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GSTP-6 Element 1 Compendium of Potential Activities –
Domains: Earth Observation, Space Transportation,
Navigation, Generic Technologies and Techniques and Space
Situational Awareness
Prepared by
Reference
Issue
Revision
Date of Issue
Status
Document Type
Distribution
TEC-TI
TEC-T/2016-03/NP
1
2
5-02-2016
ESA UNCLASSIFIED – For Official Use
Title GSTP-6 Element 1 Compendium of Potential Activities
Issue 1
Revision 2
Author
Date 5-02-2016
Approved by
Date
Reason for change
Issue
Revision
Date
Issue 1
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Date 5-02-2016 Issue 1 Rev 2
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Table of contents:
1 INTRODUCTION ................................................................................................................................ 5
2 LIST OF ACTIVITIES ......................................................................................................................... 7
3 DESCRIPTION OF ACTIVITIES ........................................................................................................ 22
3.1 Earth Observation ............................................................................................................................................................22
3.1.1 TD 6- RF Payload and Systems .....................................................................................................................................22
3.1.2 TD 7- Electromagnetic Technologies and Techniques ................................................................................................. 27
3.1.3 TD 9- Mission Operations and Ground Data Systems ................................................................................................ 30
3.1.4 TD 12- Ground Station System & Networking.............................................................................................................. 31
3.1.5 TD 16- Optics .................................................................................................................................................................33
3.1.6 TD 24 – Materials and Processes .................................................................................................................................. 35
3.1.7 TD 26- Others ................................................................................................................................................................36
3.2 Space Transportation ...................................................................................................................................................... 38
3.2.1 TD 7- Electromagnetic Technologies and Techniques ................................................................................................ 38
3.2.2 TD 18- Aerothermodynamics ........................................................................................................................................39
3.2.3 TD 19- Propulsion ......................................................................................................................................................... 40
3.3 Navigation ........................................................................................................................................................................ 41
3.3.1 TD 6- RF Payload and Systems ..................................................................................................................................... 41
3.3.2 TD 7- Electromagnetic Technologies and Techniques ................................................................................................. 59
3.4 Generic Technologies and Techniques ............................................................................................................................ 61
3.4.1 Core ................................................................................................................................................................................ 61
3.4.1.1 TD 1- On-board Data Systems .................................................................................................................................... 61
3.4.1.2 TD 2- Space System Software..................................................................................................................................... 67
3.4.1.3 TD 3- Spacecraft Electrical Power.............................................................................................................................. 75
3.4.1.4 TD 4- Spacecraft Environment & Effects .................................................................................................................. 83
3.4.1.5 TD 5- Space System Control ...................................................................................................................................... 85
3.4.1.6 TD 6- RF Payload and Systems ..................................................................................................................................87
3.4.1.7 TD 7- Electromagnetic Technologies and Techniques ..............................................................................................95
3.4.1.8 TD 8- System Design & Verification ......................................................................................................................... 99
3.4.1.9 TD 9- Mission Operations and Ground Data Systems ............................................................................................ 105
3.4.1.10 TD 10- Flight Dynamics and GNSS .......................................................................................................................... 110
3.4.1.11 TD 11- Space Debris .................................................................................................................................................. 112
3.4.1.12 TD 12- Ground Station System & Networking......................................................................................................... 118
3.4.1.13 TD 13- Automation, Telepresence & Robotics ......................................................................................................... 120
3.4.1.14 TD 14- Life & Physical Sciences ............................................................................................................................... 121
3.4.1.15 TD 15- Mechanisms & Tribology .............................................................................................................................. 122
3.4.1.16 D 16- Optics ............................................................................................................................................................... 123
3.4.1.17 TD 17- Optoelectronics ............................................................................................................................................. 127
3.4.1.18 TD 19- Propulsion ..................................................................................................................................................... 128
3.4.1.19 TD 20- Structures & Pyrotechnics ........................................................................................................................... 129
3.4.1.20 TD 21- Thermal ......................................................................................................................................................... 136
3.4.1.21 TD 23- EEE Components and quality ...................................................................................................................... 138
3.4.1.22 TD 24- Material and Processes ................................................................................................................................ 144
3.4.2 Specific area: Clean Space ........................................................................................................................................... 146
3.4.2.1 TD 5- Space System Control ..................................................................................................................................... 146
3.4.2.2 TD 13- Automation, Telepresence & Robotics ......................................................................................................... 152
3.4.2.3 TD 18- Aerothermodynamics ................................................................................................................................... 154
3.4.2.4 TD 20- Structures & Pyrotechnics ........................................................................................................................... 155
3.4.2.5 TD 24- Materials and Processes ............................................................................................................................... 158
3.4.2.6 TD 26- Others ........................................................................................................................................................... 162
3.4.3 Specific area: SAVOIR ................................................................................................................................................. 164
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3.4.3.1 TD 1- On-board Data Systems .................................................................................................................................. 164
3.4.3.2 TD 2- Space System Software................................................................................................................................... 165
3.4.4 Specific area: Space & Energy ..................................................................................................................................... 167
3.4.4.1 TD 3- Spacecraft Electrical Power............................................................................................................................ 167
3.4.4.2 TD 4- Spacecraft Environment and Effects ............................................................................................................. 168
3.4.4.3 TD 21- Thermal ......................................................................................................................................................... 169
3.4.4.4 TD 22- Environmental Control Life Support (ECLS) and InSitu Resource Utilisation (ISRU) ................. 177
3.5 Space Situational Awareness ......................................................................................................................................... 179
3.5.1 TD 4- Spacecraft Environment & Effects.................................................................................................................... 179
3.5.2 TD 7- Electromagnetic Technologies and Techniques ............................................................................................... 192
3.5.3 TD 12- Ground Station System & Networking............................................................................................................ 195
3.5.4 TD 16- Optics .............................................................................................................................................................. 200
3.5.5 TD 26- Others ............................................................................................................................................................. 202
4 ANNEX I - ACTIVITIES IN GSTP-6 E1 WORK PLAN / PROCUREMENT PLAN ............................... 205
5 ANNEX II - ACTIVITIES CANCELLED FROM THE INITIAL COMPENDIUM .................................. 217
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1
INTRODUCTION
During the Council meeting at Ministerial level held in November 2012, the sixth
Period of the GSTP was presented (ESA/C(2012)199) and extensively subscribed by
the GSTP Participating States with the following framework:
GSTP-6 Element 1 - Support Technology Activities for Projects and Industry
GSTP-6 Element 2 - Competitiveness
GSTP-6 Element 3 - Technology Flight Opportunities
GSTP-6 Element 4 - Precise Formation Flying Demonstration
The GSTP6 E1 Compendium is a list of candidate activities to the GSTP6 E1 Work
Plan, pre-selected following the ESA End to End process, including programmatic
screening and consistency checking with technology strategy and THAG Roadmaps,
as indicated in ESA-wide process described in ESA/IPC(2008)61 rev 1. The aim of
the GSTP6 E1 Compendium is to provide to industry and Delegations a consolidated
overview by Domain and Technology Domain of the priorities for ESA in the
development of technology within the GSTP Programme.
This document is a revision of the GSTP-6 Element 1 Compendium of Potential
Activities presented in 2013. In particular, of the following two documents:


GSTP-6 Element 1 – Compendium of Generic Technology Activities issued in
February 2013.
GSTP-6 Element 1 – Compendium of Potential Application- Domains: Earth
Observation, Human Spaceflight, Space Transportation, Navigation, Generic
Technologies and Techniques, Space Situation Awareness and Robotic
Exploration issued in December 2013.
The activities presented in these two documents have been reviewed and the
descriptions/budgets have been updated accordingly.
This revision of the GSTP-6 E1 Compendium provides a list and descriptions of
candidate activities to the Work Plan of the GSTP-6 Element 1 (Chapter 2 and 3 of
this document). The pre-selection of the activities corresponds to activities belonging
to the following specific domains.





Earth Observation
Space Transportation
Navigation
Generic Technologies and Techniques
Space Situation Awareness
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The activities that belong to the domains Human Spaceflight and Robotic
Exploration are under revision and they will be provided in a further revision of the
Compendium.
The activities from the initial Compendia published in 2013 that are already part of
the GSTP-6 E1 Work Plan/Procurement Plan are not included in this revision of the
GSTP E1 Compendium. However, for traceability these activities are listed in Annex I
of this document. Descriptions of these activities are presented in the document:
Complete list of GSTP-6 E1 WP/PP activities ref. ESA/IPC(2015)139.
The activities from the initial Compendia that have been considered obsolete are
withdrawn in this revision of the GSTP Compendium. For traceability these activities
are listed in the Annex II of this Compendium. The description for these activities is
not provided in this document.
In addition to the core activities in the domain Generic Technologies and Techniques
which are dedicated to the development of technologies, building blocks and
components for future space, three special areas have been identified whose activities
are shown in these documents in separate sections:

CLEAN SPACE: This is an ESA cross-cutting initiative with the aim to
contribute to the reduction of the environmental impact of space programmes,
taking into account the overall life-cycle and the management of residual
waste and pollution resulting from space activities. The list and descriptions of
candidate activities for this special area is provided in a separate document.

SAVOIR: Space Avionics Open Interface aRchitecture. This is an initiative to
federate the space avionics community and to work together in order to
improve the way that the European Space community builds avionics
subsystems.

SPACE & ENERGY: This special area addresses open innovation, spin-in /out
and joint R&T as currently initiated under GSTP 5 with the overall goal of
achieving a more sustainable, less-carbon intensive European energy sector.
This compendium is issued to Delegations of GSTP-6 Participating States and their
industries for comments. Such comments will be considered in the following updates
of the work plan for this GSTP 6 Element 1.
The objective is to have a good indication of the developments the Participants
intend to support in order to present updates of the GSTP-6 E1 Work Plan with
consolidated set of activities to the IPC for approval.
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LIST OF ACTIVITIES
2
EARTH OBSERVATION
TD 6- RF Payload and Systems
GSTP-6
Reference
G611-006ET
G611-007ET
G611-050ET
G611-051ET
Title
Budget(K€)
Pulsed HPA for Ka-band SAR instruments
Miniature filter for L-band radiometer
HBV components for space - step 2
Dual-polarization receiver prototype
900
500
650
1,200
Total
3,250
TD 7- Electromagnetic Technologies and Techniques
GSTP-6
Reference
G611-009EE
G611-010EE
G611-011EE
Title
Budget(K€)
Advanced End-to-End Testing of Active Transponders
Multi-Frequency/Multi-Pixel Integrated Lens Antenna for Microwave
Radiometers
Compact Multi-band Feeds for Radiometer Instruments
Total
350
400
400
1,150
TD 9- Mission Operations and Ground Data Systems
GSTP-6
Reference
G611-052GI
Title
Budget(K€)
Approach for Migrating the EO Kernel for MCS to EGS-CC
200
Total
200
TD 12- Electromagnetic Technologies and Techniques
GSTP-6
Reference
G611-053GS
G611-054GS
Title
Budget(K€)
Tri-band (S/X/K) feed system design for future EO missions
Tri-band (S/X/K) antenna design and manufacturing of critical RF
components for future EO missions
500
700
Total
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1,200
ESA UNCLASSIFIED – For Official Use
TD 16- Optics
GSTP-6
Reference
G611-016MM
Title
Budget(K€)
Large non-flat monolithic mirrors with ultra-lightweight honeycomb
structure
1,000
Total
1,000
TD 24- Materials and Processes
GSTP-6
Reference
G611-055QT
Title
Budget(K€)
Handheld contact less surface cleaner for removal of molecular
contamination
500
Total
500
TD 26- Others
GSTP-6
Reference
G611-024EO
G611-026EO
Title
Budget(K€)
Technologies for the Management of LOng EO Data Time SEries - LOOSE
ESE ERGOnomic User Interface ESE_ERGO
Total
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2,000
800
2,800
ESA UNCLASSIFIED – For Official Use
SPACE TRANSPORTATION
TD 7- Electromagnetic Technologies and Techniques
GSTP-6
Reference
G614-020EE
Title
Budget(K€)
Development and flight on-board launcher of electrostatic experiments
Total
1,000
1,000
TD 18- Aerothermodynamics
GSTP-6
Reference
G614-005MP
Title
Budget(K€)
Liquid film cooling in MMH-NTO rocket engines
500
Total
500
TD 19- Propulsion
GSTP-6
Reference
G614-006MP
Title
Budget(K€)
10 kW Hall Effect Thruster
2,000
Total
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2,000
ESA UNCLASSIFIED – For Official Use
NAVIGATION
TD 6- RF Payload and Systems
GSTP-6
Reference
G616-001ET
G616-002ET
G616-003ET
G616-004ET
G616-005ET
G616-009ET
G616-011ET
G616-012ET
G616-013ET
G616-014ET
G616-015ET
G616-016ET
Title
Budget(K€)
Beam-Forming Technology for GNSS Reference-Station
Flexible and reconfigurable GNSS signal testbed
Digital Beam-forming Based Advanced Navigation Receivers
Prototype Terminal
Advanced hybrid navigation user platform
Advanced receiver architecture platform
Payload simulation tool for complex GNSS RF front-end
architectures
Study and design of a GNSS Living Lab testbed into a Smart City
Railway GNSS receiver chain technology enabler
Methodology to support characterisation of GNSS performance in
railway environments
Interference Suppression Unit (Pre-Receiver)
Clock Ensemble Monitoring and Switching Unit for Robust
Timescale Generation
Technology Validation of a Cold Atom Microwave Atomic Clock
(CAMAC)
Total
1,800
1,000
1,000
1,000
800
450
200
1,000
1,000
500
500
1,000
10,250
TD 7- Electromagnetic Technologies and Techniques
GSTP-6
Reference
G616-010EE
Title
Budget(K€)
Environment survey and calibration instrumentation for GNSS
propagation error sources, including direction of arrival
Total
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1,000
1,000
ESA UNCLASSIFIED – For Official Use
GENERIC TECHNOLOGIES AND TECHNIQUES
TD 1- On-board Data Systems
GSTP-6
Reference
G617-006ED
G617-007ED
G617-250ED
G617-251ED
Title
Budget(K€)
Micro-controller for embedded space applications: Simulator
Development
Micro-controller for embedded space applications: Software
Development Suite (part 1)
Fast Emulator for Hardware / Software codesign
Microcontroller Softcore for Space Applications
200
400
250
800
Total
1,650
TD 2- Space System Software
GSTP-6
Reference
G617-012SW
G617-013SW
G617-252SW
G617-253SW
G617-254SW
Title
Budget(K€)
On-Board Software Architecture Demonstrator
On-Board Software Reference Architecture Component Model
support
SW for Scalable Sensor Data Processor ASIC - Qualification for
flight
Qualification activity for COTS IMA Kernel
Qualification of RTEMS Symmetric multiprocessing (SMP)
Total
800
1,100
600
420
700
3,620
TD 3- Spacecraft Electrical Power
GSTP-6
Reference
G617-016EP
G617-018EP
G617-019EP
G617-020EP
G617-257EP
G617-258EP
G617-259EP
G617-260EP
Title
Enhancement of COTS supercapacitors for space and
characterisation
Development of a new glass forming process
Yield increase and cost reduction for the 6'' wafer production
Improved Ge wafer technology for multi-junction solar cells III
Design freeze and qualification of next generation solar cell
Development of toughened solar cell coverglass
Qualification of solar cells and solar cell assemblies from 6" wafers
with and w/o integral diode (140µm)
Pre-development of an hybrid Supercapacitor / Li ion battery
system for high power demanding applications
Total
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Budget(K€)
300
150
500
1,000
1,200
400
1,000
900
5,450
ESA UNCLASSIFIED – For Official Use
TD 4- Spacecraft Environment & Effects
GSTP-6
Reference
G617-022EE
G617-261EE
Title
Budget(K€)
Highly Miniaturised Radiation Monitor Phase C-D and single-chip
(LETmeter) version
Advanced Environment Monitoring Package
Total
1,500
1,000
2,500
TD 5- Space System Control
GSTP-6
Reference
G617-032EC
G617-033EC
Title
Budget(K€)
2nd Generation APS Star Tracker
Advanced Reaction Wheel
2,500
1,750
Total
4,250
TD 6- RF Payload and Systems
GSTP-6
Reference
G617-039ET
G617-041ET
G617-042ET
G617-043ET
G617-262ET
G617-263ET
G617-264ET
Title
Budget(K€)
Assessment of cost-effective technologies for on-board RF
equipment
A small foot print lightweight GaN SSPA for TWT replacement in
satellite payloads
Critical materials for Traveling Wave Tubes
Analogue/Digital on-board Receiver EM Development for TT&C
applications
Robust miniaturised timing sources
Direct LO Generation above 100 GHz
Broadband Satellite Channel Emulator for Earth Observation and
Telecommunication Links
Total
1,000
1,000
1,200
1,000
1,000
500
1,000
6,700
TD 7- Electromagnetic Technologies and Techniques
GSTP-6
Reference
G617-048EE
G617-049EE
G617-050EE
G617-053EE
Title
Budget(K€)
Testing of passive inter-modulation (PIM) products using antenna
Near-Field testing approaches
Flat petals compact unfurlable antenna for small satellites
THz Testing Facility Development
Qualification of novel grounding for composite structural panels
Total
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450
600
500
1,000
2,550
ESA UNCLASSIFIED – For Official Use
TD 8- System Design & Verification
GSTP-6
Reference
G617-055SW
G617-056SW
G617-057SW
G617-058SW
G617-059SW
G617-060SW
Title
Budget(K€)
Adaptation and Demonstration of MBSE for a real project (Pilot)
A Generic Mapping Toolbox for Space CAE Data
Exchange of Engineering Data Between System and Sub-System
Levels
Tool support for space system data modelling with the FAMOUS
methodology
Improvement of integration and verification activities
Rationalisation and qualification of simulator tools
Total
1,000
400
450
1,500
600
800
4,750
TD 9- Mission Operations and Ground Data Systems
GSTP-6
Reference
G617-061GI
G617-063GI
G617-064GI
G617-265GI
Title
Budget(K€)
Integration of ESA Ground Data Systems into Cloud Based
Platforms (PaaS and SaaS solutions)
Demonstrator of next generation M&C protocol for space systems
Harmonisation of Numerical Software Validation Facility (NSVF)
and Operational Simulator models
Harmonisation of the EO and Science Kernels for MCS
Total
200
300
200
250
950
TD 10- Flight Dynamics and GNSS
GSTP-6
Reference
G617-067GF
Title
Budget(K€)
Extension of the DO-IT trajectory design software for
interplanetary trajectories based on low-thrust propulsion
combined with flybys
200
Total
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200
ESA UNCLASSIFIED – For Official Use
TD 11- Space Debris
GSTP-6
Reference
G617-069GR
G617-070GR
G617-071GR
G617-072GR
G617-073GR
Title
Budget(K€)
Extension of combined observation-modelling technologies for
ground-based attitude vector determination
Feasibility of CMOS on-chip processing algorithms for space debris
observations
Low thrust manoeuvres in orbit determination tools
Advanced re-entry break-up high- and low-fidelity assessment
software
Extended stare and chase concepts
500
300
Total
1,550
300
150
300
TD 12- Ground Station System & Networking
GSTP-6
Reference
G617-135GS
G617-266GS
Title
Budget(K€)
Low Cost Meter-Class Adaptive Optics Communications
Breadboard
Deep Space Low Cost 4m monolithic Optical Antenna for
Day/Night Operations
1,000
400
Total
1,400
TD 13- Automation, Telepresence & Robotics
GSTP-6
Reference
G617-076MM
Title
Budget(K€)
Development of technology tools for training and operations of the
METERON Mission Preparation and Training Centre
Total
770
770
TD 14- Life & Physical Sciences
GSTP-6
Reference
G617-078MM
Title
Budget(K€)
Self-Validating High Temperature Sensors
700
Total
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700
ESA UNCLASSIFIED – For Official Use
TD 15- Mechanisms & Tribology
GSTP-6
Reference
G617-080MS
Title
Budget(K€)
Improvement of Solar Array Deployment Mechanisms (SADM)
technologies
Total
1,250
1,250
TD 16- Optics
GSTP-6
Reference
G617-084MM
G617-086MM
G617-091MM
Title
Budget(K€)
Demonstrator for active WFE-correction of an imaging telescope
Calomel-Based TIR Hyperspectral Imager
Optical components based on high-efficiency Volume Bragg
Gratings
Total
1,000
950
300
2,250
TD 17- Optoelectronics
GSTP-6
Reference
G617-095MM
Title
Budget(K€)
Development of a low-noise current source for ultra-stable CW
laser-diode applications
Total
450
450
TD 19- Propulsion
GSTP-6
Reference
G617-098MP
Title
Budget(K€)
High Power (5 kW) HEMPT (Highly Efficiency Multistage Plasma
Thruster)
Total
1,000
1,000
TD 20- Structures & Pyrotechnics
GSTP-6
Reference
G617-102MS
G617-103MS
G617-108MS
G617-109MS
Title
Budget(K€)
Improvement of industrial approach for design and verification of
non-linear spacecraft structures
Advanced CFRP assemblies for spacecraft bus and payload module
platforms
Improved design and verification of cryocoolers subjected to very
high number of fatigue load cycles ('gigacycles')
Reshaping of Antenna and Telescope Reflectors
Total
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500
600
500
700
2,300
ESA UNCLASSIFIED – For Official Use
TD 21- Thermal
GSTP-6
Reference
G617-113MT
Extended in-flight validation of LHP modelling methods
150
G617-114MT
Heat Pump Conceptual Design and Breadboard testing
600
Title
Budget(K€)
Total
750
TD 23- EEE Components and quality
GSTP-6
Reference
G617-116QT
G617-118QT
G617-119QT
Title
Budget(K€)
Prototyping and characterization of 600V SiC MOSFET
Evaluation of high density optical links for high speed transmission
Radiation testing of non-volatile memories for space applications
700
300
300
Total
1,300
TD 24- Materials and Processes
GSTP-6
Reference
G617-128QT
G617-129QT
Title
Budget(K€)
Evaluation of low temperature processing capabilities of novel thin
and flexible ceramic coatings
Development of Improved Bonding and Repairs for OSRs
Total
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500
600
1,100
ESA UNCLASSIFIED – For Official Use
Specific area: Clean Space
TD 5- Space System Control
GSTP-6
Reference
G61C-027EC
G61C-040EC
G61C-041EC
Title
Budget(k€)
Breadboard of a Multi-Spectral Camera for Relative Navigation
GNC design and performance validation for active debris removal
with RIGID capture
GNC design and performance validation for active debris removal
with FLEXIBLE capture
Total
800
300
300
1,400
TD 13- Automation, Telepresence & Robotics
GSTP-6
Reference
G61C-042MM
Title
Budget(k€)
Capture of space debris with throw nets: Engineering Qualification
Model development and sounding rocket testing
Total
3,000
3,000
TD 18- Aerothermodynamics
GSTP-6
Reference
G61C-003MP
Title
Budget(k€)
Hot gas plume characterisation in vacuum
500
Total
500
TD 20- Structures & Pyrotechnics
GSTP-6
Reference
G61C-012MS
Bio-composite structure in space applications
G61C-043MS
Prototype and qualification of a De-orbiting subsystem
Title
Budget(k€)
500
3,000
Total
3,500
TD 24- Materials and Processes
GSTP-6
Reference
G61C-035QT
G61C-044QT
Title
Budget(k€)
Development of a complete Cr-VI anticorrosion system and process
scale-up at industrial level
Alternatives to processes affected by REACH for the manufacture of
PCBs
Total
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500
500
1,000
ESA UNCLASSIFIED – For Official Use
TD 26- Others
GSTP-6
Reference
G61C-045SW
Title
Budget(k€)
REIM - Resource Efficiency through Improved Methods for
treatment of recycling products
350
Total
350
Specific area: SAVOIR
TD 1- On-board Data Systems
GSTP-6
Reference
G61V-003ED
Title
Budget(K€)
AES/SAVOIR: Consolidation of Specification of Modular RTU
Modules (electrical, mechanical and thermal interfaces)
Total
200
200
TD 2- Space System Software
GSTP-6
Reference
G61V-004SW
Title
Budget(K€)
AES/SAVOIR: IMA-SP Execution Platform Consolidation and
Industrialisation
Total
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1,000
1,000
ESA UNCLASSIFIED – For Official Use
Specific area: Space & Energy
TD 3- Spacecraft Electrical Power
GSTP-6
Reference
G61E-001EP
Title
Budget(K€)
Life testing of solar cells for space and terrestrial applications
500
Total
500
TD 4- Spacecraft Environment and Effects
GSTP-6
Reference
G61E-006EE
Title
Budget(K€)
Technologies for space weather services supporting drilling and
surveying activities of the European energy industrial sector
Total
300
300
TD 21- Thermal
GSTP-6
Reference
G61E-002MT
G61E-003MT
G61E-004MT
G61E-005MT
G61E-009MT
G61E-010MT
G61E-011MT
Title
Budget(K€)
Heat Storage for Terrestrial Application
Thermal Insulation for Buildings & Industrial Processes
Loop Heat Pipes for Heat Recovery & Solar Power Conversion
Heat Pipes for Batteries & Fuel Cells
Cryogenic Composite Tanks - Light-Weight Long-Term Hydrogen
Storage
Slush hydrogen - up-scaling and optimising production
Slush Methane Production for Propulsion and Application to
Production of Slush Natural Gas (SLNG)
Total
400
500
200
600
400
600
300
3,000
TD 22- Environmental Control Life Support (ECLS) and In-Situ Resource
Utilisation (ISRU)
GSTP-6
Reference
G61E-007MM
G61E-008MM
Title
Budget(K€)
BIOFUEL advanced breadboard
EnRUM (energetic resources utilisation map) demonstrator
500
400
Total
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900
ESA UNCLASSIFIED – For Official Use
SPACE SITUATIONAL AWARENESS
TD 4- Spacecraft Environment and Effects
GSTP-6
Reference
G618-002EE
G618-003EE
G618-004EE
G618-006EE
G618-008EE
G618-010EE
G618-012EE
G618-020EE
G618-021EE
G618-022EE
G618-023EE
G618-024EE
Title
Budget(K€)
H-alpha Solar Telescope Network prototype for Applications
(HASTENet)
Heliospheric modelling techniques
Standardised airborne radiation detector feasibility analysis
Impact effects tools
Combined Radiation Monitor Data Analysis System
Fireball Monitor for SSA
Solar X-Ray Monitor Proto-Flight Model and Low-Resolution
Imager Design for SSA
Solar Wind Plasma Density Instrument
Solar Wind Plasma Spectrometer
Medium Energy particle Spectrometer 30 - 1000 keV - Phase A/B
Radiation Monitoring System In Package (RMSIP)
Enhancement of Physical and Assimilation Modelling of Radiation
Belts
Total
600
1,000
300
500
500
800
1,030
300
500
600
500
300
6,930
TD 7- Electromagnetic Technologies and Techniques
GSTP-6
Reference
G618-025EE
G618-026EE
G618-027EE
Title
Budget(K€)
Advanced Ionospheric Scintillation Modelling Demonstrator
Radio Spectrograph for magnetospheric and solar radio
measurement
THz technologies for space debris detection
600
500
500
Total
1,600
TD 12- Ground Station System & Networking
GSTP-6
Reference
G618-016GS
G618-029GS
G618-030GS
Title
Budget(K€)
L-Band SSPA for phased array radar transmitter and dual
polarization receiver
Flexible CCD for curved focal planes - detailed design and breadboarding
S-Band SSPA for phased array radar transmitter and dual
polarization receiver
Total
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1,000
800
1,000
2,800
ESA UNCLASSIFIED – For Official Use
TD 16- Optics
GSTP-6
Reference
G618-031MM
G618-032MM
Title
Budget(K€)
Compact Magnetograph for L mission
Heliospheric Imager for L mission
1,000
750
Total
1,750
TD 26- Others
GSTP-6
Reference
G618-028SY
Title
Budget(K€)
Cubesat/nanosat mission concepts for operational SWE system
Total
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300
300
ESA UNCLASSIFIED – For Official Use
3
DESCRIPTION OF ACTIVITIES
3.1
Earth Observation
3.1.1 TD 6- RF Payload and Systems
Domain
EARTH OBSERVATION
Technology Domain
6 RF Payload and Systems
Ref. Number:
G611-006ET
Budget (k€):
900
Title:
Pulsed HPA for Ka-band SAR instruments
Objectives:
The objective of this activity is to design, manufacture and test a breadboard of a
pulsed HPA (High Power Amplifier) meeting the specification for use in the Kaband SAR instruments (3.5 kW, 14% duty cycle, 500MHz BW).
Description:
Synthetic Aperture Radar (SAR) instruments have become essential for Earth
Observation purposes since the first instrument in space back in 1978. The
operational frequency has evolved from L- to S- and X-band. New frequency bands
have been studied in Europe such as P-band for BIOMASS and Ku-band for
CoReH2O. Ka-band has been used for Unmanned Aerial Vehicles (UAV) but has
not been utilized for SAR from space so far, although the suitability of Ka-band
SAR imaging has been proven in various airborne demonstrators and instruments.
An ESA internal study on the feasibility of a Ka-band SAR instrument and
interferometer has pointed to the need of a Ka-band HPA with capabilities beyond
what is currently available on the market. The activity will be divided in two
phases.
Phase 1 will cover the following tasks:
- Critical review of the trade-off and results of the previous TRP activity on the
feasibility study of a pulsed HPA for Ka-band SAR;
- Identification of a baseline technology (TWTA/EIKA) and design;
- Performance prediction by analysis/simulation and tests at subassembly level.
- Consolidation and update of the preliminary specification.
Phase 2 will be dedicated to the:
- Manufacturing and testing of a HPA Breadboard according to the baseline
design agreed at the end of Phase 1
- A detailed programmatic description of the necessary development steps
needed up to Flight Model, together with a realistic estimation of the duration
and cost of each development phase.
Deliverables:
Breadboard
Current TRL:
3
Target
Application /
Timeframe :
Ka-band SAR instruments, 2018
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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Domain
EARTH OBSERVATION
Technology Domain
6 RF Payload and Systems
Ref. Number:
G611-007ET
Budget (k€): 500
Title:
Miniature filter for L-band radiometer
Objectives:
The objective is to develop miniaturised high performance filter for L-band
synthetic aperture radiometer applications.
Description:
Synthetic aperture radiometer instruments like MIRAS (SMOS) require several
similar receivers to be accommodated. In this kind of instrument, the number of
elementary receivers correlates with the system performance. Therefore, in order
to improve the performance of similar instruments in the future, the
miniaturisation and mass saving of the receiver is crucial in order to allow for a
larger number of receivers to be accommodated.
One key block in the receiver is the high performance RF filter that has to provide
very efficient out-of-band interference protection and on the other hand its
transfer function has to be reproducible and uniform from unit to unit. Currently,
coaxial resonator filters are employed for this function which, however, are big and
bulky and they are not any more in line with the miniaturisation objectives of the
other parts of the receiver. However, there are potential technologies that can
provide the required degree of miniaturisation while maintaining the performance
(SAW, BAW, dielectric). It is presumed that the RF filter could be located after the
low-noise amplifier and the insertion loss is not necessarily a key design
parameter. This could open ways for the application of novel efficient design
approaches such as pre-distortion and lossy filter theory.
This activity aims first at revisiting the L-band elementary receiver requirements
for SMOS follower like missions and then flowing down from there the filter
requirements. Secondly, taking into account also the qualification aspects, the best
technologies and architectures for the miniaturised filter shall be breadboarded.
Based on the breadboarding results, the best concept shall be selected for an EM
development. Finally, the EM shall be designed, manufactured and tested.
Deliverables:
Engineering Model
Current TRL:
3
Target
Application /
Timeframe :
SMOS/MIRAS type future instruments: SMOS-Ops, Super MIRAS
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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Domain
EARTH OBSERVATION
Technology Domain
6 RF Payload and Systems
Ref. Number:
G611-050ET
Budget (k€): 650
Title:
HBV components for space - step 2
Objectives:
The objective is to establish a reproducible Hetero-Barrier Varactor (HBV)
process and then to evaluate the reliability of HBV in frequency multiplier
applications at mm-wave frequencies. This is a second step in the HBV
development towards commercialisation.
Description:
There is a strong demand for compact, room temperature sources at millimetre
waves and THz frequencies for various applications in space as well as on ground.
At frequencies above 150 GHz, multipliers are producing state-of-the-art power
levels. Even though the mainstream of the multipliers is based on more mature
Schottky technology, HBV based multipliers have a number of advantages. They
only generate odd harmonics and can operate bias free, which simplifies circuit
complexity. The HBV can easily be scaled by increasing the number of barriers to
manage higher power. At the time when W-band amplifiers will produce watts of
output power, the HBV tripler (x3) to 300 GHz is considered as a commercially
viable product. However, the HBV technology has to be brought to maturity in
terms of reproducibility and reliability in order to be accepted as a serious
competitor in this market.
This activity aims at an establishment of a reproducible HBV process and at a
reliability assessment by thermal cycling test and by life time tests under real RF
conditions.
The work starts with the performance assessment of the current HBVs and HBV
multipliers. Next, the process parameters, including passivation aspects, shall be
reviewed and improvements proposed. Then, two or more batches of engineering
samples will be manufactured and tested for model validation, performance
validation and reproducibility.
Provided the performance is acceptable, a lot of HBVs will be subjected to
reliability evaluation that comprises thermal cycling, and RF life test in waveguide
blocks. The number of required test samples is estimated in the range from 20-40.
Deliverables:
HBV devices, test blocks, report
Current TRL:
4
Target
Application /
Timeframe :
Sub-mm wave radiometers LO sources, test instrumentation, TRL5 by 2018
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
24
Technologies for Passive Millimetre & Submillimetre Wave
Instruments (2010)
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Domain
EARTH OBSERVATION
Technology Domain
6 RF Payload and Systems
Ref. Number:
G611-051ET
Budget (k€):
1,200
Title:
Dual-polarization receiver prototype
Objectives:
In order to meet the growing demand for higher data rates for Earth Observation
missions, dual-polarization transmissions have the potential of fully exploiting the
use of the 26 GHz band by virtually doubling the data rate. The goal of this activity
is to implement a prototype receiver for dual-polarization telemetry transmissions
by means of previously designed algorithms, able to handle cross-talk interference
between the 2 received streams, even with high order modulations.
Description:
Taking advantage of the results of a recently concluded TRP activity (HDRL),
where the detection of dual-polarization telemetry transmissions has been studied
at algorithmic level, the current activity should design, prototype and test a
receiver implementing the overall front-end functionalities for the demodulation
of dual-polarization data streams based on the CCSDS 131.2-B (SCCC) standard
and able to handle up to 500 MBauds for each stream. While the main application
will be for 26 GHz band systems, the prototype will have IF inputs, allowing
adaptation to different bands.
The design shall include the algorithms required for the demodulator front-end,
once dual-polarization is assumed. In particular, special care will be needed for
phase tracking and symbol time recovery, as well as channel estimation, in order
to enable the potential benefits of the receiver. The core elements of the detector
will be based on MMSE equalization, enabling the use of dual-polarization with
high order modulations, up to 64-APSK, with limited losses.
After proposing a baseline architecture, a detailed complexity estimate will be
performed, in order to select the proper platform. A detailed design will follow,
supported by a (bit-true) simulation activity, in order to maintain the
performance losses (compared to the reference provided by the TRP study)
following the evolution of the design.
Finally, the prototype will be implemented on the selected platform, to be
properly verified against the specifications and validated in a number of
significant cases: different ModCods (from CCSDS 131.2-B), different XPD
(determined by antennas characteristics and atmospheric conditions). A proper
test bench will be needed for this purpose, including representative units for the
main elements of the end-to-end system. For the purpose of emulating the
receiver back-end, i.e. decoders for the 2 data streams, software simulations may
be used (non-real time post processing). In case a similar solution, i.e. software
emulation, is chosen for the transmitter(s) as well, blocks for actual up-conversion
to IF of the software generated data will be included in the test bench.
The test bench will be used for the testing of the prototype under different
conditions, i.e. XPD values and ModCod, in order to validate its performance
against the reference results provided in the TRP precursor.
Following an initial analysis, a preliminary architecture design will be proposed,
to show how the front-end detector could fit into the overall architecture of a
receiver for Earth Observation missions: to this end, the partitioning of
functionalities, i.e. demodulation and decoding, will be analysed, including tradeoffs of the overall complexity (i.e. number of FPGAs/boards/units) versus the
required performance (i.e. FER/supported data rate/operational capability).
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Deliverables:
Prototype
Current TRL:
3
Target
Application /
Timeframe :
Earth Observation missions,2020
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
18
TT&C Transponders and Payload Data Transmitters (2012)
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3.1.2TD 7- Electromagnetic Technologies and Techniques
Domain
EARTH OBSERVATION
Technology Domain
7 Electromagnetic Technologies and Techniques
Ref. Number:
G611-009EE
Budget (k€): 350
Title:
Advanced End-to-End Testing of Active Transponders
Objectives:
To develop advanced high accuracy methodologies of radiated end-to-end testing of
ground based active transponders for Earth Observation missions.
Description:
Active ground based transponders are used for calibration of SAR instruments or
radar altimeters, typically within C and Ku bands. The techniques used nowadays
for the calibration of the transponder itself are still performed with theoretical
values of known RCS (radar cross section) targets for SAR response. In addition,
the phase delay of the target (including the contribution of the radiating apertures)
is driving stringent requirements on the accuracy of the free-space delay
measurement, in particular at Ku Band, not possible to reach with typically used
methods, which rely on the measurement of a known target to calibrate the radiated
performance.
This activity shall yield advanced high accuracy end-to-end testing techniques, that
includes the overall radiated delay, identifying needs for future missions, trade-off
and Breadboard of critical components necessary to perform the measurements.
The techniques developed shall be demonstrated with a representative test object.
Deliverables:
Current TRL:
Target
Application /
Timeframe :
Report; Breadboard of critical components
3
Target TRL:
5
Duration
(months)
Earth Observation instruments /2017
Applicable THAG Roadmap:
Not related to a Harmonisation Subject
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Domain
EARTH OBSERVATION
Technology Domain
7 Electromagnetic Technologies and Techniques
Ref. Number:
G611-010EE
Budget (k€): 400
Title:
Multi-Frequency/Multi-Pixel Integrated Lens Antenna for Microwave
Radiometers
Objectives:
The objective is to demonstrate that multi-frequency and or multi-pixel integrated
lens antennas can result in more performing radiometers in the microwave and
millimetre-wave regime. Expected improvements are in sensitivity (25% due to
increase number of detectors) and focal plane size reduction (25-30%).
Description:
Integrated lens antennas offer an attractive alternative solution as compared to
feed horns and could replace them in novel microwave radiometers and allow to
design integrated receivers. Recently advancement in lens arrays design and
manufacturing and accurate lens antenna modeling could be of benefit to get
improved performances.
Another interesting recent development in the field of flat lenses could also be
used to ease the manufacturing of large focal plane arrays. Therefore, this activity
should investigate the novel architectures that combine multi-frequency detectors
with focusing elements like lenses and how these elements could be of benefit for
multi-frequency radiometers systems.
The activity shall start with an investigation of novel architectures for use in
radiometer systems using the multi-frequency and multi-pixel integrated
antennas and novel flat lenses. A trade-off shall be performed to assess the
improvement that be gained in terms of instrument sensitivity and mass and
volume of the focal plane arrays. Next the most promising architecture shall be
subjected to detailed design and analyses and be followed by the breadboarding
and testing of the most critical components. The activity shall be concluded by
updating the instrument performance taking into account the test results.
Deliverables:
Current TRL:
Target
Application /
Timeframe :
Breadboard
3
Target TRL:
4
Duration
(months)
18
Next generation Metop-SG radiometer instruments-2017
Applicable THAG Roadmap:
Technologies for Passive Millimetre & Submillimetre Wave
Instruments (2010). Activity B56.
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Domain
EARTH OBSERVATION
Technology Domain
7 Electromagnetic Technologies and Techniques
Ref. Number:
G611-011EE
Budget (k€): 400
Title:
Compact Multi-band Feeds for Radiometer Instruments
Objectives:
To develop a compact multi-frequency and dual-polarisation feed horn for future
microwave radiometer instruments.
Description:
Earth Observation radiometers often use multi-frequency feeds to comply to the
colocation requirement of certain beams on ground. Besides the colocation
requirement there is sometimes also the requirement to have the dual linear
polarisation for certain frequency channels. Although this does not impact the
design of the feed horn itself, it has a significant impact on the design and
complexity of the feed chain excitor part.
Similar design issues can be seen in Telecommunication feed horns with receive
and transmit capability and often use dual polarisation as well. The constraint
these feed horns have is that they form part of a larger array and hence need to
have a very compact feeding chain with the lateral dimensions not larger than the
feed horn aperture. In a recent ARTES5.2 study a very compact Ka-band feed
horn was designed, manufactured and tested operating at 20 and 30 GHz.
In this activity an assessment shall be done to see what simularities exist between
the feed requirements for EO radiometers and Telecommunication array feed
horns at e.g. Ka-band. In a following step, a feed horn shall be designed, analysed,
manufactured and tested at 18/23 GHz for a future EO radiometer similar to MWI
instrument on Metop SG.
Deliverables:
Current TRL:
Target
Application /
Timeframe :
Engineering Model
3
Target TRL:
5
Duration
(months)
14
Earth Observation microwave radiometer instruments. 2017.
Applicable THAG Roadmap:
Technologies for Passive Millimetre & Submillimetre Wave
Instruments (2010)
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3.1.3TD 9- Mission Operations and Ground Data Systems
Domain
EARTH OBSERVATION
Technology Domain
9 Mission Operations and Ground Data Systems
Ref. Number:
G611-052GI
Budget (k€):
Title:
Approach for Migrating the EO Kernel for MCS to EGS-CC
Objectives:
The current strategy for the development of the Mission Control Systems of EO
missions has involved the identification, isolation and maintenance of the so
called EO Kernel. This self-standing software groups all the common needs of EO
missions which are not already included into the ESOC SW infrastructure (SCOS2000). The EO Kernel has contributed significantly to the sharp decrease in the
cost of MCS for EO missions that today are low.
There are major changes in the landscape of mission control systems on-going in
Europe. The best way to infuse the EGS-CC into Earth observation missions are
not obvious. There may be significant cost associated with the first user, but as
well significant benefits for follow up missions.
This issue is much more visible for EO missions since the ratio between generic
code versus mission specific development is much higher than for other missions.
Due to this, it is unrealistic to assume that a single mission will carry the complete
cost of migrating the common part.
Due to this, it would be beneficial to find a way to share the cost, risk and benefits
among several missions. The approach clearly need to identify the overall benefits
for each of the missions of embarking on this migration. Such an approach can
only be found via an independent activity, looking particularly into:
- The need of all future EO missions in the area of Mission Operations.
- The cost of maintaining legacy systems contra migrating to the new core.
- Identification of a minimum overall risk and cost strategy for the entire EO
program.
Description:
The activity would:
- Review existing and future EO missions to identify the requirements for
MCS systems for all EO missions. This would need to take into account as
well future operational concepts (File Based operations; Mission
Automation; MO services etc...) that will be required.
- Once a complete requirement baseline is established covering the EO needs,
the best way to achieve this system need to be identified analyzing the
existing functionality in legacy systems as well as planned functionality of
the EGS-CC system. This should as well take into account EGSE systems
based on EGS-CC systems.
- Based on this a step-by-step strategy need to be developed allowing cost/risk
to be shared between the veracious users.
Deliverables:
Study Report
Current TRL:
3
Target TRL:
5
Duration
(months)
Target
Application /
TRL 6 by 2018 to allow for a fast in-cooperation of EGS-CC in EO missions.
Timeframe :
Applicable THAG Roadmap:
Ground Systems Software (2008)
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3.1.4
TD 12- Ground Station System & Networking
Domain
EARTH OBSERVATION
Technology Domain
12 Ground Station System & Networking
Ref. Number:
G611-053GS
Title:
Tri-band (S/X/K) feed system design for future EO missions
Objectives:
So far EO missions have been operated in S-Band (TT&C) and in X-Band (payload
data). In the future TT&C services will migrate to X-Band and payload data will be
transmitted in K-Band. The objective of this activity is to design a feed that will be
able to operate in S/X/K-Band to cover running and upcoming EO missions.
Description:
The layout of the 14m X/K-Band antenna developed under a previous GSTP
activity will be used as starting point to define the feed specifications. A trade-off
among different feed configuration will be performed. After selection of the
preferred solution the feed will be designed including diplexers/filters and
tracking couplers. Mechanical drawings will be prepared and critical components
will be manufactured and tested in order to derisk the project.
Deliverables:
Breadboard
Current TRL:
3
Target
Application /
Timeframe :
TRL 6 by 2020
Applicable THAG Roadmap:
Budget (k€): 500
Target TRL:
Duration
(months)
Not related to a Harmonisation subject
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Domain
EARTH OBSERVATION
Technology Domain
12 Ground Station System & Networking
Ref. Number:
G611-054GS
Title:
Tri-band (S/X/K) antenna design and manufacturing of critical RF
components for future EO missions
Objectives:
In order to transition smoothly from present EO space communication systems
(TTC in S-band, Payload data in X-band) to future EO missions (TTC in X-band,
Payload data in K-band there is the need to develop a new antenna system able to
operate over multiple frequency bands (S/X/K-Band). New RF components need
to be designed and developed. The scope of the activity is to design/identify all the
critical components required to implement the new frequency bands in EO
antenna like: WG filters, diplexers, frequency converters and to manufacture
critical components. The corresponding feed system development is proposed as a
seperate activity.
Description:
The RF architecture of a 14m class antenna will be optimise in order to be able to
accomodate S/X/K-Band for present and future EO missions. Based on this
architecture critical components not available on the market will be identified and
designed.
Deliverables:
Breadboard
Current TRL:
3
Target
Application /
Timeframe :
TRL 6 by 2020
Applicable THAG Roadmap:
Budget (k€):
Target TRL:
Duration
(months)
Not related to a Harmonisation subject
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3.1.5 TD 16- Optics
Domain
EARTH OBSERVATION
Technology Domain
16 Optics
Ref. Number:
G611-016MM
Budget (k€): 1,000
Title:
Large non-flat monolithic
honeycomb structure
Objectives:
The first objective (Phase 1) is to optimize manufacturing and process choices for
an ultra-lightweighted honeycomb mirror (to be demonstrated with the
development and testing of a breadboard of a flat mirror). The second objective
(Phase 2) is to demonstrate the feasibility of the transfer of the ultralightweighted honeycomb structure technology to non-flat mirror surfaces
(sphere, asphere) with the development and testing of a primary mirror
demonstrator for geostationary high-resolution imaging applications.
Description:
The use of reduction technology for large mirrors located in an optical system
entrance cavity (e.g. scan mirror, primary mirror) would be an enabling key factor
in the production of large monolithic mirrors, thereby securing high-resolution
imaging capability for space systems in e.g. geostationary orbit. Currently the level
of lightweighting needed for such missions is reaching the limit of classical
techniques and decreasing optical performances due to lightweighting sideeffects. Aluminium as a structural material would most likely not be suited for
such applications due to its high coefficient of thermal expansion. An alternative
candidate material needs to be identified and incorporated in a large flat
demonstrator mirror, with the following purposes:
mirrors
with
ultra-lightweighted
- Demonstration of the successful transfer of the technology to another
structure material,
- Demonstration of the suitability of the mirror to tolerate large thermal
variation characteristics of instrument entrance cavity conditions in
geostationary orbits.
Identifying and demonstrating a concept for achieving curved figures with such a
lightweighting technology would allow significant weight reduction specifically for
large primary mirrors.
The proposed activity constitutes an important step on the way to extreme
lightweighting of mid-size (1-2 meter diameter) and large-size monolithic mirrors.
It will encompass the following activities, split into 2 phases:
Phase 1 (planar technology):
- Study leading to the selection of materials and its combinations, which are
able to ensure optical performance under geostationary environmental
conditions;
- Improvement of glass/structure cementing methods;
- Production of small-size breadboards to support technological trade-offs for
the previous 2 points;
- Production and test of a 1 meter flat demonstrator (to be tested at ambient,
thermal vacuum, vibration, radiation).
If Phase 1 is successful, the following Phase 2 will be executed.
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Phase 2 (curved technology):
- Using the results of phase 1, study leading to process and material selection
for the production of a curved surface (representative of a typical primary
mirror), able to ensure optical performance under geostationary
environmental conditions.
- Production of small-size breadboards to support technological trade-offs
regarding process and materials selection.
- Production and test of a 1-meter off-axis parabolic mirror demonstrator (to
be tested at ambient, thermal vacuum, vibration).
Deliverables:
Engineering Model
Current TRL:
4
Target
Application /
Timeframe :
2018. Geostationary high-resolution imaging applications
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
36
Technologies for Optical Passive Instruments - Mirrors (2013)
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3.1.6
TD 24 – Materials and Processes
Domain
EARTH OBSERVATION
Technology Domain
24 Materials and Processes
Ref. Number:
G611-055QT
Title:
Handheld contact less surface cleaner for removal of molecular
contamination
Objectives:
The objective of this activity is the development of a handheld surface cleaning
device that allows contact-less local cleaning of sensitive surfaces under mild
conditions, including the collection of the removed contamination for subsequent
chemical analysis.
Current cleaning methods for molecular organic contamination (MOC) are falling
following into two main categories:
1. Solvent cleaning or wiping: This process requires physical contact (dry wipe),
chemical interaction (solvent rinsing) or both (moist wiping), whereas the
latter is used in most cases because of its high cleaning efficacy. A significant
drawback occurs for cleaning of very sensitive surfaces such as reflectors,
optical windows, chemically sensitive surfaces, which may not allow direct
contact.
2. Vacuum baking: By exposing hardware to thermal vacuum, MOC can be
removed effectively as long as it sustains the required temperature over a
given time. Vacuum bakeouts for the purpose of surface cleaning only are less
common but may be necessary for non-accessible or sensitive surfaces. A
drawback for this approach is the need for a bakeout facility, time, and
hardware compatibility with the required thermal environment.
On space hardware, especially on large systems, the removal of localised MOC is
often problematic as physical contact raises the risk of surface damage, and the
access to large vacuum facilities as well as system thermal requirements can be
very restricted.
Generic system requirements for cleaning device:
- Transportable and compact enough to be used in cleanrooms and large
vacuum facilities to clean space hardware without (re)polluting nearby
surfaces.
- Contactless removal of MOC through cleaning nozzle by an inert gas
stream allowing adjustment of flow velocity and temperature.
- Re-collection of gas stream through the cleaning-nozzle, preventing crosscontamination of nearby surfaces.
- Capturing of MOC for subsequent chemical analysis.
Description:
Budget (k€): 500
In this activity the following tasks shall be done: Definition of system
requirements, especially required gas velocity and temperature versus removal
efficiency on model MOC; Preliminary design concept;Breadboard development
and cleaning process optimisation; Development of prototype; Full process
validation.
Deliverables:
Prototype
Current TRL:
3
Target
Application /
TRL 6 by 2018
Timeframe :
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Not related to a Harmonisation subject
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3.1.7
TD 26- Others
Domain
EARTH OBSERVATION
Technology Domain
26 Others
Ref. Number:
G611-024EO
Title:
Technologies for the Management of LOng EO Data Time SEries LOOSE
Objectives:
This project addresses the technology development, selection
benchmarking for the management of long time series of EO data.
Description:
The continuously increasing amount of long-term and of historic data in EO
facilities in the form of online datasets and archives makes it necessary to
address technologies for the long-term management of these data sets,
including their consolidation, preservation, and continuation across multiple
missions. The management of long EO data time series of continuing or historic
missions - with more than 20 years of data available already today - requires
technical solutions and technologies which differ considerably from the ones
exploited by existing systems. Novel technical and organizational solutions for
durable efficient handling, storage, and access of long EO data time series are
needed. To satisfy new access and data exploitation scenarios, the archiving
structures and data models will have to facilitate user-friendly bulk data
retrieval, data mining and data analytics, visualization, processing, and
accessing localized time series data stacks, as well as displaying and
downloading data layers served by standardized spatial data services. New
technologies and advanced approaches will have to be studied and proved to be
fit for the purpose before implementation into the existing ground segment
infrastructure.
In order to exploit the valuable EO data time series in the future, new archiving
and access technologies will have to be designed, developed, and implemented
today.
The new technologies addressed by this project will have to be explored and
studied in connection with long-term preservation requirements calling for data
replication and maintenance of double archive copies. Multiple data copies
structured differently, as an example, may be a way to serve specific data access
scenarios. This would require the use of alternative indexing schemas and new
overall management systems.
Deliverables:
Current TRL:
Target
Application /
Timeframe :
Budget (k€): 2,000
and
Software
Technology benchmarking and development on long time series storage, data
management, data retrieval, data mining and data analytics.
Requirements and Design Documents.
Developed prototypes software and tests.
Validation, Demonstration tests and results.
Duration
36
3
Target TRL:
5
(months)
2018. Processing and explotation of Earth Observation Data
Applicable THAG Roadmap:
Not related to a Harmonisation subject.
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Domain
EARTH OBSERVATION
Technology Domain
26 Others
Ref. Number:
G611-026EO
Budget (k€): 800
Title:
ESE ERGOnomic User Interface ESE_ERGO
Objectives:
This project addresses the technology selection, development and benchmarking
for the prototyping of next generation user interfaces for EO product and derived
information and/or data visualization analysis and access.
Description:
The wide availability of wireless and mobile communication and the maturity of
handheld devices has changed the day to day connectivity of users including
scientific ones. Applications can warn about data availability, completion of
processes, results of tests, and so on. Furthermore there are examples of Webbased applications that provide a simple and intuitive way to visualize, analyse,
and access vast amounts of Earth Observation data without having to download
the data. From the researcher's point of view, a number of interfaces could be
developed and tailored, to meet the needs of specific fields of Earth Observation
research, and same or part of the interfaces could be part of mobile applications.
These applications could as well exploit location based services empoweing the
users with multi-modal interaction.
The selected technologies shall be demonstrated on protoype user interfaces
tailored for use cases.
The issue of more efficient and high-performance computational models should
be also addressed in view of transferring applications and services to portable
devices, e.g. for deployment onto the Android Operating System of smartphones
and tablet computers.
From a technology point of view several challenges need to be addressed. First of
all the whole interaction model needs to be re-defined possibly splitting
functionality across multiple devices and exploiting location based services for the
definition of the area of interest. The possible mix of functions developed in
multiple programming and data manipulation languages like C, Java, Mathlab,
IDL etcetera, has to be addressed as there are language specific features (e.g.
compilation versus interpretation or just in time compilation) which need to be
addressed taking into account the target platform. Furthermore the evolution of
COTS and toolboxes, as well as the emerging meta-languages will have to be taken
into account.
In addition, the project shall address the analysis, definition and implementation
of state-of-the art user interfaces (mobile/tablet/touch) taking into account an
ergonomy analysis via heuristic evalution and interface usability.
Deliverables:
Software
Current TRL:
3
Target
Application /
Timeframe :
2018. Earth Observation products
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Not related to a Harmonisation subject
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3.2
Space Transportation
3.2.1 TD 7- Electromagnetic Technologies and Techniques
Domain
SPACE TRANSPORTATION
Technology Domain
18 Aerothermodynamics
Ref. Number:
Budget (k€):
G614-020EE
Title:
Development
experiments
Objectives:
Following the TRP activity who have defined an experiment to be flown on-board
A5 to measure in particular the charging current at various locations (fairing,
JAVE) due to triboelectric charging by hydro-meteors at the crossing of the cirrus,
the objective is to fly, during three launches, the experiment of interest on-board
A5.
Following those flights, there will be evidence allowing to reconsider the existent
stringent requirements regarding the surface resistance of the paint that covers
the thermal protections of the launcher. This could be applicable to A6 as well.
Description:
and
flight
on-board
launcher
of
1,000
electrostatic
- Manufacturing of the experiments in line with the design defined in the
precursor activity.
- Functional and environmental qualification of the experiments.
- Flight on-board three launchers.
- Processing of the telemetry data.
- Conclusion about the requirements for the surface resistance of the paint
covering the thermal protections.
Deliverables:
Study Report
Current TRL:
4
Target
Application /
Timeframe :
Launchers. TRL 7 by 2018
Applicable THAG Roadmap:
Target TRL:
Not related to a Harmonisation Subject
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(months)
24
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3.2.2
TD 18- Aerothermodynamics
Domain
SPACE TRANSPORTATION
Technology Domain
18 Aerothermodynamics
Ref. Number:
G614-005MP
Budget (k€):
500
Title:
Liquid film cooling in MMH-NTO rocket engines
Objectives:
The present activity aims at improving the understanding and modelling of liquid
films in MMH-NTO engines.
Description:
Monomethylhydrazine (MMH) as fuel and Nitrogen Tetroxide (NTO) as oxidizer
is a commonly used rocket propellant combination. Large and mid-size engines
such as the Ariane 5G upper stage engine Aestus are re-generatively cooled via
cooling channels using the MMH fuel. For smaller engines, this gets more and
more difficult, because the available coolant per wall surface area decreases with
the engine dimension. Therefore, liquid film cooling of the combustion chamber is
usually applied for smaller MMH-NTO rocket engines. Whenever this cooling
technique is applied in a rocket engine, it is important to have adequate
prediction tools. For liquid film cooling, the main prediction focus is on the liquid
film length and the wall heat transfer downstream of the dry-out point. The
proper prediction of the heat transfer between hot gases and film is a prerequisite
for a good film modelling and often, especially in the case of MMH-NTO
chemistry, is very difficult due to the slow and complex combustion process with
various chemical species involved. An additional challenge for the modelling of
liquid MMH-films is the fact that the evaporated MMH decomposes in a strongly
exothermic manner, releasing a far higher decomposition energy than its
evaporation consumes.
It is proposed to address the following aspects:
- Establish an inert liquid film test case (no chemical reactions) from
literature, and or new experiments.
- Improve the MMH-NTO combustion modelling based on existing
experimental MMH-NTO data.
- Elaborating 1D two-phase film-modelling incl. mass and heat transfer e.g.
vaporization, condensation; based upon existing model and/or ESA tools
such as EcosimPro/ESPSS.
- Couple the film models in 2D/3DCFD codes for rocket combustion
chambers with validation on available data and possibly extension towards
real operational conditions (i.e. combustion).
- Consider 3D effects on film evolution.
- Attempt to perform resolved CFD simulations of a film, possibly with
original fluids.
Deliverables:
Study Report
Current TRL:
3
Target
Application /
Timeframe :
Mid-size to small rocket engines like Aestus; in the future also Berta/2018
Applicable THAG Roadmap:
Target TRL:
Not related to a Harmonisation Subject
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3.2.3
TD 19- Propulsion
Domain
SPACE TRANSPORTATION
Technology Domain
19 Propulsion
Ref. Number:
G614-006MP
Title:
10 kW Hall Effect Thruster
Objectives:
The aim is to advance the qualification of a high specific impulse 10 kW Hall
Effect System. The system performance shall be commensurate with the next
generation of high total impulse space missions. The work outcome shall be the
performance demonstration of an engineering model thruster and flow control
system.
Description:
To save propellant mass, maximise payload and mission capabilities, future high
total impulse missions will require propulsion systems capable of operating at
higher specific impulse (SI) and capable of greater total impulse (Ns) which
means higher thrust than those currently being developed and qualified (5 kW). A
10 kW Hall Effect Thruster will be capable to fulfil the requirements of these
missions.
The principles of operating existing technologies at higher specific impulse and
thrust levels have been demonstrated to a limited extent and the constraints
imposed by existing technology are generally appreciated. This activity will
therefore build on the extensive heritage gained through existing EP programmes
with the objective of designing, building and testing a thruster to meet the high
specific impulse and total impulse demands whilst overcoming the limitations
imposed by current technology. It is essential that this activity be considered in
the framework of a complete system that comprises appropriate power supplies
and flow control systems.
The programme will consist of the following key activities and phases:
Phase 1
- Identification of mission requirements and selection of a baseline mission.
- System level trade-off, technology selection and system architecture
definition.
- Unit specification.
Phase 2
- Design and manufacture breadboard thruster (including flow control) and
test.
- Design and manufacture of an engineering model (EM) thruster (including
flow control system).
- Performance testing of EM thruster (including the flow control system) for a
time adequate to allow detailed performance characterisation and life time
prediction.
- Endurance test.
Report with mission requirements definition; system level trade-offs, technology
selection and system architecture; design report; manufacturing report and
endurance test report.
Duration
3
Target TRL:
5
36
(months)
Deliverables:
Current TRL:
Budget (k€): 2,000
Target
Application /
Electric Propulsion advanced upper stages and exploration missions/2018
Timeframe :
Applicable THAG Roadmap:
Electric Propulsion Technologies (2009)
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3.3
Navigation
3.3.1TD 6- RF Payload and Systems
Domain
NAVIGATION
Technology Domain
6 RF Payload and Systems
Ref. Number:
G616-001ET
Budget (k€): 1,800
Title:
Beam-Forming Technology for GNSS Reference-Station
Objectives:
The objectives of this activity are:
- To investigate a GNSS Reference-Station equipment (antenna plus receiver)
profiting from beam-forming (spatial + time filtering) technology; offering a
visibly superior interference + strong-multipath rejection capability,
compared to that achieved by current GNSS reference station equipment.
The design shall target the minimization of the overall equipment
complexity and technological risk.
- To develop a GNSS Reference-Station prototype, fully representative from
functional and performance perspective, and to validate it under real GNSS
signals.
Description:
RF interference and multipath are relevant error sources affecting the
performance of the GNSS Commercial-Reference-Station equipment.
Despite the fact of being the navigation signal of spread-spectrum type, it is visibly
vulnerable to interference, due to its very low power at reception. Excessive
interference may provoke loss of lock and false lock in the equipment.
Multipath may induce ranging errors visibly correlated over time, not easy to
mitigate at signal processing level or/and at output-observables processing level.
The impact of both interference and multipath could be largely reduced by
incorporating beamforming techniques to the GNSS Reference-Station equipment
(comprising antenna plus receiver). Beam-forming techniques could enable
efficient spatial + time filtering of RF interference and strong multipath.
Current technology is nowadays based on single antenna element, therefore this
activity shall demonstrate the viability of beam-forming technology with low
complexity.
The activity high level tasks are as follows:
- Consolidation of the equipment specification; namely functional,
performance and external interfaces requirements (initial specification
prepared by ESA).
- Definition of the equipment physical architecture; namely main physical
blocks, related internal interfaces, core hardware blocks transfer function(s)
and core processing.
- Definition of the equipment physical detailed design; namely hardware
elementary blocks, elementary processing modules, detailed internal and
external interfaces.
- Development and verification of the equipment.
- Consolidation of the validation scenarios definition (initial definition
prepared by ESA).
- Extensive analysis of the equipment performance (code-phase and carrierphase tracking errors, probability of loss of lock, probability of false lock,
acquisition and re-acquisition time, etc), in the above validation scenarios;
which shall include at least the:
 Operation with real GNSS signals (Galileo & GPS) under nominal RF-
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
environment conditions.
Operation with real GNSS signals (Galileo & GPS) under extreme RFenvironment conditions, in terms of either interference or/and
multipath.
Deliverables:
Prototype
Current TRL:
3
Target
Application /
Timeframe :
GNSS Reference Stations: Geodetic Reference Stations, RTK Reference Stations,
Differential-GNSS Stations, etc. Need Date: 2018 as TRL 6
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject.
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Domain
NAVIGATION
Technology Domain
6 RF Payload and Systems
Ref. Number:
G616-002ET
Budget (k€): 1,000
Title:
Flexible and reconfigurable GNSS signal testbed
Objectives:
The aim of this activity is to design and implement a flexible/re-configurable
signal testbed, including a signal generation/receiver platform with the twofold
objective to test performance of 1) advanced GNSS signal formats/techniques
(both at modulation and message level) and of 2) advanced tracking techniques
able to flexibly adapt to the corresponding advanced signal formats/techniques.
Description:
GNSS community is investigating new techniques and several concepts (both at
modulation and message level) to enhance future GNSS signal in space
capabilities.
For instance, the past TRP activity "ADVISE" and similar studies in the GNSS
community have investigated new message / advanced coding / interleaving
techniques (like LDPC, TURBO, Super Orthogonal Turbo codes, etc) as well as
new modulation schemes, spread spectrum techniques and mapping (like
Continuous phase modulations, Multicarrier signals, Continuous Shift Keying
(CSK), etc). They have also started to exploit link layer techniques (e.g. fountain
codes etc.) and data message content structure for improvements of Time To First
Fix and robustness of data reception.
The claimed performance advantages shall be first studied and traded-off with
respect to the enhanced complexity of the system by means of a flexible
breadboard capable of implementing:
- Advanced GNSS signal formats/techniques (in terms of both modulation
and message)
- State-of-the-art tracking and demodulation techniques able to flexibly adapt
to the corresponding advanced signal techniques.
Main focus of the activity is, on the receiver side, the definition and
implementation of mechanisms to flexibly adapt to and track the transmitted
advanced signals with the least (eventually non-existent) prior knowledge on the
actual transmitted signal, and on the generation side the support for a wide set of
modernized signals that need to be simulated to support validation and
performance assessment.
The identification, definition and implementation of advanced techniques (both at
signal generation and receiver detection side level), as well as definition and
implementation of concepts allowing required flexibility and upgrade-ability shall
be carried out within the activity, together with a final detailed performance
assessment of exemplary formats/techniques.
Thus the final hardware developed in this activity shall cover:
- Message/Advanced coding/Interleaving and decoding and deinterleaving
- Link layer techniques and new data message content structure for
improvements of TTFF and robustness of data reception.
- New Modulation schemes, Spread-Spectrum techniques and mapping and
associated receiver techniques.
- Multicarrier signals and associated receiver techniques.
Seen the many available configuration options and possible parameterisation of
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the techniques, the breadboard shall allow a flexible reconfiguration of the
generation/receiver techniques to cover all the selected Signal In Space formats.
In particular, the activity shall define and implement mechanisms to flexibly
adapt to and track the transmitted advanced signals with the least (eventually inexistent) a-priori knowledge on the actual transmitted signal.
The validation of the platform shall be carried out at least with standard GNSS
signal format/techniques and exemplary advanced techniques/formats related to
system implementation cases. Finally, validation results shall be used for detailed
performance assessment of the standard and exemplary techniques.
Deliverables:
Engineering Qualification Model
Current TRL:
3
Target
Application /
Timeframe :
Future GNSS evolutions. 2018
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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Domain
NAVIGATION
Technology Domain
6 RF Payload and Systems
Ref. Number:
G616-003ET
Budget (k€): 1,000
Title:
Digital Beam-forming Based Advanced Navigation Receivers Prototype
Terminal
Objectives:
The goal of this activity is the design and manufacturing of a prototype of
miniaturised antenna array and receiver for GNSS applications on vehicular users
requiring high precision and robustness. This advanced digital beam-forming
prototype terminal shall implement protection against interference and
multipath, and enhanced signal to noise ratio to vehicular users.
Description:
Many terrestrial vehicular GNSS receivers currently use FRPAs (Fixed Reception
Pattern Antennas) instead of CRPAs (Controlled Reception Pattern Antennas),
due to the size and weight of the current CRPA antenna arrays, whereas the CRPA
technology could offer important advantages in terms of interference and
multipath rejection, available C/N0 enhancing or even enabling a large number of
new applications.
The project will firstly study the state-of-the-art technologies for tightly packed
antenna arrays, where the antenna elements are placed in close proximity. In
particular, the problem of the mutual coupling will be faced in order to minimise
the performance degradation in terms of input impedance mismatch, sidelobe
level, scan blindness, pattern degradation, and radiation efficiency. At the same
time, state-of-the-art digital null and beam-forming signal processing algorithms
will be studied for interference and multipath mitigation at receiver level. The
main drivers for optimization will be based on the adaptive steering capability of
following the mobile user position and asset changes, the gain in terms of signal to
noise ratio, the rejection of interference and the attenuation of reflected signal
echoes. In a mobile environment, advanced digital beam-steering algorithms at
receiver level will be required in order to compensate not only for the satellite
motion, but also for the vehicle motion. The receiver platform will be able to
receive signals from multiple constellations and to provide autonomous
calibration for the different frequencies/signals. The design of the receiver will be
able also to accept external inputs for the vehicle heading that could be used to
provide real-time correction of the digital beam direction while the vehicle is in
motion.
The requirements in terms of form factor and achievable performance will be
derived from the target user needs, in particular for applications requiring high
precision and robustness, considering vehicular terminals with Dual Frequency
Multi-constellation (L1/L2, L1/L5). Single Frequency Multi-constellation (L1) can
be tested as a by-product.
In the frame of the activity, the following items will be developed:
- a dual frequency packed antenna array
- a receiver platform able to interface with the dual frequency antenna array
and with a flexible architecture able to cope with various null/beam forming
algorithms.
The complete terminal (antenna plus receiver) will be verified with proper models
representative of the user environments (in terms of interference, multipath,
shadowing) and with on-field test campaign. The on-field testing activity will
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cover different environmental scenarios, ranging from open-sky, motorway to
urban canyons conditions, intermediate and heavy tree-shadowing, and different
platform dynamics (e.g. extreme yaw accelerations).
Deliverables:
- HW:
 Prototype of a dual frequency packed antenna array for terrestrial vehicular
GNSS users.
 Receiver prototype.
- Associated design documentation.
- Validation and Test reports.
Current TRL:
3
Target
Application /
Timeframe :
Future EGNOS and Galileo/TRL 5 by 2018
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject.
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Domain
NAVIGATION
Technology Domain
6 RF Payload and Systems
Ref. Number:
G616-004ET
Budget (k€): 1,000
Title:
Advanced hybrid navigation user platform
Objectives:
The main objective of the activity is the development of a complete receiver
platform for hybrid positioning and the development of fusion algorithms for PVT
(Pipelined Version of TopHat) computation.
Description:
None of the current individual positioning technologies is able to ensure service
coverage in different and heterogeneous environment while offering positioning
accuracy. The integration of different position technologies appears to be
absolutely pivotal to the future location devices.
This activity will include the procurement of an integrated platform, able to
produce and process observables from:
- GNSS constellation signals with algorithms representative of the massmarket receivers (assisted GNSS, open loop tracking, batch processing,
snapshot positioning, power saving algorithms and ephemeris extension)
- Terrestrial positioning signals (WiFi, 3G/4G positioning e.g. OTDOA and
extended Cell-ID).
- Signals of opportunity processing.
- MEMS (Micro Electro Mechanical Systems).
The multi-constellation GNSS receiver embedded in this platform will be
considered as a sensor within others and overlaying fusion algorithms will be
implemented in order to optimise the hybrid position estimate.
The platform will embed state of the art chip scale sensors to improve
performance and keep the form factor suitable for targeted applications. In
particular in order to allow man-portable dead-reckoning devices with improved
precision, with and without GNSS, the following sensors will be included:
- chip scale antenna: the antenna and all the RF-FE components are in a low
cost single chip package
- chip scale atomic clock: short-term stability and aging characteristic of
atomic clocks, but with over two orders of magnitude decrease in size and
power consumption. They can improve notably the receiver performance in
case of high sensitivity tracking algorithms and integration with inertial
sensors.
- chip scale inertial measurement unit and micro-electro-mechanical systems
(MEMS).
The platform will be at the same time flexible and reconfigurable to allow the
experimentation of the various techniques.
The integrated platform will be used to assess the performance of the different
positioning signals in realistic propagation channels with representative models
and on-field testing activities. A complete comparison between performance
results of the single positioning techniques and the hybrid one will be presented
for the different scenarios and applications. The way of carrying out sensible field
trials will be thoroughly investigated at the beginning of the activity in terms of
user scenarios, channel characteristics and sensors capabilities. A minimum set of
experiments to run in the field will be defined to gather meaningful results to
assess performance of various hybrid positioning techniques.
Deliverables:
- HW: complete breadboard of the receiver platform for hybrid positioning (tested in
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a relevant environment)
- associated design documentation
- validation and test reports
Current TRL:
Target
Application /
Timeframe :
3
Target TRL:
5
Duration
(months)
Future EGNOS and Galileo/TRL 5 by 2018
Applicable THAG Roadmap:
Not related to a Harmonisation Subject
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Domain
NAVIGATION
Technology Domain
6 RF Payload and Systems
Ref. Number:
G616-005ET
Budget (k€): 800
Title:
Advanced receiver architecture platform
Objectives:
The objective of the activity is to develop and assess performance of an advanced
GNSS receiver architecture platform with new and state of the art receiver
architectures and signal processing algorithms to support user applications in
realistic scenarios (e.g. vehicular land, pedestrian, machine-to-machine).
Description:
This activity shall cover the development of an integrated receiving platform with
the implementation of the following algorithms (based on the outcomes of
previous TRP R&D activities):
- Interference Detection/Mitigation/Awareness
- Multipath suppression/Mitigation
- Non-Line of Sight (NLOS) tracking detection/mitigation: conditions based
on shadowing and LOS blockage effects that can lead to complete loss of
tracking or to tracking of echoed signals shall be detected
- Adaptive tracking techniques: linear adaptive filters techniques
- High sensitivity techniques for increasing availability of measurements in
non-nominal tracking conditions: such as vector tracking loops and batch
processing with external aiding (sensors)
- Robust data demodulation techniques
- Fast and robust time to first fix (TTFF)
The platform shall embed state-of-the-art chip technologies, being at the same
time flexible and re-configurable to allow experimentation of the various
techniques.
The GNSS receiver platform performance shall be verified in realistic propagation
channels with representative models and on-field testing activities. The inlaboratory testing activity shall foresee proper hardware simulators to simulate
the scenarios conditions and to reproduce the multipath and interference models.
The on-field testing activities shall thoroughly verify the single algorithm
performance in different real environments, representative of the degraded
transmission channels.
Deliverables:
Breadboard
Current TRL:
3
Target
Application /
Timeframe :
Future Galileo and EGNOS/TRL 5 by 2018
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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Domain
NAVIGATION
Technology Domain
6 RF Payload and Systems
Ref. Number:
G616-009ET
Budget (k€): 450
Title:
Payload simulation tool for complex GNSS RF front-end architectures
Objectives:
The objective of this activity is to develop a detailed simulation tool for complex
Navigation RF payload (P/L) front-ends within a system simulator. This tool will
allow to simulate different Navigation RF payload front-end architectures and will
assess the impact of payload constitutive elements impairments (e.g. linear and
non-linear distortions) onto the transmitted navigation signal and hence on the
end-to-end system performances.
The aim of the tool is to support the following system/payload engineering
activities:
- Design and analysis of future Navigation RF payload front-ends.
- Definition of the most optimized payload architecture for a given Navigation
space segment scenario.
- System to Payload Requirements flow-down.
- Prediction of payload performance and refinement of payload design for
performance optimization (including refinement of subsystems
specifications).
- Detailed and quantitative payload performance requirements definition
based on far-field performance assessment when loading the payload with
realistic signal conditions.
Description:
The tool will be of fundamental importance for the definition of future
generations of navigation P/Ls to be developed in the 2020s. The replacement of
the Navigation satellites gives the opportunity in the 2020s to address emerging
challenges (such as flexibility at antenna, signal and RF power levels) as well as to
optimize its exploitation with the definition of new services. New technologies in a
wide range of domains have the possibility to be embarked and even new and
advanced payload architectures can be defined.
The tool shall be based on industry standard simulation platforms like for
instance Matlab/Simulink, ADS, GRASP and shall allow the interfacing with
standard industry RF measurement instruments. In order to accelerate the
simulation time, parallel programming shall also be considered.
The tool shall be implemented in a modular manner to allow easy setup of
different P/L architectures that it may be needed to investigate for future
Navigation space segment scenarios.
P/L constitutive elements shall be implemented as building blocks and their
combination shall allow to develop and simulate different PL architectures, e.g.
including distributed amplification (Beam Forming Networks, Flexible tubes etc)
and different antennas options ( single feed per beam, array fed reflector, direct
radiating arrays etc.)
The P/L constitutive elements shall be simulated at functional and distortion level
with the possibility to up-load measurement characteristics.
The simulator shall be able to reproduce and analyse the most important
navigation signal quality degradation sources appearing in the Tx chain and
assess their impact into the End-to-End performances.
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The simulator will provide high flexibility in the operating frequency (e.g. L and C
band) and in signal waveforms (simulating all the available and planned GNSS
signals) and will permit step-by-step and in total analysis of the impact of at least
the following impairments:
- Phase noise introduced by satellite/receiver clock oscillators.
- Group delay (phase centre) variation over satellite and receiver antenna
field of view.
- Linear distortions coming from on-board signal/frequency generators, upconverter and output multiplexer as well as linear distortions coming from
earth-terminal front-end filter and down-converter.
- Drift in amplitude and phase responses owing to temperature variations.
- Unintentional and intentional RF interference, Multipath and propagation
impairments.
- Non-linear distortion introduced on the overall Tx and Rx chain, paying
particular attention to the on-board HPA and D/A-A/D converters.
Deliverables:
Software
Current TRL:
3
Target
Application /
Timeframe :
Navigation/2018
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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Domain
NAVIGATION
Technology Domain
6 RF Payload and Systems
Ref. Number:
G616-011ET
Budget (k€):
200
Title:
Study and design of a GNSS Living Lab testbed into a Smart City
Objectives:
The objective of this activity is to study and design of a GNSS Living Lab testbed.
This activity shall provide a thorough study on the architecture and mechanisms
required to implement this testbed within a Smart City. Thus, this design shall
optimise the amount of Smart City resources utilised, and ensure flexible testbed
configuration and open-access of data.
Description:
The Smart City GNSS Living Lab testbed, is a next-generation tool aimed to
validate current and future GNSS services, to ensure the optimisation of the
system for a large variety of usages, and to be flexible enough to allocate any
dedicated experiment. For instance, current GNSS services can be validated with
this flexible and open-access testbed able to provide field measurements in realtime, as well as it provides the means to assess multi-constellation capabilities in
real urban conditions. For this purpose, the testbed is based on the deployment of
a network of wireless sensors distributed in fixed points and vehicles (e.g. taxis
and buses) over the city. These sensors record RF samples of different bands (not
only GNSS) and stream them to a control centre able to process the data for any
suitable application, such as cloud-based GNSS navigation. Thus, the reutilisation of the Smart City resources should be maximised by the GNSS Living
Lab testbed. The current GSTP activity shall study and design the specific testbed
implementation for a specific existing Smart City, in order to optimise the testbed
performance. In addition, the proposed GNSS Living Lab is broader and
multipurpose. For instance, this Smart City testbed may support hybrid GNSS and
terrestrial solutions, which are the standard technologies used for positioning in
urban environments. Therefore, the GNSS Living Lab shall select the adequate
sensors to support the specific technology requirements. This GSTP activity,
based on the study and design of the testbed, is the first step on the
implementation of the GNSS Living Lab in a specific existing Smart City.
The tasks of this activity are to:
- Identify an existing Smart City that may support a GNSS Living Lab and
assess the resources available in such Smart City.
- Study and design a flexible architecture for the testbed based on a network
of sensors and control centres, ensuring open access of data sets to end
users.
- Study the potential reuse of existing infrastructure deployed by the city
council and the inclusion of the testbed in the existing Smart City platform.
- Investigate the sensor technology, by trading off accuracy with costs.
- Investigate the resource management and cloud computing strategies.
- Study the applications and main usages of the testbed, particularly in the
GNSS and communication fields.
- Study the economic exploitation of the testbed and the economic impact of
the testbed over the city.
- Demonstrate the details and challenges on the implementation and
installation of the GNSS Living Lab in the Smart City selected.
Deliverables:
Testbed design report, application and main usages report, demonstration and
validation reports
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Current TRL:
Target
Application /
Timeframe :
2
Target TRL:
3
Duration
(months)
12
Future navigation receivers and related applications, Future Galileo and
EGNOS/TRL 3 by 2018
Applicable THAG Roadmap:
Not related to a Harmonisation subject
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Domain
NAVIGATION
Technology Domain
6 RF Payload and Systems
Ref. Number:
G616-012ET
Budget (k€):
1,000
Title:
Railway GNSS receiver chain technology enabler
Objectives:
The objective of this activity is to develop a railway GNSS receiver chain
technology enabler to support the testing and validation of algorithms, integrity
concepts and techniques for receivers in a railway environment.
Description:
The tool is unique in that it allows any part of the GNSS receiver chain to be
modified and analysis of outputs from each part of the chain. The evaluation of
integrity performance is an essential part of the tool, where various techniques
and algorithms at each stage of the receiver chain can be evaluated in terms of
their impact.
The railway GNSS receiver chain is also intended to be part of a reference virtual
balise reader, allowing impact on the European Rail Traffic Management System
(ERTMS)/European Train Control System (ETCS) performance to be evaluated.
This activity foresees the development of an advanced real-time receiver platform
comprised of a GNSS receiver chain including an antenna element.
The platform shall support the testing of mitigation and suppression techniques
for feared events in the railway environment at all stages of the receiver chain.
This includes antenna, RF domain, DSP domain (pre-correlation, correlation),
range domain and position domain.
The platform will also provide support for GNSS/INS integration architectures
and shall include an integrity analysis and verification tool.
It is imperative that the platform is capable of real-time processing, enabling its
use within a reference virtual balise reader.
Deliverables:
Prototype
Current TRL:
3
Target
Application /
Timeframe :
Future Satellite Navigation services/applications/TRL 5 by 2017
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Not related to a Harmonisation subject
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Domain
NAVIGATION
Technology Domain
6 RF Payload and Systems
Ref. Number:
G616-013ET
Budget (k€):
1,000
Title:
Methodology to support characterisation of GNSS performance in
railway environments
Objectives:
The objective of this activity is to develop a robust methodology for characterizing
the railway environment and to test and validate models for events including
multipath, non-line-of-sight (NLOS) conditions and interference.
The activity is critical in supporting the development of a GNSS railway
simulation test-bed, as such models cannot be derived from existing models that
originate from other environments or applications. The environment and threats
are very specific to the railway application and intended operations.
Description:
This activity foresees the development of a methodology to support
characterization of the railway environment and modelling of events (including
multipath, NLOS conditions and interference) in a way that can be reproduced in
simulated scenarios.
Field data shall be used to validate the methodology and models of the
environment and events. Models developed will become a critical part of faultinjection testing and the development of test procedures to be used with the GNSS
railway simulation test-bed.
This activity foresees the development of comprehensive datasets for
electromagnetic interference (EMI) in the railway environment (e.g. DC-DC
converters in locomotives, EMI from pantograph bounce, etc.). Characterization
of EMI should include sources originating from the train, from the wayside and
external to the railway corridor. The ability to reproduce a wide range of EMI in
simulation is an important part of the fault injection testing methodology of the
GNSS railway simulation test-bed.
Deliverables:
Test campaign (data, reports)
Current TRL:
3
Target
Application /
Timeframe :
Future Satellite Navigation services/applications/TRL 5 by 2017
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Not related to a Harmonisation subject
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Domain
NAVIGATION
Technology Domain
6 RF Payload and Systems
Ref. Number:
G616-014ET
Budget (k€): 500
Title:
Interference Suppression Unit (Pre-Receiver)
Objectives:
The objective of this activity is the development of a hardware demonstrator of a
unit able to cancel interference signals within the GNSS user-bands of interest.
This unit is to be placed between the antenna and the receiver, and can be used to
enhance the ground station robustness, and to enable the installation of ground
stations at sites where the in-band interference signals levels are high.
Description:
The activity shall design and implement a hardware demonstrator of a unit able to
cancel interference signals within the GNSS user-bands of interest (E1, E6 & E5,
L1, G1, etc). Such concept has been demonstrated in past activities. This unit:
- Receives real RF GNSS signals in the GNSS user-bands of interest E1, E6 &
E5, L1, G1, etc), and pre-process them (by filtering, amplifying, downconverting and digitalizing them).
- Identifies and cancels any potential unwanted in-band interference signals;
whichever their spectral properties (which may also vary over time) are and
whichever their number is.
- Re-constructs the RF GNSS signals in the GNSS user-bands of interest (E1,
E6 & E5, L1, G1, etc), free of any contamination (by converting to analogue,
up-converting, filtering and amplifying them).
This unit is called hereafter a RFI-CANCEL unit. The main tasks of this activity
are the following:
- RFI-CANCEL Hardware Demonstrator Unit Specification Consolidation.
- RFI-CANCEL Hardware Demonstrator Unit Preliminary Design.
- RFI-CANCEL Hardware Demonstrator Unit Detailed Design.
- RFI-CANCEL Hardware Demonstrator Unit Development & Integration.
- RFI-CANCEL Hardware Demonstrator Unit Factory Verification.
- RFI-CANCEL Hardware Demonstrator Unit Field Validation.
Deliverables:
Prototype
Current TRL:
3
Target
Application /
Timeframe :
RFI-CANCEL Operational Unit needed to protect Reference Sensor Stations from
RFI.This Hardware Demonstrator Unit is a risk mitigation activity to overcome
potential RFI problems at reference station sites. 2018
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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Domain
NAVIGATION
Technology Domain
6 RF Payload and Systems
Ref. Number:
G616-015ET
Budget (k€):
500
Title:
Clock Ensemble Monitoring and Switching Unit for Robust Timescale
Generation
Objectives:
The objective of this activity is the design, development, manufacturing and test of
a clock ensembling, monitoring and switching unit for robust timescale
generation.
Description:
Current solutions for robust timescale generation, in terms of stability and
continuity relies on a distributed and complex hardware architecture with
dedicated equipment that require specific skills and experience to operate and
maintain. Several alternative solutions relying on a more integrated system have
been proposed, and some of them have been investigated.
This activity shall be dedicated to:
- Review of Timescale functional requirements in terms of:
- Clock ensembling
- Clock steering
- Clock monitoring
- Clock switching in case of failure
- Clock distribution
- Detailed design.
- Manufacturing (prototype level).
- Testing.
- Conclusions and recommendations.
Deliverables:
Prototype
Current TRL:
3
Target
Application /
Timeframe :
2020
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
18
Frequency & Time Generation and Distribution - Space
(2013)
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Domain
NAVIGATION
Technology Domain
6 RF Payload and Systems
Ref. Number:
G616-016ET
Budget (k€):
1,000
Title:
Technology Validation of a Cold Atom Microwave Atomic Clock
(CAMAC)
Objectives:
The objective of this activity is the design update, full characterization and
validation of a Cold Atom Microwave Atomic Clock (CAMAC) providing a
frequency stability below 1E-13/SQRT(t), for t = 1sec to 10 days.
Description:
Today, the generation of a reference timescale (like the Galileo System Time or any
local realisation of UTC) relies on Active Hydrogen Maser, which is a robust and
well proven technology, but that needs to be regularly steered to correct for
intrinsic frequency drift. This critical steering process requires relevant expertise
(mostly available in Metrology Laboratories) and reveals difficult to implement
and automatize in an operational context like the Galileo Precise Time facility or
the ESA Ground Stations, especially when they operate in autonomous mode. The
CAMAC technology is expected to have much lower frequency drift than the Active
Hydrogen Maser, with similar performances in terms of short-term stability,
resources and operability.
The activity shall start with a review of the existing design of the CAMAC and the
identification of the design updates required to meet the performance, operational
and resources requirements. Second, the design updates shall be implemented and
validated. Finally, a full characterization of the clock shall be performed, including
short-term stability, reproducibility, sensitivity to environment, and long-term
stability.
Deliverables:
Prototype
Current TRL:
3
Target
Application /
Timeframe :
2018
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
18
Frequency & Time Generation and Distribution - Space
(2013)
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3.3.2
TD 7- Electromagnetic Technologies and Techniques
Domain
NAVIGATION
Technology Domain
7 Electromagnetic Technologies and Techniques
Ref. Number:
G616-010EE
Budget (k€): 1,000
Title:
Environment survey and calibration instrumentation for GNSS
propagation error sources, including direction of arrival
Objectives:
Design and development of a multi-frequency multi-instrument facility to evaluate
and calibrate propagation error sources of Global Navigation Satellite Systems
(GNSS) in fixed and mobile environments. This facility shall be used to measure all
required inputs that would allow more realistic characterisation of all error
sources, including spatial discrimination and direction of arrival that would allow
an eventual replay/simulation in an existing Over-The-Air (OTA) facility for
terminal (receiver plus antenna) testing. This will allow to assess independently
effects from different propagation contributions measured on the field.
This facility will include the following features: User Performance evaluation, Error
characterization, Site Survey and Sensor Station Characterisation (for fixed
receivers), Trajectory Survey and Characterisation (for mobile receivers); including
the effects of Ionosphere and Troposphere, Multipath, Shadowing, Noise and
Interference.
Description:
Current technologies and techniques are not today able to accurately estimate the
error sources from fixed and, particularly, mobile GNSS receivers. For example,
regarding multipath, the high-frequency components can be estimated together (in
addition) to noise and interference, but the slowly varying components are more
difficult to separate. In fact, for ionosphere, the ionospheric delay calibration relies
on a dual-frequency technique that require a very good estimation / calibration of
inter-frequency bias from the receiver. This is difficult to obtain and often masks
other errors. The efficient use of meteorological stations or even radiometers is
required for tropospheric calibration. In addition, the effects of the antenna as
installed on a given platform are of critical importance for this evaluation. In the
recent past several activities where antenna array processing is used to estimate
spatial-dependent contribution or mitigate multipath and interference were
successfully completed. However, the contributions of beam-forming network
(analogue or digital) and its effects on error source evaluation should be taken into
account to properly measure the direction of arrival of interferers and possibly
exploited to increase the sensitivity of receivers against propagation impairments
(e.g. Ionospheric scintillation).
The activity shall implement a very precise GNSS carrier-phase measurement
techniques for accurate positioning of mobile users and integration of these
techniques with inertial sensors for separating environmental effects from other
error sources. Configurations with hemispherical antennas, antenna arrays and
possibly beamforming antennas and other sensors like laser ranging may be also
considered.
The technique shall enable to evaluate and calibrate error sources in fixed and
mobile environments including:
- Multipath (bias - slowly varying - and random components, including angle
of arrival).
- Shadowing.
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- Ionospheric delay and instrumental inter-frequency biases (for all
frequencies).
- Tropospheric delay.
- Ionospheric scintillation.
- Interference (narrowband and wideband, including direction)
- Noise.
The developed techniques shall be instrumental to the exploitation of -record and
replay- OTA measurements, to allow more realistic simulation scenarios, which
will account for different angle of arrivals during receivers testing.
The following tasks are anticipated:
- Consolidation of the facility definition and identification of instrument
requirements, with particular care to OTA interfaces, architectures and
processing algorithms.
- Critical evaluation of architectural concepts
- Development and procurement of hardware and algorithms
- Facility integration and testing
- Qualification including in the field experimental campaign
- Interface demonstration of the facility with an existing OTA lab
- OTA experimental campaign and validation.
- The main deliverable shall be a prototype facility able to evaluate the
different propagation error sources for fixed and mobile (automotive, train
and maritime) users.
- The same facility shall be interfaced to an existing OTA lab to allow
reproducing the measurements acquired in the field Replay. The Replay
methodology shall be validated based on several test cases.
Deliverables:
Instrumentation facility prototype
Current TRL:
4
Target
Application /
Timeframe :
Future EGNOS and Galileo site survey and user performance evaluation, GNSS site
characterization and receiver developments. Need TRL 6 by 2018
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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3.4
Generic Technologies and Techniques
3.4.1
Core
3.4.1.1 TD 1- On-board Data Systems
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
1 On-board Data Systems
Ref. Number:
G617-006ED
Budget (k€):
Title:
Micro-controller
Development
Objectives:
The main objective is the development of a time based simulator of the mixed
signal microcontroller developed in the TRP activity "Microcontroller for
embedded space applications: Specification and design verification".
Description:
The development of a highly integrated micro-controller for low-end space
applications is receiving increasing interest in the space community. In response
to such request a LEON3FT mixed signal micro-controller ASIC (code name GR716) is under development. The GR716 will include a high number of digital and
analog peripherals including MIL-STD-1553 RT, CAN, SPI, I2C, UART,
SpaceWire, ADC, DAC. In order to provide support for rapid prototyping of
systems using the GR716 device a key element is the availability of an accurate
micro-controller behavioural simulator. The simulator shall allow to emulate the
behaviour of the GR716 micro-controller including the new SPARC 16-bit
instruction set implemented in the frame the GR716 development TRP activity.
for
embedded
space
applications:
200
Simulator
The simulator shall implement an accurate time based emulation of the GR716
including the on-chip bus architecture modelling and on-chip peripherals
modelling. The simulator shall be extensible by user models developed in C.
The simulator shall run in stand-alone mode, or connected to a debugger (e.g.
GNU gdb debugger) or shall be usable as libraries for larger simulation
frameworks.
Deliverables:
Prototype
Current TRL:
3
Target
Application /
Timeframe :
Earth Observation, Exploration, Science, Navigation, Human Space Operations: a
mixed microcontroller can find applications in all the type of missions and in
different units/subsystems ( e.g. RTU, Motion control unit, AOCS sensors).
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Data Systems and On-Board Computers (2011)
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Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
1 On-board Data Systems
Ref. Number:
G617-007ED
Title:
Micro-controller for embedded
Development Suite (part 1)
Objectives:
The main objective is the development of a "native" support in a C compiler (GCC
or LLVM) of the new 16-bit instruction set designed for the mixed signal
microcontroller developed in the TRP activity "Microcontroller for embedded
space applications: Specification and design verification". Another important task
will be to extend the support to the GDB debugger.
Description:
The development of a highly integrated micro-controller for low-end space
applications is receiving increasing interest in the space community. In response
to such request a LEON3 mixed signal micro-controller ASIC (code name GR-716)
is under development. One of the key requirements for the new micro-controller
is a high software code density in order to reduce the on-chip memory storage
needed for code and to reduce the memory bandwidth needed for code fetching.
A new SPARC 16-bit instruction set (ISA) has been therefore defined and
implemented allowing a code compression ratio comparable to other architectures
like ARM Thumb while maintaining backward compatibility with existing SPARC
32-bit code. Such a solution will introduce a new instruction set for space
applications that needs to be supported on the compiler side to realize the full
compression potential of the instruction set.
The main objective of the proposed activity is to adapt and extend the LLVM or
GCC toolchain for C language to the LEON3-FT with 16-bit extension.
The first phase of the activity will detail the upgrades needed in the LLVM/GCC
SPARC backend to generate correct code and support optimisations for the full
new SPARC 16-bit ISA.
This will serve as input for the second phase where the compiler backend will be
designed and developed.
The third phase will consist in the development of a test suite to check the
correctness, to compare and characterise the accuracy, performance and code
compression ratio of the compiler backend respect to the existing SPARC 32-bit
version. The test suite shall run on the GR-716 micro-controller prototypes.
A final task shall evaluate the long term support and maintenance of the
developed compiler backend.
Deliverables:
Software
Current TRL:
3
Target
Application /
Timeframe :
Earth Observation, Exploration, Science, Navigation, Human Space Operations : a
mixed microcontroller can find applications in all the type of missions and in
different units/subsystems ( e.g. RTU, Motion control unit, AOCS sensors)
Applicable THAG Roadmap:
Budget (k€): 400
Target TRL:
4
applications:
Duration
(months)
Data Systems and On-Board Computers (2011)
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Software
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Domain – Specific
Area
GENERIC TECHNOLOGY - CORE
Technology Domain
1 On-board Data Systems
Ref. Number:
G617-250ED
Budget (k€): 250
Title:
Fast Emulator for Hardware / Software codesign
Objectives:
Main objective of the activity is the integration of the T-EMU 2 emulator with
SystemC/TLM and it addresses two complementary sides of this integration: 1) it
will allow T-EMU 2 to support emulation of hardware devices described with
SystemC/TLM and 2) it will allow the use of the T-EMU emulator engine inside a
SystemC based environment, such as the Agency’s sponsored SoCRocket, thus
speeding-up the overall system simulation.
Description:
Today, many hardware vendors write models of their hardware devices using
SystemC/TLM languages; these models usually represent the hardware very well
and they are used for preliminary hardware development. Later on in the
development cycle, usually during software development, those same hardware
devices are modeled with different methodologies, like SMP2, a de-facto standard
for the space community, leading to a lot of duplication of work. To aid software
development the hardware device models are integrated together into emulators,
thus allowing to emulate the whole on-board computer. One such emulator is TEMU 2, a high performance emulator, over 50% faster than existing emulators
such as T-SIM and the ESOC Emulator, it is also several times faster than the
instruction-set translator already embedded in SoCRocket. In addition, T-EMU 2
supports emulation of multi-core processors out of the box, which in the context
of the NGMP is a must, this support does not exist in the other emulators. In
addition to the mentioned capabilities, T-EMU 2 has been designed to in the
future support binary translation, which would increase performance even more.
This activity foresees the integration of T-EMU 2 with SystemC/TLM and it
addresses two complementary sides of this integration: 1) it will allow T-EMU 2 to
support emulation of hardware devices described with SystemC/TLM and 2) it
will allow the use of the T-EMU emulator engine inside a SystemC based
environment, such as the Agency’s sponsored SoCRocket, thus speeding-up the
overall system simulation.
The activities here serves two purposes. Firstly it opens up the opportunity to save
costs on Software Validation Facilities (SVFs) and Operational Simulators and to
shorten the time to the initial release of such a simulator (where a simulator could
initially use System-C models which gradually gets replaced with SMP2 to better
fit with existing infrastructure). Secondly the use of a high performance emulator
will increase significantly the performance of System-C based simulators (like
SoCRocket).
According to these two different purposes, the activity can be roughly split into
the following tasks:
- Emulator - System-C bridge: This activity will ensure that the T-EMU 2
emulator can communicate with SystemC/TLM models; in general this
involves the bridging of T-EMU 2 memory transactions to TLM generic
payload based transactions. It also involves the mapping of the emulator
scheduling primitives to System-C. As System-C is a framework, such a
bridge must be sufficiently customisable by the user. Other emulator
transaction to System-C TLM transaction mappings can also be provided to
ensure that bus models are compatible between emulator and SoCRocket.
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- System-C - Emulator bridge: System-C comes with its own scheduler, this
activity serves to integrate the T-EMU 2 emulator inside the System-C
scheduler and ensure that emulator interfaces such as memories and
interrupts are bridged with TLM.
- Model integration and testing: The two bridges will be tested by running
experiments on existing models and by providing different example
configurations of the bridges.
Deliverables:
Hardware Models
Current TRL:
3
Target
Application /
Timeframe :
The developed technology will be used to:
- enhance accuracy and performance of future Software Validation Facilities,
- increase the capability of designing future systems-on-chip.
Applicable THAG Roadmap:
Target TRL:
Microelectronics (2011)
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5
Duration
(months)
18
ESA UNCLASSIFIED – For Official Use
Domain – Specific
Area
GENERIC TECHNOLOGY - CORE
Technology Domain
1 On-board Data Systems
Ref. Number:
G617-251ED
Title:
Microcontroller Softcore for Space Applications
Objectives:
In the current space market, the increasing systems complexity poses great
challenges to architects, designers and verification engineers. Systems
requirements are continuously asking more functionality with less power, less
resources, less time and cost, forcing also suppliers to shrink their schedules.
One important aspect that is becoming more and more critical nowadays is a 'first
time right' design that can be scalable and adaptable to special needs, leveraging
on the reuse of building blocks which are highly configurable and already
validated.
One of these building blocks that may make a real change in the current space
market is a microcontroller IP core. In the commercial market, microcontrollers
have proven their value by being embedded in nearly every electronic device from
home appliances, automotive electronic units to hand gadgets.
Concurrently, the availability of large FPGAs for space use make this hardware
platform attractive, since logic resources optimization will be a lesser priority with
respect to a leaner and faster design cycle.
The space market has been so far confined to either use a full fledged
microprocessor, like the LEON, or has been leading to handcraft increasingly
complex state machines in overly loaded FPGAs. There's no man in the middle
available to system designers to offload the complexity of current designs and
reuse is limited to functions that are often not posing the major design or
verification challenges (memory controllers, PWMs, serial ports, ...).
A microcontroller may come to the rescue the situation, providing a solution that
fits in between the overly loaded FPGAs and the hugely complex microprocessor,
providing another layer of abstraction to tackle complexity.
Moreover, a microcontroller based solution implemented in a FPGA may
adequately respond to rapidly changing needs and securing development and
verification efforts, delegating repetitive and highly parallelizable functions to the
FPGAs (packet switching, low level protocols, hardware interface,
interconnection,...), while keeping the algorithmic intelligence of decision making.
Embarking on building a space rated microcontroller device is indeed a huge
effort and is by no means an easy task, and is already covered by other TRP
activities, therefore we are currently proposing to change perspective and look
towards a potentially more viable solution, more portable and flexible than a
microcontroller: a soft core.
Description:
Objective of this activity is the validation of a space rated uC soft core.
Thanks to the "ARM @ ESA" internal development, experience was gathered in
trading off hardening methods (at RTL and netlist level) that are FPGA
technology dependent. RTL-level rad hard by design can be covered too.
Transient faults caused by single-event upsets are a key challenge likely to gain
significantly more importance in the next few design generations, especially when
dealing with 'commercial' non RTL-hardened cores.
Techniques for dealing with these faults exist, but they come at a cost. Designers
need accurate soft-error estimates early in the design cycle to weigh the benefits of
error protection techniques against their costs.
The choice of the soft core is mainly driven by the following factors:
1. Suitable licensing and sub licensing schemes for the recurring product.
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Budget (k€):
800
ESA UNCLASSIFIED – For Official Use
2. Simplicity.
3. Vendor independent toolchains.
4. High configurability.
5. High portability
The target soft core will be designed for embedded processing functions within
System on Chips. It will be optimized for hard, real-time processing, where
deterministic response is required. Small size, low power and configurable
architectural features make this type of core suitable also for multi-core
specialized applications.
Main objectives for the proposed work are:
1. Development:
a. definition of the memory/register protections needed,
b. definition of a suitable clock distribution architecture,
c. high priority interrupt on parity error in order to signal the fault to the
application,
d. definition of correct I/O voting/triplication.
2. Verification:
a. functional coverage of the core through directed and constrained random
stimuli,
b. fault injection.
3. Validation:
a. target: Microsemi RTG4 (or as an option ProAsic A3PE3000) FPGA,
b. generic SoC implementation.
4. Use Cases:
a. Flash Translation Layer,
b. CANopen,
c. Remote Terminal Unit command handler,
reference design for I/O management.
With these list of use cases we are trying to demonstrate the flexibility and
capability of such a core in the handling of otherwise complex functions if purely
implemented in hardware.
NAND Flash devices are appealing components for next generation payloads and
platforms and the possibility to handle them through a soft core that can
implement an abstraction layer on top of the low level hardware protocol (ONFI)
is of great interest.
CANopen is a standard that is getting momentum in the space market thanks to
ECSS adoption and being able to handle the protocol through a software stack on
the soft core is of increasing interest.
The above 4 phases will be sufficient to provide an IP soft core validated in
context, as well as to show the great advantage in handling complex use cases.
Deliverables:
Current TRL:
Target
Application /
Timeframe :
- Processor soft-core RTL in Verilog HDL, with an agreed licensing scheme for
ESA activities
- Test bench in Verilog HDL (covers 100% of instruction set)
- Reference design with pre-synthesis, post-synthesis, post layout, and physical
design simulations
- Software examples
- SDK
Duration
12
3
Target TRL:
5
(months)
This core can be applied wherever FPGAs are used, so in all space missions.
The aim of this activity is to bring the technology from TRL3 to TRL5.
Applicable THAG Roadmap:
Data Systems and On-Board Computers (2011)
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3.4.1.2 TD 2- Space System Software
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
2 Space System Software
Ref. Number:
G617-012SW
Budget (k€):
800
Title:
On-Board Software Architecture Demonstrator
Objectives:
Ultimate result of the Savoir-Faire, Savoir-IMA, and industrial activities
supporting the on-board software reference architecture, the activity objective is
to demonstrate the correctness of the software reference architecture concepts in
a full on-board software use case.
Starting from various prototype available from different studies (COrDets,
OSRAC, OBCP, IMA4Sp, SIFSUP, etc), the activity aims at producing a
representative on-board software featuring the usual on-board functions, and
produced following the process and architecture of Savoir.
This activity is also preparatory for small missions aiming at in-orbit
demonstration (IOD) of new mission techniques and architectures and system
concepts as well as of new approaches for their development, verification and
operation.
Description:
This includes:
- Identification or development of a qualified set of library modules
implementing the execution platform services (PUS services, I/O stack
services, OBCP interpretor, operating systems, with and without TSP, etc).
- Integrating the modules consistently into the Execution platform of the
software reference architecture.
- Definition of application components, possibly following functional chains
generic specification.
- Integration of the application components in the architecture following the
development approach described in the software reference architecture
process, therefore configuring the execution platform to the needs of the
application. Production of a demonstrator.
In order to make the study affordable, several existing prototype elements may be
reused from COrDet (some PUS and I/O stack elements for EagleEye of the Estec
laboratory), from OSRAC (some functional chain components), from OBCP (a
LUA, Java or micro-python interpretor), from IMA4Sp (partitioning of EagleEye,
Xtratum, RTEMS). For EagleEye, an Avionics test bench exists at Estec for
validation of the software, but other environments could be used.
Deliverables:
Software
Current TRL:
3
Target
Application /
Timeframe :
Application to any spacecraft identified in the Savoir perimeter (earth obs, science,
long life telecom, launcher)
Need date 2018
Applicable THAG Roadmap:
Target TRL:
On-Board Software (2014)
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5
Duration
(months)
18
ESA UNCLASSIFIED – For Official Use
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
2 Space System Software
Ref. Number:
G617-013SW
Budget (k€):
1,100
Title:
On Board Software Reference Architecture Component Model support
Objectives:
Under the umbrella of Savoir-Faire, the several COrDeT/OSRA activities are
consolidating the reference architecture principles, in particular the execution
platform services. A Space Component Model is being defined as a prototype meta
model. A prototype development tool chain is also available. Savoir-Faire has
defined a related strategy, while Savoir-IMA has defined the needs of IMA in the
Reference Architecture. Finally, SIFSUP has combined both in consistent OSRA
concept. This activity intends to support the two working groups further.
The objectives of the activity (potentially to be seen as incremental in a stepped
approach) are:
1) Support the scenario which has been discussed by Savoir-Faire, i.e. avail
support to use the Space Component Model either as a native metamodel
with an editor, or as an equivalent UML profile with a UML tool, or a specific
DSL, adapted to industry practice.
2) Elaborate an "external model" approach, where the SCM model is
complemented with external models dealing with specific aspects such as:
avionics busses, space-ground interface, concurrency view for schedulability
analysis, TSP, etc.
3) Consolidate the interface with avionics modelling techniques at the level of
the deployment view/physical description of the hardware platform,
including the busses (e.g. 1553) and links (e.g. SpW) deployment.
4) Having done activities 1 to 3, the next objective is to consolidate the editors
used to capture the models. For this purpose, an open source approach
would allow to share the investment within a larger community such as
aeronautics, automotive and space.
This activity is also preparatory for small missions aiming at in-orbit
demonstration (IOD) of new mission techniques and architectures and system
concepts as well as of new approaches for their development, verification and
operation.
Description:
The activity shall include:
1) The production by model transformation of a UML model (e.g. based on
Marte, Chess), or a specific DSL, strictly equivalent to the SCM, such as a
model described in the SCM can be translated into the UML profile or DSL,
and the opposite.
2) List the needs for the potential external models associated to SCM, sort out
the existing and the new ones, define their interface, define the semantic of
the new models, define the exchange language and prototype.
In particular, integrate the tools developed in a previous TRP to enable the
IMA System Architect to model the system in order to perform system
design and allocate and optimise the use of the available resources, including
the CPU time and I/O for each partition.
3) Integrate the avionics modelling techniques developed in a previous TRP (or
using open source tools like Capella) to allow the avionics architect to check
the hardware and busses performance.
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4) Assemble the modelling and interchange tools and demonstrate the overall
system.
The outputs from these tasks shall be installed and demonstrated within the
ESTEC Avionics Lab.
Deliverables:
Software
Current TRL:
3
Target
Application /
Timeframe :
Impacts next generation of avionics/software for Telecoms, Earth Observation,
Rovers, constellation, swarm, formation flying, Navigation missions; also applicable
for next gen avionics/software for Launchers.
Supports Savoir-Faire and Savoir-IMA groups
Need date: 2018
Applicable THAG Roadmap:
Target TRL:
On-Board Software (2014)
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5
Duration
(months)
18
ESA UNCLASSIFIED – For Official Use
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology Domai
2 Space System Software
Ref. Number:
G617-252SW
Budget (k€):
600
Title:
SW for Scalable Sensor Data Processor ASIC - Qualification for flight
Objectives:
The objective of this activity is to complete the validation and to qualify the SW
libraries developed in the frame of the previous TRP needed to support the
Scalable Sensor Data Processor Multicore DSP ASIC developed for JUICE and
other applications.
The aim is to have a qualified set of SW libraries for the SSDP ASIC according the
ECSS SW Standard, and improvements of the SDE with respect to user
friendliness and capabilities.
Description:
The need for processing power on board of spacecraft, and in particular for many
types of payloads, is steadily increasing. Higher processing power allows to do
more complex on-board pre-processing, data selection and compression, and
allows to reduce the requirements towards the space-Earth communication link
by reducing the data volumes that need to be transmitted. In addition, increased
processing power is also needed for specific applications such as optical
navigation for exploration vehicles, where the reliable and fast processing of
image data is key to mission success.
JUICE is a mission to the Jupiter system and its moons Callisto, Ganymede and
Europa. It had been proposed as an L-class candidate mission for the Cosmic
Vision 2015-2025 and has recently been selected for Definition Phase Study.
Specific requirements of this mission include, in addition to the strong need for
efficient power consumption and mass, high radiation tolerance (in the order of
hundreds of krad) due to the specific challenges of the Jupiter system. Future
Lunar or Mars lander are foreseen to exploit optical navigation methods for
controlled entry, descent and landing, creating a need for high processing power,
predictable and combined with efficient interfaces to next generation imaging
sensors, with low mass and low power consumption. These mission and
technology requirements form the background of this activity.
The activity Scalable Sensor Data Processor (SSDP) has been started in mid 2013,
however it does not include a suitable flight SW.
An intermediate TRP activity is foreseen to extend this contract to design, develop
and test the SW libraries needed to support this multicore digital signal processor.
This GSTP will finally qualify the SW for flight and improve the SSDP SDE.
-
Finalize the SSDP software requirements.
Develop the completed set of DSP library functions.
Develop the qualification test suite software.
Qualification of the drivers and APIs for all ASIC functions following the
ECSS SW Standard.
- Improve SDE wrt LEON / DSP integration, debug support, and user
friendliness.
Deliverables:
- SW (DSP libraries)
- qualification test suite
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- updated SSDP SDE
- all documentation
Current TRL:
Target
Application /
Timeframe :
3
Target TRL:
6
2018
Applicable THAG Roadmap:
On-Board Software (2014)
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Duration
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18
ESA UNCLASSIFIED – For Official Use
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology Domai
2 Space System Software
Ref. Number:
G617-253SW
Title:
Qualification activity for COTS IMA Kernel
Objectives:
The overall purpose of this activity is to build on the work being performed in the
ongoing GSTP activity (IMA Separation Kernel Qualification CampaignPreparation). It will take and refine the defined qualification framework, adapt
existing use cases, analyse for requirements that cannot be tested, design and
develop validation tests suites, set-up a Software Validation Facility and execute
test campaigns.
Description:
Budget (k€):
420
In order to address the increasing complexity of spacecraft avionics, ESA is
adopting a technological solution from the aviation domain: Integrated Modular
Avionics (IMA). In the early 1990s, the aeronautical domain defined a solution
which, by means of software partitioning, allows for integration of several
functions onto the same computational node while still keeping them separated
from each other in a way which also preserves many of the benefits of a federated
systems approach. The IMA approach reduces the required mass, volume and
power for a given set of functions or applications.
IMA in the aeronautical domain is based on the ARINC 653 standard. ESA has
studied how IMA could be adopted in the space domain; an approach named
IMA for Space (IMA-SP for short) has been introduced providing an IMA-SP
Platform. The IMA-SP platform is dedicated to supporting the time and space
partitioning of the spacecraft applications. The core software component is called
the System Executive Platform software (SEP). The IMA-SP platform is thus
considered to be composed of the following high-level components:
- Hardware node(s).
- System Executive Platform (SEP) with the separation kernel: designed to
execute independent partitions according to a static schedule and
responsible for inter partition communication and TSP Abstraction Layer
(equivalent to APEX).
- Guest OS (optional) inside the partition(s). It is designed to execute
independent processes according to a local scheduling policy.
- System support services inside dedicated partition(s).
- Application support services.
The TSP Abstraction Layer is derived from the ARINC 653 and allows the SEP to
offer services to the hosted applications that comply with the previously
identified IMA-SP requirements. Above the Abstraction Layer are the System
and Application support services.
The studies initiated by ESA have established the following IMA Separation
Kernels as the basis for partitioning activities within the Agency: AIR, PikeOS
and XtratuM. For this study, the conformance of one dedicated separation kernel
will be assessed. This kernel will further be the target of a subsequent more
detailed case study.
Proper implementation of time and space partitioning requires support from
hardware. In order to protect memory regions, an MMU (Memory Management
Unit) is in principle required. For this reason, the hardware used in this activity
shall conform to the minimum hardware platform for IMA-SP as defined by
SAVOIR IMA. The hardware platform is as a minimum based on a LEON2-FT
with MMU, or a LEON3-FT.
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There is an ongoing GSTP activity preparing for future IMA Separation Kernel
qualification (G607-029sw, IMA Separation Kernel Qualification: Preparation).
It includes consolidation of requirements, technical as well as related to the
development process; definition of the qualification process; and identification
and evaluation of verification and validation techniques. The outcome of that
activity will provide a qualification framework containing basic technical and
process requirements that need to be fulfilled and the overall process for
qualification together with identification of the artefacts required.
The overall purpose of this activity is to continue and build on the previous GSTP
project, taking as an input the defined qualification framework assessing the
kernel PikeOS. It consists of the following tasks:
- ECSS E40 Q80 compliance assessment of PikeOS artefacts constituting
the qualification evidence
- Refinement of the qualification framework material (generic validation
test plan and techniques) made available as output of the previous
activity to fulfil the needs of the COTS product
- Consolidate the Validation test strategy resulting from the preparatory
activity and assess necessary robustness and stress tests to extend test
suit for the case of COTS hypervisor.
- Identify additional tests focus on FDIR capability of the dedicated kernel.
- Design and development of the validation tests suites
- Outline and execute the analysis foreseen to verify non-functional
requirements where analyse is the assigned validation method.
- Set up Software Validation Facility in hybrid configuration for one or
more space representative configurations to be determined - configure
subsequently PikeOS product + test application SW
- Execution of test campaigns on the various scenarios and
configurations/analysis of results and reports, In conformance with
ECSS E40/Q80.
Deliverables:
The ECSS defined artefacts for a qualification activity including assessment
analysis, product service history as well as target descriptions
Current TRL:
4
Target
Application /
Timeframe :
Target TRL:
6
TRL 6 in 2018
Applicable THAG Roadmap:
On-Board Software (2014)
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Duration
(months)
18
ESA UNCLASSIFIED – For Official Use
Domain – Specific
Area
GENERIC TECHNOLOGY - CORE
Technology Domain
2 Space System Software
Ref. Number:
G617-254SW
Budget (k€):
700
Title:
Qualification of RTEMS Symmetric multiprocessing (SMP)
Objectives:
The objective is to qualify the RTEMS version for the new multi-core
microprocessors according the ECSS SW standard to enable the usage of a safe
Real Time Operating System in all future payload missions.
Description:
The market for Real-Time Embedded Systems has experienced an unprecedented
growth, and is expected to grow for the foreseeable future. Because of the
competition on functional value, measured in terms of application services
delivered per unit of product, the embedded industry is faced with rising demands
for greater performance, increased computing power, and stricter costcontainment. These factors put pressure to deliver increasing performance for
future embedded processors, as well as to reduce the number of processing units
used in the system.
Space applications are not immune to this trend and in the past years ESA
prepared several studies to arrive prepared to this challenge. ESA has procured a
quad core processor, the NGMP, in advanced development phase and it is
available from third party a dual core processor, the GR712, ready to flight. From
SW side, thanks to TRP, ESA has also started the procurement of the version of
RTEMS for multi-core, standard de facto in the European space business.
Starting from the version resulting from the TRP activity and from the previous
qualification of the RTEMS for single core, the tasks requested are the following:
- analysis and definition of the System requirements
- analysis and definition of the SW requirements
- development of the additional components, in necessary
- development of the qualification test suite
- documentation as necessary
the deliverable is the RTEMS SMP ready to flight, the related test suite and
documentation compliant with ECSS SW Standard.
Deliverables:
Software
Current TRL:
3
Target
Application /
Timeframe :
Target TRL:
5
2018
Applicable THAG Roadmap:
On-Board Software (2014)
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Duration
(months)
24
ESA UNCLASSIFIED – For Official Use
3.4.1.3 TD 3- Spacecraft Electrical Power
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
3 Spacecraft Electrical Power
Ref. Number:
G617-016EP
Title:
Enhancement of COTS supercapacitors for space and characterisation
Objectives:
To adapt COTS supercapacitors for space applications requiring high power
Description:
COTS Supercapacitors will be adaptated to comply with space requirements for
missions requiring high power (i.e radar, lidars...) and in line with outcome of
previous ESA study ("Evaluation of supercapacitors and impacts at system level").
In a first phase the most promising COTS supercapacitor will be selected, changes
to be made to meet space requirements will be evaluated (packaging modification,
sealing...)
In a second phase, a module will be designed, manufactured and tested: electrical,
mechanical tests and life tests. The balancing system will also be studied and
implemented in the module.
Deliverables:
Supercapacitors module and associated data pack
Current TRL:
Target
Application /
Timeframe :
Budget (k€): 300
4
Target TRL:
6
Duration
(months)
Missions with radars/LIDARs - 2018
Applicable THAG Roadmap:
Electrochemical Energy Storage (2014)
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Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
3 Spacecraft Electrical Power
Ref. Number:
G617-018EP
Budget (k€):
150
Title:
Development of a new glass forming process
Objectives:
To develop a new glass forming process for future generations of solar cell
coverglasses
Description:
A new glass forming process is needed to produce larger coverglasses with
improved thickness uniformity, compatible with future solar cell needs which will
be driven by 6 and then 8 inch semiconductor wafer production. This is expected
to result in coverglass weight savings of ~10% based on thickness uniformity
alone. However, it requires a significant change to the current forming process
that will be a long term project.
As a first step in order to enable a new forming process, a new computer
simulation of the glass forming process needs to be developed and validated
against the current design during the next iteration of glass melting. This is
necessary in order to understand the interaction of the viscosity profile within the
molten glass with the forming elements at temperatures of around 1000C.
As a later step, implementation of the design modifications necessary for trials on
the full scale melter will need to be coordinated with the rebuild of the refractive
blocks which form the melter chamber, an operation which is performed
approximately once every 5 years. Since the next rebuild will be performed this
year before any design adaptation is available, implementation and trial of the
design modifications to the glass forming will be funded by a later activity.
In the meantime, requirements for the largest requested configuration (2 cells
from one 6 inch wafer) can be met, though a new process will improve the initial
flatness, reduce the need for later flattening and hence impove yield. It will also
facilitate production of toughened glass.
Deliverables:
Prototype
Current TRL:
2
Target
Application /
Timeframe :
2018
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Solar Generators & Solar Cells (2009)
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24
ESA UNCLASSIFIED – For Official Use
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
3 Spacecraft Electrical Power
Ref. Number:
G617-019EP
Budget (k€):
500
Title:
Yield increase and cost reduction for the 6'' wafer production
Objectives:
Cost reduction and reliability improvement of 6'' Ge wafer prodcuction.
Description:
A critical process step in the wafer production is the cutting process of the
Germanium ingot; the initial thickness of the wafers after this cutting process as
well as the kerf loss are basic parameters that influence the final yield - the
smaller the initial thickness and the kerf loss the higher the number of wafers per
ingot and the higher the potential yield. As a result wafer costs can be significantly
reduced.
Once a stable 6'' wafer production has been established, it is required to perform
this process improvement and cost reduction exercise.
The activity will include the following tasks:
- Reducing the distance between the wires of the wire saw to get thinner but
more wafers from one ingot.
- Reducting the thickness of the wires of the wire saw and/or the size of the
particles in the slurry basically performing the cutting which aims for
reducing the kerf loss.
Both improvements need to be carefully optimised especially by maintaining
compatibility with subsequent process steps and the yield by avoiding increased
breakage.
Finally, also the quality of the wafer characteristics need to be maintained which
will require adaptation of all process steps to the reduced initial thickness of the
wafer.
Another task is to optimise the recycling processes of the Ge material which is
wasted along the different process steps from ingot to final wafer.
Deliverables:
Engineering Model
Current TRL:
4
Target
Application /
Timeframe :
All missions/2018
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Solar Generators & Solar Cells (2009)
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ESA UNCLASSIFIED – For Official Use
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
3 Spacecraft Electrical Power
Ref. Number:
G617-020EP
Title:
Improved Ge wafer technology for multi-junction solar cells III
Objectives:
The main objective of this activity is to improve the quality of the Germanium
wafer that is a prerequisite for reaching highest efficiencies in next generation
solar cell structures.
Description:
Major improvement areas identified are "wafer strength" and "surface perfection".
Wafer strength is mainly required to avoid breakage (of wafers and/or solar cells)
and thus increase yield and decrease cost. The surface of the Germanium wafer is
the most important parameter for the success of the subsequent epitaxial process
at the solar cell manufacturer. As the quality of the epitaxy keeps on increasing, it
is ultimately the substrate that will limit the performance of the solar cell. In order
to anticipate this evolution, substrates need to be produced that only show a
minimal amount of light scattering defects. The defects shall be characterised by
the so-called "Candela tool" which is a new type of surface inspection tool capable
of inspecting ungrown substrates and to bin the defects according to their type in
pits, particles, scratches, haze, stain,etc. Minimisation of defects will be done
revising and improving all process steps from the initial crystal pulling step up to
the final clean etching step.
The wafer strength will be improved mainly by lowering the intrinsic stress and
implement a rounded edge. Intrinsic stress manifests itself as bow, warp, waviness
and total thickness variation and optimising processes shall improve these figures.
The developments needed for rounding the edge are mainly due to the thinner
wafers required by customers. Today, thin wafers do not have rounded edges
mainly because of incompatibilities of current process steps.
Deliverables:
Engineering Model
Current TRL:
4
Target
Application /
Timeframe :
All missions/2018
Applicable THAG Roadmap:
Budget (k€):
Target TRL:
Duration
(months)
Solar Generators & Solar Cells (2009)
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1,000
36
ESA UNCLASSIFIED – For Official Use
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
3 Spacecraft Electrical Power
Ref. Number:
G617-257EP
Budget (k€):
1,200
Title:
Design freeze and qualification of next generation solar cell
Objectives:
Delta-development to optimize the next generation solar cell concept especially for
End of Life.
Design shall be frozen and qualification on cell level according to ECSS shall be
performed.
Description:
The development of the next generation solar cell concept is currently ongoing.
Preliminary results on first deviced already indicate an improved performance
both, beginning and end of life, compared to the current state-of-the-art cell, the
3G30. However, there is still room for improvement especially to optimize the new
design for end of life. This is an iterative process that requires additional test
structures, irradiation tests and modelling. Once a design is found that is
optimised for end of life and demonstrates a significant improvement (about 1%
absolute in efficiency) compared to the 3G30 cell a qualification on bare cell level
shall be performed according to ECSS-E-ST-20-08C, Rev. 1.
Deliverables:
PID, once design is frozen; qualification hardware (bare cells), test report
Current TRL:
4
Target
Application /
Timeframe :
Potentially all. TRL 6 by 2017
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Solar Generators & Solar Cells (2009)
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20
ESA UNCLASSIFIED – For Official Use
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
3 Spacecraft Electrical Power
Ref. Number:
G617-258EP
Budget (k€):
400
Title:
Development of toughened solar cell coverglass
Objectives:
The objectives are to test the influence of the toughening process on different
coverglass compositions, shapes, sizes and thicknesses, followed by assessment of
the long term impact on coverglasses and solar cells when stowed in a folded solar
array configuration.
Description:
There is a trend towards thinner solar cells in order to save mass but also to be
able to realize a fully flexible solar array; this would also require flexible solar cell
coverglasses. One possibility is to use toughened glass which can tolerate a
reduced bend radius in comparison with standard coverglass material.
A toughening process has been developed by Qioptiq but has not been optimised
for all glass types and thicknesses. Additionally the toughening process influences
final component size and form.
In this activity, the influence of the toughening process on different component
shapes, sizes and thicknesses still will be assessed, followed by assessment of the
long term impact on coverglasses and solar cells when stowed in a folded
configuration.
Deliverables:
Prototype
Current TRL:
2
Target
Application /
Timeframe :
TRL 6 by 2018
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Solar Generators & Solar Cells (2009)
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24
ESA UNCLASSIFIED – For Official Use
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
3 Spacecraft Electrical Power
Ref. Number:
G617-259EP
Title:
Qualification of solar cells and solar cell assemblies from 6" wafers
with and w/o integral diode (140µm)
Objectives:
Manufacturing of the 3G30 bare solar cells from 6” wafers (6x12cm, 140µm thick)
qualification lot with and w/o integral diodes.
Qualification of 3G30 Bare solar cells for nominal GEO and LEO missions in
accordance with ECSS standards.
Qualification of 3G30 solar cell assemblies for nominal GEO and LEO missions in
accordance with ECSS standards.
Description:
The use of a larger solar cell offers a number of advantages mainly in terms of cost.
However, the large solar cell also requires some modifications in terms of
manufacturing and processing the solar cell and also the photovoltaic assembly.
Therefore, a full qualification according to ECSS is required to demonstrate that
the cell and the relevant assembly are suitable for standard missions.
Deliverables:
Solar cell manufacturing, acceptance and qualification specifications. Qualification
test plans and reports.
Current TRL:
5
Target
Application /
Timeframe :
GEO and LEO missions. TRL 6 by 2017
Applicable THAG Roadmap:
Budget (k€):
Target TRL:
Duration
(months)
Solar Generators & Solar Cells (2009)
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1,000
18
ESA UNCLASSIFIED – For Official Use
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
3 Spacecraft Electrical Power
Ref. Number:
G617-260EP
Budget (k€):
900
Title:
Pre-development of an hybrid Supercapacitor / Li ion battery system
for high power demanding applications
Objectives:
To optimise the energy storage system by the use of a hybrid Supercapacitor / Li
ion battery system.
Description:
Different space application benefiting from the use of supercapacitors were
identified in previous TRP activities
- High Power Battery Supercapacitor systems study
- Sources for high power/energy demanding devices for launchers
However, the lack of supercapacitors test results did not allow to assess in detail
the optimisation of the energy storage system in term of mass and cost.
Meanwhile, during the ARTES5.1 Activity "Evaluation of Supercapacitors and
Impact at System Level - (ended in 2014) supercapacitor cells of different
manufacturers were tested (electrical, environmental characterisation tests and
life tests). A 10 F supercapacitor from the Korean company Nesscap was selected
for designing and manufacturing a 15s2p bank of supercapacitors (BOSC). The
BOSC completed the environmental tests and passed 4 Million cycles with low
capacity fade and low internal resistance increase. However, the initially tested
Nesscap cell showed high outgassing of electrolyte in vacuum due to non-space
compatible seals. These seals were optimised by Nesscap while keeping the electric
characteristics to enable the application of these cells in space. Evaluation of these
cells is currently ongoing by Industry.
In the proposed activity, in a first phase, a system study will be run for the most
promising space applications requiring high peak power (SAR, LIDARS, pyros)
using supercapacitor test results obtained during the ARTES 5.1 activity as inputs
to assess the mass saving and cost saving by using a hybrid energy storage system :
supercapacitor/Li ion battery. European supercapacitors will also be considered in
the current proposed activity.
In a second phase, a hybrid supercapacitor/Li ion battery equipment will be
designed, manufactured and tested with most relevant space mission profiles. The
associated electronics for management and balancing will also be developed.
Deliverables:
Study Report
Current TRL:
3
Target
Application /
Timeframe :
TRL5 by 2019
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Electrochemical Energy Storage (2014)
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ESA UNCLASSIFIED – For Official Use
3.4.1.4 TD 4- Spacecraft Environment & Effects
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
4 Spacecraft Environment & Effects
Ref. Number:
G617-022EE
Budget (k€):
1,500
Title:
Highly Miniaturised Radiation Monitor Phase C-D and single-chip
(LETmeter) version
Objectives:
Based on the design of the previous TRP activity, the objective is to develop and
qualify a Flight Model of the Highly Miniaturised Radiation Monitor, in 2
versions: the monitor configuration with up to 4 ASIC sensors arranged in a stack
and the single chip version.
Description:
The Highly Miniaturised Radiation Monitor design established in the previous
TRP activity is based on mixed ASIC sensors arranged in a stack configuration
enclosed in a tiny mechanical case. The Phase A-B prototype weights only ~52 g
and is able to measure accurately radiation doses and energy spectra of electrons
and protons in a wide range of space environments. The HMRM can also be made
as small as a typical electronic component if only one packaged ASIC is used. In
that case HMRM will be limited to measure only doses/LET but it will weight only
~ 0.8 g and consume < 200 mW, thus it will be very easy to accommodate on any
type of spacecraft.
This design will be further iterated and consolidated in order to reach the level of
maturity required to proceed to the manufacturing of a flight model.
Major critical elements that require careful development are the ASIC sensors and
the back-end chip. The Phase A-B prototype includes a COTS FPGA that needs to
be replace with a flight-grade component (either a FPGA or an ASIC).
The work will be completed with a full flight qualification programme on both
version of HMRM.
Deliverables:
Flight Models
Current TRL:
5
Target
Application /
Timeframe :
Relevant for any spacecraft/mission. Needed as soon as possible
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
30
Radiation Environments & Monitoring, Effects Tools &
Testing (2009)
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ESA UNCLASSIFIED – For Official Use
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
4 Spacecraft Environment & Effects
Ref. Number:
G617-261EE
Title:
Advanced Environment Monitoring Package
Objectives:
Exploit technologies being developed under TRP for a lightweight package capable
of simultaneous monitoring of fields, plasmas and radiation on spacecraft. This
combined environments package would take advantage of miniaturization in
sensor and processing technologies, use internal processing to reduce data rates,
and provide simplified interfacing to host spacecraft.
Description:
Under TRP and other low-TRL programmes, technologies for measuring aspects of
the space environment have been pre-developed, including miniature (CMOS APS
ASIC) radiation monitoring, plasma detection (via a Bessel box), and anisotropic
magnetoresistance (AMR) magnetic field measurements. This allows a combined
package to be developed for general purpose use on missions, especially those in
hazardous/poorly-characterized orbits (EP orbit raising, high-LEO telecomms
constellations, MEO, GEO). The advantages of the additional capabilities include
the ability to monitor spacecraft charging hazards and charging levels, and EPsystem interactions. The magnetic field measurements allow disturbances to be
identified but also considerably aid the processing of the plasma and energetic
particle radiation data. The activity will assess and re-use developed miniaturized
technologies, prototype the common processing, and construct a prototype
package.
Deliverables:
Prototype
Current TRL:
3
Target
Application /
Timeframe :
TRL 6 by 2018
Applicable THAG Roadmap:
Budget (k€):
Target TRL:
Duration
(months)
30
Radiation Environments & Monitoring, Effects Tools &
Testing (2009)
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1,000
ESA UNCLASSIFIED – For Official Use
3.4.1.5 TD 5- Space System Control
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
5 Space System Control
Ref. Number:
G617-032EC
Budget (k€):
2,500
Title:
2nd Generation APS Star Tracker
Objectives:
To design, develop and demonstrate via test a second generation of APS star
trackers based on the new APS detectors currently in development (Faint Star
and/or HAS3).
Description:
The first generation of APS STRs have been very successful. In order to maintain
their world leading position a new generation based on the new and improved
detectors are needed. Such equipments also need to take full advantage of
improvments in ASIC and processor technology that have occurred since the
commencement of the first generation. It is expected that this will lead to a
smaller, lower cost, lower power consumption yet still more performant and even
more robust star tracker.
The activity will include the following key steps:
a) Technology assessment of new detectors (via breadboarding).
b) Technology assessment of new electrical design concepts (i.e. single chip
concepts, LEON IP cores etc).
c) Technology assessment of improved stray light rejection concepts and
materials for the optics including breadboard testing.
d) Conceptual design trade offs.
e) Preliminary design including algorithm improvements and s/w support for
multi-purpose hardware (i.e. easy configuration to navigation camera).
f) Detailed design supported by further breadboarding of key aspects (i.e.
optical performance, FPGA de-risking of ASIC designs).
g) Manufacture and test of an EM.
Deliverables:
Engineering Model
Current TRL:
2
Target
Application /
Timeframe :
All future missions
Applicable THAG Roadmap:
Target TRL:
AOCS Sensors and Actuators (2013)
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Duration
(months)
24
ESA UNCLASSIFIED – For Official Use
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
5 Space System Control
Ref. Number:
G617-033EC
Budget (k€):
1,750
Title:
Advanced Reaction Wheel
Objectives:
To develop a new reaction wheel utilising modern bearing and electrical motor
control technology and drawing on all lessons learnt from previous reaction wheel
developments, procurements and in orbit operations. To demonstrate this new
wheel design by test of an elegant breadboard and to show that the new design is
cheaper and easier to manufacture and integrate whilst simultaneously improving
performance (torque noise, microvibration, wheel speed measurement...) and
reducing the mass and volume of the electronics.
Description:
The activity shall design a new reaction wheel optimised for ease of MAIT and
performance and utilising new bearing, rotor and electronics technology. Key
features such as the bearing and rotor design and driving electronics shall be
breadboarded and the improvements demonstrated.
It is expected that the technologies involved could include ceramic bearings,
integrated bearing races, monolithic rotor design and manufacture, digital motor
control, digital interfaces, new lubrication systems and integral wheel speed loop.
As such several investigative hardware experiments will be required to fully
understand the new technologies and their optimum combination.
The work involved is therefore expected to be:
- Identification of key conceptual design options and features.
- Experimental prototyping of key new technologies.
- Preliminary design of the advanced reaction wheel.
- Breadboarding and testing of the preliminary design.
Further follow on work will be needed to take the preliminary design to a detailed
design and E(Q)M but that is anticipated to be the subject of a separate activity.
This follow on is expected to require a further 2M euro to complete.
This precursor activity therefore targets the development of a new reaction wheel,
in a currently underserved class of momentum storage to act also as a technology
demonstrator for eventual migration to the more used larger class of wheels in a
future roadmap.
Deliverables:
Breadboard
Current TRL:
2
Target
Application
Timeframe :
/
Target TRL:
4
Duration
(months)
21
All future science and EO missions. Possible application also to future telecoms
missions depending on end cost and telecom requirement evolution.
Applicable THAG Roadmap:
AOCS Sensors and Actuators (2013)
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3.4.1.6 TD 6- RF Payload and Systems
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
6 RF Payload and Systems
Ref. Number:
G617-039ET
Budget (k€):
1,000
Title:
Assessment of cost-effective technologies for on-board RF equipment
Objectives:
The objective is to assess the suitability of existing RF PCB solutions for on-board
RF equipment and define the necessary steps towards the qualification of the
selected technology.
Description:
Until very recently, hermeticity has been a key requirement for many types of RF
equipment ranging from professional electronics (radio-communications,
television,…), military systems to on-board equipment, whether for telecom, Earth
Observation or navigation. However, cost constraints has led to the adoption of RF
PCB technologies associated with non-hermetic packaging solution in almost all
domains, even the most stringent like e.g. military airborne radars, with the
notable exception of all the RF equipment used on-board satellites. Similar cost
constraints are also at play for the commercial satellite market which is mostly
telecom and indeed telecom equipment suffer from a constant price erosion
though not in the same proportion than terrestrial equipment. For Earth
Observation and navigation, the cost constraints may not appear at first at
equipment level but affordability of the whole system does. Indirectly, this
inevitably translates again into cost pressure for the RF equipment.
The activity will consist of the following tasks:
- Identification of suitable RF PCB technologies and existing chip level
packaging solutions.
- Selection of one or two technologies for the bread-boarding activities.
- Design, manufacturing and test of low noise receiver (representative of
telecom/navigation/EO).
- Design, manufacturing and test of power amplifier (representative of
telecom/navigation/EO).
- Definitions of steps towards qualification of the selected technologies.
Deliverables:
Breadboard
Current TRL:
4
Target
Application
Timeframe :
/
Target TRL:
5
Duration
(months)
Telecom, Navigation and EO
2017
Applicable THAG Roadmap:
Not related to a Harmonisation Subject
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ESA UNCLASSIFIED – For Official Use
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
6 RF Payload and Systems
Ref. Number:
G617-041ET
Budget (k€):
1,000
Title:
A small foot print lightweight GaN SSPA for TWT replacement in
satellite payloads
Objectives:
Development of an engineering model of a compact GaN SSPA with small
footprint and light weight to replace TWTs (Traveling Wave Tubes) in satellite
payloads.
Description:
GaN is an emerging technology, poised to replaced GaAs for SSPAs, with >5 times
higher power density, very high breakdown and operating voltages, very high
junction temperatures and high radiation tolerance.
Thanks to recent advances in GaN devices and in material technologies for
packaging and chassis, GaN SSPAs can replace TWTs with vertical or horizontal
architectures in the applications where medium or moderately high powers are
required at L,S and C bands. Applications, where mass and foot print are restricted
can benefit significantly from these GaN SSPAs. Furthermore, GaN SSPAs
inherently provides power flexibility due to its soft compression characteristic.
A GaN SSPA is proposed with vertical or horizontal architecture to replace TWTs
in one of the bands(L/S/C)
Targets: > 55 % overall efficiency, 40% reduction, both, in footprint and mass
relative to TWT is targeted. For multicarrier applications, efficiency comparable to
TWT at the same linearity shall be demonstrated. Clear demonstration of lower
cost of GaN SSPA compared to TWT shall be done.
It is a two step activity (involving modelling and design in first step and
Manufacturing and AIT in a second step).
Deliverables:
Engineering Model
Current TRL:
3
Target
Application
Timeframe :
/
Target TRL:
5
Duration
(months)
2017
Applicable THAG Roadmap:
Critical RF Payload Technologies (2014)
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ESA UNCLASSIFIED – For Official Use
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
6 RF Payload and Systems
Ref. Number:
G617-042ET
Budget (k€):
1,200
Title:
Critical materials for Traveling Wave Tubes
Objectives:
To identify European suppliers for a set of critical TWT materials/parts (ceramics,
metals and alloys), to realise an evaluation and qualification programme for the
most sensitive ones and to validate the material/part suitability for TWT
applications.
Description:
The fabrication of space-standard TWTs involves a large number of materials and
processes. This activity is meant to identify viable alternatives to existing TWT
materials due to 1) export-restrictions, 2) single source, and 3) possible shortage
due to environmental, political or technical conditions. Critical TWT
materials/parts are: a) wires from refractory metal (-alloys), with round or
rectangular shape; b) high voltage cables; c) Hf d) Glidcop; e) Fe-pure; f) CoSm
magnets; g) high performance cathodes (current densities well above 4 A/cm²).
For such materials and parts, potential solutions have to be identified and the
alternatives have to be tested and validated in order to secure the procurement of
raw/processed materials and maintain the world-wide competitiveness of the only
European TWT supplier.
The activity will be divided in two phases. Phase 1 will encompass the review and
identification of critical materials and parts; the contact with the associated
possible suppliers and setting of partnerships; the evaluation and pre-qualification
of a set of critical materials/parts w.r.t. standard requirements for TWT
applications and demanding constraints imposed by space applications. Phase 2
will be dedicated to the final demonstration of suitability of such materials/parts
for TWT applications by manufacturing and testing of a TWT BB employing the
selected European material(s)/part(s).
Deliverables:
Breadboard
Current TRL:
2
Target
Application
Timeframe :
Target TRL:
4
Duration
(months)
/ 2018
Applicable THAG Roadmap:
Critical RF Payload Technologies (2014)
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ESA UNCLASSIFIED – For Official Use
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
6 RF Payload and Systems
Ref. Number:
G617-043ET
Budget (k€):
1,000
Title:
Analogue/Digital onboard Receiver EM Development for TT&C
applications
Objectives:
Development, qualification and testing of an onboard receiver based on fully
analogue or mixed analogue/digital architecture with the capability of
demodulating and decoding TT&C uplink signals (TC & RNG).
Description:
The advent of powerful forward error correction codes such as LDPC allows for a
more power-efficient data transmission. The use of LDPC codes is being
considered by CCSDS for telecommand applications. However, from a digital
receiver point of view the use of iterative decoding algorithms would increase the
power consumption requirements. This can be mitigate by the use of analogue
decoder solutions. To prove the concept a TRP activity was completed.
Based on the analytical trade-offs of Phase 1 of this TRP activity, the use of
analogue decoders for short data blocks (1 few hundreds of information bits per
block) and moderate data throughput (a few Mbits/sec) were considered to
provide the highest energy savings in comparison to the digital decoder
implementations. This combination of the information block size and throughput
is particularly relevant for the satellite telecommand applications, especially for
missions with an extremely stringent requirement on the power consumptions,
considering a 100% duty cycle of receiver chain.
The feasibility of a fully analogue receiver for TC applications have been
demonstrated during phase 2 of this activity. A fully functional prototype of a
single-chip BPSK demodulator including an LDPC 128,64 decoder was developed
and tested in that frame and achievable performances were verified.
The TRP activity proved a factor of 10 power saving of analogue technology versus
digital and a slight frame error rate improvement. However, this was achieved for
a generic mission without a specific target in a more realistic scenario.
The proposed GSTP activity aims to apply the proved concept to a real future
mission, targeting the design and development of the receiver (not just decoder)
considering the specific mission requirements and the expected evolution of
analogue and digital ASIC manufacturing technologies.
In the first part of the activities a candidate satellite shall be selected with a launch
timeframe up to 2030 among the already announced worldwide missions. For the
selected mission a trade-off between fully analogue, fully digital or mixed receiver
designs shall be carried out while considering mass, power and form factor and
specific mission requirements.
The resulted architecture shall be designed and validated through simulation,
including ASIC schematics and layout (if required). TRP results may be provided
in case relevant to support this task.
In the second phase, the contractor shall propose which blocks of the designed
receiver are more appropriate for the development and validation on the basis of
trade-off results. The activity will finalise by implementing the contractor proposal
after ESA approval.
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Deliverables:
Engineering Model
Current TRL:
3
Target
Application
Timeframe :
/
Target TRL:
5
Duration
(months)
18
Multiple missions such as Landers and orbiters requiring very low power average
consumption. The need date is 2018 for an EM.
Applicable THAG Roadmap:
Not related to a Harmonisation Subject
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Domain
NAVIGATION
Technology Domain
6 RF Payload and Systems
Ref. Number:
G617-262ET
Budget (k€): 1,000
Title:
Robust miniaturised timing sources
Objectives:
The objective of this activity is design of an EM timing source based on micromachined atomic clock technology and its validation with a life test for
performance evaluation and reliability aspects.
Description:
A number of studies have demonstrated the many advantages of miniature
battery-powered timing sources (power consumption lower than 200 mW with
stability ten times better than a quartz oscillator). Integrated in a portable user
terminal, such sources allow for ultra-fast acquisition (e.g. for secured telecom
with long spreading codes) and long coherent integration (e.g. for GNSS operation
in interference or indoor environment). Similarly, it has been shown that such
sources would significantly improve the sensitivity of some on-board EO
instruments (e.g. radiometers, radio-occultation;).
After major non-european achievements over the last years resulting in the
availability of a commercial unit, a number of studies and investigations have
flourished in Europe for the development of miniature and low power
consumption atomic clocks. Lesson learned coming from commercial product is
that reliability shall be deeply investigated before to consider such technology
mature for a space design or even for a ground application.
The selected technology has to prove a good level of design maturity with a
physical package already proved in terms of achievable performances and solid
justifications related to adopted design solutions for reliability, reproducibility
and costs aspects. The following phase is represented by a design refinement with
the development of a full integrated device, inclusive of the external package (EM
model). This model will be fully tested before proceeding with the production of 4
additional EM models. All the models will be then submitted to a long term test
not shorter than 6 months for final technology assessment.
Deliverables:
Engineering Model
Current TRL:
4
Target
Application /
Timeframe :
GNSS Receiver, Earth observation (radio occultation), all the application
requiring time synchronization without having a permanent link.
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
24
Frequency & Time Generation and Distribution - Space
(2013)
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Domain
NAVIGATION
Technology Domain
6 RF Payload and Systems
Ref. Number:
G617-263ET
Budget (k€): 500
Title:
Direct LO Generation above 100 GHz
Objectives:
To investigate direct LO generation based on backward waves oscillators (BWO)
for frequencies above 100 GHz and beyond.
Description:
One of the biggest issues related to frequency generation in the THz domain is
associated to the achievable output power. Generally the approach to achieving
source power has been either to use multipliers to generate radiation from RF
sources or to translate down in frequency from the optical region using laser and
various forms of nonlinear mechanisms. There are exceptions to this trend in that
backward wave oscillators (BWOs), a vacuum electron device, has been available
for many years and have provided power adequate for the application of interest,
namely, spectroscopy, security (i.e. body scanners), short range high speed
communication (above 200 GHz) and healthcare (cancer diagnostic).
BWO have been built by numerous companies over the years. This devices are
able to provide tens of milliwatt up to 600 GHz, but with poor reliability (low
MTBF). In the recent years this technology has been strongly reconsidered
because it can take advantages by the application of innovative manufacturing
techniques likes micromachining and new cathode designs. Micromachining can
largely improve the tolerances of the resonant structures (also interesting for
Traveling wave tubes), resulting in enhanced resolution both spatially and
spectrally. Final results are devices which can overcome current BWO design in
terms of reliability, power level, efficiency and signal purity. Related to the latter
aspect, it is worth mentioning that BWO are intrinsically tunable oscillators,
which can easily act as VCO in a PLL architecture.
Objective of the activity is to survey the feasibility of a BWO at 300 GHz with
output power above 100 mW, manufacture and measure a prototype and make an
assessment on critical technologies, including reliability aspects and compatibility
with a space application.
Deliverables:
Breadboard
Current TRL:
3
Target
Application /
Timeframe :
Find alternatives for frequency generation in the THz domain.
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Critical RF Payload Technologies (2014)
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ESA UNCLASSIFIED – For Official Use
Domain
NAVIGATION
Technology Domain
6 RF Payload and Systems
Ref. Number:
G617-264ET
Title:
Broadband Satellite Channel Emulator for
Telecommunication Links
Objectives:
The objective of this activity is to develop and validate a Broadband Satellite
Channel Emulator of up to 3GHz bandwidth under different realistic satellite
channel impairments of Earth Observation and Telecommunications links.
Description:
Nowadays, high speed Ka-band links of up to 500Mbaud exist for Earth
Observation with the expectation for the symbol rate to even further increase in
the near future.
In addition, in Telecommunications, a high BW of up to 2.9 GHz is assigned to
the uplink and downlink of non-military Ka-band satellite services. Also, the
exploitation of the larger offered bandwidths available on the Q-, V- and W-bands
slowly becomes a necessity.
Even for just 500Mbaud, to clearly model the non-linear effects and to emulate
also multicarrier capabilities, a broadband satellite channel emulator of up to
2GHz is required. As such unit is not yet available in the European industry and
not only, it is essential to initiate such development in order to validate the
performance of ground segment equipment in a laboratory environment before
going over live trials, whenever such is required.
The activity shall thus go through the following steps:
- Define the models of the satellite channel (including uplink, payload and
downlink) impairments over the maximum exploited bandwidth of state of
the art Ka-band and future Q-, V- and W-band Earth Observation and
Telecommunication links;
- Consolidate the requirements of a broadband channel emulator of up to 3
GHz bandwidth for such links, including the characterisation of the expected
link performance degradation under different channel impairments (e.g.
channel fading, link delay, group delay, phase noise, thermal noise profiles,
Doppler profiles, linear and non-linear distortion, interference, frequency
and timing offset etc.);
SW, FW and HW design and development of the unit and formulation of a
detailed test plan;
- Thorough laboratory validation of the unit performance under combinations
of different satellite channel impairments.
Deliverables:
Design documentation, Broadband Satellite Channel Emulator.
Current TRL:
3
Target
Application /
Timeframe :
TRL 5 by 2017
Applicable THAG Roadmap:
Budget (k€): 1,000
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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Earth Observation and
18
ESA UNCLASSIFIED – For Official Use
3.4.1.7 TD 7- Electromagnetic Technologies and Techniques
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
7 Electromagnetic Technologies and Techniques
Ref. Number:
G617-048EE
Title:
Testing of passive inter-modulation (PIM) products using antenna
Near-Field testing approaches
Objectives:
The objective of this work is the demonstration that Passive Inter-Modulation
(PIM) products can be conveniently measured in near-field testing facilities that
are nowadays available at several places. The benefit is the availability of near-field
processing which permits the localization of the PIM sources.
Description:
Passive Inter-Modulation products cause very severe issues for space applications
when the satellite embark antennas or instruments operating at different
frequencies in both transmit and receive modes. This is the case for navigation
satellites with navigation and search & rescue antennas, for earth observation with
altimeters and radiometers using multi-channel downlinks as well as
telecommunication. Occurrence of PIM-products in antenna assemblies
comprising multi frequency feeds, gridded reflectors and/or frequency selective
surfaces (dichroics), mesh type reflectors or reflect arrays might be difficult to
trace back to a certain location. When a near-field facility is used, the coherent
receiver channel can be locked to a desired harmonic frequency and a coherent
near-field data set can be collected at a frequency of interest at which potentially
PIM might be present. Such a scenario is not novel, as NF testing on a harmonic
frequency was performed in the late seventies already (Georgia Tech University)
and this concept was looked into for a mesh reflector in S-band in Japan using
planar scanning. Nevertheless, a demonstration of the benefits, potential and
limitations would be of great benefit. For this purpose, the activity will:
- Define a testing scenario for PIM testing for an advanced satellite antenna
with PIM criticality
- Investigate and identify test facility aspects and modifications needed of
test ranges (equipment needed, channel isolation aspects, test facility
requirements).
- Configure a demonstration and perform planar NF testing for PIM
purposes with a representative antenna under test for different testing
conditions.
- -Establish recommendations on HW and SW facility developments
enabling Planar Near Field PIM testing.
Deliverables:
Study Report
Current TRL:
3
Target
Application /
Timeframe :
Navigation, Earth Observation, Telecommunication /2018-2020
Applicable THAG Roadmap:
Budget (k€):
Target TRL:
Duration
(months)
Telecommunications Reflector Antennas (2009)
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18
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Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
7 Electromagnetic Technologies and Techniques
Ref. Number:
G617-049EE
Budget (k€):
600
Title:
Flat petals compact unfurlable antenna for small satelittes
Objectives:
The objective of the activity is to demonstrate the feasibility and performance of a
large planar antenna apertures compatible with small platforms where a very low
stowage volume is imposed. As compared to parabolic reflectors, planar antenna
can be split in several flat panels to enable very low stowage volume.
Description:
Antenna aperture size is expected to grow for Earth Observation and Science
higher sensitivity instruments and access to the end users with small terminal.
This is anticipated not only for large platforms but as well for small and mini
satellites. In such case even 3 meter aperture shall be folded and "built" in space in
order to fit with the strong volume constraints imposed by low cost launchers.
Besides reflector antennas addressed in the Telecommunications reflector
antennas harmonised in 2009, there is a strong interest for developing planar
antennas with low areal mass and losses. Concepts based on direct radiating
arrays, conjugate matching metasurface and reflectarray/ transmitarrays are
expected to become competitive with respect to reflector antennas. Passive
reflectarrays are well known to perform a focusing system from a planar (or set of
planes) aperture. Conjugate matching metasurface integrate the feeding sytem in
the plane avoiding the neeed for a mast to suppport the feed. Transmitting array
avoid feed blockage and are well suited for large scanning domains. All the
features make these concepts very attractive and with very low stowed volume but
development shall be performed to ensure that the areal is kept under control and
that the RF performance are optimised.
For large aperture it is anticipated the use of passive antenna configuration
possibly using membrane technology that can bring low mass solution .They are
usually made of thin metallised polyimide films requiring tensioning by an
external device. For 1 D deployment, solution based on pantograph shows strong
potential, For 2 D deployment inflatable devices are of strong interest to generate
a planar structure or a convex/concave shape.
This activity will design a large antenna aperture for small satellites with very
small stowed volume. The critical elements of the antenna aperture will be
developped to validate RF/mechanical/thermal performance.
Deliverables:
Engineering Model
Current TRL:
3
Target
Application /
Timeframe :
High resolution instruments and high gain antennas/2018
Applicable THAG Roadmap:
Target TRL:
Array Antennas (2011)
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Duration
(months)
18
ESA UNCLASSIFIED – For Official Use
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
7 Electromagnetic Technologies and Techniques
Ref. Number:
G617-050EE
Budget (k€):
500
Title:
THz Testing Facility Development
Objectives:
This activity is devoted to model, design, and breadboard critical parts of a THz
testing facility (up to 1.2 THz) enabling European capability in this domain.
Description:
Currently, the operational frequency bands for both future Science and Earth
Observation missions are moving up in frequency (JUICE, ICI) and the
requirements for these instruments go well beyond those of related THz
instruments developed up to now. The consequence is that the accuracy required
on the measurement and characterization/validation of these instruments has
become very demanding and today no tools or facilities exist to fully measure the
proposed instruments.
This activity shall identify the future needs wrt frequencies, DUT (device under
test) dimensions and radiated performance requirements.
The second part of this activity shall emphasize on modelling and design of the test
facility identifying system criticality and considering both near field and far field.
Next, critical parts of the facility shall be developed, manufactured and
demonstrated at breadboard level.
The last part of this activity shall propose a development and realisation approach
expressed in a technology roadmap that eventually leads to the construction of an
operational THz test facility.
Deliverables:
Critical hardware as breadboard,technology roadmap
Current TRL:
3
Target
Application /
Timeframe :
EO and science instruments\2017
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
18
Technologies for Passive Millimetre & Submillimetre Wave
Instruments (2010)
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Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
7 Electromagnetic Technologies and Techniques
Ref. Number:
G617-053EE
Budget (k€):
1,000
Title:
Qualification of novel grounding for composite structural panels
Objectives:
To qualify the grounding of equipment housings to the structural panel through
their feet by the way of modified inserts implementing direct electrical connection
to the CFRP via rivets.
Improvement with respect to current practice (bonding stud + grounding strap +
dedicated insert), which results in poor grounding at high frequency.
Description:
The current practice of grounding on CFRP-skin structural panels is to ignore the
electrical properties of the CFRP (conductivity approx. 0.001 that of aluminium)
and to set-up a network of so-called "ground rails" usually implemented as
aluminium strips a few cm wide and a few tenths of mm thick, that interconnect
the chassis of the various electronic units.
This recurrent design practice involves constraints in terms of mass and layout
and results in a mediocre high-frequency grounding of the electronic units to the
panel, with consequences in terms of common mode and radiated emission.
R&D activities have shown that, unless the rails would be made very wide and
would track the harness throughout the satellite, which would virtually result in
implementing an aluminium ground plane on top of the CFRP, only the low
frequency part of spurious currents (common mode currents) flows through such
rails (approximately up to a few 100 kHz). Higher frequency common mode
interference actually flows through the panel in spite of its lower conductivity,
simply because of its shape as a panel.
As a consequence, the standard design would benefit from being modified by:
1) Replacing the flat ground rails with round wires easier to implement and
sufficient to handle fault currents and to ensure low frequency bonding
2) Ensuring inductance-free bonding of the electronics units to the CFRP
through their feet and rivet connections
Activity:
1) Requirements specification of the novel grounding method.
2) Qualification plan.
3) Design and manufacturing of breadboards.
4) Characterisation of the grounding before environment tests.
5) Mechanical and thermal tests.
6) Characterisation of the grounding after environment tests.
Deliverables:
Prototype
Current TRL:
3
Target
Application /
Timeframe :
Industrial competitiveness (All Spacecraft)/2018
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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ESA UNCLASSIFIED – For Official Use
3.4.1.8 TD 8- System Design & Verification
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
8 System Design & Verification
Ref. Number:
G617-055SW
Budget (k€):
1,000
Title:
Adaptation and Demonstration of MBSE for a real project (Pilot)
Objectives:
Apply methods and tools supporting model-based systems engineering in the
frame of a real project to demonstrate usefulness and benefit to industrial and
Agency engineering teams.
Description:
Methods and tools to support Model-based (or digital) systems engineering have
substantially progressed in the recent years. More and more disciplines have
digital representations of engineering data and system descriptions in their
discipline.
The challenge remaining today is the application of these new methods and tools
at system level, establishing configuration controlled traceability between
engineering information of different system parts and disciplines.
To achieve the most realistic case for the system-level engineering support by
modelling it is necessary to use actual project data, generated by the engineering
teams during the design, development, manufacturing and verification process.
It is proposed to establish a dedicated modelling team to support a project team.
This modelling team should take results of the engineering work and remodel
them in the appropriate way at system level, ensuring the principles of modelbased systems engineering (ensuring the full traceability between the different
subsystems and disciplines, ensuring proper configuration control, establishing
the verification traces to element level breakdown...) and present these models in
an adequate form back to the project team in order to evaluate their usefulness.
To minimize any impact on a project schedule and programmatic, this activity
needs to be run independently from a programmatic point of view. However,
commitments need to be made by the project team to guarantee the transparency
of data and processes between the engineering and the modelling teams.
Programmes to be considered as potential cases should be in the appropriate
phase of the life-cycle (beginning or just before phase B).
Deliverables:
Current TRL:
Full project information in a digital form, navigable and exchangeable between
team members as well as accessible by the customer.
Evaluation report containing assessment of usefulness, effort required (for
generating the models) and effort saved (e.g. by generating derived
documentation). Identification of roadmap to achieve the introduction at industry
and Agency level.
Duration
5
Target TRL:
7
24
(months)
Target
Application /
All future missions
Timeframe :
Applicable THAG Roadmap:
System Data Repository (2014)
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Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
8 System Design & Verification
Ref. Number:
G617-056SW
Title:
A Generic Mapping Toolbox for Space CAE Data
Objectives:
- Development of a software library for the mapping of CAE data across
domains, with a focus on thermal, structural and fluidic analysis.
- Selection and/or development of graphical tool to support the mapping of the
data.
Description:
The mapping of computation analysis data between tools is always a major
challenge when running multidisciplinary analysis. Examples are (not exhaustive):
- Thermo-Elastic: Mapping of temperatures from thermal analysis tools to
structural codes.
- Aero-Thermal Heating: Mapping of CFD data (e.g. heat fluxes) to a thermal
models for temperature predictions in the structure.
- Opto-thermal mechanical.
These data exchanges usually involve a transfer of the data between different
meshes, often with different levels of refinement and abstraction. Moreover, the
underlying numerical methods typically differ between disciplines with Finite
Element, Finite Volume/Difference and Lumped Parameter modelling typically
used for structural, CFD and thermal analysis respectively.
Past projects have sought to develop ad-hoc point to point data transfer tools. One
such example is the SINAS tool developed for the mapping of thermal data to
structural FE codes. This tool provides a quality mapping for temperate data,
however, it is in need of work to bring it up to date and to remove some historical
S/W dependencies.
The proposed activity would involve the development of a toolbox for the generic
mapping of CAE data. It should support all of the major analysis methods namely,
FEM, FV, and LPM. As far as possible the toolbox should be independent of actual
tool formats (e.g. ESATAN or NASTRAN) but rather use a neutral mesh
representation and, where possible, open standards such as STEP-TAS. The
interface to specific tools or solvers can then be handled via dedicated plugins.
To carry out the mapping some sort of graphical environment is essential to
support the engineer. For example SINAS uses MSC Patran as a graphical
environment and geometrical engine. Unfortunately this specific dependence has
actually restricted the use of SINAS due to the reluctance of some industrial
entities to use MSC Patran on the grounds of cost/availability/training etc.
Learning the lessons from this, the proposed activity would also seek to identify a
suitable generic graphical environment that could be used. Essential properties of
such a graphical environment (in addition to being functionality adequate) are low
cost and openness for customisation.
Deliverables:
Software
Current TRL:
2
Target
Application /
2017
Timeframe :
Applicable THAG Roadmap:
Budget (k€):
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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18
ESA UNCLASSIFIED – For Official Use
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
8 System Design & Verification
Ref. Number:
G617-057SW
Budget (k€):
450
Title:
Exchange of Engineering Data Between System and Sub-System Levels
Objectives:
- To develop a formal mapping between system level data models (e.g. E-TM-1023) and subsystem data models (e.g. STEP-TAS).
- To demonstrate the mapping using an automated data exchange tool and data
from real spacecraft project.
Description:
The ECSS Technical Memorandae E-TM-10-23 and E-TM-10-25 provide formal
data models for the representation of system engineering data including, for
example, the full spacecraft product tree and associated parametric data.
At the same time for the different sub-system there exist similar data models
which focus on the domain specific data required for design, verification and
operations. As a illustrative example, the STEP-TAS protocol is used in the
thermal domain for the neutral representation of thermal models, analysis results,
test data etc. STEP-SPE is used similarly for space environmental models and
data.
The proposed activity would develop a formal mapping between the system level
data models (e.g. E-TM-10-25) and the subsystem data models (e.g. STEPTAS/SPE). This "mapping" should include both the formal representation of the
data flows (e.g. using a data modelling language) and also the development of an
automated data exchange process (for example a S/W tool). It is proposed to
demonstrate the link using a current (or historical) spacecraft project and to use
the thermal subsystem (with e.g. STEP-TAS) and the space environment domain
(with e.g. STEP-SPE) as a proof of concept.
Deliverables:
Software
Current TRL:
2
Target
Application /
Timeframe :
2017
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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ESA UNCLASSIFIED – For Official Use
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
8 System Design & Verification
Ref. Number:
G617-058SW
Budget (k€):
1,500
Title:
Tool support for space system data modelling with the FAMOUS
methodology
Objectives:
The objectives of this activity are:
- The development of the fact based modelling unifying system system
(FAMOUS) methodology and associated ontology definition tool.
- The demonstration of the adequacy of such conceptual modelling methodology
and the ontology definition tool applying and using them to fully conceptual
model a real mission System Reference Database.
Description:
Knowledge sharing has always been a challenge for any large product development
and utilization. The key driver for succeeding in knowledge sharing is to ensure
that everyone has the same semantic understanding of the information that is
exchanged. This issue has been addressed by ECSS in a technical memorandum
(System Engineering Data Repository, ECSS-E-TM-10-23).
In 2009, reusing the outputs of many years of academic research related to
semantic modelling, a group of experts in fact based conceptual modelling
activities has decided to join their effort toward industrialisation of their research,
i.e. standardizing means to formalise conceptual modelling and enable semantic
interoperability. The resulting fact based modelling methodology is based on
formal logic and controlled natural language and permits formally specifying those
system requirements that address the information to be handled by any product
development.
Activities are ongoing to develop full methodology and system specifications in
order to allow the correct implementation of tools supporting this methodology.
With this contract, it is proposed to develop the FAMOUS software tool resulting
from the FAMOUS specification and to validate the approach by applying the
methodology for the development of a real space system reference database.
Deliverables:
Software
Current TRL:
2
Target
Application /
Timeframe :
All future ESA missions.
Applicable THAG Roadmap:
Target TRL:
System Data Repository (2014)
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Duration
(months)
24
ESA UNCLASSIFIED – For Official Use
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
8 System Design & Verification
Ref. Number:
G617-059SW
Budget (k€):
600
Title:
Improvement of integration and verification activities
Objectives:
Improve the return of experience from the integration and verification process
(including testing) in the functional and environmental domain.
Starting from an improved capturing of relevant information during the
integration and testing campaigns, it is important to assess this information
quantitatively to improve the verification of future projects already in the planning
phase.
Description:
Design and prototype a tool to record relevant anomalies encountered during
ground testing (functional and environmental) and potentially also relevant inflight anomalies. Essential element is the appropriate identification and
conceptual modelling of the required data at the different stages to ensure
coherence between the different domains.
Mechanisms shall be defined which allow a classification of this information and
an identification of actions to be planned during the verification process to
potentially detect the anomaly at an earlier stage.
Reference integration and verification plans shall be developed with clear link to
the relevant lessons learned. Links to the relevant system engineering information
need to be established to allow potential identification of improvements to the
engineering for future missions. It is also required to identify areas with less
efficient testing in order to streamline the overall verification approach.
A mapping from this reference plan to existing standards needs to be performed to
identify the deficiencies in the past verification process (analysis, testing) and
prepare recommendations for improvement of these standards.
Deliverables:
Prototype
Current TRL:
2
Target TRL:
4
Duration
(months)
Target
Application /
Timeframe :
Applicable THAG Roadmap:
Not related to a Harmonisation Subject
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ESA UNCLASSIFIED – For Official Use
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
8 System Design & Verification
Ref. Number:
G617-060SW
Budget (k€):
800
Title:
Rationalisation and qualification of simulator tools
Objectives:
1. Establish requirements for system simulation infrastructure and associated
components based on ETM-10-21 supporting the full project life cycle.
2. Establish reference architecture for system simulation infrastructure and
associated building blocks including interfaces and applicable standards.
3. Identify list of common building blocks and tools used within Europe.
4. Definition of qualification requirements for identified list of tools.
Based on the above
5. Alignment of existing simulation tools to allow for a smooth model-based
process (including model exchange/re-use) underlying the different ETM 10-21
System Simulator Infrastructures.
6. Develop qualification process and conformance suite for identified list of tools.
Description:
1. Establish requirements for system simulation infrastructure and associated
components based on ETM-10-21 supporting the full project life cycle: such as
model fidelity requirements, visualistation, post-processing, model
development, simulation kernel/scheduler, configuration database, test
procedure.
2. Establish reference architecture for system simulation infrastructure and
associated building blocks including interfaces and applicable standards: such
as SMP2 (E40-07), SSRA and REFA.
3. Identify list of common building blocks and tools used within Europe: such as
BASILES, SIMTG, K2, EuroSim, SimSat or MOSAIC, SIMVIS etc.
4. Definition of qualification requirements for identified list of tools: such as
functional, quality, interfaces and adherence to reference architecture and
standards.
5. Alignment of existing simulation tools to allow for a smooth model-based
process (including model exchange/re-use) underlying the different ETM 10-21
System Simulator Infrastructures: the aim is to improve overall functionality
and quality while reducing cost and development time.
6. Develop qualification process and suite for identified list of tools model fidelity
requirement: the aim is to generate a list of pre-qualified tools that can be used
in programs.
Deliverables:
Input for standardization documents
Current TRL:
4
Target
Application /
Timeframe :
2018
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
System Modelling and Simulation Tools (2012)
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ESA UNCLASSIFIED – For Official Use
3.4.1.9 TD 9- Mission Operations and Ground Data Systems
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
9 Mission Operations and Ground Data Systems
Ref. Number:
G617-061GI
Title:
Integration of ESA Ground Data Systems into Cloud Based Platforms
(PaaS and SaaS solutions)
Objectives:
Evaluate on the concrete case of SIMULUS the benefits and the challenges of
establishing a Platform as a Service (PaaS) cloud-provisioning Model for ESA
space mission critical systems.
Evaluate on the concrete case of the SIMULUS generic models as well as FARC,
PARC and DARC the benefits and challenges of Software as a Service cloud
provisioning model for ESA space mission critical systems.
Evaluate based on the above two use cases how Cloud Computing could address
some of the main challenges of modern Ground Data Systems, including
- IPR ownership of solutions developed by industry for ESA.
- IPR and licensing handling of ESA operational software and its provisioning
to the industry.
- Avoidance of revalidation of generic cross mission infrastructure in the
context of each mission data system (by using PaaS and SaaS).
- Management of ever growing baselines (HW/OS/COTS/Application).
A systematic analysis of the ***cloudability*** of Ground data Systems has been
performed with a focus on identifying the most suitable Cloud Computing model
for main ESOC ground data systems applications. The analysis has considered on
one side the different Cloud Computing models: Infrastructure as a Service /
Platform as a Service / Software as a Service.
And at the other side different cloud deployment models: Private Cloud / Public
Cloud /Hybrid Cloud /Community Cloud.
As a result of this study the following concrete candidates have been identified for
each service provisioning and deployment model :
1. SIMSAT as RnT.PaaS deployed on a private cloud (for operations) and on a
public/hybrid cloud for development.
2. SIMULUS Generic Models as RnT.SaaS deployed on a private cloud (for
operations) and on a public/hybrid cloud for development.
3. FARC, PARC and DARC as RnT.SaaS deployed on a private cloud (for
operations) and on a public/hybrid cloud for development.
We are proposing to take the next step and implement a concrete demonstrator for
each of the three identified CC application domains in in the context of a new
study and analyse the impact of a cloud based environment on the development,
deployment , validation and operation of related ground data systems.
Description:
Deliverables:
Current TRL:
Budget (k€):
200
Breadboard / Technical notes /Software Development Lifecycle documents (ECSSE-ST-40C TT4 for R&D type) Proof of Concept Demonstrator for each Scenario
(Software Implementation and deployment).
Duration
12
4
Target TRL:
5
(months)
Target
Application /
2017
Timeframe :
Applicable THAG Roadmap:
Ground Systems Software (2008)
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Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
9 Mission Operations and Ground Data Systems
Ref. Number:
G617-063GI
Budget (k€):
Title:
Demonstrator of next generation M&C protocol for space systems
Objectives:
This study will be the continuation of the TRP Study which will produce the
definition and a concept demonstrator of a common M&C protocol (CCSDS-MO
based) for ground equipment.
Description:
This activity will further define the concept, and will also develop a Demonstrator.
This Demonstrator will consist of a ground station Subsystem Controller on the
controlled system side and of an EGS-CC adapter for the controlling system side.
More specifically the study will address:
- The generic data model definition of the controlled space system (likely
focus on the space system model ECSS-70-31)
- Refinements and redesign of the output of the TRP Study (CCSDS-MO
framework and application level on top of the framework) taking into
account the data model definition.
- The design of the next generation generic ground station Subsystem
Controller based on the new system design and following the principles of
the current ground station subsystem controllers.
- The design of the EGS-CC adapter based on the new system design. The
study will also evaluate the impact on the EGS-CC Tailoring system and
identify the mechanism for importing the data model to the EGS-CC.
- Implementation of a demonstrator for one (lightweight) ground station
subsystem which will be monitored and controlled by the EGS-CC.
Deliverables:
Software
TN on updated Data Model
Generic Ground Station Subsystem Controller SRS
Generic Ground Station Subsystem Controller SDD / ICD
EGS-CC Adapter SDD / ICD
Code and documentation of the demonstrator
Current TRL:
4
Target
Application /
Timeframe :
2017 (ESTRACK Ground Station)
Applicable THAG Roadmap:
Target TRL:
Ground Systems Software (2008)
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6
Duration
(months)
300
12
ESA UNCLASSIFIED – For Official Use
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
9 Mission Operations and Ground Data Systems
Ref. Number:
G617-064GI
Budget (k€):
200
Title:
Harmonisation of Numerical Software Validation Facility (NSVF) and
Operational Simulator models
Objectives:
1) Interview and collect the opinion of all the European spacecraft prime
contractors on this topic.
2) Consolidate a business approach for viable and sustainable reuse of models
between SVF facilities and operational simulators including clarification of the
roles of SMEs in this process. The feasibility and the potential benefit of reusing SVF models as part of the production of the specific Reference Test
Facility of EGS-CC (EGS-Common Core) based systems shall also be
investigated.
3) Establish a set of key requirements on the SVF models that the spacecraft
prime contractors must adhere to in order to make the business case viable
including both technical, legal, license, risk and financial aspects. It should be
studied if these key requirements can form a common requirement basis
between SVFs and Operational Simulators.
4) Investigate the potential gain for different level of reuse:
1. At infrastructure level (i.e. reuse of Simsat/UMF for SVF).
2. Reuse at simulation level (i.e. reuse of complete spacecraft models).
3. Reuse of subsystem/individual models (ie. reuse of models for individual
spacecraft units).
5) Demonstrate the above established concepts with a case study of taking SVF
models and reusing them in Simsat based Operational Simulators.
6) Evaluate the various Reference Architectures existing in Europe relevant for
this topic and recommend solutions that would lead to further technical
harmonization within Europe and that would improve the overall efficiency in
the development and use of SVF and Operational Simulators.
Description:
Simulation model reuse between SVF facilities and Operational Simulators has
been talked about for a long time, but has never matured in practise within the
ESA context. During the last years several changes has occurred that now makes
this the right time to tackle this topic for real:
- The SVFs has moved to a pure numerical emulation of the OBSW, hence is
now much more similar to the Operational Simulators than in the past.
- The SMP-2 standard is now well known within European industry proving
a sound technical foundation for model transfer.
- The missions are under an ever increasing pressure to cut cost.
- The spacecraft electronic systems are getting more and more complicated,
making redevelopment a more and more complicated task.
- Larger and larger parts of the spacecraft software are put under IPR
restrictions making an independent development of operational
simulators harder.
Secondly it is required to study the approach in a generic way taking on board the
input also from all the other spacecraft prime contractors in Europe to ensure that
a consistent solution is found that reduces the overall cost of all ESA operations in
a sustainable way.
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Deliverables:
Breadboard
Current TRL:
3
Target
Application /
Timeframe :
2017 (Simulator Infrastructure, EO missions, low budget missions).
Applicable THAG Roadmap:
Target TRL:
Ground Systems Software (2008)
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6
Duration
(months)
18
ESA UNCLASSIFIED – For Official Use
Domain – Specific
Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
9 Mission Operations and Ground Data Systems
Ref. Number:
G617-265GI
Budget (k€):
250
Title:
Harmonisation of the EO and Science Kernels for MCS
Objectives:
1) Review of EO and Science Kernel requirements and implementation to
identify common areas and differences.
2) Review EGC-CC and MICONYS-CC implementation to identify overlapping
and missing functionality with respect to the existing EO/Science Kernel
MCSes.
3) Check feasibility of a common kernel for both EO and Science for EGS-CC
based systems including requirements specification of such a system and a
high level design.
Description:
Most MCS systems at ESOC is today build in 3 layers:
Layer 1) SCOS-2000, generic to all missions.
Layer 2) A Mission Family layer: There exist two major families at ESOC:
Science and Earth Observation.
Layer 3) The mission specific layer.
In resent years, the Mission Family layers have grown to a maturity where the
mission specific layer has become extremely thin. The maturity of the Mission
family layers however also reflects a new level of standardization/
harmonization of how ESA operates its spacecraft.
Now, this concept should be taken one step further, to check if the Mission
Family layer can be incorporated into a truly generic operational concept and
software covering both science and EO missions.
During the next years, the bottom, SCOS-2000 layer, will need to be replaced
with ECS-CC. This imply a major change in both the Science and EO family
layer.
This study would be a major step towards achieving a system architecture like
this common for all missions at ESOC:
Layer 1) EGS-CC
Layer 2) A common MIONYS-CC layer with all common ESOC adoptions/
extensions required for EGS-CC.
Layer 3) A thin mission specific layer, with equivalent minimal functionality as
the current mission specific layer.
Deliverables:
Prototype
Current TRL:
3
Target
Application /
Timeframe :
Application: All future missions based on EGS-CC.
Need date: TRL-6 by 2018 if the first generation of EGS-CC based systems
should benefit from it.
Applicable THAG Roadmap:
Target TRL:
Ground Systems Software (2008)
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Duration
(months)
12
ESA UNCLASSIFIED – For Official Use
3.4.1.10 TD 10- Flight Dynamics and GNSS
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
10 Flight Dynamics and GNSS
Ref. Number:
G617-067GF
Budget (k€):
200
Title:
Extension of the DO-IT trajectory design software for interplanetary
trajectories based on low-thrust propulsion combined with flybys
Objectives:
This activity shall extend the functionality of the DO-IT trajectory design software
such that low-thrust trajectories and flybys can be addressed as integral part of the
trajectory design problem.
Description:
The design of low-thrust interplanetary missions requires a good understanding of
ballistic mission design and a versatile software for low-thrust trajectories. DO-IT
is a prototype software tool that can be used to design interplanetary trajectories
like the ones for Rosetta or Solo. Due to the modular approach, the different
phases of a mission can be assembled together in forms of building blocks. The
software contains an optimiser that allows to further improve any possible mission
candidate. The software was tested and validated with numerous chemical
propulsion missions, both historically flown and also theoretical ones.
However, the prototype modules for low-thrust missions are only applicable in
very specialised cases. To make the tool useful for low-thrust trajectory design new
modules need to be developed. The thrust-coast structures between flybys
"learned" from BepiColombo and MarcoPolo-R shall be translated into simple
building blocks where the user only defines the departure body, the arrival body
and the transfer time (or equivalently the number of heliocentric revolutions). One
level above, a module needs to be developed that evaluates the most promising
permutations of the flyby bodies. A branch and bound utility which either runs
autonomously or is guided by the user shall be programmed to avoid the
calculation of non-physical solutions and excessive CPU-times.
There is a timely need for such a software tool in order to support the upcoming
interplanetary missions. For instance, the development of the ion-engines for
BepiColombo is coming close to a flight-readiness level and therefore it can be
expected that the efficiency of ion-engines in terms of fuel consumption will be
considered for many Cosmic Vision studies. In this context a commercialisation of
the DO-IT software has a good potential to be successful in specific areas of
mission analysis and flight dynamics in governmental agencies and industry.
Specific tasks to be performed:
- Development of building blocks for low-thrust trajectories. The most common
thrust profiles useful for interplanetary transfers shall be programmed (e.g.
coast-thrust-coast-thrust-coast between launch and Earth flyby).
- Development of Algorithm to scan the sequence of the flyby bodies. The
algorithm has to be tested and validated for interplanetary missions as well as
for missions like Juice in a planetary system with moons.
- Development of a branch and bound module. An efficient algorithm needs to
be development, that selects the most promising solutions and discards
options that have too high delta-V requirements.
Deliverables:
Software
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Current TRL:
Target
Application /
Timeframe :
3
Target TRL:
6
Duration
(months)
2017
Applicable THAG Roadmap:
Not related to a Harmonisation Subject
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3.4.1.11 TD 11- Space Debris
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
11 Space Debris
Ref. Number:
G617-069GR
Title:
Extension of combined observation-modelling
ground-based attitude vector determination
Objectives:
The activity shall extend the observation-modelling technologies to derive attitude
and attitude rate information. It shall meet the needs of contingency support
activities, active debris removal, re-entry events, and the space debris environment
modelling. In the scope of the extension of the technologies the activity shall
obtain the necessary data from radar, active, and passive ground-based systems to
further test and systematically analyse protoype methods.
Description:
Prototypes for estimation of the attitude motion vector have been developed as an
object characterisation technique. Capabilities of the prototype are being
demonstrated using observations acquired by ISAR imaging radars, and active and
passive optical telescopes. A prototype software module is now available, but
needs to be further extended to meet emerging needs from the application side,
and to consider recent and emerging sensor technology developments.
The prototype also needs to be further validated through extensive and systematic
test campaigns. It is important to address the different needs of contingency
support activities, active debris removal, re-entry events, and the space debris
environment modelling in the design and implementation of the test campaigns.
Based on the results of the prototype development and verification, a throughout
analysis of recent sensor technology enhancements and developments, a review of
the emerging use cases for attitude and attitude motion assessments, and by
considering the ongoing development of collaboration platforms to exchange
observational data, the activity shall consider available radar (ISAR imaging),
telescopes (laser and passive acquiring light curves, and imaging from ground. The
activity shall first derive implementation and extension needs, as well as test
campaign requirements. In a second step a database of the derived attitude and
attitude motion shall be established allowing for statistical analysis and long-term
comparison of the attitude dynamics of selected large test objects. In parallel, the
prototype shall be extended and improved based on the findings and the identified
needs. Finally, the application to operational processes shall be evaluated and
recommendations shall be given.
Deliverables:
Software, observation data and processing results, TNs
Current TRL:
5
Target
Application /
Timeframe :
Budget (k€):
Target TRL:
6
500
technologies
Duration
(months)
for
12
2017 (HSO Mission Operations, Space Debris Office services, debris research
community)
Applicable THAG Roadmap:
Not related to a Harmonisation Subject
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Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
11 Space Debris
Ref. Number:
G617-070GR
Title:
Feasibility of CMOS on-chip processing algorithms for space debris
observations
Objectives:
The activity shall develop and demonstrate new on-the-chip processing
capabilities for a CMOS sensor chip.
Description:
- Follow-on to the current TRP study on improvements of observation strategies
and processing techniques.
- Investigate possibilities for on-chip (non-destructive) processing.
- Investigate feasibility of simple b/w and complex grayscale operations.
- This activity shall include development and implementation of a small-scale
breadboard on a COTS industrial CMOS chip.
- Target applications are the acquisition of light curves and detection of fast
moving objects.
Deliverables:
Breadboard including software
Current TRL:
4
Target
Application /
Timeframe :
Budget (k€):
Target TRL:
5
Duration
(months)
300
12
2017 (Possible users are the space debris research community, designers and
developers of on-ground and in-orbit observing systems, potentially extended
to Earth observation services)
Applicable THAG Roadmap:
Not related to a Harmonisation Subject
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Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
11 Space Debris
Ref. Number:
G617-071GR
Budget (k€):
150
Title:
Low thrust manoeuvres in orbit determination tools
Objectives:
Development of a software module to model constant low thrust forces in orbit
determination and propagation
- Review of exisiting related modules, algorithms and prototypes.
- Development of a new module.
- Validation.
Description:
Continuous low thrust is becoming an option in spacecraft design and operation.
This is not only interesting for, e.g., station keeping of geostationary satellites that
must be considered in operational collision avoidance activities; it is also one
important aspect for end-of-life operations ensuring compliance with space debris
mitigation guidelines, and, finally, it is an aspect related to active debris removal.
Currently used orbit determination and propagation tools for space object
cataloguing and collision risk assessment do not sufficiently model these small
forces. Existing techniques in the spacecraft operations are assumed a starting
point for related developments.
A first task of the activity shall comprise a review of exisiting modules and
approaches in the operations domain, adressing algorithms and prototypes. The
needs for active debris removal studies, and of operational collision avoidance
tools shall be reviewed.
In a second task a software module shall be developed allowing estimate and apply
constant low thrust forces (by spacecraft or induced from the ground) in the
existing orbit determination software. This shall make it also possible to calibrate
low-thrust manoeuvre characteristics.
In a final task the prototype shall be validated, e.g., through using space
surveillance data and operational data on known low-thrust transfers and station
keeping manoeuvres.
Deliverables:
Software
Current TRL:
4
Target
Application /
Timeframe :
Target TRL:
5
Duration
(months)
2017 (Collision avoidance services; space debris research community)
Applicable THAG Roadmap:
Not related to a Harmonisation Subject
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ESA UNCLASSIFIED – For Official Use
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
11 Space Debris
Ref. Number:
G617-072GR
Title:
Advanced
software
Objectives:
SCARAB (Spacecraft Atmospheric Re-Entry and Aerothermal Break-Up is a 6
degree-of-freedom simulator for the re-entry of a complex spacecraft structure,
considering aerothermal and aerodynamic effects on the spacecraft structure, its
temperature and pressure distribution, its break-up and demise events, its attitude
and trajectory evolution, and the spread of its surviving components across a
ground impact swath.
re-entry
Budget (k€):
break-up
high-
and
low-fidelity
300
assessment
DRAMA (Debris Risk Assessment and Mitigation Analysis) is a tool suite to verify
the compliance of a space mission with space debris mitigation standards (e.g.
ESAs requirements on space debris mitigation). For a given space mission
DRAMA, in one of its modules, allows to perform simplified re-entry survival
predictions for an object composed of user-defined components, and risk
assessments for the population on ground within the impact ground swath. This
module is an engineering version of Scarab for missions in early design stages and
quick-look analyses.
The objective of this activity is to improve Scarab and its DRAMA engineering
version (to be kept synchronised) with some important additions that have been
identified from the extensive application of the tool in order to allow for new
obvious use-cases, a general modernization and consideration of new data and
findings (see description for a detailed list of identified upgrades)
Description:
Scarab is a complex software enriched by a user-friendly graphical-user interface
that has found wide application for the deterministic assessment of the re-entry
survivability of spacecraft elements, starting from a detailed (graphical
description) of a spacecraft design.
The software and an implemented spacecraft model covers all aspects for the
modelling of the attitude motion (moments of inertia computation, force
models,...). The upgrade shall allow to perform long-term simulation runs in
altitudes up to 2000km to determine the equilibrium attitude motion vector. The
knowledge of this vector is essential for the preparation of removal missions and
for the determination of the orbital lifetime (see next points).
Once the necessary data is already given in this single piece of software, it shall be
possible to also compute the average cross-section pointing into the flight
direction (and in randomly tumbling mode for other assessments). This essential
parameter is required to compute the orbital lifetime, which again is an important
aspect in space debris mitigation.
The upgrade shall also implement user parameter screening and consistency
checking before user input is transferred to the kernel for processing.
In the meantime, new material types enter into spacecraft design (e.g.
polyethylene tethers, silicone carbonide,...). It is essential to extend the material
database accordingly, which might require hyper-velocity wind-tunnel testing in
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some cases.
DRAMA still makes use of a static on-ground population model dating back to
1994 onto which an even growth factor is applied. The upgrade shall modernise
the database, allow for online updates and improve the population projection
approach. Also, the use of DRAMA shall be made more comfortable by providing a
component (many spacecraft components are standard commercial product and
can therefore be pre-defined and archived in an accessible library structure) dragand drop database for DRAMA. Further, the averaging of fragment surfaces need
to consider a refined approach based on the averaging of cross-section using the
assumption of a randomly tumbling motion.
Since Scarab is in use (although not ready-to-use for non-experts) and its results
have been cross-validated with US tools and observation data, a high TRL of 6 can
be assigned. The specified updates will allow to mature and harden (as well as
modernise the software) to close to perfection.
Deliverables:
Software
Current TRL:
6
Target
Application /
Timeframe :
Target TRL:
8
Duration
(months)
2017
Applicable THAG Roadmap:
Not related to a Harmonisation Subject
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ESA UNCLASSIFIED – For Official Use
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
11 Space Debris
Ref. Number:
G617-073GR
Title:
Extended stare and chase concepts
Objectives:
The objective is to develop and test stare and chase mode tracking approaches for
the initialisation of space object catalogue information. This activity shall
demonstrate space object catalogue cold start capability with the help of small
field-of-view (FOV) sensors. Prototype S/W for stare and chase guidance processes
shall be analysed in a test bed consisting of a passive optical telescope and a laser
ranging tracking system. The demonstration is successfull when the laser system
with its (roughly 10m at 800km altitude) FoV can pick-up and track an object with
initial guidance information from a passive (large FoV) telescope that performs the
initial detection during the same pass.
For the generation of orbit information, active laser tracking is a well-established
technology for cooperative targets with an on-board laser reflector, for
uncooperative targets this is an emerging technology which is expected to become
practically available in a few years.
Objects without a-priori orbit information e.g. newly generated objects due to
launches or fragmentation events are a challenge for these tracking systems,
because of their extremely small FoV. Consequently, they need a good prediction
in their topocentric reference frame leading to only short times available between
the observations in stare and chase mode. Passive optical telescopes depend on
sunlight to detect these objects, but their FoV can be large enough to fulfil the
"staring" part and generate guidance information for the laser in a very quick
manner. Demonstration of the principle along with sensor combination reflects
the most likely application case and represents the largest challenge. Hence, other
star and chase scenarios (where e.g. a tracking radar performs both the stare and
chase part are covered).
The encompasses the following activities:
- Review of the prototype algorithms for the trajectory determination and
prediction and generation of guidance information produced in a TRP
study.
- Expansion of the prototype after isolation from its current simulation
environment and implementation in a test bed environment.
- Deployment of the test bed at a Laser Ranging Station that is equipped with
a passive optical observatory.
- Implementation and test of image processing and detection software,
including streak detection and astrometric reduction.
- Closed-loop test employing both, the stare (passive telescope) and chase
(laser ranging) part in scheduled surveys targeted at reference objects.
- Improvement of the guidance algorithms and verification of the orbit
information by comparing to the reference.
Breadboard
Duration
12
3
Target TRL:
5
(months)
Description:
Deliverables:
Current TRL:
Target
Application /
2017
Timeframe :
Applicable THAG Roadmap:
Budget (k€):
Not related to a Harmonisation Subject
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3.4.1.12 TD 12- Ground Station System & Networking
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
12 Ground Station System & Networking
Ref. Number:
G617-135GS
Budget (k€):
1,000
Title:
Low Cost Meter-Class Adaptive Optics Communications Breadboard
Objectives:
The objective is the development of a low-cost adaptive optics system for meterclass telescopes(2.5-4m) for optical communications ranging from the Moon to the
Lagrange libration points with the clear specific objective to perform in a photonstarved regime and achieve a substantial cost-savings (< 1/2) over present-day
systems.
Description:
Optical communications technology offers the potential of a dramatic increase in
data-rates, specifically in down-link of science data, thereby allowing for a
substantial increase in science return.
While meter-class telescopes for optical communications only require good
"imaging" quality in the central part of their field of view in order to couple the
light into a fiber or small high-bandwidth detector, they also need to operate day &
night in corresponding thermal and straylight environments. Adaptive Optics
Systems (AOS) not only offer significant performance advantages, but would also
allow coherent communications. Two major challenges are hereby to be overcome:
- The ability to correct the wave-form of an extremely faint beam (likely to
require an artificial guide-star as reference with additional techniques to also
correct for tip-tilt) all the while.
- Minimizing the cost of the sub-system (given the need for several optical
ground stations to overcome local weather blockages in a single site).
On the other hand, the advantage over astronomical AOS is that the above
application requires to correct only specific wavelengths (around 1064 and
1550nm) and only in a relatively narrow field.
The primary goal of this development is thus the development of a demonstrator
and sub-sequent testing at an existing telescope (e.g. ESA's OGS).
Deliverables:
Breadboard
Current TRL:
2
Target
Application /
Timeframe :
Target TRL:
4
Duration
(months)
NGO; Lunar-, Solar-, or astrophysics missions in L1/L2
Applicable THAG Roadmap:
Optical Communication for Space (2012)
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ESA UNCLASSIFIED – For Official Use
Domain – Specific
Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
12 Ground Station System & Networking
Ref. Number:
G617-266GS
Budget (k€):
400
Title:
Deep Space Low Cost 4m monolithic Optical Antenna for Day/Night
Operations
Objectives:
The objective is an detailed design-to-cost for a monolithic(as opposed to
segmented large aperture) 4m class optical ground antenna. Based on existing
designs, the effort shall focus on the requirement of Day and Night Operation,
industrialization (to foresee an array of 7-9 such antennae) and cost
minimization given simpler specifications for optical communication.
Description:
Optical communication for deep space application is under technical
standardization in the Consultative Committee for Space Data Systems
(CCSDS), and designs for deep space on-board terminals are being developed
based on experience for near Earth optical communication systems.
It is very timely to prepare technologies necessary for the realization of
ESTRACK's future deep space optical communication capability. One of the
main challenges is a large effective aperture / collecting area within a very tight
budget envelope. While optical communications can benefit from a simpler
optical performance specifications, the additional requirement of day and night
operation and the associated thermo-mechanical design with metrology and
active optics are unique to the application and not known today.
The intenral Optical Antenna Study Group has established both concepts for a
deep-space optical ground station of
- 10-12m single aperture segmented primary antenna (proposed parallel
study)
- array of 7-9 antennae of 4m monolithic primary aperture - offering true
scalability (focus of this study)
as potentially a-priori feasible (within similar budget). In order to direct future
efficient developments, both concepts must be further elaborated in detail by
corresponding solid competence available in Europe.
While 4m astronomical telescopes are state of the art, and their manufacturing
is well understood, the thermo-mechanical solution for day and night
operations, and the industrialisation aspect to minimise recurring cost need to
be addressed.
Deliverables:
Study Report
Current TRL:
4
Target
Application /
Timeframe :
TRL 6 by 2020
Asteroid Impact Mission presently under Phase A/B1 study.
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Optical Communication for Space (2012)
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3.4.1.13 TD 13- Automation, Telepresence & Robotics
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
13 Automation, Telepresence & Robotics
Ref. Number:
G617-076MM
Title:
Development of technology tools for training and operations of the
METERON Mission Preparation and Training Centre
Objectives:
Software development for performance analysis of robotic missions involving
shared autonomy, teleoperation and autonomous robotic action sequencing.
Description:
Experiment training tools for robotic activity training and real-time operations
processes will be developed in this activity. Software for simulation of a the onboard segment functionality, failure injection, recovery strategy analysis, and
performance evaluation of ground and in-orbit operators. Including development
of ISS Mockup Hardware, Operations Software, Training Software, Comm's and
operational software and development of experiment software and scenarios for
the METERON in-orbit experiment on ISS.
Deliverables:
Software
Current TRL:
6
Target
Application /
Timeframe :
Budget (k€):
Target TRL:
7
METERON/2017
Applicable THAG Roadmap:
Automation & Robotics (2012)
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Duration
(months)
770
12
ESA UNCLASSIFIED – For Official Use
3.4.1.14 TD 14- Life & Physical Sciences
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
14 Life & Physical Sciences
Ref. Number:
G617-078MM
Budget (k€):
700
Title:
Self Validating High Temperature Sensors
Objectives:
Improving the accuracy of contact temperature measurements above 1300K up to
2600K and validation of a system prototype in relevant environment.
Description:
Contact temperature measurements above 1300K are challenging with respect to
lifetime and drift of the sensors. High Temperature Fixed Points (HTFP) cells from
carbon-metal eutectics (which will be the new reference for ITS-90) in
combination with W-Re (Type C) thermocouples provide a solution to check the
health of the sensors and to compensate for signal drift by using the melting and
freezing of the eutectic.
A current finalized TRP activity proved the feasibility of multi point calibration
cells. Further activities are needed to improve the design (stability, size) and gain
confidence in life test campaigns also in combination with other strategies e.g.
electrical noise thermometry (ENT).
Space applications are in the field of reentry or tests thereof e.g. in shielding
material tests in plasma wind channels. Propulsion tests, sensors for harsh
environments and materials characterization are potential applications. Terrestrial
application include the monitoring and control of all high temperature processes (
e.g. solar, nuclear or metallurgy) and in turbines. For this reason this proposal is
also of the 'Power and Energy' roadmap.
Deliverables:
Prototype
Current TRL:
4
Target
Application /
Timeframe :
Target TRL:
7
2018
Applicable THAG Roadmap:
Aerothermodynamic Tools (2012)
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Duration
(months)
30
ESA UNCLASSIFIED – For Official Use
3.4.1.15 TD 15- Mechanisms & Tribology
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
15 Mechanisms & Tribology
Ref. Number:
G617-080MS
Title:
Improvement of Solar Array Drive Mechanisms (SADM) technologies
Objectives:
To confirm the technical feasibility of a cost efficient Medium to High Power
SADM, based on the following sub-technologies pre-developments targeting at:
- Decreasing recurring cost of Medium to High Power range Slip-Rings,
including use of European source of sliding electrical contact materials.
- Decreasing recurring cost of stepper motors.
- Decreasing recurring cost of Ball Bearing.
Description:
For medium to high power and/or long lifetime SADMs, as well as for any mission
which foresees high temperature environment, a Europe dependence on nonEuropean products exists, especially with respect to electrical transfer contact
material, ball bearing cages material and electric motors/actuators technologies.
It is also mandatory to try to reduce the cost of the SADM hardware in order to
stay competitive on the global SADM market outside Europe.
This activity aims therefore at several sub-objectives:
- To define the activities/development needed to decrease recurring cost of
Medium to High Power range SADM (main components cost, I/F
standardisation and optimisation, etc.)
- To implement the finding from the first objective into sub technologies predevelopment.
 Define and implement necessary activities/developments needed to
decrease recurring cost of Medium to High Power range Slip-Rings
(including the use of new electrical transfer contact material (follow up of
the TRP “New electrical contact materials selection and assessment for
sliding contacts”).
 Define and implement necessary activities/development needed to
decrease recurring cost of stepper motors for Medium to High Power
range SADM.
 Define and implement necessary activities/development needed to
decrease recurring cost of Ball Bearing for Medium to High Power range
SADM (including the use of Duroid substitute material (follow up of the
ARTES Activity "Development of European self-lubricating materials").
- To merge all recommendations and pre-development into the design,
developments and testing of a dedicated SADM Engineering Model.
Emphasis shall also be put on a design that shall help making saving during AIT
activities. Outcome of this activity shall be the feasibility confirmation of a cost
effective Medium to High power SADM, based mainly on European technologies.
Engineering Model
Duration
24
2
Target TRL:
6
(months)
Deliverables:
Current TRL:
Budget (k€):
Target
Application /
TRL 6 by 2018-2019
Timeframe :
Applicable THAG Roadmap:
Solar Array Drive Mechanisms (2014)
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3.4.1.16 D 16- Optics
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
16 Optics
Ref. Number:
G617-084MM
Budget (k€):
1,000
Title:
Demonstrator for active WFE-correction of an imaging telescope
Objectives:
The activity will comprise the design, manufacturing and testing of a deformable
mirror and its integration and testing in an optical imaging system, in order to
demonstrate the performance improvement capabilities of active optics in optical
systems for space applications.
Description:
The increasing need for higher image resolution for space optical applications
has prompted the study of technologies aimed at improving the imaging
performance beyond what is currently achievable by classical optical systems.
Active Optics is a very promising example of such technologies, allowing to
correct for in-flight effects (such as thermo-elastic deformations, radiation
effects on optical materials,etc.) which impact the optical quality of space
instruments. The use of Active Optics can also decrease the stringent
requirements on the manufacturing quality for optical components (by
compensating residual surface figuring errors) and reduce the outage period of
missions caused e.g. by Sun baffle intrusions or eclipses altering the thermal
conditions within the instrument.
Applications of Active Optics range from e.g. Earth observation (meteorology,
security,etc.) and Space-Situational-Awareness (SSA) to science (e.g. planet
finding, large space telescopes)and Optical Communications (both ground-tospace and between spacecraft), making Active Optics a generic technology able to
find applications in all classes of optical instruments.
A breadboard of a deformable mirror (DM) is currently being developed in the
frame of a GSTP activity. The next critical step in the development of active
correction capabilities for space optics is the testing and demonstration of the
image quality improvements obtainable by a properly designed deformable
mirror in an actual optical system for a specific controlled source of
perturbations.
Two phases are envisaged for the proposed activity:
- Phase 1 includes
- Conceptual design of an active correction system based on a DM.
- Design, manufacture and testing of a suitable DM.
- Development of the control algorithm.
-
Phase 2 includes:
- Integration of the DM into an optical system (preferably making use of
an already existing telescope).
- Test of the DM correction capabilities to compensate for the
performance loss due to effects of controlled thermal and mechanical
perturbations of the optical system (representative of space
environment conditions).
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Budget Phase 1: 600k
Budget Phase 2: 400k
Deliverables:
Engineering Model
Current TRL:
4
Target
Application /
Timeframe :
2018; Applications of Active Optics range from e.g. Earth observation
(meteorology, security, etc.) and Space-Situational-Awareness (SSA) to science
(e.g. planet finding, large space telescopes) and Optical Communications (both
ground-to-space and between spacecraft), making Active Optics a generic
technology able to find applications in all classes of optical instruments.
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
24
Technologies for Optical Passive Instruments - Mirrors
(2013)
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Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
16 Optics
Ref. Number:
G617-086MM
Budget (k€):
950
Title:
Calomel-Based TIR Hyperspectral Imager
Objectives:
1) To design a Hyperspectral Imager operating in the Thermal Infrared (TIR)
spectral range based on Acousto-Optic Tunable Filters (AOTF) using Calomel
crystals.
2) To breadboard and test critical technologies, in particular the Calomel AOTF
assembly.
Description:
The successful development of the Calomel AOTF done in 2012 under GSTP
contract has put the basis for the development of Hyperspectral Instruments
working in the Thermal Infrared. The novelty of this technology requires to go
through an application study to better understand the potential of this new
technology and its possible applications, and to breadboard the novel and critical
optical elements.
The activity will comprise:
- Instrument architectural design & performance analysis,
- Application analysis of the instrument for Earth Observation remote
sensing / Planetary Survey/Scientific Instruments,
- Preliminary instrument design & identification of critical technologies,
- Breadboarding and testing of critical technologies.
The work will be performed in two phases, with the breadboarding performed
after completion of Phase 1.
Deliverables:
Breadboard
Current TRL:
3
Target
Application /
Timeframe :
Target TRL:
5
Duration
(months)
2017, Earth Observation Science and Robotic Exploration Missions.
Applicable THAG Roadmap:
Not related to a Harmonisation Subject
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Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
16 Optics
Ref. Number:
G617-091MM
Budget (k€):
300
Title:
Optical components based on high-efficiency Volume Bragg Gratings
Objectives:
The objective of this activity is to design and manufacture full-size Volume Bragg
Grating (VBG) components (filters, spectral dispersers, focussing elements) and to
experimentally characterise their performances under relevant environmental
conditions.
Description:
Volume Bragg Gratings (or Volume Phase Gratings) are a well-known technology
for spectral filtering and spectral dispersion applications mainly in on-ground
astronomy. Their main advantages are high peak diffraction efficiency, low
polarisation sensitivity (lower than for ruled gratings) and a low level of ghost
images and scattered light. Furthermore the possibility to record on the same
substrate several holograms contributes to the versatility of VBGs. VBG
components can be used as a replacement for strip filters in Earth Observation or
filter wheels in Science missions.
The TRP activity demonstrated the potential of such a component as highresolution, low-straylight spectral dispersers in replacement of bulk ruled gratings.
The promising results of this TRP activity have been confirmed by measurements
performed in the ESTEC laboratories on VBGs samples. The measurements have
shown that the performances of VBGs are at least comparable to or outperformed
those of other grating types at a lower cost (see reference paper).
The proposed activity aims to perform the experimental characterization of VBG
components in space environment. The tests will be performed on components
representative of flight model parts. In particular, emphasize will be put on the
opto-mechanical aspects and the impact of the space environment on the optical
performances of the component.
Deliverables:
Breadboards of VBG gratings, tested under environm.
Current TRL:
3
Target
Application /
Timeframe :
Target TRL:
5
Duration
(months)
12
2018, high-performance optical filters in Earth Observation, Science astronomy
missions, and Exploration missions.
Applicable THAG Roadmap:
Not related to a Harmonisation Subject
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3.4.1.17 TD 17- Optoelectronics
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
17 Optoelectronics
Ref. Number:
G617-095MM
Title:
Development of a low-noise current source for ultra-stable CW laserdiode applications
Objectives:
To develop an ultra-stable laser diode drive source as required for coherent lasers
in optical atomic frequency standards (optical clocks) and laser cooled atom
instruments. The focus of the development will be to engineer a current source
with ultra-high stability in amplitude and noise performance. This activity will also
cover the realization of an accurate laser diode temperature control system. The
engineering model to be developed shall minimize the mass and power
requirements and shall achieve high reliability for space environments.
Description:
Stable laser operation, as required for optical clocks and cold atom devices,
requires ultra-low noise injection currents as well as stable temperature control. In
fact the laser-diode wavelength and power characteristics strongly depend on the
junction temperature stability and on the method the injection current is
generated and controlled. This activity will address the design, development and
test in a relevant environment of a complete assembly of a laser diode drive source,
consisting of a voltage reference part, a voltage to current converter and current
boot stage. The design will address and trade-off different topologies and
implementation schemes with the aim to achieve maximum performance in a
specific environment. The work will be carried in three phases: the first phase
covering the requirements, analysis and specifications, the second phase the
design and development, and the final phase the MAIT.
Deliverables:
Engineering Model
Current TRL:
4
Target
Application /
Timeframe :
Optical clocks and Cold Atom Devices. Navigation, Inertial sensing, Gradiometry,
Fundamental Physics, Exploration, etc. Instrument technology recommended by
FTAP and HISPAC, etc. 2018
Applicable THAG Roadmap:
Budget (k€):
Target TRL:
Duration
(months)
18
Frequency & Time Generation and Distribution – Space
(2013)
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3.4.1.18 TD 19- Propulsion
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
19 Propulsion
Ref. Number:
G617-098MP
Budget (k€):
1,000
Title:
High Power (5 kW) HEMPT (Highly Efficiency Multistage Plasma
Thruster)
Objectives:
The use of electric propulsion (EP) for orbit raising manoeuvres from GTO to GEO
will allow to reduce huge amounts of propellant in telecommunication spacecraft
and Galileo Evolution satellites. For example the Boing platforms will reuire only
375 kg of Xenon to perform this manoeuvre instead of the 1700 kg of Hydrazine.
The use of EP will nevertheless increase the amount of time of such manoeuvre.
The Boeing platform will employ several months to rise the orbit from GTO to
GEO.
Therefore it is very important to increase the thrust of the current engines
developed for Small GEO (40 mN) by increasing the power we could go to 200
mN.The same argument is required for the Galileo Evolution spacecrat.
Description:
Design, manufacturing and testing of breadboard models at high power.
Deliverables:
Breadboard
Current TRL:
2
Target
Application /
Timeframe :
TRL-5 2018
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Electric Propulsion Technologies (2010)
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ESA UNCLASSIFIED – For Official Use
3.4.1.19 TD 20- Structures & Pyrotechnics
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
20 Structures & Pyrotechnics
Ref. Number:
G617-102MS
Budget (k€):
500
Title:
Improvement of industrial approach for design and verification of
non-linear spacecraft structures
Objectives:
The objectives of the proposed activity are to further consolidate existing results,
using a flight application cases, and subsequently to derive a systematic approach
and related processes how a satellite project should deal with significant
mechanical non-linearities during the complete project implementation phase.
For this purpose the study shall simulate in an "accelerated" manner the satellite
structure DD&V (Design, development and Validation) steps. In particular follow
the general project line with initial structural performance predictions at satellite
level, performance of launcher CLA (Coupled Load Analysis), test predictions and
finally the verification test execution.
Description:
The objectives shall be achieved by performing the following tasks:
1) The spacecraft structural non-linearities with most significant impact on the
system performances shall be identified and these impacts shall be assessed
in comparison to corresponding mechanical systems behaving linearly.
Based on the latter assessment the severity of these non-linearities shall be
determined in order to establish relevant guidelines to support the decision
process, to be made as early as possible in a satellite program development,
whether considerably larger efforts will be necessary to take appropriately
into account the non-linear behaviour in analysis and test.
The real-life flight application shall be selected from relevant candidate
satellites, e.g. ESA scientific or Earth observation satellites. The selection
shall be driven by the availability of relevant satellite design information
and spacecraft hardware for the final verification phase.
Based on the earlier assessment relevant structural non-linearities shall be
selected for implementation into breadboard models. These non-linearities
should exhibit both local and global (system level) effects and should be
linked to large masses elements.
2) Structural analysis models of the satellite including the non-linearities shall
be established and relevant structural analyses performed to predict the
system performances. The static effect on the dynamic responses shall be
considered.
In addition to using standard Nastran solution sequences for non-linear
problems (e.g. SOL 129) the efficiency of other FE solvers such as Abaqus
and NX SAMCEF shall be evaluated, in particular with respect to
computational efficiency and numerical stability issues.
3) A satellite model for performing a non-linear launcher CLA shall be
generated. Vega should be selected based on the expected relevance as
launcher for future spacecraft incorporating significant structural nonlinearities. The CLA shall include the relevant load cases (transient or
harmonic), and the potential reduction of iteration needs to consolidate decoupled approach shall be investigated. A damping modelling with
inhomogeneous damping coefficients shall be implemented.
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4)
5)
6)
7)
Due to numerical stability issues encountered with the Nastran solver
during previous activities, the efficiency of FE solvers as Abaqus and
SAMCEF should be evaluated for employment in non-linear CLA.
Non-linear system identification (non-linearity detection, characterization
and parameter estimation) shall be performed for the selected non-linear
devices at subsystem rather than spacecraft level including random and
local excitation as necessary. Advanced concepts shall be developed to
integrate the application of the restoring force method into the simulation
process. Test/analysis correlation shall be performed after the hardware
verification tests.
The virtual shaker testing method shall be applied to predict the shaker
control performances and to optimize the most important controller
parameters. The quality of the spacecraft model employed in the virtual
shaker testing simulations shall be sufficiently representative in the whole
frequency range of the simulation and test.
Subsequent to the verification tests the simulations shall be correlated with
the tests and as necessary updates to the simulation model shall be made.
Verification tests shall be performed to validate the analytical concepts
developed during this study, in particular concerning the potential
optimization of mechanical testing of highly non-linear structures by the
virtual shaker testing method and the subsequent optimization of the
shaker control performance. Also, the capability to perform sine response
analysis with non-symmetric non linearities shall be demonstrated.
The study synthesis shall be prepared. The experiences gained during the
study execution shall be consolidated by establishing a systematic approach
and related processes to deal with structural non-linearities during the
spacecraft structure design, development and verification phases.
The experiences gained during the proposed activity shall be used to
establish a toolbox which allows - based on the knowledge compiled in a
relevant database - identifying during a mechanical verification test the
relevant non-linear structure parameters for optimizing the test execution.
Deliverables:
Study Report plus Software toolbox
Current TRL:
3
Target
Application /
Timeframe :
CLA Verification of spacecraft considering the more realistic nonlinear structural
behaviour/2018
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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ESA UNCLASSIFIED – For Official Use
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
20 Structures & Pyrotechnics
Ref. Number:
G617-103MS
Title:
Advanced CFRP assemblies for spacecraft bus and payload module
platforms
Objectives:
Development and validation of a structurally and thermally enhanced avionics
assembly for spacecraft bus and/or payload platform by means of advanced CFRP
elements.
Description:
Studies are currently being carried out by ESA for the development and validation
of advanced CFRP structural components, both thermally and structurally
enhanced. These activities aim at introducing the use of nanostructured carbon
materials (e.g. nanotubes) and other highly conductive materials together with
traditional CFRP materials, in order to obtain structural elements with higher
performances, w.r.t. traditional technologies, in terms of stiffness, mass, strength
and thermal conductivity. However, the effects of assembling mounting these
equipment (CFRP avionics panel with CFRP housings, interface components,
panel junctions, etc.), each with a different function, have to be also considered in
order to assess and validate the final implementation at subsystem level. All the
mechanical and thermal interface characteristics shall be addressed and validated
w.r.t. launch and space operational conditions.
The framework of the proposed activity shall include the identification of a known
and qualified platform (sandwich panel+avionics and relevant servicing items)
which can be used as a reference for further development. A similar assembly shall
be then reproduced taking into consideration the outcomes of the relevant studies
at component level. As a minimum configuration, in the frame of the proposed
study, it shall be considered the development and validation of an assembly
composed of a thermally/structurally enhanced CFRP sandwich panel and a set
(e.g. 2/3 units) of equipment with different masses and different dissipative loads.
The validity of the proposed design and implementation shall then be
demonstrated by test in the relevant mechanical and thermal environment,
including thermal vacuum.
Deliverables:
Prototype
Current TRL:
4
Target
Application /
Timeframe :
Future Missions. The implementation of a complete CFRP assembly (including
fastened joints) showing a high thermal conductivity will save mass and will
reduce the thermal mismatch at interfaces so decreasing the verification effort.
Technology development needed in 2018.
Applicable THAG Roadmap:
Budget (k€):
Target TRL:
Duration
(months)
24
Technologies for Optical Passive Instruments – Stable &
Lightweigth Structures (2013)
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600
ESA UNCLASSIFIED – For Official Use
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
20 Structures & Pyrotechnics
Ref. Number:
G617-108MS
Budget (k€):
500
Title:
Improved design and verification of cryocoolers subjected to very high
number of fatigue load cycles ('gigacycles')
Objectives:
To improve design, verification and acceptance approach for hardware subjected
to very high number of fatigue load cycles.
Description:
Fatigue life verification methods for spaceflight hardware, as e.g. specified in
standards for structures, mechanisms and fracture control, and implemented in
ESACRACK/ESAFATIG software module, is primarily applicable for relatively
small to medium number of fatigue cycles (typically below 1E6 significant cycles).
Nowadays, mission critical cryocoolers (e.g. MTG) are under development that
may experience more than 1E10 (e.g. 6.5 years at 50Hz) significant fatigue cycles
during their lifetime, i.e. may experience very high cycle fatigue (VHCF) or
'gigacycle' fatigue. In literature it is indicated that a true fatigue limit may not exist
at very high numbers of cycles as is sometimes assumed.
The development, verification and qualification is complicated by the fact that
development and qualification testing have potentially very long duration (e.g.
factor 4 wrt lifetime, in nominal condition, (e.g. 1E11 cycles)), and may have to be
performed in parallel (to a certain extent) with associated development risks.
A critical appraisal and further development of design, verification, qualification
and acceptance methods/standards for these structural elements shall be
performed and implemented on a demonstrator programme, addressing the
following:
- Design, verification and qualification guidelines, addressing risks of
overtesting and potentially high scatter in achieved life in the gigacycle
regime;
- Accelerated testing methods, e.g.:
- Representative specimens (development models), cycled with margin on
load to a limited number of cycles;
- Basic specimens, cycled with margin on cycles at representative stress
levels (20kHz may be achievable, with limitations);
- Number of test articles recommended.
- To assess potentially significant variables affecting fatigue life at high
number of cycles: e.g. material factors, processing defects and variations,
size effects, surface condition, material combinations, environmental effects
(incl. temperature!), fretting, residual stress, ...;
- Availability of suitable material data for design in e.g. literature, and
selection of the most suitable material and development test methods (incl.
accelerated test methods) to generate design data;
- Recommendations for acceptance tests and inspections to ensure that
critical flight hardware elements are 'within family' of the qualification
hardware;
- To demonstrate implementation on a representative demonstrator
programme.
The main focus of this activity is foreseen on metallic materials, but may be
extendable to other materials: e.g. ceramic materials as may e.g be encountered in
ball bearings.
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Accelerated testing of 1E11 cycles will take around 3 years at 1kHz, or 4 months at
10kHz; Testing to 1E7 cycles at 50Hz will take around 55 hours (2-3 days), testing
to 1E8 cycles will take around 25 days.
The activity assumes that fracture control requirements will probably not require
(by design) verification of crack growth due to intial flaws of the items subjected to
gigacycle fatigue. Otherwise the verification may become significantly more
complicated.
Deliverables:
Whole demonstrator + reports
Current TRL:
3
Target
Application /
Timeframe :
Cryocoolers (and potentially other equipment submitted to very high number of
cycles)/2017
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Cryogenics and Focal Plane Cooling (2013)
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Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
20 Structures & Pyrotechnics
Ref. Number:
G617-109MS
Budget (k€):
700
Title:
Reshaping of Antenna and Telescope Reflectors
Objectives:
Development and testing of an active reshapable reflector - comprising flexible
reflector surface, actuators and shape sensing system - with the capabilities for
beam contouring or wavefront correction, compensation of orbital disturbances
and adaptation to material aging.
Description:
The active reshaping of antenna reflectors or telescopes can be envisaged for :
- Fast swath and footprint modification in Earth Observation missions
allowing a reduction of repeat cycles and enhancement of resolution in
Synthetic Aperture Radar and Radiometers;
- Active Secondary mirrors of Infrared telescopes for attaining ultra-stable
configurations;
- Contoured Beam Antenna for following market evolution in
telecommunications.
- Considering that the last application is covered by Artes 5 up to a certain
extent this proposed GSTP activity aims at developing and testing an active
reshapable reflector under representative radiation and thermal
environments for Earth Observation and Science.
The activity will start identifying the requirements for the recomformable reflector
considering the mission scenario and instrument needs. The benefits and
constraints of such a product will be identified. Then the activity will focus on
technology aspects for developing the material for the reflecting surface which
must exhibit :
- Easy reconformability;
- Stability under actuation and thermal loading;
- Good aging and creep properties;
- Sufficient fatigue life;
- Adequate Radio-Frequency or Submillimeter characteristics.
A trade-off between the means for performing the monitoring of the active
reflector throughout its overall lifetime and the thermoelastic distortions will be
carried out. On one hand, developments in actuator technologies could lead to
actuator units outputting forces and displacements and therefore providing a
compact and integrated sensing solution. On the other hand, an optical
measurement system, e.g. based on photogrammetry or laser scanning, could
provide information on the overall shape of the reflector and be
electromechanically simpler, but will be more challenging in terms of mass and
configuration. Alternatively , the use of Radio-Frequency ground beacon and
different actuator settings could enable the knowledge of the shape of the reflector
without added complexity or mass to the spacecraft. The robustness of the
operational performance in case of actuator failure shall be addressed.
The proposed activity constitutes the next logical step in maturing the technology
of actively reshapable space reflectors. It builds on the success of the study
Mechanical Reshaping of Antenna Reflector Shells (Artes 1) which demonstrated
the feasibility of existing actuators and reflecting surface materials for beamcontouring and on the on-going design, construction and testing of a demonstrator
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in laboratory conditions within the activity Reconfigurable Antenna Optics (Artes
5).
Deliverables:
Demonstrator and Study Reports
Current TRL:
3
Target
Application /
Timeframe :
Beam shaping in Earth Observation and wavefront correction in Science
(Astronomy), with possible spin-off for Telecommunications missions/2018
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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3.4.1.20 TD 21- Thermal
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
21 Thermal
Ref. Number:
G617-113MT
Budget (k€):
150
Title:
Extended in-flight validation of LHP modelling methods
Objectives:
Take advantage of forthcoming flight opportunities to further validate LHP
modelling.
Description:
Loop Heat Pipes (LHP) are planned to be mounted on a number of ESA projects
[AEOLUS, MTG ...].
It is therefore important to get any available feedback to have a better
understanding of behaviour of LHPs in flight and enhance the credibility of related
thermal predictions.
The objective of the proposed activity is to assess common underlying assumptions
taken in LHP modelling methods with reference to flight data, namely for what
concerns (not exhaustive):
- Start-up and shut-down conditions,
- Zero-gravity,
- Control laws,
- Heat sharing.
Deliverables:
Study Report
Current TRL:
6
Target
Application /
Timeframe :
All missions. 2017
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Two-Phase Heat Transport Systems (2009)
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Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
21 Thermal
Ref. Number:
G617-114MT
Title:
Heat Pump Conceptual Design and Breadboard testing
Objectives:
The objective is to design and develop a Heat Pump system that is adaptable for
Earth Observation, Exploration, Science and Telecommunication missions.
Description:
The activity would be a follow-on from a TRP activity where heat pump using a
high speed turbo compressors was developed and tested. The activity would focus
on the detailed design of a heat pump within a spacecraft architecture where the
following components would be designed or enhanced, compressors, evaporator,
condenser, accumulator, expansion valve, flash economizer, micrometeorite
shielding, and Optical Solar Reflectors (OSR) bonding for high temperature. The
results from the detailed design will provide an analytical verification that the
concept meets all of the requirements that were reviewed and specified at the
beginning of the activity. Furthermore, key components shall be selected for
breadboard testing in order to validate the critical design assumptions made
during the detailed design.
Deliverables:
Breadboard
Current TRL:
3
Target
Application /
Timeframe :
2017
Applicable THAG Roadmap:
Budget (k€):
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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3.4.1.21 TD 23- EEE Components and quality
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
23 EEE Components and quality
Ref. Number:
G617-116QT
Budget (k€):
700
Title:
Prototyping and characterization of 600V SiC MOSFET
Objectives:
Development, prototyping and characterization of medium voltage SiC MOSFET
for generic power switching function in space power distribution and control
function and motor driver
Description:
The activity will be focused on the developing of SiC Power MOSFET medium
voltage and medium power with the main goal to characterize the performances of
the devices in terms of switching capability, stability of the technology and main
characterization of static and dynamic parameters as a function of temperatures as
well as to characterize the technology in radiation environment in order to
evaluate their suitability for future application in space missions.
The activity will have the goal of prototyping devices with stable well characterized
parameters that could be appealing w.r.t. the same class Si MOSFET available on
the market. The prototypes should be packaged in a suitable package that allow
easy and safe handling and that can allow the full characterization in temperature
of the devices.
The main features of SiC base material (high energy gap, high electric field
breakdown in combination with reasonably high electron mobility and high
thermal conductivity) led to the following expected and in some cases already
proven capabilities for power application: low on-state voltage, low recovery
charge, fast turn-on and turn-off, high blocking voltage, higher reliable operating
junction temperature, high power density.
These characteristic together with the important point that SiC can be easily
thermally oxidized to form high quality SiO2 are promising for generic power
switching application. At the present stage, the SiC MOSFET devices are still in a
R&D level, but there is an increasing interest in realizing high performance SiC
MOSFET that shows a better switching capability of their Si based equivalent
devices showing lower Ron resistance with a comparable Qc in a wider
temperature range.
The activity will be organized with the following work structure:
- Task 1: critical analysis of the technical requirements, definitions of goal
values for the main
- key parameters
- Task 2: trade-off analysis of the main design structure and topology with
relevant simulation
- Task 3: manufacturing processes definition and main trade-off analysis,
first issue of draft
- PID, first run in foundry
- Task 4: Electrical characterization of first run in foundry and analysis of the
results
- Task 5: Review of the manufacturing processes implementing any corrective
actions come from the previous phase, second issue of PID and second run
in foundry.
- Task 6: Definition of the electrical characterization, stability assessment and
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radiation test program. For the overall test program the sample size should
be at least 30 devices.
- Task 7: critical analysis of test results. Identification of future activities
needed to industrialize the prototypes, analysis of manufacturing cost and
forecast of yield.
Deliverables:
Full report and packaged samples
Current TRL:
2
Target
Application /
Timeframe :
Due to the generic application field, any mission could benefit of the expected
improved switching capabilities of the device under development in this activity.
The availability on the market is expected in 3/4 years’ time starting 2016 with this
prototype development. This will be the first SiC based MOSFET that will be
submitted to radiation characterization for possible future space applications.
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Power Management and Distribution (2013)
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Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
23 EEE Components and quality
Ref. Number:
G617-118QT
Budget (k€):
300
Title:
Evaluation of high density optical links for high speed transmission
Objectives:
The main objective of the activity is to perform a full evaluation of high density
optical links for high transmission rate (40 Gb). The optical links will include 12
channels MM MPO connectors with optimized termination process.
Description:
Two parallel GSTP activities have been initiated in early 2011 to get ESA approval
of their optical link assembly capability. The first phase of the activity which is now
completed was aimed at confirming the need of the end users in term optical
assembly and making a survey of the components available in the market
(connectors, cables, fibres). A list of different possible assembly combinations was
selected and proposed for tested during the second Phase. The second phase
consists in the assembly of the different selected technical solutions followed by
on-ground preliminary validation testing. From these activities, according to endusers and preliminary testing results, it has been concluded that multi fibre
solution for MM transmission is one of the very suitable solution for coming need
for capacity and number of systems will that require high fibre numbers.
In the frame of Proba V, a Technology Demonstrator was proposed to test one the
selected multi-point assembly with highest interest expressed by European space
end-users. This optical payload has been assembled in Proba-V platform. This
IOD mission is to confirm that assemblies is suitable in regards of transmission
loss and also that assemblies can stand all environmental challenges as they occur
in a typical launch and during operation. The focus is mainly to show that
attenuation of assembly will stay unchanged under these conditions.
As a next step forward, the goal of this proposed activity will be to continue with
optimizing termination process, in particular polishing process. Normal IEC
connectors is specified with 1-3 um protrusion. Initial investigations shows that
this high protrusion could be difficult for extreme vibration load. To reduce
tension on fibers by less protrusion in combination with angled connectors these
problems will be reduced. Since this kind of polishing is not specified by any
standards so far, more investigations should be carried out. This could be
confirmed during this activity with higher transmission speed than used at current
program. In addition to confirming that insertion loss is good, also return loss will
be checked. New transmission system including OTDR functionality in system
could be very useful to find in which part of the assembly additional reflection or
insertion loss occur.
The activity will include the realization of the MM MPO assemblies based on the
output of the current GSTP activities, integrated in a high transmission speed test
module (40 Gb). The termination process from the current GSTP activities shall be
optimized to survive harsher environment than the initial testing. An extensive
evaluation will be carried out on these assemblies including optical testing during
shock and vibration.
Deliverables:
Engineering Model
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Current TRL:
5
Target
Application /
Timeframe :
2017
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
23 EEE Components and quality
Ref. Number:
G617-119QT
Budget (k€):
300
Title:
Radiation testing of non-volatile memories for space applications
Objectives:
Non-volatile memories are of strategic importance for advanced, innovative and
high performance digital data processing and data storage in spacecraft systems.
They are used in all satellites and spacecraft, either embedded in complex ICs or as
stand-alone devices. For example, non-volatile memories are typically used as
program memories for microprocessors, microcontrollers, and FPGAs, driving the
satellite on-board computers and other critical functions. Another example is data
storage in mass-memory systems, for which non-volatile memories (in particular
NAND-Flash) are replacing more the traditional DRAMs (Dynamic RandomAccess Memory) when large capacity and low-power are required. Recent
examples of NAND-Flash used for mass-memory are Spot6 (launched in
September 2012) and Sentinel-2 (launched in 2015); NAND-Flash were/are also
considered for other missions like EarthCare, Gaïa, EDRS, and SmallGEO.
Terrestrial applications drive a rapid evolution of technologies and device
products. This demands a correspondingly dynamic and efficient radiation
assessment of these memories for space applications. In this activity, the main
types of commercially available non-volatile memories will be studied and
radiation assessed for a potential space utilization. The following actions will be
undertaken:
- Quantify the risk and increase the confidence in NAND Flash memories for
space, by analyzing total dose effects with lot-to-lot and intra-lot variations in
statistically relevant sample populations;
- Investigate functional interrupts and dynamic errors in the new high-speed
double data rate interface implemented in modern NAND Flash devices, as
compared to the standard asynchronous interface;
- Evaluate the impact of technology scaling on single event effects in floating
gate cells, in terms of single and multiple bit upsets;
- Investigate synergistic effects between total dose, single events, and intrinsic
wear-out mechanisms in NAND and NOR Flash device types;
- Investigate root causes of (possible) destructive events induced by heavy ions
in NAND devices;
- Explore radiation effects in alternative non-volatile storage technologies, such
as phase change memories (PCM) and other maturing device concepts that will
become available during the course of this project.
Description:
This activity aims at improving our knowledge of radiation effects in non-volatile
memories and validate their utilization for space applications.
The increased variability (lot-to-lot, sample-to sample, cell-to-cell etc.) of radiation
sensitivity is an established attribute and consequence of the continuous decrease
in feature size of modern electronic devices. To maximize memory capacity per
component NAND Flash devices are among the first to use new process
technologies providing higher integration density and scaling. In order to optimize
testing and to permit probabilistic methods to determine parameter spreads,
relevant statistics have to be produced to describe component behavior under
Total Ionising Dose exposure. The data collected will be analyzed, by randomly
picking a small subset of the tested devices and evaluating the difference with the
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Deliverables:
Current TRL:
Target
Application /
Timeframe :
full data set, taking advantage of proper statistical tools to evaluate the device
variability.
To exploit the increasing capacity of NAND Flash memories, high speed I/O
interface circuitry is implemented. Double Data Rate (DDR) interfaces in the most
recent device types are competing with the conventional asynchronous I/O design.
This DDR interface is similar to that used in SDRAM and may bring about an
increased SEFI and dynamic error sensitivity in NAND Flash. Single Event Effects
testing of this new type of interface is necessary to establish the factual behavior in
a space radiation environment and to determine the appropriate application
conditions.
As the feature size is scaled, the amount of charge stored in floating gates
decreases accordingly. It is possible that the next device generations may become
sensitive to direct ionization by protons, which would largely affect error rates in
space. This requires an evaluation of single and multiple-bit upset rates.
Even at ground level, ensuring the reliability of NAND Flash memories is a
recognized concern and the characterization is becoming more and more complex.
Although recent results on current component types have ruled out synergistic
effects between intrinsic wear-out and environmental radiation effects, these
cannot be excluded in the next generations of devices. This is based on the
experience that, interactions between total dose and single events have been
observed in the past. Therefore it is foreseen to include the evaluation of possible
synergistic effects in advanced NAND and NOR Flash memories.
Destructive events on NAND Flash memories tested under radiation have been
reported but there is no conclusive proof that radiation is the root cause of these
failures. Clarification is needed.
Manufacturers are increasing development efforts on alternative non-volatile
storage technologies, such as phase change memories (PCM), starting from the 45nm node. The PCM technology concept bears the potential of being very radiation
hard and is therefore of potentially very high interest for space applications. Early
radiation characterization of these devices is therefore highly advisable.
The following documents will be delivered:
- Report on statistical variations of total dose failures in NAND Flash
memories: a benchmark NAND device (e.g. an SLC device with feature size
below 32 nm) will be selected for this study. Many (e.g. 50) nominally
identical samples will be tested in the same conditions under gamma
irradiation.
- Report on functional interrupts and dynamic errors in NAND Flash
memories with DDR interface: a benchmark NAND device with DDR
interface will be tested at speed under heavy ion irradiation. SEFIs and
dynamic errors will be assessed.
- Report on scaling of floating gate errors: NAND and NOR memories with
different feature size will be exposed to heavy ions in off conditions. Errors
in floating gate cells will be assessed.
- Report on alternative large size non-volatile memories. Available phase
change memories (PCM) with feature size equal or below 45 nm will be
tested under gamma and heavy ion sources. Total dose tolerance and single
event effects will be evaluated.
Study Report
Duration
36
4
Target TRL:
6
(months)
2018
Applicable THAG Roadmap:
Data Systems and On-Board Computers (2011)
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3.4.1.22 TD 24- Material and Processes
Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
24 Materials and Processes
Ref. Number:
G617-128QT
Budget (k€):
Title:
Evaluation of low temperature processing capabilities of novel thin
and flexible ceramic coatings
Objectives:
The use of ceramic coatings has recently been required driven by the harsh
mission environment from ESAs inner planetary missions like Bepi Colombo (BC).
One ceramic coating processing development for that mission is requiring the use
of Titanium alloys as substrates as it is a high temperature process requiring
several hundred degrees. This is not a problem for BC but it excludes the possible
use of the developed coating on lower temperature resistant materials. A possible
adaption of the processing window would enable a much wider use of the currently
available coating. A second point that shall be addressed is to increase the
flexibility of the coating by further reducing the thickness by at least a factor of 2
without impairing the functional properties such that the coating can be applied
flexible substrates like thin foils. Finally it shall be assessed whether the novel
processes can lead to a more conductive coating performance – thus to avoid
charging issues.
Description:
The following tasks shall be carried out.
Within task 1, a reduction of processing window (curing temperature) by varying
the binder matrix and the curing procedure eg. vacuum or room temperature
curing. The target substrates under study shall be at least be compatible with Al
alloys (200C) but should also be evaluated (in terms of temperature as well as
adhesion) on CRFP.
Within task 2, a reduction of layer thickness of the current technical thermal
control coating basis with target layer thickness below 10µm shall be addressed.
The flexibility of improved coatings from task 1 shall be assessed on flexible
substrates such as foils and thin metallic sheets. During that tasks also
improvements of the charging behaviour shall be studied.
Both tasks shall be accompanied by a comprehensive materials and processing
evaluation programme and shall include ground as well as space environmental
assessments. In addition an economic and environmental evaluation shall be
performed.
Deliverables:
Study Report
Current TRL:
3
Target TRL:
4
Duration
(months)
Target
Application /
Timeframe :
Applicable THAG Roadmap:
Not related to a Harmonisation Subject
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Domain –
Specific Area
GENERIC TECHNOLOGY - CORE
Technology
Domain
24 Materials and Processes
Ref. Number:
G617-129QT
Budget (k€):
600
Title:
Development of Improved Bonding and Repairs for OSRs
Objectives:
Optical Solar Reflectors (OSRs) are a key material to provide stable thermo-optical
properties on spacecraft. Currently the application of these materials is by
manual/semi-automatic bonding on spacecraft surfaces which is a tedious task. In
addition as these OSRs are extremely fragile defects such as cracks, debondings
etc. are often created during manufacturing, AIT and storage/transport. Repairs
are cumbersome and time consuming. The objective of the activity is two-fold, to
improve the bonding stability and the resistance to cracking as well as to enable a
more cost efficient way to repair in case bonded OSRs are damaged during AIT. In
addition the verification of the improved bonding processes shall be accompanied
by the use of suitable advanced state of the art NDI techniques.
Description:
The following tasks shall be carried out:
Within task 1, an in depth analysis of the weaknesses of the currently used
materials looking at the life cycle of current application. The definition of at least
three improved adhesive systems in terms of manufacturing and repairability.
Those three systems shall be tested in a ground manufacturing environment as
well as a simulated space environment and traded off in an evaluation campaign
on sample level. It shall be compared to the performance of currently used
systems. One system shall be down selected for further work. As part of the downselection a detailed environmental and cost analysis shall be performed to
establish main environmental/cost drivers incl. repair processes.
Within task 2, the down selected material system shall be used to define a
breadboard which shall be used to establish a prototype demonstration of the
improved bonding as well as repair processes. The earlier performed detailed cost
and environmental analysis shall be reiterated (now on the breadboard scale) and
possible advantages in terms of time/cost/environment shall be highlighted and
compared to classical systems.
Deliverables:
Breadboard
Current TRL:
3
Target TRL:
5
Duration
(months)
Target
Application /
Timeframe :
Applicable THAG Roadmap:
Not related to a Harmonisation Subject
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3.4.2
Specific area: Clean Space
3.4.2.1 TD 5- Space System Control
Domain –
Specific Area
GENERIC TECHNOLOGY – CLEAN SPACE
Technology
Domain
TD 5- Space System Control
Ref. Number:
G61C-027EC
Budget (k€):
800
Title:
Breadboard of a Multi-Spectral Camera for Relative Navigation
Objectives:
The objective of the activity is to breadboard a multi-spectral camera based on the
preliminary design from a TRP activity. The multi-spectral camera shall cover
thermal infrared, near-infrared and visual spectral bands. The camera
specifications shall be derived from the rendezvous with uncooperative targets.
The breadboard shall reach TRL 4. The breadboard shall include the optical head,
the proximity electronics and the Image Processing Board and algorithms.
Description:
In 2014 ESA started a TRP study (Multi-Spectral Sensing for Relative Navigation
MSRN) to design a multi-spectral camera that can be used for navigation purposes
in a variety of scenarios. The main objective is to increase the accuracy and the
robustness of the camera measurements. The activity focused on autonomous
navigation systems for missions to uncooperative targets (e.g. active debris
removal, asteroids, planetary landing). The navigation shall rely on passive
cameras to cover all mission phases. A multi-spectral camera is needed to provide
images under any illumination and environmental conditions.
In the case of e.deorbit continuous measurement of the relative states between the
chaser and the tumbling target is required independently of the illumination
conditions. That is important for safety reasons in the terminal approach to a
tumbling target, to perform inspection for characterization of the rotational state
of the target, for synchronization and capture.
This activity will work towards the design and manufacturing of a breadboard of a
multi-spectral camera including the Image processing board. The activity will
focus on 1) the manufacturing of the breadboard of a multi-spectral camera that
can be used for the rendezvous and capture of e.deorbit mission and other
missions requiring other relative navigation with uncooperative targets, 2)
validation of the performances of the breadboard, optical head and image
processing board, and 3) update a high-fidelity SW model, and a performance
model for faster-than-real-time SW simulators (both models shall have the same
interface than the breadboard).
The activity will be broken down in tasks as follows:
Task 1: Specifications and Preliminary Design Consolidation.
This task shall analyse the results of the latest activities on relative navigation for
RDV with uncooperative. These previous analyses and the results from e.deorbit
phase B1 shall be used to consolidate the mission scenario and the camera and
image processing requirements for an Active Debris Removal system. The
applicability to other missions with uncooperative targets (e.g. AIM) shall be
analysed. A validation plan shall be prepared to verify the breadboard
manufacturing and validate its performances. The validation plan shall include the
SW models, namely, a high fidelity model with image generation and image
processing, and a medium fidelity model without image generation but
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considering shape of the target, relative pose, and environment impact on the
image processing output.
Task 2: Detailed Design.
The contractor shall design the multi-spectral camera that satisfies the
requirements of Task 1. All the components of the breadboard shall be identified to
provide the equivalent functional performances of the flight model. The image
processing (IP) board and the IP algorithms shall be jointly optimized considering
the mission requirements and the candidate alternative missions. The IP
algorithms shall be implemented according to the selected HW/SW
implementation. The design shall be validated in a MIL simulator from previous
activities configured for e.deorbit mission scenario, including the high-fidelity
model of the camera and a representative implementation of the IP algorithms
(e.g. fixed-point).
Task 3: Procurement and Integration.
In this task the contractor will perform the procurement of the components of the
camera including the required IP cores and SW licenses. The characterization of
the components will be correlated with the SW models of the camera. The IP SW
shall be embedded in the IP board. The EGSE shall be developed for the validation
campaign. Integration tests shall be executed to demonstrate the readiness for
breadboard validation.
Task 4: Breadboard Testing
The system tests are executed and analysed. The results are used to correlate the
models (both high-fidelity and medium fidelity). The camera specifications are
updated. In addition, in this task the contractor shall summarise the main
findings, including any lessons learned during the course of this study. The
Contractor shall also propose future activities to raise the TRL.
Deliverables:
Breadboard, technical documentation and software
Current TRL:
3
Target
Application /
Timeframe :
Target TRL:
4
Duration
(months)
Clean Space Missions / TRL 4 by 2017
Applicable THAG Roadmap:
Not related to a Harmonisation Subject
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Domain –
Specific Area
GENERIC TECHNOLOGY – CLEAN SPACE
Technology
Domain
TD 5- Space System Control
Ref. Number:
G61C-040EC
Title:
GNC design and performance validation for active debris removal with
RIGID capture
Objectives:
The objective of the activity is to improve and consolidate the design and
performances of the Guidance, Navigation and Control (GNC) system of a chaser
spacecraft that actively removes an uncooperative debris from orbit using a
robotic arm and a clamping mechanism. This is one of the potential future
methods of debris removal being considered by ESA's Active Debris Removal
(ADR) mission, e.deorbit.
Description:
In 2015 ESA led a TRP activity (CLGARD) to design and validate a Guidance &
Control (G&C) system for the capture and de-orbit phase of an Active Debris
Removal mission using a robotic arm and a clamping mechanism. The multi-body
dynamics of the chaser with a robotic arm before capture and of the composite
(chaser and target mated with the clamping mechanism) were modelled in
MATLAB/Simulink. The CLGARD activity managed to develop the G&C of the
chaser with the robotic arm for the capture phase (finishes immediately before
contact) and the G&C for the composite SC (after clamping mechanism if
rigidized). During a CCN there was a preliminary assessment of the FDIR system
related to the GNC and an enhancement of the navigation models to improve its
representativity.
This activity will work towards the consolidation of an advanced Guidance,
Navigation and Control (GNC) concept for active debris removal using a robotic
arm and a clamping mechanism. The activity will build from the results of the
previous TRP activity and the phase B1 of e.deorbit. The activity will focus on 1)
the improvement of high-fidelity dynamics and equipment modelling, in
particular the robotic arm, the clamping mechanism and the SC flexible modes,
including the transients during the capture, 2) design of the GNC system, with
particular emphasis placed on synchronization motion of chaser with a tumbling
target, the combined control of the chaser and robotic arm during capture and
rigidization (including transients), detumbling and the deorbiting manoeuvre
(two spacecraft coupled by a clamping mechanism), and the demonstration of
global stability during these phases, and 3) design the FDIR related to the GNC
function including the Collision Avoidance Manoeuvres (CAM) during all mission
phases. This activity concentrates on debris removal from circular low-Earth
orbits, where ENVISAT is the reference target.
The activity will be broken down in tasks as follows:
Task 1: Consolidation of Requirements and Modelling.
This task shall analyse the results of the latest activities on dynamics and control
of the combined chaser - robotic arm and of the composite chaser - clamping
mechanism - debris (from CLGADR, 'GNC Simulation Tool for Active Debris
Removal with a Robot Arm', and 'Image Recognition and Processing for
Navigation (IRN)' studies). The previous analyses and the results from e.deorbit
phase B1 shall be used to consolidate the mission scenario and to elaborate the
GNC requirements for an Active Debris Removal system that is compliant with
the scenario. This task shall consolidate the requirements of a high-fidelity Modelin-the-Loop (MIL) simulation Framework, that will permit testing of the GNC
design (e.g. improved models of chaser with robotic arm, sensor models). A real-
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Budget (k€):
300
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time PIL test bench shall be developed from the MIL simulator. The task shall
create a validation plan, that demonstrates how all the GNC requirements shall be
tested and validated using the MIL Framework and the RT PIL test bench.
Task 2: GNC Design and Development.
This task shall design and develop a GNC that satisfies the requirements of Task 1.
The Guidance block shall include any feed-forward terms necessary to meet the
requirements. The Navigation chain shall be able to provide the required
estimates by the controller at the proper frequency, in particular chaser attitude in
inertial frame, chaser COM state in inertial frame (or other reference frame
required by the controller), target relative pose with respect to the chaser (the
sensor suite will be defined from e.deorbit and IRN studies and the measurements
model from sensor and image processing derived from IRN results). The robotic
arm state shall be estimated (additional sensors in the arm shall be agreed with
ESA). The Control block shall be based on modern Multiple-Input Multiple
Output (MIMO) control techniques and considered combined control of chaser
and robotic arm relative to a tumbling target. A MIL simulator shall be
implemented and validated including models from previous activities, in
particular CLGADR and 'GNC Simulation Tool for Active Debris Removal with a
Robot Arm'
Task 3: GNC Validation and Verification.
This task shall run sufficient tests with the MIL framework to successfully
demonstrate the GNC performance of the chaser. The Contractor shall run
different tests to validate the GNC design under different robotic arm, clamping
mechanism, sensor conditions and assumptions. The contractor shall perform
analyses and tests to demonstrate that the switched system is globally stable. The
tests shall demonstrate the safety of the capture phase (including the
synchronization with a tumbling target according to e.deorbit requirements). A
number of tests shall be executed in the PIL test bench to demonstrate the GNC
performances in a representative flight processor.
Task 4: Conclusions and Recommendations
This shall summarise the output of this study, including any lessons learned
during the course of this activity. The Contractor shall also propose future
activities to raise the TRL. This activity shall also update the GNC requirements
from Task 1 based on the results of this activity and shall review any sensor
characteristics and errors that lead to difficulties in achieving a satisfactory GNC
design, based on the results of this activity. The Contractor shall provide a
preliminary set of requirements on the sensor suite, in order to feed back into
future sensor design. Also the task shall review any robotic arm and clamping
mechanism characteristics and uncertainties that lead to difficulties in achieving a
satisfactory GNC design, based on the results of this activity. The Contractor shall
provide a preliminary set of requirements on the robotic arm, in order to feed
back into future robotic arm hardware design.
Deliverables:
Technical documentation and software
Current TRL:
3
Target TRL:
5
Duration
(months)
Target
Application /
Clean Space Missions / TRL 5 by 2017
Timeframe :
Applicable THAG Roadmap:
Not related to a Harmonisation Subject
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Domain –
Specific Area
GENERIC TECHNOLOGY – CLEAN SPACE
Technology
Domain
TD 5- Space System Control
Ref. Number:
G61C-041EC
Budget (k€):
300
Title:
GNC design and performance validation for active debris removal
with FLEXIBLE capture
Objectives:
The objective of the activity is to improve and consolidate the design and
performances of the Guidance, Navigation and Control (GNC) system of a chaser
spacecraft that actively removes an uncooperative debris from orbit using an
elastic tether which connects the chaser and the target object. This is one of the
potential future methods of debris removal being considered by ESA's Active
Debris Removal (ADR) mission, e.deorbit.
Description:
In 2013 ESA led several studies assessing the controllability of two spacecraft
connected via a tether. In particular, the study Multiple-body Dynamics
Simulation Tool for Active Satellite Removal System Modelling (MUST) a library
of building blocks were designed to allow a control engineer to specify, design,
and develop multi-body dynamics for flexible links (tethers) between two space
vehicles in MATLAB/Simulink. The TRP activity AGADIR managed to develop
the GNC of a tether joining a target captured by a net and a chaser. Another
activity known as BOUNCED (Bodies Under Connected Elastic Dynamics)
performed a preliminary analysis of the de-orbit burn an elastic tethered system.
This activity will work towards the consolidation of an advanced Guidance,
Navigation and Control (GNC) concept for active debris removal assuming the
use of an elastic tether. The activity will build from the results of the previous
activities. The focus of the activity will be on 1) the improvement of high-fidelity
dynamics and equipment modelling and 2) design of the GNC system, with
particular emphasis placed on the control of the coupled system during the
deorbit (two spacecraft coupled by a tether), and the demonstration of global
stability during multiple fixed-magnitude deorbit burn ignitions and shutdowns. This activity concentrates on debris removal from circular low-Earth
orbits, where ENVISAT is the reference target.
The activity will be broken down in tasks as follows:
Task 1: Consolidation of Requirements and Modelling.
This task shall analyse the results of the latest activities on dynamics and control
of the chaser - elastic tether - debris (from MUST, BOUNCED, AGADiR and
'Image Recognition and Processing for Navigation (IRN)' studies). The previous
analyses shall be used to consolidate the mission scenario (for instance tether
stiffness and damping) and shall elaborate the GNC requirements for an Active
Debris Removal system that is compliant with the scenario (e.g. tether
pretension). This task shall consolidate the requirements of a high-fidelity
Model-in-the-Loop (MIL) simulation Framework, that will permit testing of the
GNC design (e.g. improved models of elastic tether, sensor models). A real-time
PIL test bench shall be developed from the MIL simulator. The task shall create a
validation plan, that demonstrates how all the GNC requirements shall be tested
and validated using the MIL Framework and the RT PIL test bench.
Task 2: GNC Design and Development.
This task shall design and develop a GNC that satisfies the requirements of Task
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1. The Guidance block shall include any feed-forward terms necessary to meet
the requirements. The Navigation chain shall be able to provide the required
estimates by the controller at the proper frequency, in particular chaser attitude
in inertial frame, chaser COM state in inertial frame (or other reference frame
required by the controller), target relative pose with respect to the chaser (the
sensor suite will be defined from e.deorbit and IRN studies and the
measurements model from sensor and image processing derived from IRN
results). The Control block shall be based on modern Multiple-Input Multiple
Output (MIMO) robust control techniques. A MIL simulator shall be
implemented and validated including models from previous activities, in
particular elastic tether from BOUNCED or MUST.
Task 3: GNC Validation and Verification.
This task shall run sufficient tests with the MIL framework to successfully
demonstrate the GNC performance of the chaser. The Contractor shall run
different tests to validate the GNC design under different tether and sensor
conditions and assumptions. The contractor shall perform analyses and tests to
demonstrate that the switched system is globally stable. The tests shall
demonstrate the safety of the coupled chaser-target during the complete de-orbit
phase (including the uncontrolled post-burn flight). A number of tests shall be
executed in the PIL testbench to demonstrate the GNC performances in a
representative flight processor.
Task 4: Conclusions and Recommendations
This shall summarise the output of this study, including any lessons learned
during the course of this study. The Contractor shall also propose future
activities to raise the TRL. This activity shall also update the GNC requirements
from Task 1 based on the results of this activity and shall review any sensor
characteristics and errors that lead to difficulties in achieving a satisfactory GNC
design, based on the results of this activity. The Contractor shall provide a
preliminary set of requirements on the sensor suite, in order to feed back into
future sensor design. Also the task shall review any tether characteristics and
uncertainties that lead to difficulties in achieving a satisfactory GNC design,
based on the results of this activity. The Contractor shall provide a preliminary
set of requirements on the tether, in order to feed back into future tether
hardware design.
Deliverables:
Technical documentation and software
Current TRL:
3
Target
Application /
Timeframe :
Clean Space Missions / TRL 5 by 2017
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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3.4.2.2 TD 13- Automation, Telepresence & Robotics
Domain –
Specific Area
GENERIC TECHNOLOGY – CLEAN SPACE
Technology
Domain
TD 13- Automation, Telepresence & Robotics
Ref. Number:
G61C-042MM
Budget (k€):
3,000
Title:
Capture of space debris with throw nets: Engineering Qualification
Model development and sounding rocket testing
Objectives:
The objective of this activity is to build on a number of recent technology
developments to perform the maturation, integration and final verification of
the net system for debris capture so that it is ready for inclusion in an Active
Debris Removal mission.
To achieve this, a sounding rocket campaign shall be carried out for end-end
validation of the space debris net.
Description:
This activity will have three phases.
Phase A: Development of Engineering Models (TRL 5)
This phase will get its input from current activities for tether development, net
development, and rely on high-fidelity simulation tools currently verified in the
frame of a TRP activity to consolidate and develop full-scale engineering
models of all parts of the net capture system.
The main components are
- Net
- Net closing mechanism
- Tether
- Spool
- Net ejector
A detailed test-plan shall be developed for the next phase.
The sounding rocket experiment and the sounding rocket platform design shall
be completed.
Detailed simulations of the sounding rocket campaign shall be undertaken with
validated simulators.
Phase B: Development of Qualification Model (TRL 6)
The second phase of the activity will bridge the system from TRL5 to TRL6
through a carefully designed series of environmental and mechanical tests.
The sounding rocket platform shall undergo Manufacture Assembly and
Integration as well as appropriate environmental and mechanical tests.
Phase C: Sounding Rocket Experiment (TRL 7)
The payload shall be integrated with the sounding rocket and the sounding
rocket experiment performed.
The experiment shall be fully instrumented, and high speed cameras will
record the development with the aim for a full 3D reconstruction of all phases
of the net deployment and closure.
Deliverables:
Engineering Model
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4
Target
Application
Timeframe :
e.Deorbit and any other ESA or non-ESA Active Debris Removal missions
TRL 7 by 2018
Applicable THAG Roadmap:
Target TRL:
Automation & Robotics (2012)
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7
Duration
(months)
Current TRL:
30
ESA UNCLASSIFIED – For Official Use
3.4.2.3 TD 18- Aerothermodynamics
Domain –
Specific Area
GENERIC TECHNOLOGY – CLEAN SPACE
Technology
Domain
TD 18- Aerothermodynamics
Ref. Number:
G61C-003MP
Title:
Hot gas plume characterisation in vacuum
Objectives:
The objective of the present study is a detailed experimental characterisation of
mono- and bi-propellant hot gas plumes in low density and near vacuum
conditions.
Description:
Existing data for low-Newton thrusters typically associated with low-density
applications has been collected for cold gas thrusters. As in this case, the plume
consists of single species, the important features associated with multiple gas
interactions in expanding rarefied plumes have not yet been measured (the
expansion angle of low density gases exceeds that of high density gases). Current
numerical tools such as DSMC (Direct Simulation Monte Carlo) urgently require
validation if they are to be used to predict performance and mission requirements
for ESA missions. Experimental characterisation of plumes is required for
determination of:
a) Contamination of solar panels, optical sensors etc. (satellite),
b) Parasitic force and torque measurements (all satellite and craft).
Deliverables:
Study Report
Current TRL:
3
Target
Application /
Timeframe :
Budget (k€):
Target
TRL:
6
Duration
(months)
500
12
Eco-Design, Clean Space,Technologies for space debris remediation,
All spacecraft in orbit (mainly EO and Science Satellites) requiring critical
orbital change manoeuvre.
Applicable THAG Roadmap:
Aerothermodynamic Tools (2012)
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3.4.2.4 TD 20- Structures & Pyrotechnics
Domain –
Specific Area
GENERIC TECHNOLOGY – CLEAN SPACE
Technology
Domain
20- Structures & Pyrotechnics
Ref. Number:
G61C-012MS
Budget (k€):
Title:
Bio-composite structure in space applications
Objectives:
The objective of this activity is to consider the BIO-Composite materials developed
so far in Europe for space application and apply this material to build a typical
space structure, i.e. the central cylinder of a spacecraft for a generic LEO mission
to be flown with the VEGA launcher.
This structure shall be tested against mechanical and environmental loads.
Demisability tests shall also be performed in order to verify compliance with the
new Space Debris Mitigation Requirements.
Description:
In the last years, the interest in the development of bio-composite materials for
space application has increased and the development of such materials has started
with the aim of reducing the environmental foot print of our space missions.
At ESA, material developments have been undertaken in order to design and
develop a demisable bio-composite material for load carrying applications in
spacecraft platforms, payloads and equipment. These materials have been
characterised against mechanical and environmental loads.
Having now available a set of BIO-Composite material suitable for space
application, the next step is to consider a space application and verify the
applicability of such materials for a generic LEO mission.
In order to do that, the following activities shall be accomplished:
- Material State of the Art Review.
- Design analysis and manufacturing of LEO spacecraft structural component
to be selected.
- Demonstration test campaign performed on the demonstrator structure and
test evaluation shall be presented with compliance status to the
requirements of the target application.
- A development plan established covering foreseen efforts to achieve TRL 6
in potential future ESA studies for bio-composites. The development plan
shall also describe the possible application range for current state-of-the-art
bio-composites in space structures applications.
- An evaluation of the environmental benefits for bio-composites for the
selected space structure application.
Deliverables:
Breadboard
Current TRL:
3
Target
Application
Timeframe :
/
Target
TRL:
5
Future Missions
Applicable THAG Roadmap:
Composite Materials (2014)
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Duration
(months)
500
24
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Domain –
Specific Area
GENERIC TECHNOLOGY – CLEAN SPACE
Technology
Domain
20- Structures & Pyrotechnics
Ref. Number:
G61C-043MS
Budget (k€):
3,000
Title:
Prototype and qualification of a De-orbiting subsystem
Objectives:
The objective of this activity is to develop, manufacture and fully qualify the FM of
a de-orbiting sub-system for LEO spacecraft.
Description:
Intense spaceflight activity during the past 60 years has resulted in a growing
population of debris objects that pose hazards to safe space navigation. In 2013,
experts estimate that 29 000 objects larger than 10 cm are orbiting Earth.
Spacecraft industries are facing the problem of achieving compliance with the 25
years de-orbit requirement, while minimising any impact on the cost and
effectiveness of their missions.
Technologies for the development of sail material, architectural design of passive
de-orbiting subsystem and of a Guidance, Navigation and Control (GNC)
subsystem for deployable drag-augmentation devices have been supported by ESA
during the last years raising their maturity to TRL levels of 5 to 6.
Sail materials have been developed, addressing issues as impacts with debris, and
consequent crack propagation, packaging and deploying methodologies. Recently
ESA has supported an activity to develop sail materials able to withstand the very
severe Atomic Oxygen (AtOx) and Ultra Violet (UV) environment. The
architectural design of a scalable and modular drag augmentation device has been
developed and will be tested up to TRL 6 in parallel with the development of a
GNC sub-system which includes a functional numerical engineering simulation
tool to assess quickly controllability and effectiveness of sails in various
AOCS/GNC configuration and modes. The validation of the GNC system will reach
TRL 4.
These technologies are now ready for integration into a Flight Model (FM) of a
subsystem for de-orbiting spacecraft in LEO including structures, mechanisms,
and GNC.
The flight demonstration shall ensure the de-orbit in less than 5 years, in order to
have a validation of the subsystem considering the GNC, mechanical and
aerothermo-dynamical aspects.
The spacecraft to be considered shall have a total mass of 20-40 Kg, considering
VEGA as reference launcher and an SSO orbit with an altitude of at least 700 km.
The activity shall be organised in two phases.
In phase 1, the FM shall be designed and manufactured, including additional
instrumentation needed for a demo flight, i.e. data telemetry systems, on-board
camera, sail health monitoring system (against AtOX, UV and debris impact). It
may be necessary to consider PFM model philosophy in order to cover possible
design changes for the Flight demonstration. The GNC sub-system shall be
validated up to TRL 5/6, meaning that it shall be simulated in a flight
representative environment, including processor-in-the-loop (PIL) and HW-inthe-loop (HIL) tests of the flight SW.
The second phase shall be dedicated to the full flight qualification of the FM,
including data recording and FM correlation.
Specific tasks shall include :
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Phase 1:
- Design and development of the FM.
- Mathematical Model of the FM de-orbiting performances.
- Verification and Validation of GNC system up to TRL 5/6 (starting from the
preparation of the sail deployment up to the stabilisation of the sail and the
passivation of the GNC).
- Manufacturing of the FM and of all instrumentation needed for the flight
demonstration.
- Delivery of DDVP targeting full qualification.
Phase 2:
- Test campaign.
- Data recording.
- FM correlation.
Deliverables:
Engineering Model, Test data, (P)FM model correlations
Current TRL:
5
Target
Application /
Timeframe :
Target
TRL:
8
Duration
(months)
Spacecraft sail de-orbiting; 2018
Applicable THAG Roadmap:
Not related to a Harmonisation Subject
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3.4.2.5 TD 24- Materials and Processes
Domain –
Specific Area
GENERIC TECHNOLOGY – CLEAN SPACE
Technology
Domain
24- Materials and Processes
Ref. Number:
G61C-035QT
Title:
Development of a complete Cr-VI anticorrosion system and process
scale-up at industrial level
Objectives:
Budget (k€):
500
Aluminum alloys are extensively used in space programs for both structural and
non-structural applications. As well known, the corrosion resistance of these
alloys is quite limited and anticorrosion treatment are needed.
The most used treatment currently used for improving the corrosion resistance
of aluminum alloys are usually CrVI-based conversion coating. Due to the high
environmental impact of these compounds, the REACH Regulation of the
European Union decided to limit/restrict the use of hexavalent chromium. A
sunset date of mid-2017 has been already set.
For the time being many chromate-free alternative products are available but
they have found to be significantly inferior in terms of corrosion protection
performances with respect to the chromate options.
In this regard there is a great need to develop high performance hexavalent
chromium-free anti-corrosion coatings.
ESA is currently involved in different projects concerning the development of
chromium VI free anticorrosion coatings.
In partnership with NASA Technology Evaluation for Environmental Risk
Mitigation (TEERM) a research project focused on the evaluation of alternative
pretreatment with primers is currently under development. Possible alternatives
for hexavalent chromium-free surface treatments and primers have been
evaluated and tested and preliminary, but, promising results have been
identified.
The objective of this activity is to evaluate the anticorrosion behaviour of the
different alternative pre-treatments applied to the most used aluminum alloys
(2024 in T3 and T8 treatment, 6061, 7075 in T73 treatment and 5083). The
outcome of this activity will be the identification and the optimization of the
most promising anticorrosion pre-treatment.
At this point, a natural continuation of this project would be beneficial to define
the most promising pretreatment/primer combinations and to build a complete
and performant anti-corrosion system. Furthermore an industrial upscale of the
process will be one of the major target of this new activity.
The sunset date of the 2017 defined by REACH regulation is imminent and
consistent efforts are needed in order to build a robust a reliable industrial
process for space applications.
Description:
The proposed activity will consist of the following steps:
- Identification of the most promising substrate/pre-treatment/primer
combination
- Test campaign at sample level in order to set-up a reliable and robust process
- Identification of representative case-study in order to build a strategy to
scale-up the process at industrial level
- Test campaign a prototype level in order to improve the robustness and
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reliability of the process
Deliverables:
Breadboard
Current TRL:
3
Target
Application /
Timeframe :
Target TRL:
4
Duration
(months)
2017
Applicable THAG Roadmap:
Not related to a Harmonisation Subject
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Domain –
Specific Area
GENERIC TECHNOLOGY – CLEAN SPACE
Technology
Domain
24- Materials and Processes
Ref. Number:
G61C-044QT
Title:
Alternatives to processes affected by REACH for the manufacture of
PCBs
Objectives:
-
Description:
Budget (k€):
500
Inventorise materials and processes for the manufacture of PCBs that are
impacted by REACH legislation.
Survey alternatives products that can be used as drop-in technology using the
same process flow and survey alternative process flows.
Evaluate the manufacturability and reliability of PCBs with alternative process,
compared to the existing process.
The REACH legislation deals with Registration, Evaluation, Authorisation and
Restriction of Chemical substances. The law entered into force on 1 June 2007.
The aim of REACH is to improve the protection of human health and the
environment through the better and earlier identification of the intrinsic
properties of chemical substances. REACH office maintains lists of chemical
substances of concern (SVHC) and define restriction for their use.
The ESA qualification of PCBs is, in parts, a process qualification, as detailed in
ECSS-Q-ST-70-10 Qualification of PCBs. The Product Identification Document
PID of each PCB manufacturer specifies the processes involved. Significant
changes to the process flow can be subject to delta qualification before they are
approved.
This activity aims to inventorise affected processes by defining impact factor and
priority. This is followed by testing selected alternative processes for PCB
manufacturability and reliability.
The following processes have already been identified to be impacted by REACH:
1) Electroless copper
All current processes contain formaldehyde which is a CMR (Carcinogen,
Mutagen or Reprotoxic) product. Some processes contain a salt of mercury
as a stabilizer, which will be banned around 2017 according to a European
Directive on quality of water.
Chemistry suppliers are developing drop-in electroless copper processes,
which need to be evaluated. In addition, it may be possible to use other
process flows to metallise the through-hole, by using direct metallisation
(e.g. using palladium).
2) Tin-lead surface finish
One process uses lead-methanesulfonate, which is CMR and in the SVHC
list. Another fluoroborate process uses boric acid, which is CMR and in the
SVHC list. Tin-lead processes are under threat of obsolescence due to a
general ban under RoHS regulation.
3) ENEPIG surface finish
This finish is candidate as a substitute for tin-lead and ENIG finish. The
process flow uses nickel-sulfate which is CMR, but not yet included in the
SVHC list.
4) Electrolytic nickel-gold finish
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Process flow uses boric acid, which is CMR and in the SVHC list.
5) Surface treatment on copper foils
This process commonly uses chromates. Cr (VI) is on the SVHC list.
Deliverables:
Study Report
Current TRL:
3
Target
Application /
Timeframe :
Target
TRL:
5
Duration
(months)
TRL 5 by 2017.
Applicable THAG Roadmap:
Not related to a Harmonisation Subject
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3.4.2.6 TD 26- Others
Domain –
Specific Area
GENERIC TECHNOLOGY – CLEAN SPACE
Technology
Domain
26- Others
Ref. Number:
G61C-045SW
Title:
REIM - Resource Efficiency through Improved Methods for treatment
of recycling products
Objectives:
Description:
Budget (k€):
350
1. Assessment and analysis of the impacts of the treatment and recycling
processes of scrap material during the production phase of space hardware
2. Assessment and analysis of the impacts of the treatment and recycling
processes for non-accepted components during the manufacturing and
assembly of space hardware
3. Identification of methods to reduce material waste and of alternative
treatment of scrap material and non-accepted components, reducing overall
resource consumption and impacts of the processes.
4. Update of current environmental impact models based on primary data for
waste material and component acceptance rates.
The traditional manufacturing route for many space applications involves the
procurement of large aluminium and titanium plates and forgings which are
subsequently machined into the final structure; for example for the production of
a 1 m3 titanium tank of 58 kg, 921 kg of titanium are needed. Due to the
significant amount of machining that is required to produce the final shape, the
associated manufacturing costs and environmental impacts are considerable, in
particular on resource depletion and use of Critical Raw Materials.
Studies on the environmental impacts of space activities show that the treatment
of the waste material thus becomes an important factor, but in the same time is a
major uncertainty, since the buy-to-fly ratio of a product depends on the material,
machining operation and the final product shape.
In the aerospace industry protocols are already in place which allow some of the
chips (machined material) which are produced during the manufacturing of wing
spars and ribs to be recycled by the aluminium and titanium supplier to form new
products.
Although the volume of machining in the space industry is much less than that of
the commercial aircraft industry, there is still an opportunity to recycle as much
material possible, thus reducing the associated environmental impact and making
cost savings. The use of specialised materials also makes dedicated methods
necessary in order to separate different alloys and retain their specific properties,
to maximise the benefit of the recycling process and the re-use of critical alloying
elements.
Similar considerations apply to acceptance tests of components and equipment.
The acceptance rates and the treatment of the failed products present a major gap
in the current models, but are also identified as a promising field of increasing
resource efficiency and reducing overall impacts.
Consequently this study assesses the loss and fail rates of a representative number
of manufacturing processes and acceptance tests and investigates the treatment of
waste material and failed products in a subset of these cases. With the results the
current environmental models can be updated based on the primary data
obtained and subsequently potential methods to increase the efficiency in the use
of resources and to improve the treatment of waste materials and failed products
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are developed.
This way, the study aims at providing monetary and environmental benefit to
industry through the more efficient use of resources and to decrease the
dependence on Critical Raw Materials (CRMs), identified by the European
Commission as raw materials of special value and high risk associated to their
supply.
In this activity the following tasks will be performed:
1. A number of aluminium and titanium products will be selected for possible
study, based on the amount of usage and their associated environmental
impacts as identified in earlier studies. Their fly-to-buy ratio and/or
acceptance rate will be determined and the traditional waste treatment
assessed.
2. Based on the precursor activities, eco-design principles will be applied to
determine the most appropriate methodology for recycling. Recycling
routes will be proposed, either based on traditional casting methods or by
using 3D printing.
3. The existing LCA models will be updated based on the results of the study
and potentially additional cradle-to-gate LCAs will be performed to
compare the overall environmental impact of the recycled products to
existing ones.
4.
Lessons learned and suggestions for improvement of waste materials will be
issued.
Deliverables:
Report, LCA models
Current TRL:
3
Target
Application
Timeframe :
2017
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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3.4.3
Specific area: SAVOIR
3.4.3.1 TD 1- On-board Data Systems
Domain –
Specific Area
GENERIC TECHNOLOGY - SAVOIR
Technology
Domain
1 On-board Data Systems
Ref. Number:
G61V-003ED
Title:
AES/SAVOIR: Consolidation of Specification of Modular RTU Modules
(electrical, mechanical and thermal interfaces)
Objectives:
The activity will generate a consolidated specification for RTU modules
The activity is related to the Modular RTU GSTP Activity - (G521-001ED)
Description:
The aim of the activity Modular General Purpose RTU (G521-001ED) is to develop
a concept of a Modular Unit and produce a first set of modules that will undergo
an EQM qualification. The activity Modular General Purpose RTU will produce
also as an intermediate result a preliminary specification of a generic RTU module.
The main objective of the activity here proposed is the consolidation and
standardization of this specification to define all the electrical, mechanical and
thermal interfaces of RTU modules. Detailed mechanical drawings and electrical
ICD shall be provided to be used as reference by several potential RTU board
suppliers. The final scope is to have a unique and identified form factor
specification that will drive the design and the manufacturing of board for the
Modular RTU.
Tasks: Review of the preliminary specification of a generic RTU module as defined
by G521-001ED, Generation of the final specification of a generic RTU module,
Generation of all the mechanical drawings for the Modular RTU boards,
Generation of a model for the Standardized Electrical Bus used of the Modular
RTU, Definition of all the timings with margin of the Standardized Electrical Bus
of the Modular RTU.
Deliverables:
Study report and paper specifications & drawings
Current TRL:
3
Target
Application /
Timeframe :
The Modular RTU can find applications in Earth Observation, Science, Telecom,
Exploration Missions. 2017
Applicable THAG Roadmap:
Budget (k€):
Target TRL:
Duration
(months)
Data Systems and On-Board Computers (2011)
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3.4.3.2 TD 2- Space System Software
Domain –
Specific Area
GENERIC TECHNOLOGY - SAVOIR
Technology
Domain
2 Space System Software
Ref. Number:
G61V-004SW
Budget (k€):
Title:
AES/SAVOIR: IMA-SP
Industrialisation
Objectives:
The objective of the activity includes:
- IMA-SP Consolidation of System Executive and I/O handling strategy. The
objective is to improve and optimise the System Executive technology and
the I/O strategy for spacecraft avionics in a partitioned system. This
addresses potential hardware support for I/O handling and potential
network specifically able to segregate I/O.
- Para-virtualisation of selected guest operating system for IMA. 1) Trade off
and selection of the operating system(s) to be ported on top of the
hypervisor selected by the TSP activities (in the avionics roadmap).2)
Porting of the selected operating system(s).3) Validation.
- Integration in the SAVOIR OSRA architecture, IMA demonstrator with
building blocks, e.g. Leon3-NGMP/Xtratum-PikeOS/RTEMS.
Description:
The System Executive (SE) technology provides the partitioning environment to
support Time and Space Partitioning (TSP) and contains (i) a separation kernel
(e.g. a microkernel or a hypervisor) that schedules the partitions and (ii) a
partition OS that schedules the processes within the partition. Previous ESA
activities in this field have ported separation kernels from the non-space domain
to the spacecraft context (i.e. LEON3 CPU) and demonstrated that the IMASP/TSP concept is feasible (achieving TRL 4). This activity shall take the outputs
from these activities and select one or more for improvement and optimisation.
The selected separation kernel(s) must come, with comprehensive justification,
from the list of kernel(s) that have been used on previous ESA activities (e.g. AIR2, PikeOS or XtratuM).
Each partition can then execute a different (real time) operating system on top of
the same microprocessor, for example RTEMS, GnatPro, ObjectAda, VxWorks,
PartiKle, Linux, etc.
Execution
Platform
1,000
Consolidation
and
A second element to this activity is the optimisation of the I/O strategy for
spacecraft avionics. This topic is directly associated with the System Executive
technology because adopting a time and space partitioned architecture will mean
making changes to the IO handling concept. Interrupts from IO devices cannot be
assumed to be immediately serviced in a TSP environment therefore this activity
must establish the modifications needed to the avionics IO strategy to optimise the
performance of the system. The relationship with current hardware and future
hardware is essential, as the use of dedicated I/O boards could prevent designing
an I/O partition.
The third element of this activity is the avionics bus. Beyond the classical avionics
busses, the emergence of synchronous or asynchronous Ethernet based network
gives an opportunity to simplify the I/O handling.
The activity shall cover the following tasks:
1. Selection and potential enhancement of the separation kernel and operating
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system technology, as well as the necessary building blocks to provide an
OSRA compliant execution platform.
2. In order to improve the efficiency of IO handling within the IMA-SP
avionics, selection of a combination of dedicated IO servers within the flight
software and intelligent hardware I/O-processor modules. This task shall
identify improvements to be made to the existing avionics design and then
prototype these new approaches to IO handling on bread boards or
emulators.
3. Selection of a new generation avionics network and integration in the
avionics and software architecture.
4. Development of a prototype demonstrating the benefits of the combined
software design, hardware and network selection.
The outputs from these tasks shall be installed and demonstrated within the
ESTEC Avionics Lab.
Deliverables:
Software
Current TRL:
4
Target
Application /
Timeframe :
Use of IMA and new avionics network is advocated by industry in ADCSS 2015, for
the preparation of the next product lines in 2017. Also applicable for the next
generation of avionics for Launchers
Applicable THAG Roadmap:
Target TRL:
Avionics Embedded Systems (2010)
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3.4.4
Specific area: Space & Energy
3.4.4.1 TD 3- Spacecraft Electrical Power
Domain –
Specific Area
GENERIC TECHNOLOGY – SPACE & ENERGY
Technology
Domain
3 Spacecraft Electrical Power
Ref. Number:
G61E-001EP
Title:
Life testing of solar cells for space and terrestrial applications
Objectives:
This activity will aim to evaluate and quantify the reliability of GaAs based solar
cells and associated by-pass diodes
Description:
This activity will support long term testing to verify the stability and reliability of
advanced GaAs based solar cell structures and associated protection by-pass diode
technology. Since processes such as metal contacts are similar for space and
terrestrial applications, understanding of degradation mechanisms is essential and
expected to benefit both applications.
The activity will involve electrical performance testing of solar cells and diodes for
long duration under accelerated environmental conditions (high humidity, high
temperature, thermal cycling).
Failure modes will be analysed and correlated to acceleration parameters in order
to establish conditions for safe use and accumulate statistics for reliability as a
function of operating environment.
Deliverables:
Engineering Model
Current TRL:
4
Target
Application /
Timeframe :
2017
Applicable THAG Roadmap:
Budget (k€):
Target TRL:
Duration
(months)
Solar Generators & Solar Cells (2009)
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3.4.4.2 TD 4- Spacecraft Environment and Effects
Domain –
Specific Area
GENERIC TECHNOLOGY – SPACE & ENERGY
Technology
Domain
4 Spacecraft Environment & Effects
Ref. Number:
G61E-006EE
Title:
Technologies for space weather services supporting drilling and
surveying activities of the European energy industrial sector
Objectives:
Develop key technologies required by the service and observation segments for
space weather services supporting drilling and surveying activities of the European
energy industrial sector and validation on an integrated platform.
Description:
Drilling and surveying (based on magnetic and conductivity measurements) are
two important activities of the energy sector. Both activities makes use of GNSS
based precise positioning systems, e.g., for off-shore drilling platforms location
control, that are subject to ionospheric disturbances on the signal and to
geomagnetic storms activities.
Therefore, these activities have specific needs regarding the specification, the
monitoring and the forecast of geomagnetic storms and perturbations of the GNSS
signal availability and integrity.
Provision of the relevant services may use observation and data provision assets
common to other space weather services but the specificity of the data product and
performance requirements of a service for drilling and surveying activities have to
be addressed at a more local level. Elements of such services exists in some
European countries.
The purpose of the new development is to provide:
- Environmental specifications to compute mean and deviation to the mean of
the effects in any relevant location.
- Monitoring of the cause and effects of disturbed environment and alert of out
of nominal conditions.
- Forecast of the effects and early warning allowing to planning activities of
drilling activities.
- The activities to be performed include:
- Specification of observation, measurement and data product required.
- Development and validation of a virtual service mock-up partly based on
existing data sets or deployed space and ground based sensors and/or locally
newly deployed ground based sensors (magnetometers, GNSS receivers).
Deliverables:
Prototype
Current TRL:
2
Target
Application /
Timeframe :
TRL 5-6 needed to initiate SSA service precursor in phase 3 of SSA (2019)
Applicable THAG Roadmap:
Budget (k€):
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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3.4.4.3 TD 21- Thermal
Domain –
Specific Area
GENERIC TECHNOLOGY – SPACE & ENERGY
Technology
Domain
21 Thermal
Ref. Number:
G61E-002MT
Title:
Heat Storage for Terrestrial Application
Objectives:
Based on materials/technologies investigated/developed for heat storage for space
missions e.g. Phase-Change Materials, the objective of this activity is to adapt and
expand such technologies/materials for potential application in the terrestrial
sector.
Description:
Starting with the requirements from the terrestrial sector (buildings and industry),
the currently available heat storage technologies and materials shall be reviewed
and assessed for their potential use in such potential terrestrial applications.
Where needed the technologies/materials shall be adapted or extended for this
new applications.
Deliverables:
Prototype
Current TRL:
4
Target
Application /
Timeframe :
Highly efficient heat storage technologies are needed to e.g. store solar heat for use
during night or to provide means for keeping specific items at a given (low or
cryogenic) temperature during a certain time for e.g. transport.
Applicable THAG Roadmap:
Budget (k€):
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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Domain –
Specific Area
GENERIC TECHNOLOGY – SPACE & ENERGY
Technology
Domain
21 Thermal
Ref. Number:
G61E-003MT
Title:
Thermal Insulation for Buildings & Industrial Processes
Objectives:
Based on materials/technologies investigated/developed for insulation for space
missions for e.g. Mars environment (e.g. Aerogel), the objective of this activity is to
adapt and expand such insulation technologies for application in the terrestrial
sector.
Description:
Starting with the requirements from the terrestrial sector (buildings and industry),
the currently available insulation technologies and materials shall be reviewed and
assessed for their potential use in such applications. Where needed the
design/material shall be extended for this new applications and/or necessary
delta-developments shall be performed to adapt the material to existing building
standards, also looking at aspects as large scale manufacturing, handling,
packaging, reduction of cost, etc.
Deliverables:
Prototype
Current TRL:
4
Target
Application /
Timeframe :
Highly efficient insulation for buildings and for industrial processes is an
extremely important aspect for terrestrial applications, to increase efficiency of
such processes and to reduce heating cost and the use of primary energy sources.
In addition, some insulation materials (e.g. Aerogel) can resist to very high
temperature which is essential for fire retardant applications.
Applicable THAG Roadmap:
Budget (k€):
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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Domain –
Specific Area
GENERIC TECHNOLOGY – SPACE & ENERGY
Technology
Domain
21 Thermal
Ref. Number:
G61E-004MT
Budget (k€):
200
Title:
Loop Heat Pipes for Heat Recovery & Solar Power Conversion
Objectives:
Two-Phase Heat Transport Systems (Heat Pipes and especially in the last years
Loop Heat Pipes) have been developed for a number of space applications and
have become the baseline for advance thermal control systems
Based on the work done for space applications and the experience gained, the
objective is to expand and adapt the designs for terrestrial use for heat
recovery/heat removal and for solar energy conversions (near ambient
temperatures).
Description:
In the terrestrial sector there is a large demand for energy (heat) recovery and /or
heat removal for e.g. data centers with very large amount of waste heat which
needs to be efficiently removed, LHP for cooling of electrical installations; use of
LHP for thermal management of wind turbine power convertors. Another area for
application is the efficient "harvesting" of solar energy. e.g. to transfer solar heat
from solar collectors to the heat storage unit.
LHPs will offer a high reliability cooling solution for low maintenance
applications. Unlike heat pipes, the Loop Heat Pipes exhibit much less ground
operation constraints (adverse height of 2-3 meters possible).
Starting with the requirements from the terrestrial energy sector, the currently
available heat pipe and loop heat pipe designs shall be reviewed and assessed for
their potential use in such applications. Where needed the design shall be
extended for this new application.
Aspects which will need to be addressed are material compatibility, long-time
performance, etc.
In addition, design aspects linked to the integration of heat pipes into batteries
and fuel cells will have to be addressed, in order to optimise such concepts.
Deliverables:
Prototype
Current TRL:
3
Target
Application /
Timeframe :
LHP for cooling of electrical installations; use of LHP for thermal management of
wind turbine power convertors. "harvesting" of solar energy. e.g. to transfer solar
heat from solar collectors to the heat storage unit.
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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Domain –
Specific Area
GENERIC TECHNOLOGY – SPACE & ENERGY
Technology
Domain
21 Thermal
Ref. Number:
G61E-005MT
Title:
Heat Pipes for Batteries & Fuel Cells
Objectives:
Based on the experience gained with Heat Pipes (HP) for space, the objective is to
adapt and extend the design (different working fluids, different container
materials, etc.) of such devices for integration into batteries and fuel cells, in order
to efficiently remove the dissipated heat, to better control the temperature levels
and profiles in such devices, thereby increasing the efficiency of the energy
conversion process in such devices.
Description:
Starting with the requirements from the terrestrial energy sector, the currently
available heat pipe designs shall be reviewed and extended where needed for this
new application.
Aspects which will need to be addressed are material compatibility, long-time
performance, etc.
In addition, design aspects linked to the integration of HP's into batteries and fuel
cells will have to be addressed, in order to optimise such concepts.
Deliverables:
Prototype
Current TRL:
4
Target
Application /
Timeframe :
Batteries and fuel cells are used in the terrestrial energy sector for a number of
application, as e.g. energy buffering, local energy production. The thermal design
and thermal management is of crucial interest to improve the performance and
efficiency of such devices.
Applicable THAG Roadmap:
Budget (k€):
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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Domain –
Specific Area
GENERIC TECHNOLOGY – SPACE & ENERGY
Technology
Domain
21 Thermal
Ref. Number:
G61E-009MT
Budget (k€):
400
Title:
Cryogenic Composite Tanks - Light-Weight Long-Term Hydrogen
Storage
Objectives:
The potential for application of the cryogenic composite tank, or adequately
modified version of the same tank, for long-term storage of hydrogen, has to be
analysed and established. The focus of the activity will be to study long-term
hydrogen storage for space applications (fuel cells, etc.), while at the same time
identifying benefits to terrestrial applications.
If specific modifications are required to enhance the tank performance for use with
LH2, the objective is to list the necessary steps to demonstrate the effectiveness of
the modifications to be elaborated and prioritized. Subsequently the steps with the
highest priority within the time and the budget will be completed.
Description:
It is foreseen that hydrogen from renewable resources, such as biomass and water
with input from renewable energy sources, will be an important energy carrier and
energy buffer in the future. Cryogenic hydrogen, usually simply referred to as
liquid hydrogen (LH2), has a density of 70.8 kg/m3 at normal boiling point (20 K,
-253 °C), which means that liquid hydrogen has a much better energy density than
the pressurized gas solutions.
Under a previous ESA activity, a cryogenic composite tank was under development
for long-term storage of liquid helium, with potential application for launchers and
scientific spacecraft. Much the same challenges face the use of hydrogen as energy
carrier. Besides having to be strong and light-weight, due to the use of composite
material, the tank has to show low enough hydrogen permeation and boil-off, as
well as compatibility with the long-term exposure to hydrogen and potentially to
multiple thermal cycles.
The proposed activity is intended to address and perform additional analysis and
test, and potential design modifications and associated demonstration, for use of
the cryogenic composite tank also for long-term hydrogen storage.
Deliverables:
Breadboard
Current TRL:
3
Target
Application /
Timeframe :
Definition of hydrogen as propellant, with the need for extended storage, for
launcher or scientific spacecraft, with synergy between and common technology
development needs for space (propulsion, fuel cells) and ground (automotive/
aeronautical) applications /2017
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Electrochemical Energy Storage (2014)
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Domain –
Specific Area
GENERIC TECHNOLOGY – SPACE & ENERGY
Technology
Domain
21 Thermal
Ref. Number:
G61E-010MT
Budget (k€):
600
Title:
Slush hydrogen - up-scaling and optimising production
Objectives:
The objective of the activity is to assess critical issues on upscaling and
infrastructure definition with respect slush hydrogen (SLH2) production and
transport.
In conjunction with the first objective, to improve/optimise the SLH2 production
pilot plant, in particular to permit testing of features in relation to large-scale and
sustained production and long-term storage. One such feature is the integration and
demonstration of the use of cryocoolers or recycling of helium coolant gas.
Description:
It is foreseen that hydrogen from renewable resources, such as biomass and water
with input from renewable energy sources, will be an important energy carrier and
energy buffer in the future. Cryogenic hydrogen, usually simply referred to as liquid
hydrogen (LH2), has a density of 70.8 kg/m3 at normal boiling point (20 K, -253
°C), which means that liquid hydrogen has a much better energy density than the
pressurized gas solutions.
Densified propellants were identified by ESA studies (FESTIP) as a promising
method to design more compact launchers. Applied research into slush hydrogen
(SLH2) production using the Slush Gun Method started at ESA around 2000. Good
results from the initial activities has led to the decision to build a pilot plant to
demonstrate large-scale production of SLH2. By using slush, with the cryogen
cooled to the triple point, for hydrogen 14 K, instead of the boiling point, for
hydrogen 20 K, continuous boil-off losses can be avoided. For SLH2 the increase in
density, i.e. decrease in volume, is 16% with a solid content of 50%.
The plan for SLH2 will be to explore benefits for hydrogen storage. Local/regional
storage of hydrogen, produced from water during periods with excess capability
from wind and solar power, can be used as an energy buffer
The produced hydrogen is also a potential source of energy for fuel-cell powered
vehicles. Compact and safe storage of the hydrogen can be offered with the SLH2
method. The available technology from ESA activities, based on the Slush Gun
Method, easily lends itself to up-scaling, by multiplying the number of nozzles in the
plant. In addition to more or larger nozzles, economically sustainable SLH2
production will require improvement of the method to subcool the hydrogen, with
cryocoolers and/or recycling of helium coolant gas.
Deliverables:
Prototype
Current TRL:
3
Target
Application /
Timeframe :
Definition of slush hydrogen production infrastructure and synergy between and
common technology development needs for space (launcher) and ground
applications/2017
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Chemical Propulsion - Upper Stage Propulsion (2003)
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Domain –
Specific Area
GENERIC TECHNOLOGY – SPACE & ENERGY
Technology
Domain
21 Thermal
Ref. Number:
G61E-011MT
Budget (k€):
Title:
Slush Methane Production for Propulsion
Production of Slush Natural Gas (SLNG)
Objectives:
The main objective of the activity will be the demonstration of suitability of the
slush-gun method for SLNG production, with the technology from the pilot plant
already available from the FLPP project on slush hydrogen. The use of the pilot
plant with LNG has been studied and documented in information that was
enclosed with ESA contract 20375, CCN 2.
and
300
Application
to
The outcome of the demonstration will serve to validate the predicted performance
and economy of large-scale SLNG production and transport. In principle LNG can
be treated like liquid methane (standard LNG is allowed to include trace
contamination which is not present in pure methane), which is one of the
candidate propellants for future European launchers, and the study also has to
address commonalities in SLNG and slush methane production and storage
infrastructure for the event that slush methane would be required for European
launch operations.
Description:
Densified propellants were identified by ESA studies (FESTIP) as a promising
method to design more compact launchers. Applied research into slush hydrogen
(SLH2) production using the "Slush Gun Method" started at ESA around 2000.
Good results from the initial activities has led to the decision to build a pilot plant
to demonstrate large-scale production of SLH2. By using slush, with the cryogen
cooled to the triple point, for hydrogen 14 K, instead of the boiling point, for
hydrogen 20 K, continuous boil-off losses can be avoided
For SLH2 the increase in density, i.e. decrease in volume, is 16% with a solid
content of 50%. The same process can be used also for Liquid Natural Gas (LNG).
For slush natural gas, predominantly methane, the corresponding gain will be 14%
Even more important for LNG is that boil-off of methane can be avoided, since the
methane, if released, is a strong green-house gas.
Under a previous ESA activity a pilot plant for slush hydrogen production has been
designed and built. In comparison to slush hydrogen, SLNG production is
expected to be less complicated and less costly, considering that it can occur at a
temperature of 90 K, compared to 14 K for hydrogen, making it possible to use
nitrogen instead of helium as cooling medium.
With increased global interest in LNG as an alternative to other fossil fuels, due to
less pollution and sizeable global reserves, successful demonstration of the SLNG
technology is anticipated to attract attention due to advantages here described.
Methane is a potential propellant for future launchers. Thanks to a higher boiling
point, (upper) stage tank design can be simplified. Actually, the triple point for
methane (90 K, see above) is very close to LOX, which can be used to make the
design very compact, since no particular thermal decoupling is required.
A TRP activity will establish the effect of using slush, both hydrogen and methane,
on stage design, in particular in relation to the propulsive elements/engine
components.
It is anticipated that the initial work under the activity has to determine the degree
to which existing hardware can be re-used or has to be modified and the extent to
which preparatory tests at laboratory level are required.
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Deliverables:
Prototype
Current TRL:
2
Target
Application /
Timeframe :
Preparation of natural gas for transport in the form of slush/Estimation of
infrastructure investment needs for SLNG (ground application) and slush methane
(launcher application)/2017
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
18
Chemical Propulsion - Upper Stage Propulsion (2003)
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3.4.4.4 TD 22- Environmental Control Life Support (ECLS) and InSitu Resource Utilisation (ISRU)
Domain –
Specific Area
GENERIC TECHNOLOGY – SPACE & ENERGY
Technology
Domain
22 Environmental Control Life Support (ECLS) and In-Situ Resource Utilisation
(ISRU)
Ref. Number:
G61E-007MM
Title:
BIOFUEL advanced breadboard
Objectives:
Design, manufacture and characterise a breadboard for integrated demonstration
and preliminary mathematical model validation.
Description:
Photo-bioreactor design for high biomass productivity (i.e. enhanced energy
production) raises few engineering challenges such as for instance light energy
transfer, hydrodynamics, fouling, bio-compatibility of materials, harvesting and
predictive mathematical models. A currently running activity, focusing on the
feasibility of production intensification, demonstrates the possibility to reach
higher productivity. However, current limitations in increasing further the
productivity are related to material selection and system integration strategy,
which require further considerations. Therefore, it is now proposed to study the
interfaces, the engineering drivers at system level, the mathematical model of the
system in order to progress toward an engineering breadboard. This advanced
breadboard will be manufactured and its performances will be characterised in
various operational modes to support a preliminary validation of the associated
mathematical model as well as the energy production range.
Deliverables:
Breadboard
Current TRL:
3
Target
Application /
Timeframe :
2018
Applicable THAG Roadmap:
Budget (k€):
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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Domain –
Specific Area
GENERIC TECHNOLOGY – SPACE & ENERGY
Technology
Domain
22 Environmental Control Life Support (ECLS) and In-Situ Resource Utilisation
(ISRU)
Ref. Number:
G61E-008MM
Title:
EnRUM (energetic resources utilisation map) demonstrator
Objectives:
Develop and test the demonstrator
Description:
A system analysis tool for comparative evaluation of regenerative life support
systems architecture has been previously developed. The methodology and the
simulation platform are available and were validated for system mass evaluation.
In the case of regenerative system, mass transfer and transformation is always
associated to energy consumption or dissipation, which needs to be taken into
account in the system evaluation. The currently running development focuses on
the detailed study of energy models and software to demonstrate the feasibility to
perform energy balance at system level. On this basis, it is now proposed to
develop and test the associated demonstrator, i.e. integrating the previous findings
(energy models and selected software) into the existing platform.
Deliverables:
Mathematical model+software+documentation
Current TRL:
3
Target
Application /
Timeframe :
2018
Applicable THAG Roadmap:
Budget (k€):
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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3.5
Space Situational Awareness
3.5.1
TD 4- Spacecraft Environment & Effects
Domain
SPACE SITUATIONAL AWARENESS
Technology Domain
4 Spacecraft Environment & Effects
Ref. Number:
G618-002EE
Budget (k€): 600
Title:
H-alpha Solar
(HASTENet)
Objectives:
Prototype networking of ground-based H-alpha monitoring for SSA space weather
element.
Description:
Establish a ground-based capability in Europe for monitoring of the Sun at Halpha wavelength dedicated to operational space weather use. Analysis of
European capabilities, upgrading existing facilities and infrastructure. Integration
into an international network where appropriate.
Telescope
Network
prototype
for
Applications
This activity will analyse existing facilities in terms of existing hardware, software,
data availability and telescope seeing conditions. Prototyping of the network will
include operation of selected and adapted telescopes and real-time dissemination
of the products to the SSA SWE Network. Requirements and implementation
planning for a dedicated European H-alpha Service Telescope System will be
established in order to address fully European SSA requirements. This will include
preliminary designs for any new instrumentation or infrastructure technologies
required.
Deliverables:
Prototype
Current TRL:
4
Target
Application /
Timeframe :
2018
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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Domain
SPACE SITUATIONAL AWARENESS
Technology Domain
4 Spacecraft Environment & Effects
Ref. Number:
G618-003EE
Budget (k€): 1,000
Title:
Heliospheric modelling techniques
Objectives:
Development of a physics-based models for operational prediction of the
propagation of CMEs and solar energetic particles to the Earth.
Description:
The background solar wind and solar eruptions, such as coronal mass ejections
(CMEs) and High-speed Solar wind Streams (HSSs), propagating into
interplanetary space are drivers for space weather phenomena. Resulting impacts
include geomagnetically induced currents (GICs), ionospheric disturbances
interfering with GNSS systems, spacecraft charging, single event effects on
spacecraft and launchers resulting from accelerated Solar Energetic Particles
(SEPs) and aurora especially at high latitudes. Many physics-based models have
been developed for simulating parts of the Sun-to-Earth space weather system,
consisting of plasma, fields and energetic charged particles. Depending on the
problem, these use a variety of modelling techniques (magneto hydrodynamics,
particle-in-cell, etc.). At this time such models exist in the form of scientific codes
but require additional technical development before a transition to operations.
This activity shall develop and enhance existing physics-based models of Coronal
Mass Ejection (CME) structure, propagation and evolution creating a full global 3D
code. Outputs shall include the prediction of arrival times of CMEs and HSSs,
event-time profiles of the plasma density along with the magnetic field strength and
direction in the heliosphere from a few solar radii up to and beyond 1 AU.
The inclusion of an SEP propagation model driven by the modelled CME-driven
shock shall be explored. Efforts to unify such codes have been previously
undertaken as part of the ESA SEPEM project and the FP7 SEP Server projects but
the creation of a physics based European operational model for SEP onset and
evolution is lacking.
The model(s) will initially be integrated into the SWE Network via the Virtual Space
Weather Modelling Centre.
Deliverables:
Prototype
Current TRL:
3
Target
Application /
Timeframe :
TRL 6 by 2018/2019
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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Domain
SPACE SITUATIONAL AWARENESS
Technology Domain
4 Spacecraft Environment & Effects
Ref. Number:
G618-004EE
Budget (k€): 300
Title:
Standardised airborne radiation detector feasibility analysis
Objectives:
Feasibility analysis of the design and implementation of a standardised radiation
detector to be flown on-board commercial aircraft.
Description:
SSA Programme provides air travellers and commercial aircraft crew members a
possibility to estimate their background radiation doses from Galactic Cosmic
Radiation (GCR) and Solar Energetic Particle events (SEPs) using the AVIDOS tool.
These estimates are based on global, ground based neutron measurements and
spaceborne measurements of the solar proton flux. While the models used by this
service have been statistically validated, a continuous validation will be vital to
ensure that the accumulated dose estimates provided by the service will be within
expected error margins. The best way to validate the service would be that a
sufficient number of commercial aircraft would carry a radiation monitoring
instrument. Standardisation and acceptance testing of the instrument will be
necessary to ensure that all airlines will be able to consider carrying an instrument
on-board.
This activity assess the feasibility to develop such a standardised airborne radiation
monitor, identify required technology developments and produce a roadmap for the
development. This study will also analyse available short term options for validating
the accumulated dose estimates while the standardised radiation monitor
instrument is not available.
Deliverables:
Feasibility analysis of the instrument development. Development roadmap.
Current TRL:
Not specified
Target
Application /
Timeframe :
Target TRL:
Not specified
Duration
(months)
2018
Applicable THAG Roadmap:
Not related to a Harmonisation Subject
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Domain
SPACE SITUATIONAL AWARENESS
Technology Domain
4 Spacecraft Environment & Effects
Ref. Number:
G618-006EE
Budget (k€): 500
Title:
Impact effects tools
Objectives:
The effects a NEO would have on assets and population when impacting our planet
depends on its size, composition, the impact trajectory and velocity and the impact
location. When a potential impact risk from a NEO has been identified it is
important to know if the object could cause damage on the ground and the extent of
such damage. Engineering-type tools are needed to analyse the complete process
from atmospheric interaction, break-up and energy release in the atmosphere,
assessment on which size objects can reach the ground and impact effects on
ground. A number of - mainly scientific- related models and tools are available. A
review of the existing relevant knowledge and tools was performed during the SSA
preparatory phase (activity SSA SN-VII) and a roadmap for the development of
missing tools was established.
In addition to state of the art scientific tools an operational tool for a quick
assessment of impact effects and potential damage is required. This tool shall be
able to provide easy to understand but reliable results within minutes.
Description:
An operational tool for the quick assessment of effects resulting from impacting
asteroids shall be developed. It could be based on a large number of reference cases
which are stored in a database. A higher level tool with a user friendly interface
could interpolate the stored results for the specified input parameters.
This activity will consist of 3 main tasks:
- Develop capabilities which are missing in the existing tools as recommended
by the roadmap. Examples are: Electromagnetic pulse effects, acoustic effects,
realistic object break-up modelling and the treatment of smaller objects.
- Produce the database of reference cases covering the full range of realistic
impact parameters.
- Develop the operational tool for a quick impact risk assessment including the
user interface.
Deliverables:
Software
Current TRL:
3
Target
Application /
Timeframe :
For SSA-NEO precursor servicies. Needed as soon as possible.
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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Domain
SPACE SITUATIONAL AWARENESS
Technology Domain
4 Spacecraft Environment & Effects
Ref. Number:
G618-008EE
Budget (k€): 500
Title:
Combined Radiation Monitor Data Analysis System
Objectives:
Develop a coherent near-real time radiation environment data resource through
development of a system for importing, cross-validating, fusing and analysing
data from a range of European radiation monitors and instruments (e.g. SREMs,
EPT, MFS, EMU, HMRM, NGRM, ICARE).
Description:
There are a number of different European radiation monitor instruments already
flying, or about to fly, each with their own dedicated data (pre-) processing chains
and systems. These include the SREM instrument on Proba-1, Integral, and
Rosetta; EPT and SATRAM on Proba-V; MFS on AlphaSat, and others. These
systems are thus far largely disparate, requiring the user to separately access
them, while differing data formats are also used that make intercomparison and
data fusion difficult.
This activity will utilise those various networked data sources by combining them
to a single, near-real time product. Existing capabilities, such as the ODI interface
and SEISOP system, shall be used to the extent possible.
Task description:
- Analysis of the existing data formats, processing chains and data validation
for the various European radiation monitors and collection of user
requirements.
- Definition and design of a coherent system for merging of the various data
sources into a near-real time product providing energetic electron and
proton fluxes and spectra in the different orbital environments.
- Development of the system and software.
- Validation of the system and the data products.
- Maintenance and updates.
The end customers will be Space Weather application developers and users,
spacecraft radiation effects engineers, mission designers, various instrument PIs,
as well as spacecraft operators.
Deliverables:
Software
Current TRL:
3
Target
Application /
Timeframe :
2017
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
24
Radiation Environments & Monitoring, Effects Tools &
Testing (2009)
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Domain
SPACE SITUATIONAL AWARENESS
Technology Domain
4 Spacecraft Environment & Effects
Ref. Number:
G618-010EE
Title:
Fireball Monitor for SSA
Objectives:
To design and develop an optical monitor and related image processing software
to detect, measure and record fireballs from large meteoroids/small Near-Earth
Objects when entering the Earth atmosphere. The monitor shall aim to observe
Earth from a high space altitude (e.g. GEO).
Description:
The Earth is constantly bombarded by objects in all size ranges coming from
space. The smaller the objects, the more frequent they are. Ground-based video
camera systems typically record several to several tens of meteors per hour. These
events are generated by particles in the size range from micrometres to
centimetres. Objects in the size range of tens to hundreds of metres are called
asteroids and are typically observed far away from the Earth using telescopes
equipped with CCD cameras. Objects in the intermediate size range several
decimetres to several tens of meters in size cause so-called fireballs in the
atmosphere. They are too rare to have produced statistically significant
observations to date and the precise number flux of particles in this size range is
not known very well. On the other hand, they can produce damage on the Earth,
like e.g. the impact of the Carancas meteoroid on 15 Sep 2007, an object of about 1
m diameter which produced a 13 m diameter crater very close to a small town in
Peru (Borovicka and Spurny 2008). Thus, a better knowledge of the expected
impact flux is important to assess the impact risk on the Earth. This study will
contribute to solving this issue.
To get a statistically significant number of observations of fireballs, the detection
area has to be as large as possible. One solution is to put a camera into
geostationary orbit and monitor the complete visible atmosphere of the Earth for
fireball events.
An optical/IR monitor will be designed and developed to detect fireballs from
small (about 1 m or larger) near-Earth objects when they collide with Earth. The
monitor will be optimised for operation from a location in GEO. It will be able to
monitor one complete hemisphere and to determine size and trajectory of the
impactors. Starting point of the design will be two completed studies for the
development of a wide-angle visible light camera for faint meteors. The optics will
be optimised for a field of view covering the complete Earth from GEO (about 18
degrees full angle). The best wavelength for the detection of fireballs (infrared or
visible) shall be determined. An important aspect is the on-board data processing
and storage which has to cope with a large amount of data and with false events
(e.g. city lights, lightning flashes). The study shall include the design and
development of the fireball camera and corresponding on-board software up to
the level of TRL 6. The experience gained from the previous studies (SPOSH and
SPOSH-IR) should be used as a starting point for the activity.
Deliverables:
Breadboard
Current TRL:
Target
Application /
Timeframe :
Budget (k€): 800
Duration
24
(months)
To derive population models for large meteoroids and small Near Earth Asteroids.
Needed for the NEO segment of SSA and to derive better meteoroid flux models
which are applicable to all missions. The instrument will be an attached payload
to a mission in high Earth orbits, preferentially GEO.
4
Applicable THAG Roadmap
Target TRL:
Not related to a Harmonisation Subject
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Domain
SPACE SITUATIONAL AWARENESS
Technology Domain
4 Spacecraft Environment & Effects
Ref. Number:
G618-012EE
Budget (k€): 1,030
Title:
Solar X-Ray Monitor Proto-Flight Model and Low-Resolution Imager
Design for SSA
Objectives:
Development of proto-flight model sun-integrating monitor of solar X-rays, with
low mass and data rate, long lifespan and spectral resolution sufficient for
operational use in space weather monitoring and forecasting. Additionally, design
of instrument evolution into a low resolution imager to determine the location of
activity on the solar disk.
Description:
X-ray emission plays an important role in characterising and locating energetic
eruptions on the surface of the Sun and as a result there is a long history of X-ray
imagers and radiometers. X-ray imagers include the SXI imager on recent GOES
satellites and the SXT instrument onboard Yohkoh. As an alternative to imagers,
whole-disk monitors provide typically higher time resolution a simpler means of
capturing the onset and evolution of solar events, and so providing alerts.
Monitors (or radiometers) include those on RHESSI and the XRS instrument on
GOES satellites. X-ray flares, classified from A (smallest) to X (largest), are often a
precursor to high energy particle radiation storms and disturbances in the nearEarth magnetic and electric fields. In addition, flares directly disturb the
ionosphere, which is further disturbed by magnetospheric storms. Considerable
expertise in X-ray instrumentation and data analysis exists in Europe.
This activity will develop the CXSMO (compact X-ray solar monitor for
operations) instrument with a baseline spectrum of 0.05 - 0.8 nm over multiple
channels. The space-based detection of X-rays is a crucial aspect of the Space
Weather element of SSA. This instrument will be geared towards monitoring and
forecasting of space weather phenomena that could be accommodated easily on
various spacecraft. The monitor should be capable of detecting all flare of class B1
and above with a cadence of 1 minute and timeliness of delivery of 5 minutes. The
instrument will be small (< 1000 cm3) and lightweight (<500g), with low power
consumption and a minimum lifespan of 10 years.
In Phase A/B (12 months) a breadboard XSM (X-ray Solar Monitor) shall be
manufactured using components with path-to-flight equivalents. Detailed
mechanical, optical and electronics design for the final CXSMO instrument shall
be produced along with simulations of the tolerance with respect to the launch and
space environments. This shall include end-to-end functional testing of the
electronics and software.
In Phase C (12 months), an Engineering Model (EM) of the CXSMO instruments
with fully-representative, flight equivalent components shall be manufactured and
tested. The units shall undergo mechanical, thermal vacuum and radiation testing
and full end-to-end functional tests including calibration testing and
representative power and data interfaces.
In Phase D (18 months), the CXSMO Proto-Flight Model (PFM) shall be
manufactured using space qualified techniques and components and shall undergo
previously-defined acceptance tests.
The feasibility to perform a delta development for the instrument to include optics
for the determination of the flare location and likely geo-effectiveness, by use of
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compatible detector technology such as quadrant or pixelated photodiodes, shall
be explored. The resulting Imaging XSM (IXSM) shall have baseline flare angular
position determination requirement is 7 arc-min for M1, 0.7 arc-min for X1 and
0.07 arc-min for X10 class flares.
Deliverables:
Protoflight model
Current TRL:
5
Target
Application /
Timeframe :
Missions from 2020 onwards - requires Phase D (44 months) completed at that
time.
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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Domain
SPACE SITUATIONAL AWARENESS
Technology Domai 4 Spacecraft Environment & Effects
Ref. Number:
G618-020EE
Budget (k€):
300
Title:
Solar Wind Plasma Density Instrument
Objectives:
To develop a low-resource instrument to return solar wind plasma density for
input to Space Weather tools within the SSA programme.
Description:
Although Solar Wind velocity is best measured by electrostatic analyzers, this
can be inaccurate in calculating total plasma density, especially if energy bands
are broad or if there are gaps in the parameter space measured. More reliable
methods may be based on the measurement of the total ion flux from which
ion density can be derived if the mean velocity is known or the measurement of
the electron population, since ion and electron density are equal.
This activity shall trade off technologies for making reliable measurements of
solar wind density on a 3-axis stabilized spacecraft. The trade-off is expected to
include the use of Langmuir probe techniques versus Faraday cup. The use of
retarding grids shall be considered as well as the possibility to measure solar
wind electron temperature.
The results of the activity will include a prototype that shall be tested in a
suitable plasma source. Ion and UV effects shall also be tested. A design for a
flight model shall also be made.
Deliverables:
Prototype and FM design
Current TRL:
3
Target
Application /
Timeframe :
TRL 6 by 2018/2019
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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Domain
SPACE SITUATIONAL AWARENESS
Technology Domai 4 Spacecraft Environment & Effects
Ref. Number:
G618-021EE
Budget (k€):
500
Title:
Solar Wind Plasma Spectrometer
Objectives:
To develop a low-resource plasma spectrometer capable of continuous
monitoring of solar wind ions on a 3-axis stabilized spacecraft, for SSA
services.
Description:
The Sun's energy drives the complex physical interactions that we call Space
Weather. A key means of transferring energy from the Sun to the Earth’s
magnetic field is via the Solar Wind. Momentum and energy of solar wind ions
is imparted to the terrestrial magnetic field and this in turn drives the
circulation, energisation and losses of other plasma and trapped radiation
populations. Because of this, data on solar wind velocity and pressure are key
inputs to predictive physical and numerical models of a host of Space Weather
effects. To make this measurement accurately requires fine resolution in terms
of energy and direction. These fine measurements can cover a relatively limited
parameter space, centred on the solar wind mean ion energy for Hydrogen and
the mean flow direction. The spectrometer is expected to be based on the
electrostatic plasma analyser technique, whereby electric fields are used to
deflect and select particles within a series of energy bands.
Information on the direction of arrival of the ions is of interest but this could
be sacrificed for a design with low requirements for mass, power and
expenditure. However, all possible arrival angles of these ions (~+/- 15 degrees
from the Sun direction) must be covered. The energy range is expected to
include all energies between 400eV and 10keV. Clear separation of Hydrogen
and Helium ions shall be achieved.
In this phase B study a prototype sensor shall be developed and characterised
by simulation, supported by experimental testing. The result of the activity
include be a design for a flight model.
Deliverables:
Prototype and FM design
Current TRL:
4
Target
Application /
Timeframe :
TRL 6 by 2018/2019
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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Domain
SPACE SITUATIONAL AWARENESS
Technology Domain 4 Spacecraft Environment & Effects
Ref. Number:
G618-022EE
Budget (k€):
600
Title:
Medium Energy Particle Spectrometer 30-1000keV - Phase A/B
Objectives:
To design and develop a particle spectrometer to detect electrons and ions in the
range 30keV to 1MeV for use in providing data for SSA services.
Description:
Measurement of trapped particles in the Earth's magnetosphere is crucial to
provide Space Weather services for real-time now-casting and as an input to
forecasting models. Typically plasma measurements stop at around 30keV
because of the available technology of high voltage supplies in electrostatic
analysers. Radiation measurements often using solid state detectors with a
minimum energy of 100s keV for electrons or several MeV for ions. Low energy
electron channels in these detectors can be subject to proton contamination.
This leaves a gap of coverage between the plasma and radiation instruments that
is important , particularly for electrons. At these energies, electrons cause dose
effects and internal charging in thin films and they form part of the seed
population that gets energised to higher energies.
This activity shall trade off technologies for making reliable measurements of
electrons in particular in the energy range 30keV to 1 MeV. Separation of
electron measurements from ions is essential. Ion measurements are desirable
but not essential. The trade-off is expected to include the use of magnetic
deflection and thin solid state detectors. To act as a space weather monitor, the
instrument should have a wide field of view. Angular resolution is desirable but
this could be sacrificed for a simpler design.
In phase A preliminary design will be made after the trade off. A prototype will
be built and tested in phase B. Subsequently an FM design will be made.
Deliverables:
Prototype and FM design
Current TRL:
4
Target
Application /
Timeframe :
TRL 6 by 2018/2019
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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Domain
SPACE SITUATIONAL AWARENESS
Technology Domai 4 Spacecraft Environment & Effects
Ref. Number:
G618-023EE
Title:
Radiation Monitor System in a Package (RMSIP)
Objectives:
Develop a general-purpose radiation monitor with small size, easy interfacing
and low unit cost that is capable of registering and categorizing single particles.
Description:
Traditional radiation monitoring based on discrete components usually results
in relatively heavy instruments with relatively high procurement cost. However,
recent advances in Systems In Packages (SIPs), ASICs and Monolithic CMOS
sensors allows the development of highly integrated packages containing the
detection and processing electronics, and avoiding high voltages. This activity
will select the most appropriate technology from previous R&D in the space and
high energy physics domains, and design and prototype a radiation monitor that
can distinguish particle energy deposits in well-defined volumes, as a basis for
general purpose monitoring of electrons, protons and heavy ions. Spectroscopy
may be implemented in follow-on development with add-on selection
techniques based on shielding, stacking or magnetic field selection, but the
baseline should be a stand-alone minimal single sensor system. Target mass for
the system is <200g, including interfaces.
Deliverables:
Prototype, FM design
Current TRL:
3
Target
Application /
Timeframe :
2018/2019
Applicable THAG Roadmap:
Budget (k€):
Target TRL:
Duration
(months)
24
Radiation Environments & Monitoring, Effects Tools &
Testing (2009)
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500
ESA UNCLASSIFIED – For Official Use
Domain
SPACE SITUATIONAL AWARENESS
Technology Domain 4 Spacecraft Environment & Effects
Ref. Number:
G618-024EE
Title:
Enhancement of Physical and Assimilation Modelling of Radiation
Belts
Objectives:
Create a prototype of a service to predict the state of the radiation belts in
response to solar-terrestrial disturbances known to cause large variations in the
radiation belt fluxes - drop-outs, injections, energisation, radial transport, etc.
The starting point will be physics-based models of the radiation belts, supported
by assimilation of in-situ data. The service will conform to requirements related
to execution efficiency and usability, and will be validated through data
comparisons.
Description:
Improved understanding of radiation belt physics, aided in part by better data
availability and increasing computational power, has allowed the establishment
of complex multi-dimensional simulation capabilities that have shown some
success at simulating and predicting radiation belt dynamics, particularly for the
very dynamic "outer" electron belt. High fluxes of energetic electrons in the
outer belt are the main sources of radiation dose to electronic components but
also give rise to electrostatic discharge and solar array degradation. Affected
orbits include GEO and MEO, but also the orbits foreseen for some large
communications satellite constellations under development. There is a need to
predict the state of the outer radiation belt over long and short timescales and
scientific efforts have led to understanding of the key processes responsible and
an ability to simulate them. However, these scientific capabilities need to
developed into robust user-oriented systems that can deliver data to users in a
reasonable timescale in response to input on the state of the solar-terrestrial
system. The service prototype will be able to take as input data on solar wind
magnetic and plasma properties, geomagnetic indices and magnetosphere wave
conditions. Where input data are unavailable, for example on wave conditions,
the data will be derived from statistical correlation analyses. Data from particle
measurements (fluxes, counts) will be assimilated into the system to allow
improved predictions. The output will be a forecast of the global state of the
outer radiation belt as a function of time, and tailored outputs for key user orbits
(GEO, MEO, constellation orbits). Rigorous validation will be undertaken with
well-characterised case studies.
Deliverables:
Models, software and documentation, validation reports, TNs
Current TRL:
3
Target
Application /
Timeframe :
TRL 7 by 2018
Applicable THAG Roadmap:
Budget (k€):
Target TRL:
Duration
(months)
24
Radiation Environments & Monitoring, Effects Tools &
Testing (2009)
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3.5.2
TD 7- Electromagnetic Technologies and Techniques
Domain
SPACE SITUATIONAL AWARENESS
Technology Domain 7 Electromagnetic Technologies and Techniques
Ref. Number:
G618-025EE
Budget (k€):
600
Title:
Advanced Ionospheric Scintillation Modelling Demonstrator
Objectives:
To develop an operational demonstrator including existing and further
developed scintillation models in support to space weather nowcast applications.
Requirements for future physics-based modelling of space weather forecast
applications will as well be formulated.
Description:
Ionospheric scintillations are rapid fluctuations of amplitude and/or phase of a
radio wave signal caused by small scale irregularities which modify the
ionospheric refractive index. Strong scintillations can degrade GNSS receiver
performance leading to cycle slips and potentially loss-of-lock and navigation
solution. As such, they can impact the activities of a wide range of space weather
service users who rely on precise navigation and timing information.
Scintillations are most severe and prevalent in and north of the auroral zone and
near the geomagnetic equator. In the arctic region, they are thought to be
primarily caused by density gradients associated with polar cap patches, while at
equatorial latitudes scintillations are frequently observed after sunset resulting
from the change in solar ionisation. As a result, scintillation occurrence varies
with location, time of day, year and level of solar and geomagnetic activity.
Strong scintillations are rarely observed at mid-latitudes, but may occur during
very disturbed geomagnetic conditions.
This activity will develop an operational demonstrator that will include recent
scintillation models. The activity will further develop these models as necessary
for their inclusion in an operational demonstrator which will take into account
improved understanding of the conditions leading to scintillations in particular
in the arctic region. The output of this activity shall be capable of reflecting a
wide variety of the ionospheric conditions, including polar cap patches.
This demonstrator shall be capable of generating
regional and global
scintillation nowcast maps constructed by assimilating near real-time
scintillation measurements into the improved scintillation model. Requirements
will be formulated for future physics-based modelling in support of space
weather nowcast and forecast applications.
Deliverables:
Nowcast model demonstration including validation reporting, forecast model
specification.
Current TRL:
4
Target
Application /
Timeframe :
TRL 6 by 2018
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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Domain
SPACE SITUATIONAL AWARENESS
Technology Domain 7 Electromagnetic Technologies and Techniques
Ref. Number:
G618-026EE
Budget (k€):
Title:
Radio Spectrograph
measurement
Objectives:
Development of a space instrument enabling the measurement of Solar radio
emissions and Auroral kilometric radiation which are good indicators of
respectively solar activity and geomagnetic activities.
Description:
The radio emissions of interest are: Solar Type II (emitted along shock fronts
propagating in the inner heliosphere), Solar Type III (emitted by electron beams
by mode conversion from Langmuir waves) and terrestrial Auroral Kilometric
Radiation (emitted by precipitating electron particles in the auroral region of
Earth). The Frequency range of interest range from : ~1kHz => 16 MHz (AKR:
~50 kHz - ~500 kHz). These emissions, at frequencies below 10MHz, cannot be
measured from ground because of the ionosphere cut-off. An absolute
measurement accuracy of ~5% is targeted.
for
magnetospheric
and
solar
500
radio
The activity covers the Engineering Model development of a low mass space
instrument to monitor key radio emissions from the Sun and the Earth
magnetosphere.
The instrument shall include a low noise preamplifier and receiver with 3
parallel channels connected to 3 antenna simultaneously sensing each
frequency. Typical mass and power to achieve are 1kg (without antenna) and
1W.
The Engineering Model shall include the antennas and the electronic
equipments and be tested w.r.t. space environment.
Deliverables:
Engineering Model
Current TRL:
3
Target
Application /
Timeframe :
2018
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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Domain
SPACE SITUATIONAL AWARENESS
Technology Domain 7 Electromagnetic Technologies and Techniques
Ref. Number:
G618-027EE
Budget (k€):
500
Title:
THz technologies for space objects detection
Objectives:
The objective of this activity is to design, manufacture and test a ground
demonstrator of THz camera for space object detection.
Description:
Different space object detection mechanisms are being considered, and among
them (sub) millimetre wave instruments based on state-of-the-art terahertz
technologies. One of the main characteristics of (sub) millimetre wave
instruments is the possibility of seeing through clouds and dust at certain
window frequencies, which are not affected by the atmosphere or adverse
weather conditions. This would allow the continuous detection under all weather
conditions, even cloudy or foggy, which is a significant advantage with respect to
optical instruments.
The shorter wavelength of sub-millimetre wave instruments (300 to 3000 GHz)
as compared to millimetre wave (30 to 300 GHz), offers opportunities for
improved spatial resolution and therefore the possibility of detecting and
cataloguing much smaller particles. This is considered of paramount importance
for the safe operation of future satellites.
(Sub) millimetre wave detection and imaging offers large potential due to the
inherent spatial resolution and the all-weather detection capability. The activity
shall study the current status of this technology and shall assess the main SSTrelated performance parameters: detectable diameter, measurement accuracy of
position, range, and size quantities. Recommendations for further developments
shall be given.
Ground THz cameras, mainly for security and health applications, have been
successfully designed and tested. Although the concept is similar, an
optimization of the system in terms of configuration and optics, detector
technology and working frequency is required considering the requirements for
object detection.
The work logic of this study shall be:
- Consolidation of the requirements and assessment of performance
parameters.
- Trade-off analysis.
- Preliminary design.
- Breadboarding activities.
- Testing of the demonstrator.
- Conclusions and recommendations for further developments.
Deliverables:
Breadboard
Current TRL:
2
Target
Application /
Timeframe :
Debris detection/TRL 5 by 2018
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
18
Technologies for Passive Millimetre & Submillimetre
Wave Instruments (2010)
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3.5.3
TD 12- Ground Station System & Networking
Domain
SPACE SITUATIONAL AWARENESS
Technology Domain
12 Ground Station System & Networking
Ref. Number:
G618-016GS
Budget (k€): 1,000
Title:
L-Band SSPA for phased array radar transmitter (optimization of the
amplifier topology and of the mechanical/thermal design) and dual
polarization receiver (improved ADC and DSP)
Objectives:
To develop efficient transmitters to be used in a ground based surveillance radar
consisting of several thousands of elements. Moreover the activity aims at
supporting SSA final radar design activities by demonstrating the required
technologies for dual-pol multi-beam digital receivers.
Description:
The SSA final radar will require very powerful transmitters (order of Megawatts).
Each 1% increase on the efficiency mean tenths of kilowatts saved (and operational
costs reduced). In parallel, the dissipation is lower and the cost of the cooling
systems drops dramatically.
Presently there are state of the art topologies for SSPA that allow much better
efficiencies (on the power stage) than the typical 40% of the SSPAs presently used
in the ground stations (Class A or AB). Novel designs like Class D, E and F show
theoretical efficiencies up to 80% and articles show implementations that claim 6070% efficiency. Unfortunately this is still at academic level. Besides, many
parameters of interest for our application are not of interest for other applications
and there is no information available (phase stability, phase linearity, etc.).
The testing of the prototype shall include the effects of a ground station
environment and long duration test in order to assess the reliability and stability of
the power stages designed and manufactured. Also, the number of SSPA modules in
the transmitter will be in the order of thousands. The physical constraints of a
phased array antenna (spacing between radiating elements is fixed to
0.7*wavelength) generates demanding performances to the mechanical and thermal
design (electrical design is already covered by another TRP development).
Additionally a smart design looking on cost saving during the manufacturing phase
will save large amounts of money due to the high number of units to be
manufactured. The study shall perform the analysis of the physical constraints and
complete the mechanical and thermal design of the module to fulfil the
requirements especially on what relates to mechanical and thermal requirements. A
prototype shall be built. A first batch of 5 to 10 pre series units will be manufactured
after prototype acceptance to analyse the production process yield and allow the
integration in the Radar prototype and in- field performance testing.
A final SSA radar will be based on dual-polarization receivers and multiple beams
observations for both close-monostatic and bistatic configurations. The unknown
backscattering behaviour of space debris and the depolarization effects of the
ionosphere pose the requirement for dual polarization receivers. This implies the
development of compact RX antenna elements capable of receiving the two
components, which has not been addressed so far. The optimization of the resulting
RX antenna in terms of antenna pattern due to mutual coupling effects and return
loss is not trivial. The requirement on multiple beams (eg clusters) comes from the
requirement on scanning rate of the area of interest. In general, upgrading SSA
demonstrated technologies to the final radar architecture implies the evolution of
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the available Digital Receiver into a multiple-beam dual-pol Receiver with
enhanced data communication capabilities. The Digital Receiver is in charge of A/D
conversion, Digital Down Conversion, and (Adaptive) Digital Beamforming.
The current SSA implementation offers the possibility of handling 9 beams for
single polarization. It is based on daisy-chain sub-units connected in hierarchical 2level network. It is fully scalable, but the available components (ADC, FPGA I/O)
might represent bottlenecks in terms of maximum data rate and unit costs.
Handling tens or hundreds of beams with full signal bandwidth might lead to
requirements that cannot be met by available off the shelf technologies. This needs
to be further investigated in order to (i) reduce the risk in final radar procurement,
(ii) ensure non-dependence from non-EU or military technologies, and (iii) avoid
dramatic cost increase of the single receiver. The proposed activity aims at
designing, procuring and developing dual pol multi-beam Digital Receiver boards
for testing the entire set of RX functionalities in the final radar configuration.
Deliverables:
Breadboard
Current TRL:
4
Target
Application /
Timeframe :
2018
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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Domain
SPACE SITUATIONAL AWARENESS
Technology Domain 12 Ground Station System & Networking
Ref. Number:
G618-029GS
Budget (k€):
800
Title:
Flexible CCD for curved focal planes - detailed design and breadboarding
Objectives:
Produce a breadboard of a flexible CCD on a curved surface to demonstrate the
feasibility for Near Earth Objects (NEO) surveys for SSA. Produce a detailed
CCD design and prototype for an existing Schmidt telescope to be selected in
coordination with ESA.
Description:
For efficient NEO surveys telescopes require a wide field of view (FoV). Existing
Schmidt cameras have a FoV of up to 5 deg. x 5 deg. They could be used to
support NEO surveys by dedicated telescopes. While Schmidt telescopes have a
simple spherically shaped primary mirror they have a complex shaped corrector
plate and curved focal plane. While that was no problem for photographic film
CCD sensors are usually rigid. Present technology should allow developing
flexible CCDs that could be fitted to the given curvature of the Schmidt telescope
focal plane. Such a flexible CCD would allow the refurbishment and re-use of
existing Schmidt telescopes of various sizes for NEO observations.
This activity shall produce a breadboard of a flexible CCD on a curved surface to
demonstrate the feasibility and produce a detailed CCD design and prototype for
an existing Schmidt telescope to be selected in coordination with ESA.
Deliverables:
Breadboard
Current TRL:
3
Target
Application /
Timeframe :
2018/2019
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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Domain
SPACE SITUATIONAL AWARENESS
Technology Domain 12 Ground Station System & Networking
Ref. Number:
G618-030GS
Budget (k€):
1,000
Title:
S-Band SSPA for phased array radar transmitter (optimization of the
amplifier topology and of the mechanical/thermal design) and dual
polarization receiver (improved ADC and DSP)
Objectives:
To develop efficient transmitters to be used in a ground based surveillance radar
consisting of several thousands of elements. Moreover the activity aims at
supporting SSA final radar design activities by demonstrating the required
technologies for dual-pol multi-beam digital receivers.
Description:
The SSA final radar will require very powerful transmitters (order of Megawatts).
Each 1% increase on the efficiency mean tenths of kilowatts saved (and
operational costs reduced). In parallel the dissipation is lower and the cost of the
cooling systems drops dramatically.
Presently there are state of the art topologies for SSPA that allow much better
efficiencies (on the power stage) than the typical 40% of the SSPAs presently used
in the ground stations (Class A or AB). Novel designs like Class D, E and F show
theoretical efficiencies up to 80% and articles show implementations that claim
60-70% efficiency. Unfortunately this is still at academic level. Besides, many
parameters of interest for our application are not of interest for other applications
and there is no information available (phase stability, phase linearity, etc.). The
testing of the prototype shall include the effects of a ground station environment
and long duration test in order to assess the reliability and stability of the power
stages designed and manufactured. Also, the number of SSPA modules in the
transmitter will be in the order of thousands. The physical constraints of a phased
array antenna (spacing between radiating elements is fixed to 0.7*wavelength)
generates demanding performances to the mechanical and thermal design
(electrical design is already covered by another TRP development). Additionally a
smart design looking on cost saving during the manufacturing phase will save
large amounts of money due to the high number of units to be manufactured. The
study shall perform the analysis of the physical constraints and complete the
mechanical and thermal design of the module to fulfil the requirements especially
on what relates to mechanical and thermal requirements. A prototype shall be
built. A first batch of 5 to 10 (TBC) pre series units will be manufactured after
prototype acceptance to analyse the yield of the production process and allow the
integration in the Radar prototype and real on field testing of the units
performance.
Final SSA radar will be based on dual-polarization receivers and multiple beams
observations for both close-monostatic and bistatic configurations. The unknown
backscattering behaviour of space debris and the depolarization effects of the
ionosphere pose the requirement for dual polarization receivers. This implies the
development of compact RX antenna elements capable of receiving the two
components, which has not been addressed so far. The optimization of the
resulting RX antenna in terms of antenna pattern due to mutual coupling effects
and return loss is not trivial. The requirement on multiple beams (eg clusters)
comes from the requirement on scanning rate of the area of interest. In general,
upgrading SSA demonstrated technologies to the final radar architecture implies
the evolution of the available Digital Receiver into a multiple-beam dual-pol
Receiver with enhanced data communication capabilities. The Digital Receiver is
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ESA UNCLASSIFIED – For Official Use
in charge of A/D conversion, Digital Down Conversion, and (Adaptive) Digital
Beamforming. The current SSA implementation offers the possibility of handling
9 beams for single polarization. It is based on daisy-chain sub-units connected in
hierarchical 2-level network. It is fully scalable, but the available components
(ADC, FPGA I/O) might represent bottlenecks in terms of maximum data rate and
unit costs.
Handling tens or hundreds of beams with full signal bandwidth might lead to
requirements that cannot be met by available off the shelf technologies. This
needs to be further investigated in order to (i) reduce the risk in final radar
procurement, (ii) ensure nondependence from non-EU or military technologies,
and (iii) avoid dramatic cost increase of the single receiver. The proposed activity
aims at designing, procuring and developing dual pol multi-beam Digital Receiver
boards for testing the entire set of RX functionalities in the final radar
configuration.
Deliverables:
Breadboard
Current TRL:
4
Target
Application /
Timeframe :
2018
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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3.5.4
TD 16- Optics
Domain
SPACE SITUATIONAL AWARENESS
Technology Domain 16 Optics
Ref. Number:
G618-031MM
Title:
Compact Magnetograph for L-mission
Objectives:
Design and develop a prototype of a small space-based magnetograph required for
space weather applications (L1 or L5 mission - monitoring of the Sun's magnetic
field).
Description:
This activity will design and prototype a small magnetograph with appropriate
field of view, resolution and timing as defined in Enhanced Space Weather System
studies (~34 x 34 arcmin FOV, 10 arcsec pixel FoV, image cadence 1 minute). The
dynamic range must be up to +/- 4 kG with a tolerable noise contribution of ~20
Gauss. Standard instruments such as the magnetograph HMI onboard of SDO are
complex and overdesigned for a space weather mission. A new concept has been
investigated recently by JPL and a breadboard has been produced confirming the
potential to build a small and compact instrument. Technologies will build up on
such initial concept, shall prepare the European capability, mature the concept
and demonstrate the observational capabilities within the anticipated resources.
The instrument shall be deployable on a medium sized satellite expected to be
positioned in the L1 and/or L5 Lagrange point. Accommodation constraints
(interfaces, data rate, power, mass pointing requirements, etc.) will be analysed
on a conceptual basis. The main emphasis is to demonstrate the optical concept in
form of a prototype making use of laboratory detector. The prototype or
breadboard shall be designed and tested as much as possible in representative
environment. Phase C/D planning and development needs shall also be provided.
Hardware prototyping and demonstration of the feasibility to build such
instrument is the main goal of the activity.
Deliverables:
Breadboard
Current TRL:
4
Target
Application /
Timeframe :
TRL 6 by 2018
Applicable THAG Roadmap:
Budget (k€):
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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1,000
24
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Domain
SPACE SITUATIONAL AWARENESS
Technology Domain 16 Optics
Ref. Number:
G618-032MM
Title:
Heliospheric imager for L-mission
Objectives:
Design and develop a prototype of a small space-based heliospheric imager
required for space weather applications within SSA.
Description:
This activity will take advantage of the heritage from STEREO HI instrument.
The activity shall review the current performance and update and optimise it for
the needs of the SSA programme. This is needed because the technology is
already about to retire, and therefore considered as partly out-dated and not
consistent with the state-of-the-art technologies for upcoming missions. The
instrument shall enable the monitoring of the space between the Sun and the
Earth extending its field from the Sun towards as much as possible to the Earth
when positioned at L1 or L5. The prototype shall be compatible with the
requirements as established in the Enhanced Space Weather System studies. It
shall have 30 (T) to 60(G) degree FOV, ~1.5 arcmin pixel FoV, and operate at an
image cadence of 30 minutes. The dynamic range shall allow the monitoring of
CMEs in the designated interplanetary space with light rejection levels between
3x10-13 to 10-14. Technologies will build up on the heritage from STEREO HI
and shall focus on the optimisation of the instrument for the specified
requirements and address potential difficulties for a rebuild of the instrument
for the L missions. The instrument shall therefore be deployable on a medium
satellite expected to be positioned in the L1 or L5 Lagrange points.
Accommodation constraints (interfaces, data rate, power, mass pointing
requirements, etc.) will be analysed on a conceptual basis. The main emphasis is
to demonstrate the optical and sensor concept in form of a prototype that shall
be tested in representative environment. Phase C/D planning will also be made.
Hardware prototyping of the critical technologies is included in the activity.
Deliverables:
Engineering Model
Current TRL:
Not specified
Target
Application /
Timeframe :
2018
Applicable THAG Roadmap:
Budget (k€):
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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18
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3.5.5
Domain
TD 26- Others
SPACE SITUATIONAL AWARENESS
Technology Domai 8 System Design & Verification
Ref. Number:
G618-028SY
Budget (k€):
300
Title:
Cubesat/nanosat mission concepts for operational SWE system
Objectives:
Definition and analysis of mission concepts utilising cubesats and nanosats for
performing observations for operational space weather services in SSA
Description:
Cubesats and nanosats offer low cost access to space for small instrumentation.
Within R&D programmes various small payloads are under development (e.g.
highly miniaturized radiation and plasma monitors, GPS receivers, cameras,
magnetometers). In the ESA R&D programmes very small instruments and cubesat
platform technologies are also under development.
This activity will address the challenge of how cubesat and nanosat missions can be
utilised in the framework of an operational space weather monitoring system.
While the usability of very small satellites for scientific experiments and technology
demonstration has been demonstrated, operational mission concepts have to also
consider the continuity of the measurements, measurement accuracy, data
timeliness, and many other challenges. This activity shall define and analyse
cubesat and nanosat mission concepts that would address the space based
observation needs of the operational SSA SWE system. This activity shall identify
technology developments that would be necessary to make these missions feasible
and propose a roadmap for implementing demonstration missions. The activity
shall also address the contamination and electrostatic cleanliness issues associated
with the integration of payloads in case that off-the-shelf cubesat platforms are
proposed.
Deliverables:
Study Report
Current TRL:
Not specified
Target
Application /
Timeframe :
2018
Applicable THAG Roadmap:
Target TRL:
Duration
(months)
Not related to a Harmonisation Subject
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Not specified
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ESA UNCLASSIFIED – For Official Use
ANNEX I
List of activities in
GSTP-6 E1 Work Plan/Procurement Plan
Annex I, Page 203/222
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Annex I, Page 204/222
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4
ANNEX I - ACTIVITIES IN GSTP-6 E1 WORK PLAN /
PROCUREMENT PLAN
EARTH OBSERVATION
TD 6- RF Payload and Systems
GSTP-6
Reference
G611-008ET
Title
Budget(K€)
High Power GaN C-band TRM Demonstrator
1,000
Total
1,000
TD 17- Optoelectronics
GSTP-6
Reference
G611-017MM
Title
Budget(K€)
High stability laser for interferometric Earth Gravity measurements in the
context of a Next Generation Gravity Mission (NGGM)
Total
1,700
1,700
TD 26- Other: Earth Observation (Systems and Ground)
GSTP-6
Reference
G611-018EO
G611-021EO
G611-022EO
Title
Budget(K€)
Broker Technology enabling discovery and exploitation of Earth
Observation data (BT4EEO)
EVOlution of EO Online Data Access Services - EVO-ODAS
Technology and Atmospheric Mission Platform (TAMP)
500
1,000
500
Total
2,000
SPACE TRANSPORTATION
TD 18- Aerothermodynamics
GSTP-6
Reference
G614-004MP
Title
Budget(K€)
Experimental characterisation of transient flow phenomena in cryogenic
fluids
Total
Annex I, Page 205/222
GSTP-6 Element 1 Compendium of Potential Activities
Date 5-02-2016 Issue 1 Rev 2
500
500
ESA UNCLASSIFIED – For Official Use
NAVIGATION
TD 6- RF Payload and Systems
GSTP-6
Reference
G616-008ET
Title
Budget(K€)
Compact ultra-high stability atomic clock for Space applications
1,000
Total
1,000
GENERIC TECHNOLOGIES AND TECHNIQUES
TD 1- On-board Data Systems
GSTP-6
Reference
G617-003ED
G617-005ED
G617-008ED
Title
Budget(K€)
Reconfigurable Payload Processor
Transducer interface ASIC
Demonstration and validation of an inter-processor link for future
OBCs
Total
1,000
1,000
300
2,300
TD 2- Space System Software
GSTP-6
Reference
G617-010SW
G617-011SW
Title
Budget(K€)
Multicore implementation of the On-Board Software Reference
Architecture with IMA capability
RTEMS qualification extensions
Total
500
500
1,000
TD 3- Spacecraft Electrical Power
GSTP-6
Reference
G617-015EP
G617-017EP
Title
Budget(K€)
Implementation of new Power Systems architectures for LEO
missions - Solar Array Regulator based on Buck-Boost Regulator
Lithium-ion VES16 cell Balancing System
Total
600
400
1,000
TD 4- Spacecraft Environment & Effects
GSTP-6
Reference
G617-024EE
Title
Budget(K€)
ESD monitor
500
Total
Annex I, Page 206/222
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Date 5-02-2016 Issue 1 Rev 2
500
ESA UNCLASSIFIED – For Official Use
TD 5- Space System Control
GSTP-6
Reference
G617-028EC
G617-030EC
G617-035EC
G617-036EC
Title
Budget(K€)
High accuracy image stabilization system prototyping
GNC Analysis, Design and Verification Framework using MATLAB
only
Generic AOCS/GNC techniques and design framework for Failure
Detection Isolation and Recovery
Pointing Error Engineering Software Framework
Total
1,000
300
700
400
2,400
TD 6- RF Payload and Systems
GSTP-6
Reference
G617-037ET
G617-040ET
G617-045ET
Title
Budget(K€)
Advanced manufacturing and integration techniques for TT&C
transponders/transceivers
Miniaturized Timing Sources
GNSS Software-defined Space Receiver
Total
800
1,000
600
2,400
TD 7- Electromagnetic Technologies and Techniques
GSTP-6
Reference
G617-047EE
G617-051EE
G617-052EE
Title
Budget(K€)
Millimeter wave Validation Standard (mm-VAST) antenna
Accurate RF material characterisation using scattering
measurements from Quasi-Optical bench
Medium-to-high gain X-band antenna with customisable pattern
and polarisation
Total
350
300
600
1,250
TD 8- System Design & Verification
GSTP-6
Reference
G617-054SW
Title
Budget(K€)
Precise and Flexible Wiki-Based Requirements Engineering
700
Total
Annex I, Page 207/222
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Date 5-02-2016 Issue 1 Rev 2
700
ESA UNCLASSIFIED – For Official Use
TD 9- Mission Operations and Ground Data Systems
GSTP-6
Reference
G617-062GI
G617-065GI
G617-066GI
Title
Budget(K€)
Security as a Service for Ground Data Systems
Scalable ground systems for high rate and high volume mission
operational data
Automated rule-based cross-validation of operational data
Total
300
500
400
1,200
TD 12- Ground Station System & Networking
GSTP-6
Reference
G617-074GS
G617-075GS
Title
Budget(K€)
Eye-Safe Ground Beacon System
Experimental 20-40 GHz band InP MMIC based cryogenic LNAs
prototyping
Total
400
500
900
TD 14- Life & Physical Sciences
GSTP-6
Reference
G617-077MM
Title
Budget(K€)
In Situ Plasma Cleaning of Space Optics
600
Total
600
TD 15- Mechanisms & Tribology
GSTP-6
Reference
G617-081MS
G617-082MS
Title
Budget(K€)
Improvement of high accuracy angular optical sensors
Advanced simulation tools for deployment, dynamics predictions
and on-ground verification
Total
Annex I, Page 208/222
GSTP-6 Element 1 Compendium of Potential Activities
Date 5-02-2016 Issue 1 Rev 2
800
300
1,100
ESA UNCLASSIFIED – For Official Use
TD 16- Optics
GSTP-6
Reference
G617-085MM
G617-087MM
G617-088MM
G617-089MM
G617-090MM
Title
Budget(K€)
Digital Micro-Mirror Array (DMA) for space optical instruments
High Speed Deterministic Polishing of Strongly Aspherical Mirrors
WFE test of large aspheric optics
Effect of radiation on light-weighted mirror substrates (in
particular Zerodur)
Particle contamination: scattering models and measurement device
1,000
800
500
750
Total
3,550
500
TD 17- Optoelectronics
GSTP-6
Reference
G617-092MM
G617-096MM
G617-097MM
Title
Budget(K€)
Multi-Gigabit Optical Fiber Communications
Low cost, low power, medium performance resonant-micro-optical
Gyrosope (RMOG) based on resonant ring lasers
High performance optical filters based on Si fine grid supported
ultra thin SiN foils
Total
600
800
220
1,620
TD 19- Propulsion
GSTP-6
Reference
G617-099MP
G617-100MP
Title
Budget(K€)
CUSP ION ENGINE
Improvement of the lifetime of Electric Propulsion Thrusters using
different propellant by reducing sputtering effects on materials
Total
1,000
300
1,300
TD 20- Structures & Pyrotechnics
GSTP-6
Reference
G617-083MS*
G617-101MS
G617-104MS
G617-106MS
G617-107MS
Title
Budget(K€)
In-orbit manufacturing of very long booms.
Verification of Composite Laminates under Cryogenic ThermoMechanical Loading
Development of modular multifunctional structure panel prototype
Demonstration of Thermoplastic Composites
MATS: Multilayer Adaptive Thin Shell Reflectors for Future Space
Telescopes
Total
* This activity was previously in TD15 and has been moved to TD20.
Annex I, Page 209/222
GSTP-6 Element 1 Compendium of Potential Activities
Date 5-02-2016 Issue 1 Rev 2
200
300
450
500
600
2,050
ESA UNCLASSIFIED – For Official Use
TD 21- Thermal
GSTP-6
Reference
G617-110MT
G617-111MT
G617-112MT
Title
Budget(K€)
Low Profile, Low Thermal Conductivity and Highly Stable StandOffs
Enhancement of Loop Heat Pipe (LHP) Modelling Tool
Bi-Metallic Junctions for Loop Heat Pipes and Heat Pipes
Total
300
150
300
750
TD 22- Environmental Control Life Support (ECLS) and In-Situ Resource
Utilisation (ISRU)
GSTP-6
Reference
G617-115MM
Title
Budget(K€)
Study of countermeasures against microbial contamination of
spacecraft and payloads
Total
350
350
TD 23- EEE Components and quality
GSTP-6
Reference
G617-123QT
Title
Budget(K€)
Improved thermal management capability of power
semiconductors
2,000
Total
2,000
TD 24- Materials and Processes
GSTP-6
Reference
G617-125QT
G617-127QT
G617-130QT
G617-131QT
G617-132QT
Title
Budget(K€)
Friction Stir Welded Low Cost Titanium Propellant Tank
Evaluation of the potential of the Thin Ply Technology for space
applications
Evaluation of lighter and more efficient radiation protection for
electronic and sensitive parts
Filament winding TISIC
Electron Beam Welding for Safety Critical Space Applications
Total
Annex I, Page 210/222
GSTP-6 Element 1 Compendium of Potential Activities
Date 5-02-2016 Issue 1 Rev 2
1,500
700
500
2,500
500
5,700
ESA UNCLASSIFIED – For Official Use
Specific area: Clean Space
TD 3- Spacecraft Electrical Power
GSTP-6
Reference
G61C-021EP
Title
Budget(k€)
Spacecraft power system passivation at end of mission
400
Total
400
TD 5- Space System Control
GSTP-6
Reference
G61C-016EC
GNC for drag augmentation devices
450
G61C-018EC
Rapid Assessment of Design Impact on Debris Generation
500
G61C-029EC
Image Recognition and Processing for Navigation
600
Title
Budget(k€)
Total
1,550
TD 11- Space Debris
GSTP-6
Reference
G61C-024GR
Title
Budget(k€)
G61C-026SY
Optical In-Situ Monitor
Enhancement of S/C Fragmentation and Environmental Evolution
Models
Phase B1 of an Active Debris Removal mission (2 parallel studies)
G61C-034GR
Debris Attitude Motion Measurements and Modelling
G61C-025GR
1,200
300
1,600
600
Total
3,700
TD 13- Automation, Telepresence & Robotics
GSTP-6
Reference
G61C-032MM
Title
Budget(k€)
Harpoon characterisation, breadboarding and testing for Active
Debris Removal (ADR)
Total
700
700
TD 16- Optics
GSTP-6
Reference
G61C-028MM
Title
Budget(k€)
Miniaturized Imaging LIDAR System (MILS) for Rendezvous &
Docking operations between spacecraft
Total
Annex I, Page 211/222
GSTP-6 Element 1 Compendium of Potential Activities
Date 5-02-2016 Issue 1 Rev 2
1,200
1,200
ESA UNCLASSIFIED – For Official Use
TD 19- Propulsion
GSTP-6
Reference
G61C-005MP
Hydrogen Peroxide Storability/Compatibility Verification
1,000
G61C-017MP
De-orbit motor Engineering Model Manufacturing and Testing
1,300
Title
Budget(k€)
Total
2,300
TD 20- Structures & Pyrotechnics
GSTP-6
Reference
G61C-014MS
Deployable Membrane
400
G61C-015MS
Architectural design and testing of the Sub-system boom-sails
600
Title
Budget(k€)
Total
1,000
TD 24- Materials and Processes
GSTP-6
Reference
G61C-007QT
G61C-008QT
Title
Budget(k€)
Surface Engineering for parts made by Additive Manufacturing
(Step 1)
Verification methodology for parts made by Additive Manufacturing
G61C-010QT
Sustainable, green ancillary materials for structure manufacturing
G61C-036QT
Development and test of Additive Manufactured space hardware
Total
600
500
200
1,300
2,600
26- Others
GSTP-6
Reference
G61C-001SY
G61C-002SY
Title
Budget(k€)
Space propellants Life Cycle Assessment (LCA)
Life Cycle Assessment (LCA) of manufacturing processes and space
materials
Total
Annex I, Page 212/222
GSTP-6 Element 1 Compendium of Potential Activities
Date 5-02-2016 Issue 1 Rev 2
300
400
700
ESA UNCLASSIFIED – For Official Use
Specific area: SAVOIR
GSTP-6
Reference
G61V-001EC
G61V-005ED
Title
Budget(K€)
AES/SAVOIR New models for the AOCS Unit Simulation Models
Library (AOCS UnitSim)
AES/SAVOIR Electronic Data sheet definition
Total
400
800
1,200
SPACE SITUATIONAL AWARENESS
TD 4- Spacecraft Environment and Effects
GSTP-6
Reference
G618-007EE
G618-009EE
G618-011EE
Title
Budget(K€)
Development of a compact Remote Interface Unit (RIU) - Phase A/B/C/D
Prototype Compact Wide Angle Coronagraph
Phase C/D of 3D Energetic Electron Spectrometer
Total
650
700
2,000
3,350
TD 9- Mission Operations and Ground Data Systems
GSTP-6
Reference
G618-013GD
Title
Budget(K€)
General-purpose computing on graphics processing units for SSA Ground
Data Systems
Total
Annex I, Page 213/222
GSTP-6 Element 1 Compendium of Potential Activities
Date 5-02-2016 Issue 1 Rev 2
300
300
ESA UNCLASSIFIED – For Official Use
Page intentionally left blank
Annex I, Page 214/222
GSTP-6 Element 1 Compendium of Potential Activities
Date 5-02-2016 Issue 1 Rev 2
ESA UNCLASSIFIED – For Official Use
ANNEX II
List of cancelled activities from the initial
Compendium
Annex II, Page 215/222
GSTP-6 Element 1 Compendium of Potential Activities
Date 5-02-2016 Issue 1 Rev 2
ESA UNCLASSIFIED – For Official Use
Page intentionally left blank
Annex II, Page 216/222
GSTP-6 Element 1 Compendium of Potential Activities
Date 5-02-2016 Issue 1 Rev 2
ESA UNCLASSIFIED – For Official Use
5
ANNEX II - ACTIVITIES CANCELLED FROM THE
INITIAL COMPENDIUM
EARTH OBSERVATION
TD 7- Electromagnetic Technologies and Techniques
GSTP-6
Reference
G611-012EE
Title
Budget(K€)
Synthesis, analysis and optimization of slotted waveguide antennas
300
Total
300
TD 12- Ground Station System & Networking
GSTP-6
Reference
G611-013GS
G611-014GS
Title
Budget(K€)
Enhanced antenna tracking receiver for 26 GHz K-band
8-PSK modulation in ESA TT&C receiver
600
350
Total
950
TD 16- Optics
GSTP-6
Reference
G611-015MM
Title
Budget(K€)
BSDF measurement facility
500
Total
500
TD 26- Other: Earth Observation (Systems and Ground)
GSTP-6
Reference
G611-019EO
G611-020EO
G611-023EO
G611-025EO
Title
Budget(K€)
Geosounder products, data processing study, and end-to-end performance
study
Geosounder Requirements Consolidation Study
Multimission Environmental DatA
FAst Multimission tEstbed architecture - FAME-C
Total
Annex II, Page 217/222
GSTP-6 Element 1 Compendium of Potential Activities
Date 5-02-2016 Issue 1 Rev 2
300
200
800
900
2,200
ESA UNCLASSIFIED – For Official Use
SPACE TRANSPORTATION
TD 5- Space System Control
GSTP-6
Reference
G614-002EC
Title
Budget(K€)
Hybrid navigation breadboard and demonstration
2,000
Total
2,000
TD 14- Life and Physical Sciences
GSTP-6
Reference
G614-003MM
Title
Budget(K€)
Optical Tomography on bubble formation in cryogenic fuel tanks
600
Total
600
NAVIGATION
TD 6- RF Payload and Systems
GSTP-6
Reference
G616-006ET
G616-007ET
Title
Budget(K€)
Advanced GNSS Reference Station DSP technology platform
A 300W L band GaN power module and EM SSPA demonstrator
1,500
1,000
Total
2,500
GENERIC TECHNOLOGIES AND TECHNIQUES
TD 1- On-board Data Systems
GSTP-6
Reference
G617-002ED
G617-004ED
Title
Budget(K€)
European DSP for Space Radhard Implementation
SpaceWire Node Interface Chip
6,000
1,000
Total
7,000
TD 2- Space System Software
GSTP-6
Reference
G617-009SW
Title
Budget(K€)
OBCP BB Product Specification Validation
700
Total
Annex II, Page 218/222
GSTP-6 Element 1 Compendium of Potential Activities
Date 5-02-2016 Issue 1 Rev 2
700
ESA UNCLASSIFIED – For Official Use
TD 3- Spacecraft Electrical Power
GSTP-6
Reference
G617-014EP
Title
Budget(K€)
Voltage Clamp Integrated Circuit
Total
350
350
TD 4- Spacecraft Environment & Effects
GSTP-6
Reference
G617-021EE
G617-023EE
G617-025EE
G617-026EE
G617-027EE
Title
Budget(K€)
Magnetic Radiation Shielding Simulator
Experimental validation of 3D shielding tools for electrons
Phase C/D Compact Hot Plasma Monitor
Study of radiation energy effects on electronic components with
high energy heavy ion beams.
Geant4 kernel speed-up for high-efficiency simulations in space
Total
400
500
1,400
500
500
3,300
TD 5- Space System Control
GSTP-6
Reference
G617-031EC
Title
Budget(K€)
Micro Miniature Star Tracker
1,400
Total
1,400
TD 7- Electromagnetic Technologies and Techniques
GSTP-6
Reference
G617-046EE
Title
Budget(K€)
Scattering analysis by surface current mapping utilizing NF
scanners with contactless antenna surface profile measurement
instrumentation.
Total
300
300
TD 14- Life & Physical Sciences
GSTP-6
Reference
G617-079MM
Title
Budget(K€)
Optimisation and validation of ultra cleaning methods applied to
spacecraft materials
Total
Annex II, Page 219/222
GSTP-6 Element 1 Compendium of Potential Activities
Date 5-02-2016 Issue 1 Rev 2
500
500
ESA UNCLASSIFIED – For Official Use
TD 17- Optoelectronics
GSTP-6
Reference
G617-093MM
G617-094MM
Title
Budget(K€)
Vacuum chamber technologies for Atom Interferometry
applications
Enhancement of electrostatic accelerometers for earth and
planetary science and fundamental physics: flight data analysis,
model and design refinement, breadboarding and testing
Total
800
800
1,600
TD 23- EEE Components and quality
GSTP-6
Reference
G617-117QT
G617-122QT
G617-124QT
Title
Budget(K€)
ESCC evaluation and qualification of a monolithic magnetometer
based on micro technology
Miniature Solderless Interposer Type Connector
Development of Standard Interface Components
Total
600
500
800
1,900
Specific area: Clean Space
TD 13- Automation, Telepresence & Robotics
GSTP-6
Reference
G61C-030MM
Title
Budget(k€)
Net-Winch-Tether design and breadboard development
450
Total
450
TD 15- Mechanisms & Tribology
GSTP-6
Reference
G61C-031MS
Breadboard development of the throw-net ejector mechanism
400
G61C-033MS
Breadboard of a clamping based capture mechanism
450
Title
Budget(k€)
Total
Annex II, Page 220/222
GSTP-6 Element 1 Compendium of Potential Activities
Date 5-02-2016 Issue 1 Rev 2
850
ESA UNCLASSIFIED – For Official Use
TD 19- Propulsion
GSTP-6
Reference
G61C-004MP
MON/MMH replacement with green bi-propellant - Phase 1
750
G61C-006MP
Key propulsion system hardware development/requal - Phase 1
500
G61C-020MP
Development of a non-pyrotechnic passivation valve
600
G61C-022MP
Characterization of Ultrasonic Gauging Sensor for membrane tanks
Enhancement of Passivation Techniques for Current and Future
Missions
300
G61C-023MP
Title
Budget(k€)
Total
800
2,950
TD 20- Structures & Pyrotechnics
GSTP-6
Reference
G617-105MS
Title
Budget(K€)
Fibre Steering
750
Total
750
*In GSTP-5 Work Plan.
TD 24- Materials and Processes
GSTP-6
Reference
G61C-009QT
G61C-011QT
G61C-013QT
Title
Budget(k€)
Qualification of green cleaning processes
Development of Green Polyurethane Materials for Use in Space
Applications
Novel energy efficient processes for thermoplastic composite
manufacturing
Total
300
300
500
1,100
Specific area: SAVOIR
GSTP-6
Reference
G61V-002SW
Title
Budget(K€)
AES/SAVOIR: IMA-SP Execution Platform partition kernel
qualification
500
Total
Annex II, Page 221/222
GSTP-6 Element 1 Compendium of Potential Activities
Date 5-02-2016 Issue 1 Rev 2
500
ESA UNCLASSIFIED – For Official Use
SPACE SITUATIONAL AWARENESS
TD 4- Spacecraft Environment and Effects
GSTP-6
Reference
G618-005EE
Title
Budget(K€)
Wide-field space-based auroral camera prototype
500
Total
500
TD 11- Space Debris
GSTP-6
Reference
G618-014GR
G618-015GR
Title
Budget(K€)
Development of semi-analytical methods for orbital lifetime estimation
and re-entry propagation
Development of an efficient method for mean elements computation from
precise orbital data and its associated analytic propagation method
Total
250
300
550
TD 12- Ground Station System & Networking
GSTP-6
Reference
G618-017GS
Title
Budget(K€)
Breadboarding of an intelligent telescope CMOS APS
1,500
Total
Annex II, Page 222/222
GSTP-6 Element 1 Compendium of Potential Activities
Date 5-02-2016 Issue 1 Rev 2
1,500