Vega VV02
a new chapter in a
success story
ASI HQ, Tor Vergata, Rome
10th July 2013
Flight Program SW 2ND Source
(FPSA) Development/Validation
and Qualification Programme
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proprietary and is disclosed in confidence. It is the property of
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Chapter #1 – The challenges of FPS-A
This venture sounds tough
You definitely need help.
(to fly, navigate, guide, control,
separate the stages, to release the
P/L…)
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Chapter #2 – The challenges of FPS-A :
the Teamwork
To answer to the ESA challenging request, ELV as FPS Prime contractor, put in place
a well committed industrial team, selecting the best competence and skills in Europe
from GNC and SW disciplines, each with a specific role:
AVIO (Italy) – Starting from TRR, AVIO activities have been
performed by ELV
Centro Italiano Ricerche Aerospaziali - Most in Colocation
MBDA (Italy) – Partly in Colocation
Telespazio (Italy)
Spacebel (Belgium) - Most in Colocation
GMV (Spain) - Most in Colocation
SENER (Spain) for ISVV directly managed by ESA
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Chapter #2 – The challenges of FPS-A :
the Teamwork-Project Organization
TELESPAZIO
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Chapter #2 – The challenges of FPS-A :
the Teamwork- Project Organization
ELV
Remote
TELESPAZIO
Program & Project
Manager
Local
PA & RAMS
MBDA
AVIO/ELV
SpaceBel
CIRA
GNC & SW
Design Phase
GMV
GNC Algos
SW System
Design
GNC Technical
Responsible
SW Technical
Responsible
GNC Development
FPSA Detailed
Design and
Integration Phase
Validation &
Refinement Phase
SW Technical
Responsible
SW Technical
Responsible
Qualification
Phase
SW Tools
Development
Phase
SW Technical
Responsible
SW Technical
Responsible
GNC Simulation &
RACS
GNC support
SW Technical
Responsible
SW Tecnical
Responsible
SW Technical
Responsible
GNC Support
GNC
DevelopmentTeam
GNC Simulation &
RACS Team
GNC Support
RACS Support
FPSA Design
Team
FPSA Development
Team
Support to
SW design
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Validation Team
Qualification
Team
SW Tools
Development Team
OBC Simulator
COMIT
Development
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Chapter #2 – The challenges of FPS-A :
the Teamwork- Project Organization
ELV roles:
Is the LV System Prime and the FPS-A
Design Authority:
• Manages Program and Technical
activities as prime contractor;
• Defines the functional specifications
and follows the development for the
principal SW products (On Board
Computer Software e SW tools);
• Adapts and updates the simulation
environments. Prepares the validation plans
for the GNC algorithms and verifies the • Performs system activities. Defines,
results;
tunes and validates GNC algorithms
in frequency/time domain;
• Validates the integrated FPSA Products at SW
& GNC level. Qualifies FPSA in HWIL
platform.
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Chapter #2 – The challenges of FPS-A :
the Teamwork- Project Organization
MBDA roles:
Develop “Software Validation Facility”
(SVF) used to perform the software
validation tests of the FPSA SW. The
SVF is developed in two benches:
• SVF-SIM: simulated environment
using the OBC Simulator
• SVF-SDM:
real-time
environment using the OBC SW
Development Model
TELESPAZIO
Verify the GNC algorithms :
• Test Procedure
• Simulation & Performance
Assessment
• Compliance Analysis
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Chapter #2 – The challenges of FPS-A :
the Teamwork- Project Organization
Telespazio roles:
• Detailed Design, Coding, Unit and part
of Integration Testing of Flight
Programme Software (FPS) Alternative
TELESPAZIO
• Operational flight implementation of
Guidance, Navigation and Control
(GNC) algorithms and their integration
within FPSA
• Development of GNC numerical validation tool
(FPSSIM) to be used by ELV to validate GNC
algorithms functionality in all different mission
types
• Development of the Sign Verification Software
tool (SVS) to check LV actuators before
uploading FPSA to the rocket itself
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Chapter #2 – The challenges of FPS-A :
the Teamwork- Project Organization
CIRA roles:
GNC Support activities on
• Roll and Attitude Control Algorithm Design
and Assessment for both the Propelled and
the Ballistic Mission phases of the VEGA
• Definition of the RACS Algorithm
Verification Plan
Two algorithms were compared under several
aspects for the most relevant and sizing
mission phases (P/L release – spinned and
stabilized – and Long Coasting Phase):
 Switching Lines (SL)
 Quaternion Feedback Regulator (QFR)
TELESPAZIO
• Participating to Detailed Algorithm
Development and Preliminary Assessment
• Supporting the C-code prototype
implementation and testing
From VV02 flight outcomes, the RACS
algorithms resulted more propellant efficient
than the previous FPS architecture
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Chapter #2 – The challenges of FPS-A :
the Teamwork- Project Organization
SpaceBel roles:
• Develops and validates the OBC
simulator, a model of the VEGA OBC,
used in SVF platform to support the
verification of the FPSA
TELESPAZIO
• Strongly and effectively involved in
the definition and implementation of
the Configuration and Missionization
tool
• Supports GNC team for consolidation of the
FPSA GNC Engineering Code
• Involved in the Optimisation of the
missionization process
• Supports SW team in the definition of FPSA
Architecture and SW Tools
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Chapter #2 – The challenges of FPS-A :
the Teamwork- Project Organization
GMV roles:
• Provides support for the GNC
development( consolidation phase);
• Provides support to define and issue
the relevant GNC algos Definition
Files ;
• Deeply involved in GNC Engineering
code improvement during the
preliminary phase of design;
• Support for validation activities of
GNC algos and relevant Test Report
TELESPAZIO
• Support for improvements on GNC algos to
better manage all the LV flight phases
mainly focus on Guidance/Navigation and
RACS algos;
• SW PA and RAMS activities
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Chapter #3 – The challenges of FPS-A :
Development logic in a tight schedule
The FPSA is a Mission Critical SW and required special Development and testing
Rules imposed by ESA ECSS rules and VEGA standards MR-90 and SG-34
 Specific design at GNC/SW level have been performed to be compliant with:
 Safety constraints (stage re-entry and footprint reduction in adaptive mode in flight)
 LOS ( space debris meeting French law) mainly for AVUM de-orbiting phase
 FPSA has to be compatible with the VEGA Mission Scenario covering:
 P/L Mass range from 300 to 2500 Kg
 Orbit inclination : from Equatorial to SSO
 To manage the AVUM (Upper Stage) Re-ignition for a total of 5 ignitions
Note that FPS developed by Astrium for VV_01 covered only mission “Type 2” with only 3 AVUM boosts
The full FPSA qualification logic was designed to be compatible with all the technical
needs and with a very tight schedule on which the main constraints was VV_02 (multi PL
mission with 5 AVUM ignitions and 3 satellites released in different orbits).
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Chapter #3 – The challenges of FPS-A :
FPS Development logic in a tight schedule
FPS Development Logic
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Chapter #4 – The challenges of FPS-A :
An original Development Logic
To matches the technical and programme challenges the FPS-A development
life cycle has been deeply optimized and presents several original features.
Concurrent development of GNC algorithms and Software are managed
through a Double V cycle with specific instances of integration between the
two branches of development.
ATPl, ATPr, QTPl, QTPr
System
Requirements
Qualification
(HWIL)
Validated SW,
VaTRe
CF, SI
VaTPl, VaTPr
Technical
Specification
Validation
ST, ICD
Integrated SW,
ITRe
Architectural
Design
Integration
HW/SW
SW/SW
ITPl, ITPr
AD
SW Modules,
UTRe
UTPl, UTPr
Detailed Design
Unit Tests
SW Modules
DD
Coding
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Chapter #4 – The challenges of FPS-A :
FPS Development logic in a tight schedule
Original Phasing and Planning
6 Months
18 Months
9 Months
1st Phase (up to PDR)
Requirements Definition
2nd Phase (optional)
SW Architect. Design
SW Delta Design
HWIL 6 Qualification
GNC Design and Tuning
SW Detailed Design
SW Coding (incl. GNC)
SW Integration and Testing
System Activities
OBCS Design. Auth. Act.
SW Validation
OBCS Dev. Activities
SW Qualification (HWIL)
SW Tools Dev. Activities
SW Tools Development
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SW Missionization
SW Qualification (HWIL6)
Chapter #4 – The challenges of FPS-A :
An original Development Logic
An original and innovative approach has been used into FPSA programme with the aim
to include in the SW the multi-mission capabilities already provided by the launcher.
The design foresees:
 Short time for SW reconfiguration: the mission timeline is defined as a configurable
table-driven state machine that defines the ‘SW operating modes’ sequence and
the actions to be performed in each state (for launcher and GNC management)
 Definition of pre-defined I/O messages towards external equipment (for
commands and retrieval of data) generated through automatic exports of System
Database
 Missionisation and Configuration tool which guarantees time saving during the
flight parameters definition and the coherence/correctness of handled data and, at
the same time, limit the recurrent production costs of the FPS missionized
executable
 GNC library: designed as configurable module with defined I/F with the SW
Key of success was the usage of the last (state of the art) technologies in
terms of design tool, development environments and validation/
qualification platforms. Most of the tasks were supported by a concurrent
infrastructure that allowed an effective management of technical facts and
activities, among partners and customer.
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Chapter #5 – The challenges of FPS-A :
OBC functions in Flight
 The main functions of FPSA are to :
 Manage the LV main functions during flight (stage separations, motors ignitions…);

Perform the GNC activities and guide the LV to the desired orbits (with required specified
accuracy);
 Send Telemetry data to ground;
 Manage the On-Board Computer Hardware;
 Perform the De-orbit Manouvre and Passivation phases.
 The GNC algorithms and relevant flight management events have been designed to
cover all needs at system level and satisfy the Launch Vehicle Main Function “To guide
and control the LV to achieve required orbital conditions”. The GNC flight algorithms
have been designed and developed to achieve this target taking into account each
specific sub-tasks or sub-function.
 The LV control is based on the following loop , so called “big loop”
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Chapter #6 – VV02 Mission
VV_02 MISSION DESCRIPTION
The second Vega launch from the Guiana Space Center (CSG) placed three
satellites in different orbits:
 Main Payload:
PROBA_V
(140 Kg)
PROBA_V : Project for On-Board Autonomy and Vegetation
 Secondary Payload:
VNREDSat-1
(116 Kg)
VNREDSat: Vietnam Natural Resources Environment & Disaster Monitoring Satellite
 Secondary Payload:
ESTCube-1
Vega VV-02
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(2Kg )
Chapter #6 – VV02 Mission
VV02 mission was horribly demanding:
• The Launch Vehicle had to act as a school bus, releasing three payloads, with
first release on the higher orbit; a significant orbital plane change was
necessary from Proba-V to Vnredsat.
• The Payload Adapter (Vespa) had to be released in indirect re-entry orbit.
• Several constraints due to safety RF links and TLM links had to be respected,
implying, in example, roll attitude angle control during part of the ascent
phase.
• Five ignitions/cut-offs of the AVUM engine
• Long duration of the mission (almost 3 hours)
• High number of maneuvers for P/L thermal conditioning, release and
pointings/CCAMs
• AVUM Direct deorbiting
• The mission implied a null launch window
Record setting for Europe in terms of number of maneuvers, duration, first
direct deorbiting…
Vega VV-02
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Chapter #6 – VV02 Mission
Payloads Accomodation
Vega VV-02
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Chapter #7 – ALTS
On the VV02 additional equipments were installed to better investigate the LV behavior
during overall flight, so called “ALTS”.
• GPS: working during all flight.
• IMU: first 25 seconds, but data are considered “nice to have” up to H0 + 360 sec.
• Shock sensors: mandatory during separation of Fairing, 3rd stage, Main P/L, VUP (VESPA Upper
Part). Four sensors will separate with VUP.
• Units housekeeping signals and temperature telemetries (RF TX and Battery): acquired during all the
mission.
• Internal (IC) and external (EC) cameras will be activated according to their mission:
o IC1 will record the main payload separation.
o IC2 will record the secondary payload and the VUP separation
o IC3 is dedicated to record the Fairing separation
o EC aims to record the separation of the lower stages and relative bodies kinematics.
Vega VV-02
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Chapter #8 – VV02 Mission : Results 1/2
From a SW point of view VV_02 was a complete success:
• Flight Timeline scheduled as expected. No error detected;
• Guide, Navigation and Control functions remarkably matching
the predictions;
• Launch vehicle managed correctly (ignitions, separations,
avionics, …). At the end of mission, 1.9s of difference between
expected and TLM timeline (over 8300s)
• Telemetry data correctly sent to ground
• Correct management of the OBC HW and of the 1553
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Chapter
#8 – VV_02
Mission : Results 1/2
Vega Typical
Mission
VV02 Mission Profile
3 P/L were injected into 2 different orbits.
4th stage performed the direct re-entry into
the Pacific Ocean
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Chapter #8 – VV02 Mission : Results 2/2
Accuracy sensibly better than mission specification
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Chapter #9 Vega –
A true world of opportunities
Vega Second Flight completes the process of qualification of the LV
and start its (hopefully) long and honourable life as a space
workhorse. The qualification of the FPS-A secures the industrial
mastering of the Launch Vehicle system and open a true world of
opportunities for users of the Launch System. In fact its flexibility
allows right now missions whose implications are not yet explored
in the field of In Orbit Testing, In Orbit Servicing, Active Debris
Removal, Solar System Exploration (with Vega Electric Propulsion
Module) and candidates as a optimal carrier for electric satellite to
GEO.
Spiral Raising
orbit
GE
O
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End of Mission
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