processing of spacecraft which would lead to faster (and hence
cheaper) ground processing activities. A low-fill fraction capability would expand the range of missions that a single
propellant tank would be able to fulfil, thus reducing the need to develop a large range of tanks for European
spacecraft.
Deliverables:
Concepts trade-off, preliminary design datapackage
Current TRL:
TRL 1
Target TRL:
TRL 2
Application/Mission: Exploration, SCI S/C telecom S/C
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
2012
Application
Need/Date:
Contract Duration:
9 months
Dossier0 Ref.: T-867
N/A
TRP Reference:
T718-077MP
TD:
TD19
Title:
Throttable Flow Control Valves for Spacecraft class thrusters
Objectives
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TRP Work Plan 2008-2010
Description of Activities
The objectives of this study is to evaluate the different valve concepts and mission scenarios as well as
performing a market evaluation. The study will focus on evaluating valves for thrusters of 500N or less.
Once the most promising concept has been selected a breadboard model will be constructed and tested
to demonstrate the key technologies/operating principles of the valve. A way forward will then be defined
to take the design forward to future design completion and qualification.
Description
A number of spacecraft/lander systems are considering different thrust ranges for different mission phases. The
current generation of bi-propellant thrusters have limited ranges in thrust variation and this change in thrust can only
be achieved by the controlling pressure conditions in the propellant tanks. The purpose of this activity is to control
thrust ranges by throttling the engine flow control valves, thus adding flexibilty to the propuslion system that is not
achievable by pressure regulation. There are several cases where this would be desirable - 1. Exploration where a
throttable engine would be useful for planetary descent/ascent and 2. Next generation science/telecommunication
spacecraft which envisage 20N and 10N thrusters for ACS systems. These could be replaced for example with a
single choice of thruster eg a 20N thruster with a 50% throttablity range. In both cases this will lead to a sub-system
reliabilty increase and reduction in cost by the reduction in the number of components required.
Deliverables:
Breadboard
TRL 1
Current TRL:
Target TRL:
TRL 3
Application/Mission: Exploration, SCI S/C telecom S/C
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
2011
18 months
Dossier0 Ref.: T-867
N/A
TRP Reference:
T718-078MP
TD:
TD19
Title:
Performance characterisation of aged Hall Effect thrusters
Objectives
The objective of the activity is be to perform a characterization test campaign with existing Hall Effect
thrusters to understand the wearing mechanisms and thus the lifetime limitations
Description
A lifetime test of around 12 000 hours has been performed on a Hall Effect thruster within the frame of the Alphabus
project. The thruster was still running when the test was stopped. In the frame of future missions using electric
propulsion (telecom, exploration missions to outer planets, etc.) it is important to understand the real limiting factors of
the Hall Effect thruster technology for different powerlevels. Therefore during the course of this activity available aged
Hall Effect thrusters (PPS1350 and SPT-100) shall be tested in order to validate the available modelling tools with the
results of this activity. Extrapollation of lifetime issues to higher operational ranges shall also be performed.
Deliverables:
Performances and lifetime models
TRL 4
Current TRL:
TRL 3
Application/Mission:
all missions with Hall Effect
thrusters
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-856
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
24 months
N/A
7-20 - Structures & Pyrotechnics
TRP Reference:
T601-50MC
TD:
Title:
Advancement in Thermo-Elastic Distortion Verification Methods for Spacecraft
Structures (Phase 2)
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TD20
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TRP Work Plan 2008-2010
Description of Activities
Objectives
The objectives of the proposed activity are the following:
- Improvement of materials modeling, especially composites and other advanced materials.
- Improvement of numerical simulation of materials, components and assemblies of structures by using
existing FEM software tools, but including in the mathematical models the specific aspects of materials
and components. This shall consider non-linear and stochastic analysis.
- Application of new measurement and monitoring techniques, such as ESPI (Speckle interferometry),
laser radar and optical fibre sensing (Bragg grating), thermography...
Description
The activity consists of two phases:
Phase 1 - short review of current state of the art with regard to analysis, control and test methods; - Modeling of
composite materials, components, joints and assemblies. Typical hypothesis, such as the linearity of thermal
expansion, shall be investigated, as well as the effects of anisotropy and large temperature ranges; - Measurement of
material properties on coupons, including expansion coefficients, stiffness, thermal conductivity and all relevant
parameters identified previously; - Verification of simulation tools and methods on coupons and joints; - Establishment
of measurement uncertainty requirements and stochastic character of simulation tools;
- Establish guidelines for predicting thermo-elastic distortions. In addition to methodologies for improved modeling,
these guidelines shall also consider making recommendations on the need to perform material and component level
tests.
Phase 2 - Definition of a breadboard representative of the complexity of a scientific instrument; - Modeling and
prediction; - Stochastic (and non-linear) analysis; - Definition of test set-up and selection of measurement technique; Correlation Where necessary, updating of guidelines established in Phase-1, and extension of guidelines to include
recommendations on performance of system level test verification methods.
Deliverables:
Design and verification guidelines; test coupons and breadboard; modeling procedures.
TRL 3-TRL 4
Current TRL:
TRL 2
Application/Mission:
Engineering tools applicable to all
S/C.
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
Contract Duration:
TRL5 > 2012
18 months
Dossier0 Ref.: T-543
This work has been planned since 2005 in the frame of the Space
Debris Programme. It is supported by CNES and DLR in the frame
of the Network of Centre Space Debris Coordination Group (NoC
SDCG).
TRP Reference:
T719-079MC
Title:
Mechanical design and verification methodologies for ceramic structures
TD:
TD20
Objectives
Development of design and verification methodologies for highly stable structures manufactured from
ceramic materials. Analysis methodologies as well test methodologies shall be defined. This shall include:
appropriate methods for derivation of allowables; numerical analysis methodologies e.g. effect of stress
concentrations, failure criteria etc; test methodologies, e.g. for prooftesting.
Description
Ceramic materials are being used in larger and load carrying structures and subsystems, however design and
verification methodologies to assure the reliability of such structures are lacking. The characteristics of such materials,
e.g. the variation in properties, brittleness, low damping etc makeing the application of conventional design and
verification approaches questionable - and in some cases unconservative.
Deliverables:
test results, TN for all aspects related to the developed methodologies
Current TRL:
TRL 3
Target TRL:
TRL 6
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Application
Need/Date:
2010
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TRP Work Plan 2008-2010
Description of Activities
Preferably in support to current
and new projects using ceramic
Application/Mission:
Contract Duration:
structures (optical benches, struts,
tores etc)
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
18 months
Dossier0 Ref.: T-5296, T-7750
N/A
TRP Reference:
T719-080MC
TD:
TD20
Title:
Self-Deploying Structures PHASE-1 : Concepts and Tools
Objectives
To develop and validate new concepts for a deployable structures
Description
Self-deploying structures offer an alternative to inflatable structures and classical mechanical constructions, with
outstanding mass/stiffness efficiency. Examples range from long masts and booms, foldable antennas, elastic hinges,
sunshields and sunshades... Operational constraints however, can require strict verification of requirements that are
not always possible with existing technologies. An example of operational difficulties is the deployment of the MARSIS
antenna onboard Mars-Express. A better knowledge and understanding in this technical discipline would have
simplified the operational difficulties.
Following tasks shall be performed: 1. Consolidate the state of the art of deployable structures exploiting the
self-deployment principle of elastic energy storage, 2. Study of applicability in terms of performances, failure modes
and verification approach, 3. Provide materials characteristics, 4. Select benchmark cases for different applications
(deployable masts, foldable antennas...), 5. Develop verification methods, in particular mechanical analysis of
deployment, shock and thermal stability. 6. Breadboard of elastic hinge and foldable mast for correlation of tools.
Deliverables:
Material data base, Mathematical models, Prototype software, Samples and breadboards
Current TRL:
TRL 2
Target TRL:
Science missions, Earth
Observation missions, Telecom
missions, exploration, manned
Application/Mission: modules, specifically: booms
(SCI), Radar/P band antenna
(EOP), Shields, Solar Array
structure.
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
2012
12 months
Dossier0 Ref.: T-617, T-7896 T-534
N/A
TRP Reference:
T719-081MC
TD:
TD20
Title:
Verification of New Sources of Composite Materials for Spacecraft Structures
Applications
Objectives
The objectives of this activity is to identify and verify European sources for fibres and resin.
Description
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TRP Work Plan 2008-2010
Description of Activities
European manufacturers of space structures are mainly using materials from the US and Japan. Although European
providers of resins and fibres are available their acceptance for space projects is limited. Typical reasons are a lack of
familiarity and missing confidence in those materials. Also costs, risks and efforts for performing individual qualification
programs is discouraging European manufacturers to select local suppliers. However, within the last year the
availability of “space proven” composite materials has become critical and may soon require to have reliable
alternatives.
THerefore, during the course of this activity following tasks are foreseen:
a) Researching the European market w.r.t. available resins and fibre materials (e.g. UMS 3536 carbon PAN fiber),
b) identifying two or three materials of each category, which are mostly used by all manufacturers of space structures
(eg. RS-3, RS-9, T300, M40J, M55J),
c) identifying the advantages of European “new generation materials” compared to older, certified materials, e.g. ACG
LTM123 low temperature moulding cyanate ester resin or novel spreading technology, which enables production of
very lightweight (80gsm) fabrics from more available/affordable large tows (12k and higher),
d) performing Qualification Tests according to ECSS and other standards and directly comparing the performance of
the materials under otherwise identical conditions (stiffness, strength, CTE, outgassing, thermal cycling, degradation
by radiation).
Deliverables:
Samples, Test Procedures, Test Results and statistical analysis, Documentation
Current TRL:
TRL 3
Target TRL:
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 4
Application
Need/Date:
Contract Duration:
2010
18 months
Dossier0 Ref.: T-534, T-7750
Consistent (Composites Harmonisation)
TRP Reference:
T719-082MC
TD:
TD20
Title:
Innovative curing systems for polymerisation in space
Objectives
To improve existing concept or find innovative solutions of curing system for rigidization by polymerisation,
of an inflatable composite structure.
Description
In the frame of TRP " Ultra-Light Structures", specification of curing system requirements (lighting characteristics,
temperature, inflatable structure geometry, polymerisation duration) and review of the available technologies for
lighting and/or heating system have been undertaken. During the course of the proposed activity, this will be updated
taking into account lessons learnt from the TRP project and problems identified on the current solution.
Deliverables:
Curing technology for inflatable and deployable structures, test samples, test reports
Current TRL:
TRL 3
Application/Mission: All spacecraft
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
TRL 4
Application
Need/Date:
Contract Duration:
2011
18 months
Dossier0 Ref.: T-534, T-7754, T-617
Consistent (Inflatable structures RoadMap)
TRP Reference:
T719-083MC
TD:
TD20
Title:
Methodology for analysis of structural born micro-vibration
Objectives
Development of a methodology for analysis of micro-vibration transmission through spacecraft structures.
Description
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Description of Activities
Equipment like Reaction Wheels, Gyros and Coolers are sources of micro-vibration in spacecraft. Often such
payloads/instruments onboard spacecraft have restrictions wrt the allovable micro-vibration disturbance allowed. The
verification is generally based on analysis, in some cases supported by source characterisation tests and tests to
define the transfer function in the structure. However, methodologies on how to perform the required analysis is
missing. Often the higher/mid-range frequencies are disregarded due to shortcomings in the FE models, and often the
dynamics and damping of the structural models are not verified for micro-vibrations (the dynamics and damping of teh
structure can be different when very small amplitudes are applied). In this study methodologies for micro-vibration
analysis will be developed, addressing details of the math models to be used as well as tests needed to characterize
the structure.
Deliverables:
documentation, test results,
TRL 5
Current TRL:
-
Application/Mission:
all spacecraft having
micro-vibration restrictions
Contract Duration:
SW Clause :
N/A
Dossier0 Ref.: T-7750, T-7766
Target TRL:
Application
Need/Date:
2011
18 months
Consistency with Harmonisation
Roadmap and Conclusions:
TRP Reference:
T719-084MC
TD:
TD20
Title:
Vulnerability of spacecraft equipment against space debris impacts
Objectives
The objective of the work is to provide quantified survivability data of meteoroid and debris impacts on
critical spacecraft subsystems to improve the mission success rate and/or to reduce the structural mass of
future spacecraft.
Description
Impact tests have to be performed on various equipment or representative samples (wiring, electronic boxes, pressure
vessels, batteries) to assess their functional degradation when damaged by space debris impacts. The test conditions
(low and high velocity, obllique impacts) will complement the test results already available.This could lead to a more
effective design of future spacecraft.
Deliverables:
Functional Ballistic Limit Equations suitable for Risk Analysis.
TRL 5
Current TRL:
TRL 3
Application/Mission:
All spacecraft subject to meteroid
and debris impact risk
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Application
Need/Date:
Contract Duration:
2010
24 months
Dossier0 Ref.: T-584, T-7765
This work has been planned since 2005 in the frame of the Space
Debris Programme. It is supported by CNES and DLR in the frame
of the Network of Centre Space Debris Coordination Group (NoC
SDCG).
7-21 - Thermal
TRP Reference:
T720-085MC
TD:
TD21
Title:
Innovative Analysis Methods for Improved Thermal Testing
Objectives
Develop and demonstrate innovative methods and software to reduce cost and time for performing
thermal tests and correlating between analysis predictions and test results.
Description
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Description of Activities
Today's ubiquitous availability of affordable and high performance computing and network communication enables
several options to significantly increase the efficiency of thermal testing. In this activity a coherent set of methods and
proof-of-concept software implementations to achieve such efficiency improvements will be developed:
(1) Early prediction of the thermal equilibrium during a TB test;
(2) Near-real-time correlation of observed test results with analysis predictions;
(3) Near-real-time extrapolation of temperature sensor readings of a system's test specimen to nodal temperatures of
a thermal mathematical model of the same system, including mapping onto and visualisation of a 3D geometric
representation of the system.
As a realistic target these measures should result in a reduction of both cost and elapsed time of TB/TV tests in the
order of 20%.
In detail:
Ad (1): After some time into a test it is possible using advanced discrete signal processing techniques (a.o. Kalman
filters) to predict, on the basis of the observations collected so far, what equilibrium temperatures will be reached
when. It enables better planning and allocation of people in the 24 hour shifts and, second, it permits shortening of test
phases.
Ad (2): Using automatically reduced models and advanced (stochastic) mathematical techniques for mapping,
inter/extrapolation and data fitting, it is in principle possible to correlate thermal mathematical models with observed
test results in a highly automatic way, much faster than today and already during the test.
Ad (3): Near-real-time display of temperature fields on a 3D geometric representation of the test article (similar to or
identical with the thermal geometric model) during the test greatly enhances the understanding of the thermal
engineers participating in a test, and thereby make them more efficient in performing their task.
The improvements shall be validated and demonstrated on at least two representative Phase C/D thermal test articles
and facilities (ESA space missions). The proof-of-concept software implementations shall be mature at beta version
level and shall be implemented in, or work seamlessly with, existing thermal analysis and test data processing
software that is commonly in use in ESA space projects.
Deliverables:
(a) Technical report on new method to predict thermal equilibrium during space system thermal balance tests;
(b) Technical report on new method to perform near-real-time correlation of observed test results with analysis
predictions;
(c) Technical report on new method to extrapolate temperature sensor readings onto 3D geometric model
representations;
(d) Software implementations at beta version level for all improvements;
(e) Demonstration report and presentation;
(f) Executive summary report and final presentation.
Note: In accordance with agreement reached in the Technical Harmonisation of Thermal and Space Environment
Analysis Software, all deliverables shall be published in the NESTA "R&D Pool"
Current TRL:
TRL 3
Target TRL:
TRL 5
All space missions, and in
Application/Mission: particular for those with stringent
thermal requirements
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
2010
12 months
Dossier0 Ref.: T-7882
Consistent with Technical Harmonisation of Thermal and Space
Environment Analysis Software (2002-2005) and subsequent
Network of Experts on Space Thermal Analysis (NESTA)
TRP Reference:
T720-086MC
TD:
TD21
Title:
Integrating the Finite Element Method into the Space Thermal Analysis Process
Objectives
The objective of the proposed activity is to address the deficiencies in current Finite Element Method
(FEM) tools that make them unsuitable for space thermal analysis. Prototype software and technical
documentation will be produced.
Description
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Description of Activities
The use of the Finite Element Method (FEM) for space thermal analysis promises many benefits compared with the
current Thermal Lumped Parameter (TLP) method used today. Thermal engineers would have access to state of the
art FEM pre-processors, providing more modelling functionality and increasing their efficiency. The fidelity of thermal
models, and their applicability for high accuracy and thermo-elastic applications, would also be improved.
Furthermore, the use of FEM modelling tools, and the link with CAD that they provide, would bring advantages for the
mechanical engineering design process (e.g. sharing of models with structures).
The objective of the proposed activity is to attain these potential benefits by addressing deficiencies, for S/C thermal
analysis, in current FEM tools, such as:
• FEM modelling of specific hardware for space thermal control such as multi-layer insulation (MLI), heat pipes, fluid
loops and heaters.
• FEM modelling of phenomena crucial for space thermal analysis e.g. thermal contact resistance
• Modelling of radiation exchange in an efficient way using FEM tools and solvers
• Implementation of thermal control logic in FEM models e.g. different operational modes of equipment
• Integration of traditional TLP models and FEM models e.g. how to plug in a subsystem level TLP model into a S/C
level FEM model or vice-versa
Deliverables:
(a) Software implementations at beta version level with user manual;
(b) Technical report providing:
- New finite element types developed, including generic mathematical formulations
- Techniques for modeling radiation and environmental heat fluxes using FEM
- Case studies / tutorials demonstrating the use of FEM for space thermal analysis and the functionality of the
developed prototype software
- Methodology for integrating hybrid FEM/TLP models and how to translate between the two methodologies
(c) Executive summary report and final presentation.
Note: In accordance with agreement reached in the Technical Harmonisation of Thermal and Space Environment
Analysis Software, all deliverables shall be published in the NESTA "R&D Pool"
Current TRL:
TRL 3
Target TRL:
Application/Mission: All space missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 5
Application
Need/Date:
Contract Duration:
2010
12 months
Dossier0 Ref.: T-7882
Consistent with Technical Harmonisation of Thermal and Space
Environment Analysis Software (2002-2005) and subsequent
Network of Experts on Space Thermal Analysis (NESTA)
TRP Reference:
T720-087MC
Title:
Thermal-radiative analysis of systems with wavelength dependent
thermo-optical surfaces
TD:
TD21
Objectives
Develop a method and software for thermal analysis of systems in which thermal radiation in the solar and
infra-red spectral bands depends on wavelength to such a degree that surfaces can no longer be idealized
as grey bodies.
Description
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Traditionally space thermal-radiative analysis is performed using the idealisation of grey bodies, which means that the
thermo-optical properties of all surfaces are regarded to be constant (i.e. independent of the wavelength of the
incoming radiation) within two spectral bands: the solar spectrum and the infra-red spectrum. This idealisation is
implemented in all space thermal analysis tools, such as ESARAD and ESATAN.
For systems in that have parts (in relatively close proximity) operating at very different temperature ranges – e.g.
some parts at moderate (room) temperature and some parts at very low (cryogenic) temperature or a mix of moderate
and very high temperatures – the grey body idealisation is no longer correct and causes large discrepancies between
analysis predictions and observed thermal behaviour. Also such thermal analysis models do not provide the thermal
engineer with an adequate insight in the heat balances that govern the thermal design problem. A so-called non-grey
body analysis capability is needed. This situation has arisen in a number of thermally demanding spacecraft
programmes, e.g. for the Herschel cryostat.
In this activity a method to perform thermal analysis for such systems shall be developed and clearly documented.
The method shall then be implemented and demonstrated on one of the space thermal analysis tool suites that are
commonly used in European space projects. The demonstration models shall comprise at least three simple reference
configurations for which theoretical results are available and at least two representative real ESA space project
models.
Deliverables:
(a) Technical report on method to perform thermal-radiative analysis for models with wavelength dependent
thermo-optical surfaces;
(b) Software implementations at beta version level with user manual;
(c) Demonstration report and presentation;
(d) Executive summary report and final presentation.
Note: In accordance with agreement reached in the Technical Harmonisation of Thermal and Space Environment
Analysis Software, all deliverables shall be published in the NESTA "R&D Pool"
Current TRL:
TRL 3
Target TRL:
Application/Mission: Science/EO Missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 5
Application
Need/Date:
Contract Duration:
2010
12 months
Dossier0 Ref.: T-7882
Consistent with Technical Harmonisation of Thermal and Space
Environment Analysis Software (2002-2005) and subsequent
Network of Experts on Space Thermal Analysis (NESTA)
TRP Reference:
T720-088MC
Title:
Small Scale Cooler
TD:
TD21
Objectives
The objective is to develop and test a small scale cooler for the temperature range down to 80K for small
payloads.
Description
For Earth Observation, Science and Exploration, there is a need in the future to have small scale coolers (with a mass
of less than 1 kg) providing cooling capacities of 0.5 W down to 80K to fulfil the needs of small payloads, experiments
and piggy-back missions. Currently several European and non-European missions use a Israelian tactical cooler for
this purpose, however with limited visibility on the configuration and qualification status.
In Europe there exist today a variety of suitable cooler and compressor technologies which are currently used for
different space and military applications, such as Stirling, Pulse Tube and JT coolers using either linear, rotary or
sorption compressors.
Based on these technologies, a small, compact and competitive cooler shall be developed. In addition, such a cooler
shall also provide a standard I/F towards the detectors as e.g. used for military ground aplications to allow the
potential use off COTS detectors and dewars in the future.
In the first part of the activity, a detailed design of the cooler shall be performed, supported by a detailed
modelling study on miniaturisation, based on an
existing proven cooler design. In the second part, the
cooler shall be manufactured and performance tests
shall be performed.
Deliverables:
Cooler Prototype; complete set of technical documents incl. design, test and test evaluation documents
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Current TRL:
TRL 2
Target TRL:
TRL 4
Application/Mission: SCI/EO/Exloration
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRP Reference:
T720-089MC
Title:
Linear Fluid Pump
Application
Need/Date:
Contract Duration:
2010
24 months
Dossier0 Ref.: T-7877
Under discussion
TD:
TD21
Objectives
The objective is to develop a highly reliable longlife pump for liquids based on the existing flexure bearing
linear compressor technology developed for Stirling/Pulse Tube coolers,
Description
Compressors based on flexure bearings have been successfully developed in Europe for driving Stirling and Pulse
Tube coolers and have shown a lifetimes of up to 16 years during ground tests and 8 to 10 years of in-orbit operation.
For pumping liquids as for example in heat transport loops (single or two-phase), the pumps are mainly based on
rotary types, with the need for dynamic seals and bearings. As potential alternative to such pumps, an existing longlife
compressor (based on flexure bearings and hence not needing any dynamic bearings) shalll be adapted to allow the
use of liquids instead of gases as working fluid. As this design does have the potential for scaling, potential
applications for such pumps in cooling loops (single- and/or two-phase) can cover a large range, from the thermal
control of Rovers, dedicated thermal control of laser instrument, up to pumped thermal control loops for future telecom
S/C.
The activity shall start with the establishment of a list of liquids compatible with the compressors and with thermal
properties needed for thermal control loops and potentially also in heat pumps. The existing compressor design shall
then be adapted for such fluids if and where needed, however without changing any of the design features which are
related to lifetime issues. The adapted compressor shall then be tested with various fluids, mainly focussing on fluids
suitable for thermal control purposes.
After evaluation of the results, an improved, preliminary design of a liquid linear longlife compressor shall be
established and performance estimates provided
Deliverables:
Linear Fluid Pump breadboard; complete set of technical documents incl. design, test and test evaluation documents
Current TRL:
TRL 1
Target TRL:
Application/Mission: All
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
2010
18 months
Dossier0 Ref.: T-8437
N/A
TRP Reference:
T720-090MC
TD:
Title:
Thermo-Electric Cooler
TD21
Objectives
The objective is to develop a European highly reliable thermo-electric cooler for detector and sample
cooling compatible with the Space Environment.
Description
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A number of instruments and payloads for Earth Observation, Exploration and Science require active solid state
cooling of detectors or samples up to 30K below the environment to either achieve the operating temperature or to
stabilise the temperature. Such a technology could also be used as add-on stage to a passive cooler/radiator to reach
cryogenic temperatures without the use of Stirling or Pulse-Tube coolers (e.g. for SWIR detectors).
Thermoelectric (Peltier) coolers can provide an effcient and compact solution for such applications.
However, there is currently no European source for such items for use in space applications.
Within the activity, a thermo-electric cooler, suitable to cool detectors or sample 30-40 K below the environment in
Space shall be developed, taking advantage of existing technologies and capabilities developed in Europe for ground
and military applications. Various staging concepts shall be investigated. The packaging and I/F shall be compliant
with standard space procedure/standards and a suitable electronics concept to operate the
Thermo-Electric Cooler shall also be established. A
prototype of such a cooler shall then be
manufactured and tested to establish its
perfomance map.
Deliverables:
Cooler Prototype; complete set of technical documents incl. design, test and test evaluation documents
Current TRL:
TRL 2
Application/Mission:
EO/SCI/Microgravity
Payloads/Exploration
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
TRL 4
Application
Need/Date:
Contract Duration:
2010
18 months
Dossier0 Ref.: T-7877
Under discussion in the frame of Cryogenics & FocalPlane Cooling
Harmonisation 2007; strongly supported by EuroSpace
TRP Reference:
T720-091MC
TD:
Title:
Extra Flat Mini Two-Phase Loop
TD21
Objectives
The objective is to design, manufacture and test extra flat miniaturised two-phase loop at development
model level
Description
The thickness of a miniaturised European loop heat pipe (Mini-LHP) evaporator-reservoir bloc is currently around
18-20 mm depending on the overall loop architecture (mainly fluid line and condenser length).
Even though there are a number of very promising applications for this design, the accommdation of such an
evaporator inside electronic equipment and directly on electronic boards is limited due to this thickness. A further
reduction of this thickness would allow to implement such Mini-LHP much closer to the actual heat source, e.g. on or
next to the high power component.
The goal of the activity is to reduce the thickness of the miniaturised evaporator to less than 10 mm. This could be
obtained by design modification of the reservoir which could be located close to (maintaining the LHP concept) or
remotely from the loop evaporator (baselining the CPL concept).
The activity shall start with a trade-off of all potential design concepts allowing to further reduce the evaporator
thickness, followed by a detailed design of such a device and a complete test programme to fully
elaborate its performance.
Deliverables:
Development model(s) of Extra Flat Mini-TPL; complete set of technical documents incl. design, test and test
evaluation documents
Current TRL:
TRL 2
Target TRL:
Application/Mission: EO, Telecom, Sci, Exploration
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 4
Application
Need/Date:
Contract Duration:
2010
18 months
Dossier0 Ref.: T-7875
Consistent with Heat Pipe & Two-Phase Harmonisation 2003
TRP Reference:
T720-092MC
Title:
Heat Pump conceptual study and design
TD:
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Description of Activities
Objectives
The objective is to establish a conceptual thermal control design based on a heat pump system to enable
future ESA Exploration missions subjected to "warm" environment and/or to enable future very
high-powered telecommunication satellites
Description
The heat rejection for future Moon/Mars missions and high-powered S/C will necessitate unacceptably large radiating
surface with current thermal control devices. The only way to enable those missions is to raise significantly the
operating temperature of the limited radiating surfaces that could be implemented in the spacecraft and/or on a
planetary base. This could be obtained by using heat pumps which are not yet used for space applications. A heat
pump is by definition any device that accepts heat at one or more temperatures and rejects heat at a higher
temperature. The study will be divided into several tasks :
- To perform a complete review/assessment of all terrestrial heat-pump technologies resulting in an extensive
heat-pump database
- To review the compliance of all heat-pump technologies with respect to space environment in general and to lunar
and martian specific environment
- To perform an extensive trade-off between the selected heat-pump technologies
- To establish a conceptual design and a Development Plan based on the most promising
technology/technologies, clearly indicating all
steps to be taken in order to reach
space-useable/qualified heat pumps.
Deliverables:
Heat Pump Database; conceptual design of heat pump; development plan for a heat pump for space
Current TRL:
TRL 1
Target TRL:
Application/Mission: Exploration, Telecom
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
2012
12 months
Dossier0 Ref.: T-8439
N/A
7-24 - Materials & Processes
TRP Reference:
T723-093QM
TD:
TD24
Title:
Gecko mimetic Tape as new joining technology.
Objectives
To investigate the possible methods of mass producing adhesiveless pressure sensitive tape.
Description
There have been numerous attempts to replicate the adhesive properties of the gecko lizard whose mechanism is
dependent on submicron keratin hairs, each of which produces a small adhesive force. Recently, prototypes of this
tape have been produced by replicating the structure of these hairs though microfabrication of dense arrays of flexible
plastic pillars.
Some laboratories already produce this tape, but with small surfaces size (typically a few square centimetres).
The work performed through this activity will aim at:
• Developing size,
• Developing reliability (same properties everywhere),
• Investigating on which surfaces such a tape can work,
• Investigating in which conditions of temperature, pressure and so on such a tape can work.
Deliverables:
Test samples, Test report.
Current TRL:
TRL 2
Application/Mission: All missions
N/A
SW Clause :
Target TRL:
TRL 3
Application
Need/Date:
Contract Duration:
TRL 5 by 2012
24 months
Dossier0 Ref.: T-8388
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Consistency with Harmonisation
Roadmap and Conclusions:
N/A
TRP Reference:
T723-094QM
TD:
TD24
Title:
Stress Corrosion Testing of Particle Metal Matrix Composite (PMMC) and Friction
Stir Welded (FSW) of Particle Metal Matrix Composite (PMMC) Materials
Objectives
To screen suitable ultra-fine PMMCs and FSW PMMCs for space applications. Investigate
stress-corrosion susceptibility of the selected combination of PMMCs and FSW PMMCs.
Description
In the last few decades, Particle Metal Matrix Composites (PMMCs) have come increasingly to the attention of the
academic community and of the industrial sector.
The main improvements brought by PMMCs with respect to the mere matrix are higher stiffness, mechanical and wear
resistance, with a quasi-isotropic mechanical response. A major concern for PMMCs application lies in the joining
technology and the resulting strength of the bond. Solid state processes, like Friction Stir Welding (FSW), have
generally a lower detrimental impact on the strength of PMMCs than liquid state processes.
Until now the PMMCs submitted to test campaign, did not reach the Stress Corrosion Cracking (SCC) resistance,
required for space applications. New materials reinforced with ultra-fine particles, new manufacturing and joining
technologies could allow PMMCs to be used in structural space components
The study shall include screening of new ultra-fine PMMCs suitable for space application, screening of optimum FSW
parameter for the selected PMMCs, test-plans, test samples, test reports.
In case of successful outcome of FSW of PMMC, a definition of deeper mechanical characterisation of the selected
materials and joints will be performed. Preparation of test plan and costs estimate for future test activities will also be
drafted.
Deliverables:
Material procurement, Tests data and report.
Current TRL:
TRL 2
Target TRL:
Application/Mission: All primary Spacecraft structure
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
TRL 5 by 2011
12 months
Dossier0 Ref.: T-8388,
N/A
TRP Reference:
T723-095QM
TD:
TD24
Title:
Carbon Nano Fibre based material for high conductivity
Objectives
To develop high conductivity materials based on Carbon Nano Fibres (CNF) / metal.
Description
The feasibility of mixing very high volume-percent of Carbon Nano Tubes (CNT) into a metallic matrix has been
demonstrated through the TRP “Carbon nanotube based composite materials” contract (number 19128).
The expected advantage of such CNT reinforced material was a very high conductivity.
It nevertheless appeared that the conductivity was not as high as expected. The matrix / reinforcement combination
was not optimal. The matrix reactivity toward CNT was not sufficient and the very small diameter of the CNT was
impeding the thorough mixing of the CNT with the matrix.
Two means of improvement can be pursued in order to obtain the desired very high conductivity:
• Using CNF (Carbon Nano Fibres) as they are bigger and their surface is more reactive than CNT,
• Work on the matrix composition to further increase reactivity.
The activity shall include the selection of composite system (matrix and reinforcement), the optimisation of material
processing and the characterisation of the materials developed.
Trade-offs between these materials will also be performed.
Deliverables:
Samples production, Test report.
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Description of Activities
Current TRL:
TRL 1
Target TRL:
Application/Mission: Lidars, LISA
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 2
Application
Need/Date:
Contract Duration:
2015
24 months
Dossier0 Ref.: T-8390
N/A
TRP Reference:
T723-096QM
TD:
TD24
Title:
Coefficient of Thermal Expansion (CTE) variation of thermally stable materials
Objectives
To establish the best technique to measure accurately CTE of dimensionally stable materials (e.g.
Zerodur, SiC and Invar) down to a temperature of at least 10K and with an accuracy of 10 ppb/K (parts per
billion/Kelvin), in order to predict large structures behaviour.
Description
The basic problem tackled through this activity will be the ability to predict, based on small samples, the behaviour of a
large structure made of stable materials.
The activity shall include a literature survey of possible techniques for CTE measurement and trade-off of CTE
measurement techniques. A round robin (i.e. same materials tested with different techniques at various spots)
measurement of some stable materials shall be performed. The definition of requirements for manufacturing
equipment able to measure CTE variations of stable materials shall be established.
Deliverables:
Test programme, Test report, definition of measurement facilities requirements.
Current TRL:
TRL 1
Target TRL:
Application/Mission: LISA, JWST, EO missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 2
Application
Need/Date:
Contract Duration:
2012
36 months
Dossier0 Ref.: T-8391
N/A
7-26 - Spacecraft Avionic System
TRP Reference:
T701-097ED
TD:
TD01
Title:
Reference Architecture for High Reliability - Availability systems
Objectives
Provide a Reference architecture for the category of “Highly reliable-Available systems”
Description
Within the AVIONICS initiative a new architecture for the category of “Highly reliable-Available systems” needs to be
developed. It shall be a multi-mission avionics based on a compact integrated and open design with emphasis on:
- Reusability,
- Reduction of mass/power/size/harness budgets, AIT effort,
- Plug and Play architecture based on standards such as CCSDS SOIS,
- Specifications of main building blocks and related interfaces,
- Implementation of FDIR-Autonomy requirements
The activity will be performed into two main phases. In the first phase, from the analysis of the reliable/available
missions and of the ESA SOW, the contractor shall provide an initial definition of the reference architecture to be
object of a SSR and a public presentation forconsolidation.
When consolidated, the contractor shall perform the specifications of the architecture, identification of the main
building blocks and o their internal and external interfaces that shall include models generation.
Those specifications after PDR , will be provided as an input to the activities dedicated to the development of the
reference building blocks
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Description of Activities
Deliverables:
Reference Specifications of requirements of reference architecture, Models of the building blocks and interfaces,
Specifications of requirements for the Use cases “test applications”, Behavioural parameters
Current TRL:
TRL 2
Target TRL:
Application/Mission: SCI/EO/Exloration Missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 5
Application
Need/Date:
Contract Duration:
2012
18 months
Dossier0 Ref.: T-7803
Consistent (“Avionics- Embedded System” (2nd semester 2006) –
activity D1)
TRP Reference:
T701-098ED
Title:
Requirements Definition for On Board Data Systems and software for end to end
security
TD:
TD01
Objectives
Within the frame of the multi-mission avionics reference architecture and within the scope of scientific or
commercial missions, this activity is the first step to perform the definition of an end to end security
concept (single and multi-systems) and using the proper methodology on which to base the definition and
the specifications of the on board security building blocks that shall be designed and developed by
follow-on activity in GTSP or Artes .
Description
To provide in a first step an end to end security concept from use cases analysis in different service domains
(telecommunication, EO, science, Man space, robotics exploration)
To infer and extract the set of requirements to be met on board by the on board equipment (TM-TC, internal
communications support, O/B software) that shall be subject of a PDR
To publish the consolidated requirements as an input to the activities in charge of developing the corresponding on
board building blocks as well as establishing the overall validation strategy
Deliverables:
specifications of requirements, validation strategy
Current TRL:
TRL 2
Target TRL:
Application/Mission: SCI/EO/Exloration Missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
2011
12 months
Dossier0 Ref.: T-7805
Avionics- Embedded System (2nd s'r 2006) – activity E1
TRP Reference:
T701-099ED
TD:
TD01
Title:
Spacecraft Controller on Chip (SCOC3) ASIC manufacturing & test
Objectives
Manufacturing, test and initial validation (TRL4) of the SCOC ASIC and its establishment as a standard
component available to European space industry
Description
SCOC is a concept integrating various functions of an on-board computer into a single (System-On-Chip = SOC),
such as the main processor, memory interfaces, telecommand/telemetry units, housekeeping data collection, time
generation and various interfaces to other subsystems (spacewire, CAN, 1553 etc.). Main benefits of the SOC
integration are the improvement of the performance vs. power and mass ratio, and the increase in reliability by
reducing board-level interconnect. Feasibility study and proof of concept with an FPGA demonstrator has been
conducted previously in TRP contract C13345, and the Architectural Design of the SCOC ASIC is currently ongoing in
TRP contract C20167. The architectural design, which has been established, coded in circuit description language
and verified during the predecessor contract (C20167), will be finalised (e.g. adding test logic) and synthesised into a
gate level netlist mapped on the ASIC vendor's standard cell library. ASIC Layout will then be produced by/in
cooperation with the selected ASIC foundry. ASIC manufacturing and production test is outsourced entirely to the
ASIC vendor. Finally, the contractor shall perform validation of the ASIC in an application board. Continuous
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Description of Activities
verification of the results by various techniques and tools accompanies the whole development flow and is an
important part of the activity. Availability of this new chip as a "standard ASIC" shall be ensured by making appropriate
contractual agreements in order to guarantee fair commercialisation of the device for European space industry,
supported by comprehensive device documentation and technical support. Task breakdown: Feasibility and Delta
Architectural Design: updating the existing design to latest known versions of its basic building blocks, adding
testability logic etc. Feasibility study to confirm the ASIC technology selected in the predecessor contract. Concluded
with Delta-PDR. Detailed Design: Logic Synthesis (translation into gate level netlist), concluded with Detailed Design
Review. Layout: Mainly performed by the ASIC foundry, but contractor gives support during layout optimisation and
verification of the post-layout netlist. Concluded with Design Review (or CDR). Manufacturing in the Atmel ATC18RHA
technology and Testing: Performed by the ASIC foundry, but contractor has to provide test pattern and analyse test
results (failures). Silicon cost to be covered by the SMPW programme. Validation: Development and production of a
validation board, where the chip will be exercised in various operating situations, following a validation plan.
Concluded with Validation/Final Review.
Deliverables:
Verification/validation plan, Datasheet, Detail Specification, Design Reports, Design Database with source code,
scripts and netlists at various stages until final gate netlist, ASIC prototypes, validation hardware (board) and software,
standard component agreement/commitment
Current TRL:
TRL 4
Target TRL:
Application/Mission: SCI/EO/Exloration Missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 6
Application
Need/Date:
Contract Duration:
2010
18 months
Dossier0 Ref.: T-7753 T-7799
Consistent (E12, in µE Dossier)
TRP Reference:
T701-100ED
Title:
Network Discovery Protocols
TD:
TD01
Objectives
Definition, implementation and test of the network discovery protocol and plug and play techniques over a
SpaceWire network. Prototyping of the technique prior to the formal standardisation.
Description
The SpaceWire working group on PnP has drafted a protocol specification to allow network discovery and the
detection of configuration changes in the network. The objective of using these techniques is to support rapid
integration of future spacecraft that are using SpaceWire networks. A SpaceWire network PnP test bed shall be built
up mainly from existing SpaceWire equipment. The necessary functions to support the PnP protocol shall be
implemented firmware and in software. Functional tests shall be performed, assessing the usefulness and derive
recommendations for improvements.
Deliverables:
SpaceWire network PnP test bed, test results and protocol recommendations
Current TRL:
TRL 2
Target TRL:
Application/Mission: SCI/EO/Exloration Missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 4
Application
Need/Date:
Contract Duration:
2011
12 months
Dossier0 Ref.: T-7801
"On-board Paylaod Data Processing" (activity B2)
TRP Reference:
T701-101ED
TD:
Title:
Avionics System Integration and Validation
TD01
Objectives
This activity is a complement to the "Reference Architecture for High Reliability - Availability systems"
activity, aiming at seting up a test and validation testbench for building blocks conformant to the
architecture definition.
Description
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Description of Activities
Under this activity the specification of a common evaluation environment will be prepared and provided as input to all
relevant activities. The specification shall take the existing ESTEC RASTA test-bed as input and include any upgrades
that may be required to incorporate TRP activity output or reach system level integration. Support shall be provided for
the acceptance of each TRP deliverable and subsequent overall system integration and test. Tasks will include the
connection to similar test-beds both within estec and and ESOC.
Deliverables:
Technical report of expected TRP outputs and how they may be evaluated in the RASTA environment; the report will
identify any updates required to RASTA.
Updated RASTA test-bench implementation;
Specification of the finalised RASTA environment to be applied to the delivery and test requirements of all relevant
TRP activities.
Support for the integration and acceptance testing of each TRP deliverable;
Current TRL:
TRL 4
Target TRL:
Application/Mission: SCI/EO/Exloration Missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 6
Application
Need/Date:
Contract Duration:
2010
18 months
Dossier0 Ref.: T-7803
“Avionics- Embedded System” (2nd semester 2006)
TRP Reference:
T701-103ED
Title:
Delay Tolerant Networking prototyping (Ph.2 of T701-012ED +T701-103ED)
TD:
TD01
Objectives
In relation to the ESA exploration programme and the constellation programme of NASA, the CCSDS is
developing new protocols applicable to a networked environment involving significant delays and disjoint
connectivity. As part of the CCSDS specification process, there is a need to prototype the selected
protocol stack and validate the communication protocols in a realistic test-bedding environment.
Description
This activity Ph.2 of the combined T701-012ED + T701-103ED developement, and will perform the necessary
prototyping and validation exercise for the flight implementation. A separate activity is performed for the ground
segment and as part of the work the two implementations will be interconnected and evaluated.
Deliverables:
Prototype implementation of the selected protocol suite covering both forward and return links ported to the Estec
Rasta facility.
Test suite suitable for analysing all aspects of the protocols.
Test report providing feedback on the protocol stack specification.
Current TRL:
TRL 2
Target TRL:
Application/Mission: SCI/EO/Exloration Missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 4
Application
Need/Date:
Contract Duration:
2012
18 months
Dossier0 Ref.: T-7727
Consistent with “Avionics- Embedded System” (2nd semester
2006)
TRP Reference:
T702-104SW
TD:
TD02
Title:
Software Reference Architecture implementation prototype
Objectives
Following the definition of a generic on-board software architecture in CORDET, this study intends to
consolidate the definition and prototype an implementation
Description
Update the CORDET reference architecture with the last technology update and harmonisation decision; baseline the
tools for the genericity definition and the vertical transformation and the middleware; develop the functional models
and the non functional architecture and interface; generate code and integrate and validate
Deliverables:
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Description of Activities
CORDET requirement baseline, prototype implementation including technical specification and associated models,
design, code, tests; sw development environment
Current TRL:
TRL 2
Target TRL:
TRL 3
Application/Mission: SCI/EO/Exloration Missions
Operational SW
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
2011
18 months
Dossier0 Ref.: T7671
Consistent (G1)
TRP Reference:
T702-105SW
TD:
Title:
Guidelines for the selection of architectures
TD02
Objectives
Within the context of the definition of reference architectures, provide a methodology to select one of them
w.r.t a set of paremeters relevant to space missions.
Description
Establishment of a systematic list of criteria impacting on the design of an avionic embedded system (physical
characteristics such as power and throughput, functional capabilities such as applications type, non-functional such as
dependability, security, safety); establishment of a set of potential solutions (number of processor, hot/cold
redundancy, IMA, decentralized, distributed, etc); systematic trace criteria/solutions and guidelines on trade-offs.
Deliverables:
Guidelines for the selection of an avionics embedded system
Current TRL:
TRL 2
Target TRL:
Application/Mission: SCI/EO/Exloration Missions
SW Clause :
Application
Need/Date:
Contract Duration:
2009
12 months
T7743, T7661, T7662, T7753,
Dossier0 Ref.: T7937, T7739, T7660, T7803,
T5224
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Consistent (I7)
TRP Reference:
T702-106SW
TD:
TD02
Title:
Functional requirements and verification techniques for the software reference
architecture
Objectives
To complement ASSERT with a systematic investigations for verification aspects (proof-based) for
real-time and fault tolerance
Description
selection of list of methods and tools for functional and non functional aspects and of a middleware; systematic
analysis of the methods and tools to derive possible verification and associated methods; analysis of the possibilities
of the proof of the middleware (e.g. formal methods or other modelling); investigate the Globally Asynchronous Locally
Synchronous approach; implement missing tools; demonstration on a case study
Deliverables:
guidelines and user manual on the systematic approach of verification of models and middleware; associated toolset;
case study
Current TRL:
TRL 2
Target TRL:
Application/Mission: SCI/EO/Exloration Missions
TRL 3
Application
Need/Date:
Contract Duration:
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Description of Activities
SW Clause :
T7743, T8157, T7667, T7661,
T7662, 7666, 7753, 7937,
Dossier0 Ref.:
7660, 908, T7820, T5224,
T1560, T1073
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Consistent (I4)
TRP Reference:
T702-107SW
TD:
Title:
System impact of distributed multicore systems
TD02
Objectives
How to make best use of the future multicore and to mitigate the risks due to (software) complexity, in
relation with the system needs
Description
setup the various system scenarios where a multicore can be used (distribution, segeragation, debugger-on-chip,
parallel processing, reconfiguration, etc); analyze the hardware capabilities of the chip as designed at that time; define
guidelines on the use of the chip, hardware configuration, software use or misuse; software implementation in various
cases to measure the impact
Deliverables:
guidelines for the use of multicore in spacecrafts; prototype implementation with software, case study and report
Current TRL:
TRL 1
Target TRL:
Application/Mission: SCI/EO/Exloration Missions
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 2
Application
Need/Date:
Contract Duration:
2010
18 months
Dossier0 Ref.:
T7743, T8157, T7803, T7799,
T5224,
TD:
TD02
Consistent (I5)
TRP Reference:
T702-108SW
Title:
Verification of failure impact by model checking
Objectives
To complement the work done with discrete model checking with hybrid model checking
Description
The activity shall complement the scenarios investigated up to now for on-board model checking with the control
needs (monitoring of continuous values). Furthermore, it shall investigate the hybrid model checking technologies;
realize an on-board component prototype and demonstrate it with a case study
Deliverables:
prototype component of on-board hybrid model checking and documentation; case study
Current TRL:
TRL 2
Target TRL:
Application/Mission: SCI/EO/Exloration Missions
SW Clause :
Application
Need/Date:
Contract Duration:
2012
18 months
T7743, T8157, T7727, T7667,
Dossier0 Ref.: T7662, T7666, T5224, T1073,
T1259
Operational SW
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Consistent (I6)
TRP Reference:
T702-109SW
TD:
Title:
Spacecraft Controller on Chip (SCOC3) software support
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Description of Activities
Objectives
Software support development for the SCOC3
Description
Selection of software functions from the reference architectures to be implemented on the scoc3 board in order to
exercize the design in a representative manner, with focus on the lower level layers of the software, plus a dummy
application or VSRF like. Implementation, test and validation.
Deliverables:
Software support components, Selected key S/W functions, Representative application, Test reports for SCOC3 and
associated E40 tailored documentation
Current TRL:
TRL 2
Target TRL:
TRL 3
Application/Mission: SCI/EO/Exloration Missions
Open Source
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRP Reference:
T702-110SW
Title:
HW-SW Codesign
Application
Need/Date:
Contract Duration:
2010
18 months
Dossier0 Ref.: T-7753 T-7799
Consistent (activity D1)
TD:
TD02
Objectives
Derive a common approach for SW and HW design, with common up-front descriptions/specifications and
tools.
Description
Summary of the model based technologies for avionics and software (SysML, UML, AADL, Scade, SDL, etc);
summary of the current trends in microelectronic in the beginning of the life cycle (SystemC); consistent mapping and
continuity (model transformation) between avionics and [software/microelectronics] in order to make consistent the
HW/SW co-design; identification of needed tools; methodological guidelines
Deliverables:
Study report documenting methodologies avionics, sofwtare and microelectronic; description of a development
environment
Guidelines for a common SW and HW design methodology
Current TRL:
TRL 1
Target TRL:
TRL 2
Application/Mission: SCI/EO/Exloration Missions
SW Clause :
Contract Duration:
2010
18 months
T7743, T7661, T7662, T7753,
Dossier0 Ref.:
T908, T7799
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Consistent (K1)
TRP Reference:
T702-111SW
TD:
Title:
Full Model Driven Development for o/b software
TD02
Objectives
Use Assert for the aspects which are consistent, complement the assert pilot projects, prepare the
commercialisation of the tools, adapt methodology for use in projects
Description
selection of a virtual machine, vertical transformation tools; selection of functional tools; consolidation of the links
functional/non-functional; case study selection, requirements and technical specification; code generation and vertical
transformation, integration and test
Deliverables:
case study functional and non functional models, sw development environmnt, validated case study
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Description of Activities
Current TRL:
TRL 2
Target TRL:
TRL 3
Application/Mission: SCI/EO/Exloration Missions
SW Clause :
Contract Duration:
2010
18 months
T7743, T8157, T7667, T7661,
T7662, 7666, 7753, 7937,
Dossier0 Ref.:
7660, 908, T7820, T5224,
T1560
Open source
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Consistent (I1)
TRP Reference:
T705-112EC
TD:
Title:
FDIR using Model Predictive Control
TD05
Objectives
In the preparation of future avionics technologies the activity will prove the concept of model-based FDIR
using MPC (Model Predictive Control) technology. In particular, it will demonstrate that the GNC
implements safe and precise control, while enabling automatic reconfiguration capabilities to cope with
e.g. actuator degradation, mission goal change, and even collision avoidance. In addition, a HW-SW
co-design approach will allow to trade-off software and FPGA implementation in view of very demanding
computational resources required.
Description
The activity will study the guidance and control unit includes flight management function for mode control, fault
tolerance and trajectory planning and reconfiguration.
At system level, the activity will study the Impact of MPC on system design and architecture, in particular hardware
and software performance and architecture. The verification aspects of such a system, in particular real-time
behaviour (predictability), will be also investigated
A trade-off of various real-time FPGA processor implementations of the MPC algorithms for autonomous rendezvous
shall be examined to establish and understand timing effects and decision of the reconfiguration strategies in the face
of the closed loop control system properties. Based on real time considerations and operational constraints a trade-off
study must be conducted to develop new FPGA based GNC architectures and relate it to the on-board software
architecture.
The activity will select an industrial case study (e.g. the micro inspector), and develop an experiment that shall be
implemented on a dedicated experimental unit that tests the functional capabilities of the autonomous reconfiguration
GNC based on the MPC concept. The experimental unit will activate the FPGA based GNC and collect data for online
and post processing.
The activity shall consolidate the MPC based GNC optimization and processing algorithms including MPC support
functions.
The FPGA related tasks should include:
• Establish FPGA based MPC implementation issues, integration with all GNC functions, consolidate a suitable GNC
architecture.
• Development of MPC based rendezvous GNC architecture and software components and detailed design, coding
and validation in a flight-like processor.
• Design, development and testing of the FPGA implementation of the identified rendezvous critical functions such as
self test and online MPC validation function that guarantee performance and the stablity of the closed loop system at
any time.
• Detailed design, manufacturing, integration and testing (electrical and functional) of the experiment unit integrated
with of the rendezvous GNC on the FPGA.
Deliverables:
Development of autonomous and fault tolerant rendezvous GNC expriment with MPC implementation on an FPGA.
Validated MPC GNC on an FPGA breadboard.
Current TRL:
TRL 2
Target TRL:
TRL 3
Application/Mission: SCI/EO/Exloration Missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
2010
18 months
Dossier0 Ref.: T-7821
Consistent (D1)
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Description of Activities
TRP Reference:
T705-113EC
Title:
Anytime Monitoring and Control
TD:
TD05
Objectives
Current digital control systems are based on a fixed cyclic implementation. This activity will analyse the
interest (e.g. for high accuracy systems) and feasibility of adapting during execution the value of the
control loop cycle to external constraints such as dynamics of the input, accuracy needs, or computer
throughput availability.
Description
Anytime algorithms for realtime systems are special computational structures that provide optimal monitoring and
control with respect to the available computational resources.This activity aims at developing theoretically well
founded real time control implementations of nonlinear systems and structured paramter varying systems. The
objective is to first develop special system decompositions into multiplexed Linear Time Invariant modules to allow
variable structured system implementations reflecting varying hierarchical levels of performance and robustness. The
sum of the all the LTI components allow fixed time computation and can always be executed within a fixed available
CPU. However when CPU resources vary and become less that allocated, the control algorithms cannot be executed.
By multiplexing the right amount of switched systems to fit the available CPU an optimal performance can be achieved
anytime. Second the activity aims at studing the system theoretic aspects relavant to real time implementations of
model based estimation and control algorithms as to be able to guarantee online system robustness and performance.
Definition of a scenario to measure the impact of anytime control compared to traditional one (e.g. thruster Pulse
Width Modulation). Architecure definition and trade-off on hardware (FPGA) and software implementation.
Implementation of case study and benchmarking. Impact on the schedulability analysis.
Deliverables:
System architecture, method (schedulability verification), tools, implementation of software demonstrator of anytime
monitoring and control
Current TRL:
TRL 1
Target TRL:
TRL 3
Application/Mission: SCI/EO/Exloration Missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
2010
12 months
Dossier0 Ref.: T-8384
Consistent (H3)
TRP Reference:
T705-113EC
Title:
Mathematical Library for On-board AOCS Algorithms
TD:
TD05
Objectives
The end objective of this activity is to develop on board SW library offering generic mathematical services
(trigonometric functions, matrices and quaternions operations ...) and high level functions such as
integrators, filters, propagators on-board a spacecraft. The intention is that these building blocks will be
made available to ESA member states, in line with the Embedded Systems Harmonisation roadmap.
Description
The AOCS application software is based today on mathematical models which include some operators and basic
functions on several types of data. In a first time, the goal of this activity will be to specify a hierarchical library of
mathematical functions. The first layer of this library will be the basic trigonometric functions and operators on data
type as quaternion, vector, matrice. The second layer will be based on the "state of art" AOCS need , with a first set of
high level functions such as integrator, filter, propagator etc ....
From this library specification, the activity will proceed with the implementation of the functions (the definition beeing
captured on a Matlab/simulink model), and the qualification of these ones for a Leon environment. As output of the
qualification, a user manual will be delivered to precise the domain of use and numerical accuracy of each on board
algorithm. To avoid to embed systematically all the library if not necessary, a build procedure to take into account only
the final user needs will be proposed.
During all this activity the ECSS E40/Q80 shall be applicable.
Deliverables:
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Description of Activities
Deliverables will be compliant with the SW ECSS :
- software design development and validation plan
- requirement document
- design document with appropriate justification
- verification and validation report
- user manual
- source code
- test plans and procedures to rerun the validation campaign as needed
Current TRL:
Algorithm
Target TRL:
Prototype/Beta
version
Application/Mission: SCI/EO/Exloration Missions
Operational SW
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
2011
9 months
Dossier0 Ref.: T-7817
Consistent (H3)
TRP Reference:
T705-185EC
TD:
Title:
AOCS unit simulation models
TD05
Objectives
Framework definition and prototyping for the coordinated development and validation of AOCS units
simulation models by AOCS unit suppliers. The generic development of such Building Blocks has been
recommended by the ESA avionics workshop ADCSS in 2007 and the associated bilaterals with industry.
Description
An experienced AOCS contractor shall develop the generic requirements and framework for AOCS units modelling
and together with some unit supplier(s) develop a first set of simulation models. The initiative will consider both
functional models of adequate fidelity needed for AOCS system design, and interface-representative models for
avionics verification on Virtual Test Bench. This contract should be followed by dedicated model developments with
each unit supplier to produce and validate, against real unit tests, the models for their units. These models shall be
made available to all European companies as part of unit procurement.
Deliverables:
- Generic guidelines for the development of European units simulation models.
- Requirement specifications for Simulation Models.
- Validated simulation models for one representative AOCS unit.
Current TRL:
Algorithm
Target TRL:
Prototype/Beta
version
Application/Mission: SCI/EO/Exloration Missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
2010
12 months
Dossier0 Ref.: T-7816
Consistent (D1)
TRP Reference:
T706-114ET
TD:
TD06
Title:
Securely Partitioning Spacecraft Computing Resources
Objectives
Enable future evolutions of earth observation, telecom and navigation missions to be of dual use nature,
providing service to commercial, scientific, civilian security and defence endeavours simultaneously from a
single platform
Description
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Description of Activities
This proposal aims at analysing, adapting and prototyping the fundamental concept of securely separating a physical
computer resource into multiple logical partitions for computer systems on board a spacecraft. The overall objective of
this TRP is to substantially contribute to the technological foundation for the evolution of earth observation, telecom
(e.g. AmerHis) and navigation missions as well as “new initiatives in the dual-use, security and defence sectors (quote
taken from ESA/ADMIN/ORG(2006)11, DG’s Policy Office). Apart from traditional dual-use, secure partitioning could
also enable competing commercial entities using a single platform by providing confidentiality guarantees for sensor
data, intellectual property like FPGA program codes for space-reprogrammable devices and operational procedures
inside a partition
Deliverables:
Technical Note and Proof-of-concept of a secure partitioning operating system kernel
Current TRL:
TRL 1
Target TRL:
Application/Mission: SCI/EO/Exloration Missions
SW Clause :
Operational SW
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
Dossier0 Ref.:
2011
12 months
T959, T1259, T1261, T7751,
T7753, T8157
Consistent (SD7 Avionics vision)
TRP Reference:
T709-115GI
Title:
Ground Segment Data System Architecture to support CFDP, Bundle Protocol &
IP
TD:
TD09
Objectives
To definee an on-board / Ground Reference Architecture around the CFDP, Bundle & Internet Protocols. It
shall encompasse all the on-board and ground system elements, its interactions and the guidelines and
principles for its governance. The Reference Architecture shall represent the recommended long-term
target architecture that should evolve from the current ESA's capabilities
Description
Under this activity the specification of a generic On-Board - Ground Segment architecture based on the CCSDS FDP,
Bundle & IP protocols will be provided. This top level ESA reference architecture has to be developed to address all
known ESA Earth Observation, Science, Exploration, Telecommunications, Navigation and Operations needs through
the 2025 time period.
This activity will be complemented by a similar one for the on-board architecture.
An SSR shall be produced for the Reference Architecture considering the ESA current Ground Segment Legacy and
its future evolution when addressing the CCSDS FDP, Bundle and IP protocols. Once consolidated, the main building
blocks and its interfaces shall be specified and the respective models generated. A prototype, as proof of concept,
shall be implemented.D
Deliverables:
Architecture, Component Interface Definition, Component, Prototype as proof of concept
Current TRL:
TRL 1
Target TRL:
Application/Mission: SCI/EO/Exloration Missions
Operational SW
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
2011
12 months
Dossier0 Ref.: T7843
TD9 Avionics Vision
TRP Reference:
T709-116GI
TD:
Title:
Global Security: The Ground Component
TD09
Objectives
Provide an ESA Global secure System (Space & Ground) with a suitable architecture and protocols.
Description
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Description of Activities
The security of space missions depend on many factors, most notably the ability to secure the communications
involved in the command and control of spacecraft. The security architecture provides the capabilities to verify the
authenticity of Command and Control data and to prevent the unauthorized disclosure of TM data while it is sent
through the communications infrastructure.It also covers major aspects of Information Assurance.
Under this activity the following will be covered:
- Implications of incorporating security services at the physical, network and application layers
- possible implementation options at each of these layers (in particular for authentication and encryption)
- criteria used for consideration by a mission for selecting a secutrity implementation
This activity will be complemented by a similar one for the on-board system
Deliverables:
Generic Secure Ground Architecture, Secure Ground Component Interface Definition/Component Design Concept,
Prototype as proof of concept
Current TRL:
TRL 1
Target TRL:
Application/Mission: SCI/EO/Exloration Missions
Operational SW
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
2010
12 months
Dossier0 Ref.: T7839
Consistent (TD9 Avionics Vision)
TRP Reference:
T709-121GI
Title:
Ground Segment Data Systems Plug & Operations
TD:
TD09
Objectives
Devlop an On-Board / Ground Architecture based on the Plug & Operations concept. The architecture will
be based on a Mission Operations (MO) Service Framework, which follows the principles of Service
Oriented Architecture (SOA). It defines an extensible set of end-to-end services that support interactions
between distributable mission operations functions, e.g. software applications specific to the mission
operations domain. This architecture will also be based on the Plug & Play CCSDS architecture standards
(MOIS and SOIS)
Description
Definition of a framework and design, which will allow a ground architecture following the Plug and Play concept. This
concept is based on the work currenttly being done in CCSDS
i.e. CCSDS SOIS Services (on-board), CCSDS SM&C Services (ground)
The Missions Operations Service Framework sits between application software specific to the domain of spacecraft
mission operations and the underlying technology used for communications between distributed applications. This
isolates compliant software applications both from each other and the underlying communications technology.
Applications may be plugged in and operated to the service Framework through standardised Service Access points
(SAPs), one for each end-to-end service. This activity will be complemented by a similar one for the on-board plug &
ops. concept
Deliverables:
Architecture, Service Interface Definition/Design Concept, Prototype as proof of concept
Current TRL:
TRL 1
Target TRL:
Application/Mission: SCI/EO/Exloration Missions
Operational SW
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
2011
12 months
Dossier0 Ref.: T-7843
Consistent (TD9 Avionics Vision)
TRP Reference:
T710-117GF
Title:
Flight Dynamics Components for Rapid Support System Generation
TD:
TD10
Objectives
To compose a Flight Dynamics System within 6 months from validated generic building blocks
Description
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Description of Activities
Definition of a generic FDS architecture, interfaces and components based on validated elements matching
standardised S/C components.
Deliverables:
Architecture, Component Interface Definition/Design Concept
Current TRL:
TRL 1
Target TRL:
Application/Mission: SCI/EO/Exloration Missions
Operational SW
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
2012
24 months
Dossier0 Ref.: T-7938
Consistent (ESOC G6)
TRP Reference:
T710-118GF
TD:
TD10
Title:
Concepts for common utilisation of advanced emulation and validation tools
Objectives
Speed-up development and save cost by enabling E2E utilisation of emulation tools throughout mission
design, implementation and execution.
Description
Definition of a framework and concepts for sharing emulation and validation tools between teams of spacecraft
manufacturer, ESA engineering and groundsegement throughout the developmentcycle and even while these tools
are still evolving.
Deliverables:
Advanced emulation requirements, Open emulation framework concept, Utilisation interface definition.
Current TRL:
TRL 2
Target TRL:
Application/Mission: SCI/EO/Exloration Missions
Operational SW
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
2011
24 months
Dossier0 Ref.: T-7938
Consistent (ESOC G7)
TRP Reference:
T710-119GF
TD:
TD10
Title:
Common concepts and components for environmental modelling
Objectives
To consistently use and share environment models between the various parties involved in the design,
implementation and execution of space missions.
Description
Identification of future needs for environment models within advanced mission concepts. Definition of a standardised
approach (plug-and-play) for model impementation.
Deliverables:
Space environment models identification, Definition of plug-and-play framework for implementation, Methodology for
shared model updates
Current TRL:
TRL 2
Target TRL:
Application/Mission: SCI/EO/Exloration Missions
Operational SW
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
2011
24 months
Dossier0 Ref.: T-7938
Consistent (ESOC G8)
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Description of Activities
TRP Reference:
T710-120GF
TD:
TD10
Title:
New concepts for relative navigation at planetary approach
Objectives
Satisfy high-precision navigation requirements at planetary approach resulting from upcoming, advanced
missions by utilisation of new concepts involving also unconventional measurement types.
Description
Survey of present and future measurement types, identification of navigation concepts, elaboration of a S/W
implementation approach
Deliverables:
Survey of advanced measurement types, Navigation concepts identification, S/W implementation concept
Current TRL:
TRL 1
Target TRL:
TRL 3
Application/Mission: SCI/EO/Exloration Missions
Operational SW
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
2013
24 months
Dossier0 Ref.: no ref.
Consistent (ESOC G5)
7-27 - End to End System Design Processes
TRP Reference:
T708-122MC
TD:
TD08
Title:
Next generation requirements engineering as a basis for MBSE and E2E
performance analysis
Objectives
Establish a mechanism for the specification, use and verification of complete, computer-interpretable
requirement specifications using a combination of structured natural language and formal language
Description
Background: A complete and consistent set of verifiable requirements form the basis for MBSE and End-to-End
performance analysis. Wherever possible requirements should be quantified in the form of constraints (mathematical
formulae) w.r.t. properties, i.e. relating a quantity to a (range of) desired values. Also the logical relationship between
requirements should be made explicit. Where needed uncertainty margins and probability distributions should be
taken into account. Such requirements then form in principle a set of equations to be satisfied during verification and
validation. This activity should build on earlier studies on requirements specification such as SpecRight.
Inputs: MathML (content and presentation), OpenMath, OCL, SysML, Structured Natural Languages, Formal
Languages, ...
Tasks: (1) Analyze common patterns in requirements specification and develop/document methods to transform test
based requirements into property-based requirements; (2) Develop automated transformation of sets of
property-based requirements into SysML Parametric Diagrams or similar notations; Feed into non-causal
mathematical solver engines such as Ecosim or Modelica; Link with MBSE for automated computer executable
verification of design models w.r.t. the property based requirement specifications; (3) Integrate and demonstrate in at
least two requirements engineering tools.
Deliverables:
Sample Executable Specifications; Demonstrations with two requirements engineering tools
Current TRL:
TRL 2
Target TRL:
Application/Mission: All mission
Operational SW
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 5
Application
Need/Date:
Contract Duration:
12 months
Dossier0 Ref.: T-1073, T-7863
N/A
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Description of Activities
TRP Reference:
T708-123MC
TD:
Title:
System to Discipline Integration Layer
TD08
Objectives
Establish and demonstrate an integration layer that supports data exchange between discipline specific
tools and the system model / engineering database and other systems engineering tools.
Description
Develop a data exchange integration layer that implements the ECSS ETM-10-23 data model in the form of
middleware, i.e. a middleware layer that facilitates the creation of robust data exchange interfaces between system
engineering tools / databases and discipline-specific tools / databases. Following OMG's MDA approach the
middleware should be auto-generated as much as possible from the formal ETM-10-23 UML2 data model into open
standard based protocols such as: SysML, XML, XML/Schema, RDF/OWL, Web Services, STEP Express, ECSS
E-40-07 (SMP2). Relevant programming languages should be targetted. The integration layer shall be demonstrated
in an application for generation of a VCD (Verification Control Document) from a real world system engineering
database in which design and verification data from at least three different specific engineering disciplines has been
collected.
Deliverables:
Distributable ECSS ETM-10-23 data integration layer, VCD generator demonstration
Current TRL:
Algorithm
Target TRL:
Application/Mission: All mission
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Prototype
Application
Need/Date:
Contract Duration:
18 months
Dossier0 Ref.: T-7863, T-1076, T-1238
N/A
TRP Reference:
T708-124MC
TD:
TD08
Title:
Simple interface for near real-time provision of EGSE sensor data to tools of
other engineering domains
Objectives
More efficient system level AIT
Description
A simple telemetry query interface shall be developed for use by clients from outside the EGSE LAN (e.g. DynaWorks)
to get sensors readings in near real-time. SCOS2000 EGSE will be an important reference.
Background: Many non-electrical subsystem tests (structural, thermal, RF, EMC, optical/payload integration, ...) need
sensor readings (telemetry) that are only available in EGSE. Today mostly dedicated project specific interfaces are
developed to provide this data. Often data is not available in real-time.
Deliverables:
Telemetry query i/f unit breadboard (initial protocol and software implementation)
Current TRL:
Algorithm
Target TRL:
Application/Mission: All mission
Operational SW
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Beta Version
Application
Need/Date:
Contract Duration:
12 months
Dossier0 Ref.: T-7292
N/A
TRP Reference:
T708-125SY
TD:
Title:
Global CE infrastructure for Space Project Lifecycle
TD08
Objectives
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Description of Activities
Assessment and demonstration of a global distributed concurrent engineering infrastructure to later project
phases.
Description
- Integration of already developed concurrent engineering tools into a global infrastructure
- Evolve available GRID tools, data server (OCDS) and accessing tools (iCDF) towards later phases of space projects.
- Assessment of the applications of the global infrastructure in support of the system, design and product reviews
Deliverables:
a global infrastructure layer integrating and linking current and future elements of the CDF infrastructure such as:
- the OCDS (Open Concurrent Design Server), industrialisation of the CDF integrated design model
- tools like i-CDF (remote access to the design environment via Internet)
- and GRID based techniques and infrastructure.
Current TRL:
TRL 2
Target TRL:
TRL 3
Application/Mission: All mission
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
24 months
Dossier0 Ref.: T-1076
N/A
TRP Reference:
T708-126SY
TD:
Title:
Space instrument design modelling
TD08
Objectives
Develop modelling tools for optical active, microwave passive & active instruments Design Activity to be
able to perform end-to-end instrument studies and to perform independent technical assessments of
instruments (Extension of existing IDA Instrument Design Activity)
Description
- Develop modelling tools for optical passive, microwave passive and active instruments, like done for the optical
passive instruments
- Enhance the CDF IDA Model with interfaces
- Integration in the CDF
- Validation with contractors and ESA test cases
Deliverables:
Integrated Design Model tool for active optical and the passive & active microwave instruments
Current TRL:
Algorithm
Target TRL:
Application/Mission: All mission
Operational SW
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Beta Version
Application
Need/Date:
Contract Duration:
SW
>2009
operational
12 months
Dossier0 Ref.: T-7835
N/A
TRP Reference:
T708-127EE
TD:
TD08
Title:
Model-based System Engineering components of antennas
Objectives
To implement simple high-level antenna models suitable for the quick assessment of antenna
performances in Phase0/A and early Phase B.
Description
Rather sophisticated antenna models, based on a Virtual Electromagnetic Satellite paradigm, are available within the
European Electromagnetic Modelling Library for accurate prediction of antenna performances. However these models
are not suitable for Phase 0/A and early phase B activities in a Model-Based System Engineering context, where fast,
not so accurate but reliable predictions, with a known uncertainty margin, are required in order to avoid over- or
under-specification and reduce the risk of under or over-design in later phases.
Parametric techniques to model antenna performances have been recently developed and applied, among others, to
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Description of Activities
antenna synthesis problems. High-level models suitable for quick iterations can be implemented using these
techniques as data reduction algorithms to estimate the parameter values of the high-level models for the relevant
antenna configuration case, on the basis of information extracted from suitable databases or from ad-hoc runs of
antenna design tools.
The synthesis algorithms, based on the same parametric models, can be coupled with a facility to derive a quantitative
form of the antenna requirements from system-level and can be extended to generate antenna configuration and
performance descriptions suitable for the system modelling. Such an extension of existing antenna synthesis
algorithms implies computing different quality figures from those usually applied in antenna design, typically tied to
directly measurable performances like directivity, and producing different descriptions of the antenna configurations,
closer to their actual physical appearance than to the modelling needs of antenna design tools.
Finally to allow the use of the result produced by existing antenna design tools in the derivation of the model
parameters it is necessary to develop and implement a methodology to estimate their uncertainty. Metrics derived
from physical invariant and boundary conditions can be used to obtain a quantitative estimate of the quality of the
results and consequently derive model uncertainties.
The activity covers the study, design and development of a proof-of-concept demonstrator of the antenna high-level
models including all the above elements in the form of a small tool, suitable as validation test bed (against accurate
predictions and available measured data) and adequate to practically demonstrate the model themselves on selected
real-life test cases. The demonstrator will be developed as a component of the European Antenna Modelling Library
so as to optimise the connection to the antenna design tool needed to feed it with initial data and to simplify its
demonstration.
Deliverables:
MBSE models and demonstrator (modelling tool prototype)
Current TRL:
Algorithm
Target TRL:
Application/Mission: All mission
Operational SW
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Prototype
Application
Need/Date:
Contract Duration:
2010
12 months
Dossier0 Ref.: T-8397, T-7835
N/A
TRP Reference:
T708-128EE
Title:
Innovative RF testing approaches for reduced antenna/payoload AIT/AIV
TD:
TD08
Objectives
To develop testing methodologies for antenna/payload end-to-end RF testing at satellite level
Description
The increasing complexity and stringent performances required in RF instruments and payloads demands more and
more that RF functional verification be performed on the integrated satellite under the most realistic operational
conditions. As a consequence and in order to minimise the cost and duration of test campaigns it is necessary to
develop advanced RF test methodologies.
Extending testing to end-to-end performance requires a significant departure from traditional techniques, mostly based
on CW tests (Continuous Wave tests, i.e. using non-modulated single frequency input signals) under (simulated)
worst-case conditions, in favour of methods that expose antennas, instrument or payload to realistic operational
conditions, in terms of signals, power levels, etc.
While easy to conceive, such evolution implies a large shift in testing methods and test facility configuration as well as
a much more extensive permanence of the unit under test in the test facilities, since functional testing typically
requires a virtually complete and systematic coverage of the full spectrum of operational conditions.
Ways to extend existing test facilities to cover the new needs have to be explored, taking into account the different
type of performance figure required for system-level assessment and, at the same time, assessing the use of existing
accurate models as interpolators to achieve complete functional characterisation from a reduced number of
measurements so as to keep the overall testing time within acceptable limits. Such approach has been variously
experimented and successfully applied in the past to specific cases, but a systematic in depth study of the test
configurations and procedures is missing, in particular a careful determination of the "performance sampling rules" to
be used in common cases and in dept assessment of the suitability and procedures for the use of the relevant
antenna modelling tools.
The objective of this activity is to study and demonstrate a functional testing solution for antenna/payload verification
based on extended testing capabilities and combined use of antenna modelling tools, with a thorough assessment of
the test configuration, basic procedures and modelling tools usage.
Deliverables:
Methodology with proof-of-concept demonstration
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Description of Activities
Current TRL:
TRL 2
Target TRL:
Application/Mission: All mission
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
2010
18 months
Dossier0 Ref.: T-7557
N/A
TRP Reference:
T708-129EE
TD:
TD08
Title:
Innovative EMI/EMC testing and modelling approaches for full development
cycle support and reduced AIT/AIV
Objectives
To develop methodologies to perform EMC testing at satellite level
Description
The complexity and stringent performances of most satellites demand reliable and complete EMI/EMC assessment
during the full development cycle, in particular before final integration and verification at system level. At the same
time there is need for verification under the most realistic operational conditions, while worst-case testing at unit level
does not always provide the right answer.
As a consequence new testing methods are necessary as well as advanced modelling tools to support full-life cycle
EMI/EMC assessment, with objective of minimising the cost and duration of test campaigns at satellite level while
ensuring design optimisation.
Generic EMC models, validation of simulation tools, and advanced instrumentation and test beds are required to this
end and to enable the application of best practices across the full development cycle.
The activity involves the development of new techniques for EMC testing under realistic conditions, the consolidation
of generic EMC models and of ad-hoc modelling tools. The resulting methodology will be demonstrated against
selected case studies.
Deliverables:
Methodology with proof-of-concept demonstration
Current TRL:
TRL 2
Target TRL:
Application/Mission: All mission
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
2008
18 months
Dossier0 Ref.: T-7557
N/A
TRP Reference:
T708-133TC
TD:
Title:
Portable Virtual AIT Visualiser
TD08
Objectives
To develop an application able to visualise the AIT procedures in Augmented Reality, for real-time
comparison on real HW
Description
•Develop a portable model tool based on DMU and Virtual Facility data, allowing superimposition of the AIT
procedures (derived following the results of the Virtual Spacecraft Design TRP activity) and the target HW in an
“Augmented reality” fashion.
Develop and test the relevant MMI.
Implement interfaces with Virtual AIT environment (applicable Virtual Spacecarft Design + test facility).
Deliverables:
A Portable Virtual AIt Visualiser implementing:
- Eye-controlled application enabling hands-free performance of demonstration application
- Selectable View recording functionality (video streaming)
- Data import-, processing-, post processing software for demonstration
- Indoor position acquisition and adaptation of scale and perspective depending on position
The tool shall run on a portable (PDA sized), light weight processing unit, complemented by augmented display
glasses
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Description of Activities
Current TRL:
Prototype
Target TRL:
Application/Mission: All mission
Operational SW
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Beta Version
Application
Need/Date:
Contract Duration:
18 months
Dossier0 Ref.: T-7863
N/A
TRP Reference:
T708-134SW
TD:
TD08
Title:
Low Cost Functional System Qualification Testbench and Electrical AIT
Objectives
Advance the Electrical AIT state of the art by the use of simulation in closed-loop during system
qualification
Description
Based on the output of ongoing Spacecraft Vritual Design studies, and EGSE modular architectures, the methodology
and tools necessary to build low-cost, closed loop qualifiation testbenches will be developed. These testbechnhes
effectively cosntitute the EQM necessary to qualify the design regarding functional and electrical aspects. The
seamless integration of the simulator developed in support of the design will be implemented, taking into account the
lessons learnt in past projects (typically ATV, H-P and MDVE-based systems used for Earth Observation). The system
shall be scalable to low cost projects and shall implement the EGSE interface standards currently developed in the
frame of the European Harmonisation on GS software.
Deliverables:
Methodology and tools to integrate system qualification testbenches on the basis of sub-system EGSE and design
simulations
Current TRL:
Prototype
Target TRL:
Application/Mission: All mission
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Beta Version
Application
Need/Date:
Contract Duration:
24 months
Dossier0 Ref.: T-7863
N/A
TRP Reference:
T708-135SW
TD:
Title:
Model Based System Tools Integration
TD08
Objectives
Integrate and industrialise the system development environment for MBSE
Description
Taking the results of the Virtual Spacecraft Design activity and associated element developments (such as the system
reference model and associated engineering database, the architecture modelling tool etc.) the overall environment
needs to be integrated and prepared for a deployment in projects, starting with a pilot application, for all stakeholders
in the space industry. Focus will be on
- distribution
- collaboration
- standardisation
of the elements. The deployment in industry needs to be addressed.
Deliverables:
Integrated and validated MBSE environment
Current TRL:
Prototype
Application/Mission: All mission
Open Source
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
Beta Version
Application
Need/Date:
Contract Duration:
24 months
Dossier0 Ref.: T-7863
Consistent with "System Modelling and Simulation Tools" (B7)
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Description of Activities
TRP Reference:
T709-130GI
TD:
Title:
Knowledge Capturing, Transfer and Recovery
TD09
Objectives
Support the capturing, recovery and transfer of specialised knowledge about space systems . Reduce the
‘duplication’ of efforts in projects with highly specialised staff working in separate teams but requiring a
common knowledge base.
Description
Analyse the different types of knowledge that need to be supported, with particular attention to all the disciplines
where transfer of knowledge is required between the spacecraft development teams and the operations teams (e.g.
on-board S/W troubleshooting, test outputs, behavioural knowledge, configuration details)
Identify suitable technologies enabling the capturing and recovery of specialised knowledge in a model-based
engineering approach. In particular, wikis based shared repositories shall be explored.
Define a methodology and select supporting products for operational implementation.
Deliverables:
1.- Technical notes and other supporting documents reporting about the technical outputs of the study, in particular:
- Overview of existing technologies addressing this domain
- Recommendations for an approach to the layout of such a knowledge capturing environment.
2.- S/W prototype of infrastructure supporting the feasibility of the approach including associated source code.
Current TRL:
Algorithm
Target TRL:
Application/Mission: All mission
Operational SW
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Prototype
Application
Need/Date:
Contract Duration:
2013-2015
12 months
Dossier0 Ref.: T-120
N/A
TRP Reference:
T709-131GI
Title:
Collaborative Environment for Space Systems Engineering
TD:
TD09
Objectives
Enable the effective ‘integration’ of geographically distributed teams collaborating for a given mission
throughout all phases (from specification to operations)
Description
Identify the domains/needs driving the collaborative environment (e.g. system specification, S/C design, on-board
S/W, end-to-end verification)
Select technologies enabling the sharing of common elements (e.g. the model) between different teams and
throughout different phases
Establish a suitable methodology to improve efficiency across domains (e.g. verification/synchronisation points,
interfaces definitions):
?‘Virtual integration’ at any given point
Establish a suitable methodology to bridge subsequent phases (e.g. traceability, knowledge transfer):
? Transition from design verification to implementation verification models/environments.
Deliverables:
1.- Technical notes and other supporting documents reporting about the technical outputs of the study, in particular
including recommendations for an approach to the layout of such a concurrent collaborative environment.
2.- S/W prototype of infrastructure supporting the feasibility of the approach.
Current TRL:
Algorithm
Target TRL:
Prototype
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Application
Need/Date:
2013-2015
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Description of Activities
Application/Mission: All mission
Operational SW
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Contract Duration:
24 months
Dossier0 Ref.: T-120
N/A
TRP Reference:
T709-132GI
TD:
Title:
Model Based Operations Validation System
TD09
Objectives
Reduce the efforts required to ensure full validation of spacecraft operations. Increase the safety of
operations execution
Description
‘Off-line’ (‘fully automated’) validation of operational procedures against a set of rules
‘On-line’ automatic synchronisation of the underlying models with the current spacecraft state, as determined based
on telemetry and auxiliary data
‘Fast prediction’ of the future spacecraft state, such to ensure that no safety rule will be violated during the execution
of all commands currently scheduled for (ground or space) execution.
Deliverables:
1.- Technical notes and other supporting documents reporting about the technical outputs of the study, in particular
including recommendations for an approach to the layout of such a concurrent collaborative environment.
2.- S/W prototype of infrastructure supporting the feasibility of the approach.
Current TRL:
-
Target TRL:
Application/Mission: All mission
Operational SW
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Prototype
2013-2015
Application
Need/Date:
Contract Duration:
18 months
Dossier0 Ref.: T-95, T-98
N/A
7-28 - Electronic Components
TRP Reference:
T703-136EP
TD:
TD03
Title:
Study of mitigation techniques/optimisation for analogue circuits in space
radiation environment
Objectives
1. To study mitigation techniques for He-Ion radiation effect in critical spacecraft functions that is using
common analogue electronic components, To trade-off complexity vs. reliability, i.e. how complex a circuit
needs to be to achieve a certain likelihood of activation.
2. To analyse and test known critical circuits using established analogue components and compare the
same circuities also with COTS candidate devices for replacement in future missions.
Description
In digital electronics circuitry's, we have well established solutions for handling SET/SEU effects and guarantee
reliable functionality (TMR solutions etc). The solutions have also usually been tested in real application cases and
with Rad-test.
For analogue circuits however, the SET testing are usually made only on component-level in open-loop conditions or
even as a stand-alone applications, whereas the real applications almost always are operated in closed loop
configuration and even with positive feedback conditions (latches etc.).
Very little test data and analysis exist on these circuit configurations. Furthermore, many COTS alternatives are
discarded in evaluation or after component-level radiation testing, where it still could be useful to study specific
operating conditions where the component possibly could be used for space applications.
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Description of Activities
The following activities are foreseen:
1 - To make a survey on known SET/SEU performances on the target analogue components, commonly used in
space applications
(op amp, comparators, transistors, memory cells, voltage references), analyse the data and critically map issues
related to components
based on similar technologies (Bipolar, CMOS, BCD, etc).
2 - To study analogue voting, latching, "failure silent" or in general fail-safe circuit solutions for S/C critical functions,
with classically used
space components, and determine the trade-off between designing complexity and cost.
3. To set up test-HW and run Radiation tests for a number of critical functions, where one mitigation of a critical
function is tested in He-Ion
and/of Proton environment with different complexity in circuit designs. Results of SET/SEU sensitivity shall be traded
with mitigation complexity.
To derive possible explanations and analyse the SET/SEU results in order to extend the evaluation to similar
components based on the same technology.
4. To set up the same circuit as a well known analogue component (example: LM139), but with a COTS candidate
comparing the results using the
same mitigation techniques
5. To propose, as far as possible, as set of design recommendations using European components and/or ITAR-free
components to establish common critical
analogue build blocks (i.e. PCDU MEA, over-voltage protections, Latches, Optical-interfaces, Point of Load converter
stages)
Deliverables:
Design Recommendations,Test reports, Breadboards
Current TRL:
TRL 1
Target TRL:
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 4
2011
Application
Need/Date:
Contract Duration:
12 months
Dossier0 Ref.: T-7804
N/A
TRP Reference:
T722-137QC
TD:
TD23
Title:
Evaluation of new assembly methods of IGBT dice on hybrids
Objectives
The objectives of this study are to develop and evaluate a laser die soldering method that has voiding of
less than 5%, capable of soldering die of 1.2mmx1.2mm on a range of substrates. While the interconnect
issue shall be addressed by the use of a copper frame process.
Description
Power Modules often use IGBT (Insulated Gate Bipolar Transistors) and MOSFET (Metal Oxide Semiconductor
Field-Effect Transistor) die attached to a substrate by glue or solder. In order to have good thermal conductivity this
die attach must be of very good quality and be homogeneous and void free. The quality of the solder joint is very
process dependent and with an appropriate choice of technique a void free joint may be realised. In addition the
electrical connection of these power devices also uses very heavy wire interconnects which are reliability drivers. An
alternate and more reliable interconnection scheme coupled with an improved die attach will improve the overall
performance of IGBT and MOSFET modules.
Deliverables:
Technical note listing the existing soldering power dices process and defined the new process method.
And evaluation plan defining the percentage of voids.
Technical note listing the existing connections techniques for power hybrid and defining the new method.
Current TRL:
TRL 2
Application/Mission: All missions
Target TRL:
TRL 5
Application
Need/Date:
Contract Duration:
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Description of Activities
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Dossier0 Ref.: T-8404
Consistent (Component Technology Board (CTB) Dossier)
TRP Reference:
T722-138QC
TD:
TD23
Title:
Evaluation Of Junction Temp reduction techniques on metal ceramic substrate
Objectives
Aim of the activity will be to test different technological solution of hybrid circuits design and manufacturing
in order to reduce backside temperature of functional chips and, consequently, their junction temperature.
Another scope of the activity will be to develop the thermal test capability on active junction of GaAs
components (p-hemt/HBT or other), based on measurement of electrical parameters related to
temperature (indirect parameter measurement).
Description
It is very important to reduce operating junction temperature of functional chip to increase lifetime of them.
Technological design skills and development of junction temperature measurement techniques (for instance indirect Tj
measurement) can play a crucial role in the effort of reducing operating temperature of power components
Deliverables:
new test method and design methodology for junction temperature management and reliability improvement.
Current TRL:
TRL 2
Target TRL:
TRL 5
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
2009
12 months
Dossier0 Ref.: T-8404
Consistent (Component Technology Board (CTB) Dossier)
TRP Reference:
T722-139QC
TD:
Title:
Very high dissipative RF/LF package
TD23
Objectives
The activity is aiming at developing a new generation of packaging technology - in particular for wide band
gap semiconductors.
Description
There is a constant need for thermally managed microwave packages. In particular as the wide band gap technologies
start to yieled products and the new power MMIC processes are being developed there is a clear need for a European
package based on the emerging state of teh art materials in which Europe excels. European industry is developing
higly thermal conductivity materials ( >600W/mK is the target) in AlSi, Metals matrix composites and Carbon Nano
tube filled matracies. Using these emerging technologies it should be possible to meet the needs of the new
semiconductor market for a highly disspitive package with the insertion of RF ceramic feedthroughs for high
frequenciesand high current LF feedthroug.
The real technology challenge will be to development a series of processes to machinge, form and high temperature
braxe (AgCu #800°C)/ assembly and test such a package.The new wide band gap – WBG – components have a
thermal dissipation 10 times the actual GaAs power transistors (i.e. SSPA as an example) The materials used as base
for the power micro package, needs to be able to match the CTE of the mounted devices, have a strong thermal
conductivity limitation (CuW is in the range 200 – 250 W/m.K).That means new materials need to be introduced. A
survey of the availiability of European materials will be under taken determining what can be machined and formed
with high yeileds and subsequently formed in to a highly disspitaive hermetic package with Rf and power
feedthroughs.
Deliverables:
Develop an European range of highly dissipative packages, evaluated packages, procurement specification, thermal
models.
Current TRL:
TRL 2
Application/Mission: All missions
Target TRL:
TRL 4
Application
Need/Date:
Contract Duration:
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Description of Activities
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Dossier0 Ref.: T-8404
Consistent (Component Technology Board (CTB) Dossier)
TRP Reference:
T722-140QC
TD:
TD23
Title:
Influence of glob top thickness on reliability of GaAs dice and the successful
application of the process.
Objectives
To determine resin types vailaible that a compatible with GaAs, Silicon, Gold interconnection, dertmne
optimum processing and qulaity assurance methods for the application of such a technique. This includes
thickness of the resin as a function of :
Process requirements : height of bondings related to micorwave componet constraints. The relaibility of
the system on component performance and the ability to determine the amount o resisn to demonstrate a
quasi-hermetic approach.
Description
Different studies through ESA and CNES contracts have shown the capability for RF glob-top to fulfil the space
requirements in term of reliability (through thermal cycles, humidity tests…).However, all the tests have been
conducted with a "standard" thickness of resin on the top of the bare dice. For microwave considerations, the
thickness of the resin on the top of components must be minimized (cavity effects…) to ensure optimium RF
performance. This has an impact on the materials choice and the relaibility considerations. While on the process and
qulaity aspects, the standard procedure for hybrids includes a visual inspection before hermetic sealing and for
microwave applications, the control has to take into account the small size of the cavities (to minimize resonances),
i.e. the presence of metallic walls close to the area to be inspected. These are all probelmatic. With glob-top
technology the hermticity requirement may be removed but the technique introduces an extra operation with the resin
deposition on top of dice and around all the wire bondings. A specific control has to be included in the process flow to
check the influence of the resin deposition and polymerisation on the bondings and the homogeneity of the resin (no
bubbles) is considered vital. Techniques must therefore considered to determine the influence of inhomogentiety of
performance.
Deliverables:
A materials selection, process assessement, evaluation on RF demonstrators. Leads to new tools, techniques and
low cost approach for microwave assemblies.
Current TRL:
TRL 2
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
TRL 5
Application
Need/Date:
Contract Duration:
2010
12 months
Dossier0 Ref.: T-8404
Consistent (Component Technology Board (CTB) Dossier)
TRP Reference:
T722-141QC
TD:
TD23
Title:
Evaluation of high fatigue resistance of lead free solder
Objectives
To evaluate some of the Sn/Ag/Cu, Sn/Ag/Bi, Sn/Cu/In/Ga alloys. Scope of the study shall be: the
selection of materials and Assembly and Evaluation testing of Test Vehicles that cover both SMT and
Hybrid technologies.
Description
The WEEE (Waste of Electrical and Electronic Equipment) EU Commision Directive will put the ban on the use of Pb,
Hg, Cd, esavalent Cr and halogenized FR’s from 01/06/2006 (last reschedule) in the electronic products sold in the
EU countries. Also Japan has a similar directive (RoHS) and is already going “lead free” and USA is hardly working
on the matter to be prepared. At present there are a large number of materials that have been proposed as
replacements for lead containing solder. Primary among these are the Sn/Ag/Cu (SAC) alloys. There are several
variations of the Sn/Ag/Cu alloys that have been suggested as the preferred replacements for Sn/Pb solders. Two are
of special interest: the Japanese adopted alloy of Sn96.5/Ag3.0/Cu0.5 and the North American Electronics
Manufacturing Initiative (NEMI) alloy of Sn95.5/Ag3.9/Cu0.6. Also Sn/Ag/Bi and Sn/Cu/In/Ga alloys have shown good
fatigue resistance compared to Sn63/Pb37
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Description of Activities
Deliverables:
Evaluation test reports of the performance of the candidate solders and relevant procurement specifications of the
solders.
Current TRL:
TRL 2
Target TRL:
TRL 5
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
2010
12 months
Dossier0 Ref.: T-8404
Consistent (Component Technology Board (CTB) Dossier)
TRP Reference:
T722-142QC
Title:
SMT Evaluation of LCC and micro-BGA packages on LTCC boards
TD:
TD23
Objectives
To evaluate LTCC substrate manufacturing with different internal/ external pastes and the assembly
techniques for such paste technologies. Focus on LCC and micro BGA's to LTCC substrates.
Description
LTCC continutes to grow in its importnace for low cost custom packaged hybrid soultions. Indeed as the process has
matured and the relibaility and reproducability probelms have been addressed more companies have sought to use
this as a technology option in their equipments. In Euorpe there are several leading companies using this to provide
commercial hybrids one of whom is a space company. It is the objective of this work to evaluate the critical process
parameters for the SMT techniques against the LTCC options, and determine the optimum structure and materiials
and design rules for SMD's on these LTCC substrates. The activity will concern the SMT boards environmental test
for a technological evaluation of involved manufacturing subtechniques.
Deliverables:
Test vehicle, design rules or guidelines for LTCC technology that will have SMD, characterisation to environmental
standards of LCC and Micro BGA components. Development of European assembly capability, designs for SMD and
inspection techniques for users.
Current TRL:
TRL 2
Target TRL:
TRL 5
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
2009
12 months
Dossier0 Ref.: T-8404
Consistent (Component Technology Board (CTB) Dossier)
TRP Reference:
T722-143QC
TD:
TD23
Title:
Utilisation of a Heavy and Light Ion Facility at UCL for Component Radiation
Studies (Time period 2008-2012)
Objectives
To utilise, improve and maintain the capabilities of the UCL Heavy Ion (HI) and Light Ion (LI) irradiation
test facility for the purpose of characterising SEE effects in EEE components for flight on ESA missions
and missions developed by European industry.
Description
This activity concerns execution of regular irradiation test campaigns on EEE components for flight on ESA and
European space missions. Up to 330 hours of beam time is available free of charge on a priority basis for ESA.
Additionally, a minimum of 500 hours is available for ESA sub-contractors, research institutes and other interested
users (based on hourly beam time cost). The agency provides the facility with a detailed work programme of the test
campaigns. Subsequently, the facility performs test campaign scheduling (in agreement with the Agency).
Deliverables:
D1: Annual Report
Current TRL:
N/A
Target TRL:
N/A
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Need/Date:
2008
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Description of Activities
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Contract Duration:
36 months
Dossier0 Ref.: T-7888, T-7887
Consistent (Component Technology Board (CTB) Dossier)
TRP Reference:
T722-144QC
TD:
TD23
Title:
Utilisation of the High Energy Heavy Ion Test Facility at JYFL for Component
Radiation Studies (Time period 2008-2012)
Objectives
To utilise, improve and maintain the capabilities of the RADEF High Energy Heavy Ion (HI) irradiation test
facility for the purpose of characterising SEE effects in EEE components for flight on ESA missions and
and missions developed by European industry.
Description
This activity concerns execution of regular irradiation test campaigns on EEE components for flight on ESA and
European space missions. Up to 240 hours of beam time is available free of charge on a priority basis for ESA.
Additionally a minimum of 500 hours is available for ESA sub-contractors, research institutes and other interested
users (based on hourly beam time cost). The agency provides the facility with a detailed work programme of the test
campaigns. Subsequently, the facility performs test campaign scheduling (in agreement with the Agency).
Deliverables:
D1: Annual Report
Current TRL:
N/A
Target TRL:
N/A
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
N/A
36 months
Dossier0 Ref.: T7888, T 7887
Consistent (Component Technology Board (CTB) Dossier)
TRP Reference:
T722-145QC
TD:
TD23
Title:
Utilisation of the Proton Irradiation Facility at PSI for Component Radiation
Studies (Time period 2008-2012)
Objectives
To utilise, improve and maintain the capabilities of the PSI High Energy Proton irradiation test facility for
the purpose of characterising Single Event Effects (SEE) and Displacement Damage (DD) effects in EEE
components for flight on ESA missions and missions developed by European industry.
Description
This activity concerns execution of regular irradiation test campaigns on EEE components for flight on ESA and
European space missions. Up to 240 hours of beam time is available free of charge on a priority basis for ESA.
Additionally, a minimum of 500 hours is available for ESA sub-contractors, research institutes and other interested
users (based on hourly beam time cost). The agency provides the facility with a detailed work programme of the test
campaigns. Subsequently, the facility performs test campaign scheduling (in agreement with the Agency).
Deliverables:
D1: Annual Report
Current TRL:
N/A
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
N/A
Application
Need/Date:
Contract Duration:
N/A
36 months
Dossier0 Ref.: T7888, T 7887
Consistent (Component Technology Board (CTB) Dossier)
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Description of Activities
TRP Reference:
T722-146QC
Title:
MTSL Laboratory Test Service
TD:
TD23
Objectives
Continue to maintain a call off order based system for component assessments and specialist testing
open to all of ESA.
Description
Tyndall formerly the NMRC Cork has had a working relationship with ESA for several years providing expert test
services that complement the ESA laboratories. This service supported by the host government acts as extra capacity
as well as providing access to a prototype foundry. Typical tests include the evaluation of DC/ DC converters, the
constructional analysis of complex hybrids and the development of new component topologies. The structure of this
relationship has been a TRP funded call off order based system that is open to all ESA projects.
Deliverables:
Reports for each activity, regular reporting and competence transfer between ESa and contractor.
Current TRL:
N/A
Target TRL:
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
N/A
N/A
Application
Need/Date:
Contract Duration:
36 months
Dossier0 Ref.: no ref.
CAB
TRP Reference:
T722-147QC
TD:
TD23
Title:
Enabling of Ultra short gate length commercial MMIC process
Objectives
The activity will aim at developing a dual MMIC Process usable for both Low Noise and Medium Power
applications at very high frequency.
Description
The activity is listed in the CTB microwave dossier. It shall considert results obtained via previous ESA TRP (ESA
contract N° 15909 : “Process Development and Concept Validation of Metamorphic HEMT”) and CNES activity on
Ommic D01MH process as well as French MoD contract (DGAcontract N° 01 34 013 : ETUDE ET REALISATION
TECHNOLOGIQUE POUR L’AMPLIFICATION DE PUISSANCE MILLIMETRIQUE )
The activity will aim at developing a dual MMIC Process usable for both Low Noise and Medium Power applications at
very high frequency. It will first focus on solving basic technical problems for the processing of short channel
metamorphic or pseudomorphic HEMT (targeted maximum gate length 70 nm), with the goal to optimise the high
frequency performance of these devices in terms of gain and cut off frequency with a final Lg ~ 5 0 nm as target for
processing ultra short gate.
Following tasks are included:
Task 1: Process development: optimisation of existing process to achieve short channel metamorphic or
pseudomorphic very high frequency active devices; integration with existing MMIC passive components .
Task 2: MMIC process validation: The Characterization of the active elements will be done in terms of noise and gain
to analyse whether the technology and material is capable of meeting the low noise requirements of mm-wave
receivers for future space applications. Libraries will be updated and a RIC (Representative Integrated Circuit) will be
designed to evaluate the device performance.
Task 3: MMIC process Space Evaluation: Together with the RIC, adequate TCV (Technology Characterization
Vehicle) and DEC (Dynamic Evaluation Vehicle) will be designed and processed for performing MMIC process
evaluation as per ESCC 2269010. Accelerated life tests on TCVs and DECs and RIC testing will be used to evaluate
the reliability performance of this advanced technology.
Deliverables:
After successful evaluation, the possibility to expand the acquired expertise and technological know-how to process
ultra short gate length active HFETs will be studied. Evaluated technology will be available for user designs.
Current TRL:
TRL 1
Application/Mission: All missions
N/A
SW Clause :
Target TRL:
TRL 4
Application
Need/Date:
Contract Duration:
2008
18 months
Dossier0 Ref.: T283
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Description of Activities
Consistency with Harmonisation
Roadmap and Conclusions:
Consistent (Component Technology Board (CTB) Dossier)
TRP Reference:
T722-148QC
TD:
TD23
Title:
Laser diode reliability study, derating and optimization of screening and
qualification
Objectives
To investigate laserdiode life time reliability, investigating and developing a test method to measure COD
threshol and to develop a laser diode derating rule based on life time relibility findings.
Description
High power laser diode are becoming increasingly critical components for many ESA missions since they are used to
pump semiconductor laser source such as Nd:Yag Laser, which are use in more and more ESA projects, example,
space based LIDAR applications. The reliability of these laser diodes is not fully understood and effort to understand
failure mechanism, life time and other degradation modes is a pressing need. Within this activity it is proposed to
study the life time degradation mechanism in the main types of laser diode at the stuck level, used today. Another
area of study should be the investigation of Catastrophic Optical Damage (COD) mechanism and fine tuning a
universal test method to measure COD threshold that will enable us to compare different technologies from different
manufacturers when lasers are procured. The later activity stems from a recommendation made by the laser diode
working group since we do not have a standard test method at the moment. The COD threshold is test method
dependant and hence it is difficult today to make reasonable judgement based on any one manufacturer test method.
As a consequence of this activity a general laser derating rule could be established.
Deliverables:
Technical document
Current TRL:
TRL 2
Target TRL:
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 5
Immediate
Application
Need/Date:
Contract Duration:
18 months
Dossier0 Ref.: T7889
Consistent (Component Technology Board (CTB) Dossier)
TRP Reference:
T722-149QC
TD:
TD23
Title:
Base metal electrode ceramic capacitors studies
Objectives
A study shall be undertaken to determine the suitability of such metal electrode system products for use in
space equipments. The objective is to reduce procurement time and cost by a significant factor while
demonstrating the same level of performance
Description
The base metal electrodes (copper and nickel) are used in commercial products in place of noble metal electrodes
(silver and palladium), so as to allow cost reduction of these components. This has been the aim of the commercial
electronics industry for long term. However there are issues on the reliability and long term performance in space on
such electrode based components. Understanding these issues is important, when the cost of passive components is
relevant (European passives are 10X the cost of the US military counterparts)
Deliverables:
Industrial evaluation of commercial technologies, ESCC evaluation of chosen technology types.
Current TRL:
TRL 2
Target TRL:
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 4
Application
Need/Date:
Contract Duration:
2009
24 months
Dossier0 Ref.: T 7890
N/A
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Description of Activities
TRP Reference:
T722-150QC
TD:
TD23
Title:
High Temperature RF/Microwave interconnection
Objectives
This activity consists of the study the actual limitation of the existing microwave interconnection, following
by a trade off of possible solution to meet operating temperature requiurements of the worst case
applications. A first design will be manufactured and tested before a final batch of an updated design.
Description
RF cabling is needed in many missions such as Planetary exploration, launcher and propulsion activity high
temperature operation. In addition Rf cables are used in the qualification activity where accelerated life testing is
undertaken. All of this requires high temperature capabilities beyond the actual rating of the cables and interconnects
used. An activity is required to develop such cables and interconnects.
Deliverables:
component design and evaluation that preceedes formal ESCC evaluation.
Current TRL:
TRL 2
Target TRL:
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 5
Application
Need/Date:
Contract Duration:
2009
24 months
Dossier0 Ref.: T 283
N/A
TRP Reference:
T722-151QC
TD:
TD23
Title:
Technology assessment of DRAM and advanced memory productsfollowing in
from Radiation test and benchmark of commercial products against space
requirements.
Objectives
A study shall be undertaken to assess commerciale state-of the-art Dynamic Random Access Memories
(DRAM). It shall identify and assess the suitablility and reliability of such a technology for space
applications, following a first radiation assessment already done under different funding scheme. A second
objective shall be to carry out a reliability assessment of advanced memory devices that are of potential
interest for space application like FeRAM, MRAM and CPM due to their intrinsic robustness against
radiation effects.
Description
Users have increased demand to larger memory sizes in future applications. Dynamic Random Access Memories
(DRAM) in state-of-the-art technolgies has therefore already been investigated by ESA in order to pre-assess
radiation performance (up to 512M modules). In this study large difference of radiation performance, depending of the
manfuacturer, has been found. The difference can be based in the used technologies and/or error correction.
The Advanced Memory devices such as Phase Change Memory (PCM) and Magnetic RAM (MRAM) and FeRAm
(Ferroelectric RAM) are promising great performances compared to commonly used non volatile EEPROM and Flash.
MRAM is seen as an attractive technology for generations about the 65nm node, and could be of large interest here
also for the space applications. However, further scaling is hampered by the large current required to generate the
magnetic switching while the half select problem requires complex solutions like the toggle switching cell. Also, control
of the thickness uniformity of the thin tunnel barrier over wafer size will remain very critical.
PCM is a technology with much better scaling potential. However, reliability properties as cycling endurance and
high-temperature retention so far are still inferior to that of the rival technologies, while also program speed is slower.
Scope of this activity is to cosnider the types of memories on the market and identify the most promising DRAM
candidates following a detailed analysis of the radiation tests, consider the current market offer for PCM, MRAM and
FeRAM, select the devices the shows on the datasheet the most promising performances compared to existing used
memory devices, procure a number of parts, characterize and evaluate their reliability and radiation performance and
identify the devices that show the greatest potential for use in space application.
Deliverables:
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Description of Activities
D1: Study report, further radiation assessment, recomemndations of candidate technologies , D2: Reliabilty test report
of promising DRAM components
AD1- Report on the market offer of MRAm, PCM and FeRAM. Identification of
most promising memory devices
AD2- Procurement of 30-50 parts of each part type as identified in D1
AD3- Preparation of a radiation tets plan and a reliability assessment plan
AD4- Report on the results of the radiation and reliability assessment test.
AD5- Conclusions and suggestions on the prosecution of the activities- Lessons learned.
Current TRL:
TRL 2
Target TRL:
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 5
Application
Need/Date:
Contract Duration:
2011
24 months
Dossier0 Ref.: T7892
N/A
TRP Reference:
T722-152QC
Title:
Reliability testing of Commercial Available Flash memories (Follow on from:
Radaition assessment of Commercial Flash)
TD:
TD23
Objectives
A study shall be undertaken to determine the testing sequence for non-volatile flash memory with respect
to space applications.
Description
Non-volatile memory (NVM), especially FG flash based, is becoming increasingly popular for many commercial
applications. In this context industry has developed own test / bake sequences to assess flash based failure modes
(data retention, endurance, moving bit, erratic bit). However, space application have significantely different
requirements, i.e. especially lower endurane requirements (ca. 100 write/erase cycles vs >10E5 in industry), but
much higher data retention requirements (>15yrs vs. ca 7yrs in industry). Goal of this activity is to analyse available
and develope further on optimized test sequences for enabling ESA to clearly predict the reliability performance of
such devices in space.
Deliverables:
D1: ESCC generic specification for Flash test, initial test results of candidate technologies.
Current TRL:
TRL 2
Target TRL:
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 5
Application
Need/Date:
Contract Duration:
2010
24 months
Dossier0 Ref.: T 7855
N/A
TRP Reference:
T722-153QC
TD:
TD23
Title:
Comparative Study of the PGS test as a relaibility assessment tool for MOSFET
devices
Objectives
Objective of the study will be to analyse standard reliability test methods to assess Power MOSFET oxide
reliability. Part of the study is the execution of the test methods, the analysis of the results and the drafting
of recommendations for improving current space standards.
Description
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Description of Activities
ESCC 5000 together with MIL-750 standards are the reference for screening and qualification of discrete devices. In
particular MIL-STD-750E test method 1080 is the reference test method for SINGLE-EVENT BURNOUT AND
SINGLE-EVENT GATE RUPTURE. As part of this test method is the SEGR post gate-stress test (PGS test) that
consists in the verification of the integrity of the gate oxide after the SEGR test. Recent radiation tests performed on
European Radiation Hardened Power MOSFET (ref ECI/I) have indicated a potential weakness of the gate oxide of
these devices that was not revealed by HTGB and HTRB tests which are normally carried on during evaluation and
qualification phases. The study has the objective to analyse the test method conditions, perform a comparison of the
standards and propose a test plan to verify the equivalence of the test methods in screening out devices affected by
latent damage to the gate oxide, Implement the test plan on currently available Power MOSFETs (commercial level
IR, commercial ST, ST rad hard, JAXA- Fuji commercial and rad-hard), analyze the results and draft
recommendations for improving current space standards.
Deliverables:
Comparative test method report, Test plan, Test results, Recommendations.
Current TRL:
TRL 2
Target TRL:
TRL 5
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
2010
18 months
Dossier0 Ref.: T 7888
N/A
TRP Reference:
T722-154QC
Title:
Radiation Testing Methodology's for FLASH Memories
TD:
TD23
Objectives
This activity concerns the study of long term radiation effects in commercially available state-of-the-art
COTS FLASH memories.
Description
In support of ongoing radiation characterisation with IDA of 1-Gbit, 2-Gbit and 4-Gbit FLASH memories for "SafeGuard
Data Recorder" applications, it is also desirable to have additional technology and reliability information on these
state-of-the-art memories. Basic radiation characterisation of various types of FLASH memories have been covered
during heavy ion, proton and Co-60 campaigns and a baseline SGDR design successfully demonstrated during
Cf-252 testing. Further on-going SGDR radiation, reliability and benchmarking testing will still continue to be carried
out as well as further radiation characterisation of new candidate FLASH memory types.
However, as these FLASH memories are commercially available state-of-the-art COTS components – driven by
performance, cost and short life time – radiation reliability and long term effects also need to be addressed, in
particular if used in space applications. Candidate memory types need to be technology and architectural evaluated in
order to optimise their selection for flight. Safe operating modes, life testing, 1 vs 2 bit/cell, array size, floating or
biased storage, errors in FG array, endurance tests, retention tests and other long term radiation effects need to be
addressed. Optimised screening and testing methodologies shall be identified in order to minimise failures in flight
selected FLASH types.
Following irradiation exposures of 2Gbit, 4Gbit and 8Gbit FLASH memories under different test conditions and using
different radiation environments, floating gate charge loss, charge pump, SRAM buffers and their finite state machines
degradations need to be fully characterized. As FLASH memories rely on a tiny amount of charge stored in a floating
gate and a single ion strike can cause severe leakage, effects of ion energy and angle also need to be characterized.
Deliverables:
D1: Technical report covering heavy ion effects in state-of-the-art FLASH memories.
D2: Technical report covering proton effects in state-of-the-art FLASH memories.
D3: Technical report covering gamma effects in state-of-the-art FLASH memories.
D4: Final report covering Radiation effects in state-of-the-art FLASH memories.
Current TRL:
TRL 3
Target TRL:
TRL 5
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
2009
24 months
Dossier0 Ref.: T7888, T 7887
Not harmonised
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Description of Activities
TRP Reference:
T722-155QC
Title:
Radiation Assessment of Deep Submicron CMOS Devices
TD:
TD23
Objectives
In a previous contract (nr. C14924) radiation assessment of advanced submicron devices down to 65nm
feature size has been carried out. In previous years such exercises had established the tolerance of
submicron technology to total ionising dose radiation. However, the most current results from the contract
C14924 indicate radiation sensitivity of 90nm and 65nm devices to proton irradiation. Technology trends
in downscaling is progressing very fast and smaller than 90nm technology nodes will soon be
commercially available. The rapid technology development and the increasing trend to employ COTS
devices in Agency space applications make it essential to characterise these state-of-the-art technologies
enabling identification and selection of the appropriate technology for space missions.
Description
This activity consist of irradiation characterisation of 65nm devices including initial gamma irradiation characterisation
followed by detailed proton irradiation characterisation. Gamma characterisation is performed to verify whether the
observed catastrophic gate leakage current increase (in 90nm and 65nm proton irradiated devices) is due to surface
effects (total ionising dose) or bulk effects (displacement damage). The gamma characterisation is followed by
detailed proton irradiation characterisation of these devices under various operating and environmental conditions. At
the completion of the activity an assessment shall be made to identify whether the observed radiation effects also
impact commercial sub-micron technologies planned employed in future ESA space missions and discuss engineering
approaches for characterising these effects in commercial technologies.
Deliverables:
D1: Technical report on the gamma radiation assessment of the IMEC 65 nm high-performance CMOS technology.
D2: Technical report related to the systematic proton radiation testing of the IMEC 65 nm CMOS technology. D3:
Technical report related to the investigation of thermal annealing on the post-irradiation performance of the 65 nm
CMOS technology. D4: Summary report on the radiation activities performed in the two Activities and general
guidelines concerning radiation effects in potential semiconductor devices for future space applications. This report
will be considered as the Final Report of the activity.
Current TRL:
TRL 2
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
TRL 5
Application
Need/Date:
Contract Duration:
2009
20 months
Dossier0 Ref.: T7888, T 7887
To be discussed in Component Technology Board (CTB) Radiation
Working Group
TRP Reference:
T722-156QC
TD:
TD23
Title:
TID characterization of power-up behaviour for FPGAs
Objectives
The aim of this activity is to characterise Atmel's AT40KE and AT280 FPGAs and Actel AX2000 (RT or
non-RT) power-up behaviour as a function of cumulated dose
Description
Previous irradiation test results of FPGAs have indicated the criticality of the power-up sequence with total dose
degradation. In a previous contract (nr. 11407/NL/MV/CCN-3, COO-3) this failure mechanism was observed for the
Xilinx Virtex-I FPGA. The Actel RT14100 FPGA is another example. However, no TID reports from FPGA
manufacturers address this issue. It is likely that the power supply solutions used for these TID tests are over
dimensioned and far from representative of space applications and too optimistic.
The activity will be initiated by studying issues related to FPGA power-up sequence, TID effects and power supply
impact. In the study phase possible power solutions for the FPGAs addressing space applications shall be
investigated. For these power solutions critical parameters of the power-up sequence of the FPGA shall be identified.
Subsequently an irradiation test plan for the FPGAs shall be developed. The test shall be optimised for characterising
critical parameters in the power-up sequence behaviour as a function of cumulative dose. At the same time Atmel's
AT40KE and AT280 including Actel AX2000 (RT or non-RT) shall be procured. Following the evaluation of the
irradiation test plan the irradiation test campaign shall be initiated. Finally, an irradiation test report shall be generated
including a final technical document detailing the findings of the activity.
Deliverables:
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Description of Activities
D1: Study report D2: Test system specification
D3: Radiation Test plan, D4: Test system design documentation
D5: Radiation test report
D6: Final Report
Current TRL:
TRL 2
Target TRL:
TRL 4
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
2009
18 months
Dossier0 Ref.: T7888, T 7887
Not harmonised
TRP Reference:
T722-157QC
TD:
TD23
Title:
Development of 2-D imaging devices (CCD, APS, etc.) displacement damage test
guideline - First Assessment
Objectives
The aim of this activity is to characterise the extent of displacement damage and to propose test
guidelines for 2D-imaging arrays operated at cold temperatures.
Description
CCDs display sensitivity to displacement damage as well as ionising damage when exposed to the harsh space
radiation environment. The large number of parameters affected by radiation makes the usability of CCDs strongly
application dependant. Many scientific applications (e.g. GAIA) operate CCDs at cold temperatures to improve the
device performance. CCDs may be at cold temperatures during the major part of their operational life time. Currently,
most CCD irradiation tests are performed at room temperature for practical reasons. However, recent work performed
in activity 17928/04/NL/PA illustrates that some displacement damage effects may enhanced when irradiated at cold
temperatures.
THerefore, during the first phase of the activity and in discussion with CTB RWG members a draft low-temperature
displacement damage test guideline shall be generated. Additionally, suitable CCD and APS components shall be
selected and purchased for irradiation test campaign. Subsequently, an irradiation test campaign shall be carried out
at a suitable facility capable of handling low-temperature irradiation. Following the test campaign, an irradiation test
report shall be generated and the low-temperature displacement damage test guideline updated.
Deliverables:
D1: Draft low-temperature 2D-imaging device displacement damage test guideline.D2: Irradiation test plan. D3:
Irradiation Test Report. D4: Final low-temperature 2D-imaging device displacement damage test guideline.
Current TRL:
TRL 2
Target TRL:
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 4
Application
Need/Date:
Contract Duration:
2009
18 months
Dossier0 Ref.: T7888,
N/A
TRP Reference:
T722-158QC
TD:
Title:
Avoidance of MEMS dielectric charge trapping
TD23
Objectives
Investigate dielectric charging and charge trapping phenomena. Define identification procedures. Propose
and validate through actual testing possible technological solution including solution based on
nanomaterials
Description
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Description of Activities
MEMS in development today at ESA generally suffer from the so called dielectric charging effect which is limiting their
lifetime and also their state of the art performance over time. This is obviously the case for capacitive RF MEMS but
other components such as MEMS gyro, MOEMS and we anticipate the same limitations will be observed on
accelerometers. Sometimes, the presemceof just a native oxyde left during processing is sufficient to see the
phenomena. This is also the case for major MEMS development going on presently for ESA projects. The activity wll
therefore concentrate on defining method to detect such phenomena and define adequate procedures to test it. In a
second stage possible technological solutions including the usage of nanotechnology will be investigated and tested.
Deliverables:
Samples characterization report, processing recommendations
Current TRL:
TRL 1
Target TRL:
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 2
Application
Need/Date:
Contract Duration:
2010
18 months
Dossier0 Ref.: T7892
Consistent (MNT Component Technology Board (CTB) WG)
TRP Reference:
T722-159QC
TD:
TD23
Title:
Development of standard test methods for Single Event Transient
characterisation in CMOS using FPGA as test vehicle
Objectives
This activity aims at developing and verifying a standard test method (based on a FPGA) for
characterization of Single event transients (SET) in CMOS ASICs and FPGAs.
Description
With shrinking CMOS technology feature sizes the single event transients SET is becoming a major concern. SET
sensitivity has been reported for the Atmel ATC18RHA ASIC technology, Atmel AT697E leon processor, Actel
RTSX-SU and RTAX-S families. However the test methods used to characterize these events vary widely and are
often inadequate. Considering the growing impact of SETs on device performance for these technologies, it is
considered crucial to develop improved and standard test methods for SET characterisation for such devices. The test
method is additionally beneficial during the development phase of custom ASICs and FPGAs.
The activity is initiated by studing issues related to SETs in digital ASICs and FPGAs and currently applied test
methods. Following the study phase, the activity shall identify standard test structures optimised to accuratley
characterise the SET generation and progagation phenomena within real life digital ASICs and FPGAs. These test
structures shall represent as many "common" designs employed in ESA missions and applications as possible. Test
methods to characterise the standard test structures are subsequently developed optimised for reduced measurement
complexity and maximum efficiency. As a minimum test structures for characterisation of SETs in combinatorial logics,
asynchronous reset logics and clock network shall be developed. An irradiation test campaigns shall be executed
employing a FPGA for reduced cost and development time (e.g. Atmel AT280). Following the irradiation test a
preliminary SET test standard plus a verification plan are presented in a one day workshop with participants from the
CTB Radiation Working Group memebers and experts in the field. Following the workshop and update of documents a
second irradiation test campaigns shall be executed employing a second FPGA(or maybe ASIC). This test campaign
is used for verification of the applicability of the SET test standard. The SET test standard shall be updated based on
the verification activity results. The SET test standard shall be supplemented with a report discussing advantages,
disadvantages and limitations of all evaluated test concepts.
Deliverables:
D1: Study Plan,
D2: Test vehicle design report,
D3: Irradiation test plan,
D4: Irradiation test report,
D5: Draft SET test standard,
D6: Verification plan,
D7: Irradiation test report for second test vehicle,
D8: SET test standard with supplementary report
Current TRL:
TRL 2
Application/Mission: All missions
N/A
SW Clause :
Target TRL:
TRL 4
Application
Need/Date:
Contract Duration:
2009
24 months
Dossier0 Ref.: T7888, T 7887
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Description of Activities
Consistency with Harmonisation
Roadmap and Conclusions:
Not harmonised
TRP Reference:
T722-160QC
TD:
TD23
Title:
Possible micro power sources and associated architectures
Objectives
Perform a technology watch on possible MEMS-based micro power generation sources and propose
associated system architectures.
Description
To investigate the possibilities offered by MSTs (Micro Systems Technologies) to design, develop and prototype a
smart micro-power generator to be used on micro-aerobots, microprobes and nanorovers for planetary exploration.
Traditional power systems such as batteries or solar cells very often limit the lifetime (e.g. dust storms on Mars) or are
an impediment to the foreseen extreme miniaturization. New concepts for micro-power generation are already
reported today with various maturity levels, which should allow to achieve the challenge of limiting the associated
weight of the micro power generator to less than 25 grammes with an order of magnitude power density improvement
over current battery technology!! The technologies currently under development include: 1) Power extraction from
ambient vibration, in this case the micro power generator is based on ambient energy. The mechanical energy issued
from a movement (like self spinning of the probe for example) is converted into electrical energy based on charge
transportation between 2 parallel capacitors.2)Micro Electrical Generators integrated on a micro-turbine using for
example micro-lithographed planar Copper Circuits on Silicon, 3)“Spatialisation” of biomedical thermopiles, 4)
Micro-tubular or other fuel cells 5)Last but not least, efficient conversion from radiation energy into electrical energy
may also be an interesting concept for which suitability with ESA requirements may be checked. Different approaches
may be reviewed: the radiation is used to generate a cantilever movement which is then converted into energy; the
irradiated power is stopped using MEMS membrane thermally isolated structure; this results in a temperature
difference, which is convertible into electrical power using thermopiles. This activity will aim at performing a trade off
study of the various concepts listed above for selection of a preferred concept to be designed, breadborded and tested
in a follow on activity. The possible architectures associated to these various concepts will also be studied.
Deliverables:
Report on the market survey, technology study and recommendations.
Current TRL:
TRL 1
Target TRL:
Application/Mission: Sci, Exploration
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 1
Application
Need/Date:
Contract Duration:
N/A
12 months
Dossier0 Ref.: no ref.
Consistent (MNT Component Technology Board (CTB) WG)
TRP Reference:
T722-161QC
TD:
TD23
Title:
RF potentialities of Carbon nanotubes for nanoscale interconnections
Objectives
Based on a complete survey of the domain of nanowire/CNT for RF application, status of localised growth
of carbon nanotubes/nanowire will be given. Selection of 2 main test structure (one with CNT, the other
with nanowire) will enable first demonstration of nano based RF application. The activity will be concluded
by RF measurement of individual carbon nanotubes/nanowire and arrays of carbon nanotubes/nanowire
implemented into new RF component and/or interconnect scheme.
Description
Phase 1 : Literature survey on potentiality of CNT and nanowire for RF application. State of the art in the field of
characterization
of
nano-objects
with
focus
on
electrical
performances.
Phase 2 : Design of RF test structure enabling to determine intrinsic behaviour of CNT. Manufacturing of 2 selected
test structures based on localized nano object growth
Phase 3 : Measurement of individual carbon nanotubes/nano wire and arrays of carbon nanotubes/nano wire RF
properties.
Deliverables:
Reports and prototypes and caharcetised materials
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Description of Activities
Current TRL:
TRL 2
Target TRL:
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRP Reference:
T722-162QC
Title:
Hot Vias MMICs
TRL 3
Application
Need/Date:
Contract Duration:
2010
18 months
Dossier0 Ref.: T7892
Consistent (MNT Component Technology Board (CTB) WG)
TD:
TD23
Objectives
Development and space evaluation of Hot Via technology for Low Noise and Low Power application
Description
The activity shall aim in improving a MMIC Process suitable for both Low Noise and Low Power applications in the
frequency range of 10 GHz to 14 GHz. It will first solve the technical problems in designing a LNA circuit with hot via
transitions, with the goal to optimize the targeted performance in the frequency range. Special focus will be on the
simulation of thermal performance of the MMIC chip assembled with solder bumps on a substrate. Investigation and
development of on wafer measurement techniques under the special requirements of the access of the DC and RF
pads from the backside of the wafer only. Assembly evaluation of the diced MMIC chips on a substrate using solder
bump reflow techniques. Validation of the mounting process by existing investigation methods shall be performed.
After successful assembly of the representative MMIC on a substrate as test vehicle, the evaluation shall be
performed according to relevant ESCC specification to evaluate the reliabilty performance of this advanced
technology.
Deliverables:
Report and hot vias MMICs
Current TRL:
TRL 1
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
TRL 2
Application
Need/Date:
Contract Duration:
ASAP
12 months
Dossier0 Ref.: T-7908
Consistent (MNT Component Technology Board (CTB) Microwave
dossier)
TRP Reference:
T722-163QC
TD:
TD23
Title:
Evaluation of new FPGA technologies (hardened-SRAM, Flash, mixed-signal)
Objectives
The objective of the proposed activity is to evaluate the suitability of the new FPGA technologies (mixed
signal, flash based, low power, RadHard SRAM-based) for space designs. The FPGA technologies
addressed are not yet available for the space market but they are already present for the commercial
applications and the vendors are planning to bring them to the space community in the future. This
evaluation therefore aims to learn best practices in the use of the new FPGA devices for space taking
advantage of their current availability and anticipating its eventual future introduction into space.
Description
In the present Actel devices based on antifuse technology are the predominant technology used for FPGAs in the
space sector. However, Actel is already working on bringing other mature technologies into the space domain:
Flash-based (the ProASIC family) and eventually also the mixed signal FPGAs (the FUSION family). Other major
players in the commercial sector are moving since some years into the space sector: Xilinx offers large SRAM-based
Rad Tolerant FPGAs and are already working on Rad Hard versions of their newest Virtex-5 family based on 65nm
geometry. The proposed activity is an evaluation of these new FPGA technologies in designs for space. The Task
breakdown is as follows: - Feasibility analysis on the FPGA devices and development boards to be used in the
evaluation (commercial boards), on the target designs and on the metrics to be used (as for example resource usage,
max. frequency, …).- Architectural and detailed design phases of the target designs to be used; porting of the design
to the different FPGA technologies- Performance measurements according to the metrics on the development boardsFinal report including the comparison of the different FPGA technologies and the predicted and measured metrics
Deliverables:
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Description of Activities
The deliverables include: - the final report with the evaluation of the new FPGA technologies- guidelines for the usage
of these FPGAs in space applications- the boards and designs used in the evaluation (to be negotiated if proprietary
design/s are used as part of the evaluation). - the documentation required by ECSS-Q-60-02 on FPGA development
for the target FPGAs
TRL 4
Current TRL:
Target TRL:
Application/Mission: All missions
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 5
Application
Need/Date:
Contract Duration:
2010
18 months
Dossier0 Ref.: T-7795, T-7802, T-7746
Consistent (D1, in µE Dossier)
7-29 - NEOMEX
TRP Reference:
T701-164ED
TD:
TD01
Title:
Data handling system design and proof-of-concept for modular
system-of-microsystems approach
Objectives
Define a modular data handling system architecture based on system-of-microsystems for nanosatellites.
Build a proof-of-concept setup and demonstrate the architecture.
Description
A top level systems design with preliminary microsystem modules can be assumed as an input. The activity shall
trade-off different data handling systems concepts and select the best one for proof-of-concept. The trade-off shall
consider for instance computational power, task sharing, power reduction, identification of possible ASIC
implementation of low power standard interfaces, standardized micro scale connectors and interfaces.
The design and implementation of the physical bus, application protocols, distributed data flow (DDF) vs. client/server
(centralized) vs. point-to-point (P2P) architectures, and added value of plug ’n play (PnP), needs to be addressed.
Standards such as Space Plug ‘n play Architecture (SPA-C, SPA-U, SPA-S) and the OpenSAT initiative shall be
considered.
The data system in itself shall be highly miniaturized (using e.g. 3D System-in-Package, ASIC, FPGA-based solutions,
or 3D-SiP technology) and low-power, but shall also be developed with minimum recurring cost in mind. The data
system must also be modularized and scalable in an appropriate way. Modular means that the same system/unit can
be used for different system designs and geometrical platforms with only application s/w level changes. The study
shall decide on the proper hardware technology, given the initial trade-off, and the intended general application.
The system shall be suitable for system-of-microsystem based nanosatellite platform. General applicability and
modularity are major drivers. Mission-specific payload modules can be hooked into the system. A specific trade-off
shall be conducted on the payload expected requirements and bus selected for the architecture. For example, it may
or may not be efficient to use a high speed bus and low-speed bus in parallel to save power (with only a few units
using the high speed bus).
Bandwidth analysis or equivalent shall be performed, in order to evaluate the proposed design.
The data handling architecture shall address thermal issues and if possible by multifunctional design allow a higher
power outtake than today, up to 10-15 W per unit to allow high performing nanosatellites. Note the design shall also
decide on the overall s/c computing architecture (e.g. fully centralised vs de-centralised by sub-system) and should
consider different plug and play architectures per sub-system as appropriate.
Deliverables:
Survey of current technologies, Design trade-off report, Proof-of-concept setup (including PDR, H/W, S/W - embedded
and PC control manager, debugger -), Final report.
Current TRL:
TRL 1
Target TRL:
Application/Mission: NEOMEX
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRP Reference:
T703-165EP
TRL 2
Application
Need/Date:
Contract Duration:
TRL5 by 2016
18 months
Dossier0 Ref.: no ref.
N/A
TD:
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TD03
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TRP Work Plan 2008-2010
Description of Activities
Title:
Thin-film Lithium Batteries
Objectives
To assess the potential of the thin-film batteries for use in space.
Description
All-solid-state Lithium batteries are made by depositing the components as thin films (<5µm) on a substrate. When
embedded in micro-devices, such batteries act as an autonomous power source. This technology is foreseen for
medical applications, RFID tags, memory chips. Many US small companies hold licences of the Oak Ridge Lab
technology. In Europe there have been some previous developments and expertise exists, e.g., in Germany and
France.
The performances are extremely interesting. One company claims to have a lithium batteries working from -40°C to
+150°C. A system based on a lithium metal anode, LIPON electrolyte, would have the following characteristics: 300
Wh/kg, 959 Wh/l, 6000 W/kg, 40000 cycles. The maximum capacity claimed is 10 mAh.
If confirmed, these type of batteries could have a large potential for use in space, e.g. in miniaturized S/C. Therefore,
within this activity, an assessment of the potential applications of thin film batteries and the impacts of such technology
on the power system needs to be undertaken, as the first step. Furthermore, a review of the thin film batteries
available in Europe will be conducted, followed by a full study of this technology including characterisation, evaluation,
possible scalability.
Deliverables:
Test Report, batteries samples
Current TRL:
TRL 2
Target TRL:
Application/Mission: NEOMEX
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 4
Application
Need/Date:
Contract Duration:
TRL5 >2012
18 months
Dossier0 Ref.: T-7810
N/A
TRP Reference:
T703-166EP
TD:
Title:
Very thin GaAs MJ solar cell development
TD03
Objectives
To demonstration of a concept for ultrathin solar cells
Description
The performance to weight ration of multi-solar cells is dominated by the Germanium substrate. Being able to
realeasing the cell from the Ge-substrate after manufacture would dramatically change this ratio. Several
developments worldwide, both in Europe, Japan and the US, have shown that the concept of an ultra-thin GaAs based
solar cell is a realistic proposition:
- Report of TRP (ITI) contract 18993
- Flexible thin-film III-V multijunction solar cells, T. Takamoto, et al, Proc. 19th European Solar Energy Conference,
Paris (2004) 3689.
- Lattice mismatched approaches for high-performance, III-V photovoltaic energy convertors, M.W. Wanlass, et al.,
Proc. IEEE Photovoltaics specialists conference, (January 2005).
In particular, Sharp has demonstrated a string of operational multi-junction cells with a thickness of a few microns. In
Europe, the work performed in previous a TRP contract (ITI contract 18993) has shown the potential to both to make a
cell with a thickness of a few microns (hence dramatically improved W/kg) and to recover the substrate upon which
the cells structure is grown – this can account for of the order of 30% of the cell cost. In a different concept, IMEC
have produced 20?m Ge substrates by physically grinding / polishing away material which can then be recycled.
As there are many possible concepts and process flows which show potential, the scope of this new activity is to
improve the substrate release process and also to manufacture first samples of ultra-thin 3J solar cells. New bonding
techniques may be implemented. The Substrate release process shall be improved and the reliability of this process
after high temperature exposure shall be demonstrated. State-of-the art 3J solar cells shall be grown epitaxially on thin
Ge substrates which are bonded to a support structure.
Deliverables:
at least 20 samples of ultra-thin 3J cells
Current TRL:
TRL 1
Target TRL:
TRL 2
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Application
Need/Date:
2011
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Description of Activities
Application/Mission: NEOMEX
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Contract Duration:
24 months
Dossier0 Ref.: T-7806
N/A
TRP Reference:
T705-167EC
TD:
TD05
Title:
Definition and sizing of AOCS for NEOMEX Nanosatellite
Objectives
Analysis and definition of a modular, flexible AOCS for Nano satellites
Description
During the course of the activity an analysis of the AOCS design to show the capabilities of the s/c, the limitations of
the s/c, the AOCS mass and power budgets, the level of re-use between missions and the AIT effort shall be
performed:
- An assessment of the potential improvements in terms of mass, power, AIT effort and development time over a
‘standard’ current approach.
- Demonstration of the potential capabilities and feasibility of an advanced multi mission nano satellite and providing
inputs for the development of the AOCS and associated sensors and actuators to realise such a s/c.
The work shall be based on the ESA provided ‘straw man’ NEOMEX nano-sat design concept as a starting point.
However, other example applications shall also be considered: a distributed science mission experiment (e.g. radio
telescope or magnetometry) and a LEO constellation mission for either data relay or rapid disaster monitoring.
Furthermore, the AOCS software architecture shall be defined demonstrating modularity and ease of development,
test and mission configurability. The Activity shall also assess need unit specifications and unit suite, including
propulsion needs, for each mission type (LEO, NeoMex, Constellation, inspector). The unit definition shall include
consideration of an AOCS sensor 'plug and play' TM/TC interface suitable for all units and which considers all units to
be provided with a digital data interface:
- Definition of a basic central computer software structure that schedules, runs and allows the easy replacement of
AOCS (and other) application software ‘modules’ with minimum re-test needed for quick and cheap mission
customisation.
- Definition of a plug and play data interface standard for AOCS hardware allowing rapid s/c customisation with
minimal re-testing
- Definition of the AOCS hardware suite required for each of the different supported mission types
- Derivation of the functional requirements for each of the AOCS sensors and actuators
- Selection of three example missions, and production of the AOCS design for those missions.
Deliverables:
AOCS design report covering the modular design concept and the three example missions, proposed AOCS
hardware plug and play draft standard, AOCS nano satellite unit requirement specifications, nano satellite simulator
running on Matlab.
Current TRL:
TRL 2
Target TRL:
Application/Mission: NEOMEX
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
2012
15 months
Dossier0 Ref.: no ref.
N/A
TRP Reference:
T705-168EC
TD:
Title:
Digital sun sensor on a chip prototyping
TD05
Objectives
The development, production and test of a plug and play compatible digital sunsensor prototype on chip
that is capable of being used in an AOCS test bench.
Description
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Description of Activities
The activity includes the design, manufacture and test of a sun sensor on a chip prototype with following
characteristics:
- Plug and Play interface and alternative SpW interface
- Mass < 20g
- Power < 0.1 Watt
- Accuracy < 60”
- Dimensions < 3*3* 1.5 cm
- Power supply – 5V
Demonstration of capability to realise useful AOCS equipments ‘on a chip’ and to verify the feasibility, workability and
benefits of a plug and play system for AOCS hardware.
Deliverables:
The outputs shall include:
- 5 tested prototypes
Current TRL:
TRL 3
Target TRL:
Application/Mission: NEOMEX
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 6
Application
Need/Date:
Contract Duration:
2012
15 months
Dossier0 Ref.: T-7816
N/A
TRP Reference:
T706-169ET
TD:
Title:
Transmitter Vacuum Electric Power Amplifier
TD06
Objectives
To design, realise and test a Vacuum Electronic Device Power Amplifier.
Description
Travelling wave tube amplifiers (TWTAs) are often opposed to solid-state power amplifiers (SSPAs). As a rule of
thumb, TWTAs outperform SSPAs in efficiency and absolute output power while SSPAs are more linear than TWTAs.
In addition, in terms of mass/size, TWTs scale down with frequency while SSPAs scale up with output power. Ideally,
one would like to have a device which exhibits the linearity of an SSPA combined with the efficiency of a TWTA at a
fraction of the size: this is the goal of this activity. The activity shall first address the main building blocks of the
Vacuum Electronic Device Power Amplifier which are the modulated source of electrons and the amplifying vacuum
electronic structure. The source of electron is foreseen as a semiconductor device based on promising gallium nitride
(GaN) structures which would offer a very simple modulation access, up to possibly X to Ku-band. The amplifying
vacuum electronic structure is expected to be a shrunk version of existing structures used in vacuum power
electronics e.g. the helix of a travelling wave tube (TWT). The two building blocks shall then be assembled and
connected to a laboratory power supply to form the VEPA breadboard which shall be fully tested.
Deliverables:
Breadboard of Vacuum Electronic Power Amplifier
Current TRL:
TRL 2
Target TRL:
Application/Mission: NEOMEX
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
TRL5 >2013
24 months
Dossier0 Ref.: no ref.
N/A
TRP Reference:
T706-170ET
TD:
Title:
Receiver low-power analogue decoder
TD06
Objectives
The proposed activity aims at demonstrating the feasibility of iterative analogue decoding for on-board
receivers with low DC power consumption. The demonstrator shall include the implementation of analogue
decoder for a practical coding scheme. The comparative assessment of the analogue decoder versus their
conventional digital decoder counterparts shall be based on energy efficiency, decoder throughput, and
circuit complexity and decoding performance.
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Description of Activities
Description
There have been several research activities in recent years to study and design analogue decoding schemes for
terrestrial applications. Potential improvements in power-to-speed ratio (i.e. reduction in energy spent per each
decoded bit) as well as circuit complexity provide a strong incentive for continuation of such research activities.
Several prototype analogue decoders, albeit for simple decoders, have been implemented and reported in the open
literature. Published test results indicate more than 5 folds reduction in power-to-speed ratio while predictions for such
improvements are as high as 10 times improvement.
Iterative analogue decoding can in principle provide an attractive solution, particularly for on-board receivers with
stringent requirements on DC power consumption and payload mass. The proposed activity aim at demonstrating the
feasibility of iterative analogue decoders for space applications. Some of the technological challenges to be addressed
in this activity include: analogue storage, serial to parallel conversion and interleaver wiring. In addition, techniques for
dealing with large coding block sizes will be investigated.
In the first phase of proposed activity, the applicability of the proposed techniques to implementation of on-board
demodulators with low DC power consumption shall be investigated. In addition, the proposed activity shall address
the required VLSI technologies to implement analogue decoders for space applications. Upon a successful selection
of the architecture as well as the space qualified technology, an iterative analogue decoder shall be prototyped for the
selected practical coding scheme. The output of the second phase of the activity shall include a hardware
demonstrator based on a customized design that implements the iterative process for one selected coding scheme.
Deliverables:
Technical Notes, Test Reports, Hardware Demonstrator
Current TRL:
TRL 2
Target TRL:
Application/Mission: NEOMEX
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
2012
18 months
Dossier0 Ref.: no ref.
N/A
TRP Reference:
T707-171EE
TD:
TD07
Title:
Miniaturised multi-functional antenna system for micro/nano-satellites
Objectives
To study and demonstrate a miniaturised antenna system suitable for TT&C and data transmission fitting
the ultra-tight accommodation requirments of micro/nano-satellites.
Description
Distributed antennas are used for TT&C sub-systems in all spacecrafts, however micro-nano satellites pose the extra
challenge of ultra stringent accommodation requirements, leading to the need of antenna system miniaturisation and
multifunctionality.
The very small size of the platform results in the fact that the whole satellite acts as an antenna, leading to very
specific design requirements. On the other hand this fact can be exploited to reduce the size of the RF-emitters to the
bare minimum, provided that suitable design methodologies and tools are available for the purpose. Furthermore a
clever use of a small number of RF-emitters will provide at the same time robustness, via the added redundancy,
better link margin as well as the possibility of extra functionality, like an RF tracking capability that could be used to
help pointing the spacecraft using a beacon on the mother-ship and the use as a single higher-gain antenna for the
transmission of observation data.
To design a distributed RF-emitter advanced modelling capabilities are necessary, for both the antenna elements and
the spacecraft structure that dominates the antenna performances and shall be developed, based on existing and
proven tools used for "calssical" distributed antenna systems and on the knowledge derived form other applications
(e.g. cellular phones and WIFI equipment), including the integration of active elements with the RF-emitter. The same
knowledge shall be applied to design the protype antenna system for a demonstration platform having realistic sizes
and features. A proof-of-concept prototype of the antenna system will be built and tested on a platform model.
Deliverables:
Proof-of-concept prototype
Current TRL:
TRL 1
Application/Mission: NEOMEX
N/A
SW Clause :
Target TRL:
TRL 2
Application
Need/Date:
Contract Duration:
2012
18 months
Dossier0 Ref.: T-7832, T-48
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Description of Activities
Consistency with Harmonisation
Roadmap and Conclusions:
N/A
TRP Reference:
T713-172MM
TD:
TD13
Title:
Architect of the System-of-Microsystems nanospacecraft
Objectives
The objective of this activity is to adopt the role of an eventual systems architect and potential systems
integrator for the future system-of-microsystems nanospacecraft. Hereby, a consistent evaluation of the
concept and technology needs and performance shall be obtained.
Description
Within this activity, the contractor shall keep track of the progress of other relevant developments within ESA,
particulartly those associated with the Disruptive technologies theme, in order to evaluate the performance of the
developed technologies from the perspective of an would-be system architect and systems integrator for a
system-of-microsystems nanospacecraft. Particular emphasis shall be on the general applicability, a Near Earth Micro
Explorer mission (NEOMEx) and an early LEO demonstrator mission. The activity shall roadmap future necessary
developments with the goal of a real mission with use of an intermediate in-orbit demonstration. The roadmap shall
build on the experience gained from the associated evaluated activities. The activity is also expected to identify
additional necessary activities during the progress, and the contractor shall report such items continuously.
Deliverables:
Evaluation of system-of-microsystems, Critical further activities list (constantly updated), Roadmap
Current TRL:
TRL 1
Target TRL:
Application/Mission: NEOMEX
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
2012
24 months
Dossier0 Ref.: no ref.
N/A
TRP Reference:
T713-173MM
TD:
TD13
Title:
Standard modular microsystems interface definition and proof-of-concept
Objectives
Trade-off, definition and proof-of-concept of a standard micro-interface to be used to the modular
microsystems of the system-of-microsystems.
Description
Trade-off, definition and proof of concept of a microsystem interface to be used to the modular microsystems of the
system-of-microsystems. The activity shall prove the concept for data and command, power distribution, and
propellant management.
It is recognised that it may be difficult to obtain a true standards interface for everything. The activity shall trade-off
and define the requirements and designs for interfacing between microsystems, microsystems to circuit boards,
microsystems to fluidic systems, and microsystems to power electronics.
The following items shall be addressed within the activity:
- Modularization guidelines: How to define interfaces between power, data, communications, payload, AOCS, and
propulsion in the system-of-microsystems?
- For true modularity, local/distributed micro power conversion (dc/dc/step-down), power control (solid state power
controller (SSPC), latch-up protection, must be included. A trade-off between the recommended unit size and level of
power distribution should be investigated.
- Top-level module interfaces requirements definition and module interfaces conceptual designs. Trade-off and critical
items identification.
- The activity shall also perform proof-of-concept demonstrations of the critical interface items, separately and in a
breadboard setup.
Deliverables:
Survey of current developments, Trade-off report, Proof-of-concept of separate interface functions, demonstration of
critical interfaces in breadboard test setup.
Current TRL:
TRL 2
Target TRL:
TRL 4
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Application
Need/Date:
2012
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Description of Activities
Application/Mission: NEOMEX
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Contract Duration:
18 months
Dossier0 Ref.: T-8382
N/A
TRP Reference:
T713-174MM
TD:
Title:
Integrated harness technology
TD13
Objectives
To evaluate the performance of integrated harness technology in the context of a system-of-microsystems
architecture.
Description
The concept to be developed would be the application of new technologies to the harness function, such as wireless
technology. Although the mass saving for a wireless harness may not be significant for a system of Microsystems the
concept when proved would have major implications for larger spacecraft. This development is linked to the
multifunctional structures activity. Studies and breadboards of embedding electronic components and harness into the
structure have been performed and a complete test campaign should be performed to assess the structure.
Deliverables:
Test report
Current TRL:
TRL 3
Target TRL:
Application/Mission: NEOMEX
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 5
Application
Need/Date:
Contract Duration:
TRL5 by 2012
18 months
Dossier0 Ref.: T-8382
N/A
TRP Reference:
T716-175MM
TD:
TD16
Title:
Space instruments based on microtelescope array, proof-of-concept
Objectives
This study will investige innovative micro optical systems and explore potential inclusions of sensing
capabilities like vision, spectroscopy, polarization or distance detection
Description
The objective of this study is the design and development of a microoptical system for close-up imaging in space. This
micro optical system will be integrated into a larger system of microsystems. Optical microsystems are particularly
interesting for applications where size, power consumption, ruggedness and multifunctionality are important such as
planetary probes. Functions such as imaging, spectrometry and distance measurement (e.g., altimetry) can be
performed by very compact devices using fabrication and packaging techniques akin to silicon chips and microlenses.
The study will investigate innovative micro optical imaging concepts (e.g., compound - insect eye systems) and
explore potential inclusion of additional sensing capabilities such as spectroscopy or distance measurement. The
activity will start with an identification and review of possible microptical imaging concepts, followed by an assement of
their performance capabilities and technical feasibility. Promising solutions will be further elaborated and traded off
with a view of selecting a preferred design, with due consideration being given to the interfacing and later integration
of the microoptical system into a larger system of microsystems. After the detailed design, critical technologies will be
breadboarded and the achievable performances experimentally assessed.
Deliverables:
Micro optical system study + BB of micro optical system
Current TRL:
TRL 1
Target TRL:
Application/Mission: NEOMEX
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
2012
24 months
Dossier0 Ref.: T-7861
N/A
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Description of Activities
TRP Reference:
T718-176MP
TD:
TD19
Title:
Medium delta-v, low-power, low-voltage microthruster module breadboarding
Objectives
The objective of this activity is to demonstrate the feasibility of a Hollow Cathode Thruster for micro S/C.
Description
The proposal aims to achieve a micro-thruster suitable for stand-alone use or as an enabling technology for all-electric
spacecraft ready for space qualification. In particular, the microthruster should be adapted to use on a modular
nanospacecraft platform, for medium delta-v manoeuvres and possibly attitude control and free-flying operations. The
limitation when considering the application of micro-propulsion technologies to small spacecraft, particularly for
attitude control, is constraints in volume, mass and power. While larger satellites (>200kg) may be able to incorporate
high performance systems for such as mono-propellant, bi-propellant and conventional electric propulsion systems,
smaller spacecraft face severe resource limitations which place these systems beyond their reach. The inability to
suitably scale conventional high performance systems down means these satellites are generally forced to operate
with only the simplest of propulsion systems, such as cold gas or resistojets and leave these spacecraft unsuited to
anything other than low earth orbit operations.
Hollow cathodes are a mature technology developed and tested extensively in the space industry as electron sources
for gridded ion engines and hall thrusters. While hollow cathode plasma devices have recently been shown to produce
usable thrusts (>5mN) at reasonable performance (>500s specific impulse), and highlights a possibility to integrate a
high performance thruster and associated subsystems onto an integrated and scalable device suitable for use with
limited onboard resources or as part of an all-electric spacecraft. The work would aim to generate an optimized
microthruster, e.g. based on hollow cathode, with appropriate operational characteristics, propulsive performance and
life to fulfill this role.
Deliverables:
Microthruster demonstration model
Current TRL:
TRL 2
Target TRL:
Application/Mission: NEOMEX
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 4
Application
Need/Date:
Contract Duration:
TRL5 >2012
24 months
Dossier0 Ref.: no ref.
N/A
TRP Reference:
T718-177MP
TD:
Title:
Propellant management and storage module
TD19
Objectives
The contractor shall design a modular miniaturised propellant storage system and show that the design
can meet the requirements for different missions, in particular the NEOMEx. In a second phase the
contractor shall build a breadboard of the system and perform functional tests on it.
Description
Small and very small spacecraft will perform more and more advanced missions requiring attitude control, power
storage, payload purging and propulsion. A suitable miniaturised propellant storage device can help these satellites to
perform these functions. These satellites will need a suitable fuel storage system for propulsion, energy supply, or (in
the long term) also possibly for the inflation of structures like antennae, airbags etc.
Envisioned applications are nanosatellites (< 10 kg), miniature planetary landers and inspection satellites that can be
used for Space Station or could accompanying larger satellites. In particular, a Near Earth Object Micro Explorer is
used as a strawman mission.
In order to be efficient, such a miniature storage system should have features that allow autonomy, long storage and
no loading or venting activities after integration into the spacecraft. The system should have a high inherent flexibility
so it can easily be adapted to different spacecraft and missions.
As small spacecraft are often launched piggy-back the main payload dictates that high pressures, pyrotechnics or high
temperatures should be avoided as much as possible during storage and launch.
The system shall be able to survive long storage periods on earth and in space and shall have a negligible leakage
during this time. The storage system shall include valves and pressure sensors to monitor its status. These functions
should be integrated in a microsystem system device. The activity should demonstrate this through proof-of-concept
breadboard.
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Description of Activities
Deliverables:
Propellant storage module breadboard
Current TRL:
TRL 2
Target TRL:
Application/Mission: NEOMEX
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 4
Application
Need/Date:
Contract Duration:
2012
18 months
Dossier0 Ref.: no ref.
N/A
TRP Reference:
T719-178MC
TD:
Title:
Multifunctional structure
TD20
Objectives
To combine the primary and secondary structure, integration microsystem functions into the structure.
Description
The main aim of this activity would be to combine the roles of primary and secondary structures. Currently primary
structure carries the loads and secondary structure is attached to the primary structure and houses electronics. This
would introduce significant mass savings, but the focus of interest would be on developing structure which perform
both roles: To act as the load path and also to protect the electronics and microsystems. Current studies into small
self deploying structures could be advanced to a flight demonstrator concept. Foldable structures which would achieve
low volume and good performance in the launcher environment could be investigated. Compact structures with the
ability to self deploy, such as Silicone based materials, could have electrical subsystems integrated into them.
Deliverables:
TN, breadboard
Current TRL:
TRL 1
Target TRL:
Application/Mission: NEOMEX
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 3
Application
Need/Date:
Contract Duration:
TRL5 >2013
18 months
Dossier0 Ref.: no ref.
N/A
TRP Reference:
T720-179MC
Title:
Temperature-dependent thermal coatings
TD:
TD21
Objectives
To develop thermal coating which change their thermo-optical properties with temperature such as to
minimise the need of electric heater power. Specific emphasis will be on coatings which minimises the
need of electrical power during eclipse times.
Description
Materials with thermo-optical materials changing with temperatures are known already. Within the activity, the
dynamic range epsilon (alpha) with temperature shall be further increased and the long term behaviour in space shall
be assessed. The application of the coatings on various structural materials shall be tested and the physical
performance parameters shall be measured.
Deliverables:
Technical documentation, physical properties of the coatings, samples on various substrates
Current TRL:
TRL 2
Target TRL:
Application/Mission: NEOMEX
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 4
Application
Need/Date:
Contract Duration:
TRL5 >2012
18 months
Dossier0 Ref.: no ref.
N/A
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Description of Activities
TRP Reference:
T720-180MC
TD:
Title:
Micro-phase-change materials
TD21
Objectives
The objective of this Activity is to develop a space Phase change material, which can be easily applied on
various geometries of different size, including micro/nano satellites, based on commercially available
microencapsulated PCM’s. The PCM’s shall be used to minimise the electrical heating power during
eclipse times to minimise the size of the on-board batteries.
Description
Various microencapsulated commercially available PCM materials shall be analysed for their use in a space
environment. The most promising materials shall then be embedded in a Phase change capacitor, which can be
applied in a flexible way on any spacecraft. It shall therefore be possible to apply the PCC directly to the dissipating
unit or to fill any void volume which might be available in the satellite. Investigation to implement the PCM into
structural elements (compound materials) shall be investigated
Deliverables:
Technical documentation, physical properties of the PCM, PCC design, PCC breadboard
Current TRL:
TRL 2
Target TRL:
TRL 4
Application/Mission: NEOMEX
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
2012
18 months
Dossier0 Ref.: T-8440
N/A
TRP Reference:
T720-181MC
Title:
Micro heat management systems
TD:
TD21
Objectives
The objective is to identify suitable thermal control means for micro/nano satellites, identify suitable
standard thermal hardware (e.g. thermistors, MLI) and design tools compatible with the mass and volume
of a micro/nano sat and identify any novel technology required to enable a passive, low power thermal
control system for a multipurpose micro/nano satellite
Description
Within the activity a thermal control system fo0r a micro/nano sat shall be established, with the goal to minimise the
heater power required, specifically during eclipse times, when no power from the solar arrays are available. For this
purpose, coatings with variable epsilon/alpha shall be analysed and the use of PCM’s shall be considered. In addition,
it shall be assessed whether the use of heatswitches, micro heat pipes or other thermal technologies are required to
simplify the thermal control system of a Micro/nano sat
After this, an equipment list for the micro heat management system shall be established and suitable suppliers shall
be identified. In case no existing hardware can be identified, a development plan for the missing items shall be
established.
In parallel, the applicability of thermal design tools and margins philosophies used in classical Spacecraft shall be
critical assessed for micro/nano spacecraft technologies. If required, alternative tools shall be investigated and a new
margin philosophy shall be established.
Deliverables:
Thermal control system of a nano/micro sat, supplier list, development plans
Current TRL:
TRL 2
Target TRL:
Application/Mission: NEOMEX
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 4
Application
Need/Date:
Contract Duration:
2012
18 months
Dossier0 Ref.: T-7880
N/A
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Description of Activities
TRP Reference:
T722-182QC
Title:
Connectivity and Packaging of systems-of-microsystems
TD:
TD23
Objectives
Design, prototyping and testing of a system-of-microsystems packaging approach including connectivity
issue.
Description
This activity will address the packaging of a system of micro-systems it will be a logical complement of WALES, a TRP
activity being presently initiated which will cover MEMS Wafer Level Packaging. The activity will aim at designing,
prototyping and testing a global packaging solution for micro-systems including wafer level packaged MEMS. Critical
points that need to be adressed are:
- Packaging techniques and 3D stacking technologies for the fabrication of miniaturised SIP (System-In-Package)
- Micro-systems integration including MEMS, electronics and other relevant functions
- Hermeticity, internal package atmosphere and getters
- Assessment of the reliability for space applications
Attention will also be given to the connectivity of the System-In-Package.
The activity will be sub-divided as follows:Task 1: Survey of packaging/connecting techniques,Task 2: Trade off , Task
3: Design,Task 4: Manufacturing/prototyping of a micro-system including a reasonable amount of wafer level package
MEMS, Task 5 Validation by testing
Deliverables:
TN, design, breadboards, test programme, test reports
Current TRL:
TRL 2
Target TRL:
Application/Mission: NEOMEX
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
TRL 4
Application
Need/Date:
Contract Duration:
TRL5 >2012
24 months
Dossier0 Ref.: T7892
Consistent (Harmonised via MNT CTB dossier Paragraph 12.7.2)
TRP Reference:
T722-183QC
TD:
TD23
Title:
Reliability and standardisation for systems-of-microsystems
Objectives
Esatblish and validate methodology and procedure for evaluating MEMS realiability, exploit Neomex
environment for a tentative standardisation.
Description
The activity will take advantage of having several MEMS candidates integrated in Neomex to establish generic (or at
least as much generic as possible) methodologies for assessing the reliability / quality of these MEMS. This shall be
done at sub-system level and then review the commonalities for each device in order to get a basic generic MEMS
reliability procedure to which additional quality assessment can be added depending on the type of micro-system
which is addressed. It shall also address the complete system reliability assessment and help to decide how we
should in the future treat a system of micro-systems: “black box” approach or do we need specific approach for the
global system which takes into consideration the type of embedded micro-systems? Today different approaches are
taken according to the project (GAIA, JWST…) but we need to standardise that in the future.
The following tasks will be included: identification of available micro systems, definition of a reliability approach for
each candidate, validation, consolidation. brainstorming, standardisation
Deliverables:
TN, design, breadboards, test programme, test reports
Current TRL:
TRL 2
Application/Mission: NEOMEX
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Target TRL:
TRL 4
Application
Need/Date:
Contract Duration:
TRL5 by 2012
16 months
Dossier0 Ref.: T7892
Consistent (Harmonised via MNT CTB dossier Paragraph 12.7.3)
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Description of Activities
TRP Reference:
T723-184QM
Title:
Advanced manufacturing methods for systems-of-microsystems nanospacecraft
TD:
TD24
Objectives
To implement the design of a nanospacecraft supporting structure into a technology allowing to
manufacture it in one shot and possibly to implement using this manufacturing techniques additional
functional features.
Description
When "buy to fly ratio" is below about 30% (meaning that 70% of the initial block of material is machined away)
additive manufacturing technologies becomes an alternative to conventional machining. With systems of
micro-systems spacecraft, the integration level of the micro-systems can be heavily improved using such techniques.
Taking into account the system study and the capabilities of the advanced manufacturing technologies, geometry of
the casing will be adapted to embedd additional features compared to classical design, thus lowering further mass.
Deliverables:
TN, design, prototype, test and final reports
Current TRL:
TRL 2
Target TRL:
TRL 4
Application/Mission: NEOMEX
N/A
SW Clause :
Consistency with Harmonisation
Roadmap and Conclusions:
Application
Need/Date:
Contract Duration:
2012
24 months
Dossier0 Ref.: no ref.
N/A
7-27 - Electronic Components
TRP Reference:
T709-133QT
TD:
Title:
SEE Testing of european GaAs Technologies
TD22
Objectives
SEE Radiation testing of European GaAs MMIC processes in order to try relaxing the relative ESA ALERT
EA-2008-EEE-05 issued after Metop LRTP Failure. Determination of the need or no-need for RF signal
applied during SEE testing. Possibly diminution of the Alert perimeter by additional testing on HEMT and
HBT technologies.
Description
The most likely cause of Metop HRTP in flight failure is today considered as the sensitivity of a GaAs MESFET to SEE
radiation. This finding ended up last year as an ESA Alert ESA EA-2008-EEE-05 in which a couple of
recommendations were made with only a limited set of results and which now require more in depth investigation in
order to better advise european space end users and possibly relax the alert by limiting its perimeter to a couple of
devices or/and processes rather than advising to consider all GaAs technologies for testing has it had to be done a
couple of months ago, The study will therfore aim at selecting a set of preferred european GaAs MMIC technologies
for SEE testing with and without RF testing under various DC conditions. The main objective is to answer 5 major
questions daily raised today by end users: 1) do we or not need to test for SSE sensitivity with RF applied 2)Do we
need to test other technologies than the MESFET GaAs processes?. 3) How do our preferred european processes
behave wrt SEE radiation. 4) Can we relax the ESA Alert by limiting it to a couple of devices or/and thechnologies. 5)
Can we test SEE sensitivity in the future during ESCC process evaluation or do we need to test for each design (like
for some VLSI technologies and products) and therfore do radiation testing on a product to product basis?
Deliverables:
Final Report and technical recommendations for SEE testing of GaAs MMIC devices as well as possible relaxation of
the Alert issued in 2008.
Current TRL:
N/A
Target TRL:
N/A
Application
Need/Date:
All without exception, all programs
used and will continue using GaAs
Application/Mission: technologies for a minimum of 5
Contract Duration:
years before GaN start to take
slowly over.
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Immediate
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TRP Work Plan 2008-2010
Description of Activities
SW Clause :
N/A
Consistency with Harmonisation
Roadmap and Conclusions:
Dossier0 Ref.: All programs without any exception need radiation data and
relaxation of the ESA Alert EA-2008-EEE-05 to facilitate project
PADs approval
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