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ESA/IPC(2007)71Paris, 13th June 2007(English Only) Att.: Annexes

EUROPEAN SPACE AGENCY

INDUSTRIAL POLICY COMMITTEE

GENERAL SUPPORT TECHNOLOGY PROGRAMME

GSTP-4 WORK PLAN/PROCUREMENT PLAN

(Complete list of Activities Approved)

SUMMARY

Following a request made by several Delegations, this information note presents the complete list of activities that constitute the present GSTP-4 Work Plan and Procurement Plan as approved by previous IPCs (including up to IPC 236th of May 2007).

Activities currently in the Work Plan can be grouped, according to their status, as follows:

- Activities already implemented or in implementation are the ones marked as 2005 or 2006 in Annex 1.

- Activities procured during this year or currently supported and in procurement are the ones marked as 2007 in Annex 1.

- Activities that did not receive enough support yet are presented in the Annex 1 under the heading 2008. The Executive intends to review these activities and propose the ones not longer of interest for cancellation.

It should be noted that this document only presents activities in the standard GSTP-4 Work Plan. A full list of activities implemented under the Announcement of Opportunities can be found in the document ESA/IPC(2007)72 and revisions (GSTP-4 Status Report). For the activities implemented under Specific Areas Work Plans please refer to the corresponding Work Plans: ESA/IPC(2006)75 and addendums for NewPro and ESA/IPC(2006)76 and addendums for PROBA-3 / Formation Flying.

REQUIRED ACTIONS

Delegations are invited to take note of this complete list of Activities Approved for GSTP-4 Work Plan and Procurement Plan.

Delegations are also invited to review the activities marked as 2008 and provide feedback to the Executive regarding their interest and their willingness to support them.

2007-0925

This Document is in DODIS

ESA/IPC(2007)71

KEY TO TABLES IN ANNEXES

The GSTP Work Plan is presented along the following headings:

- EARTH OBSERVATION - SCIENCE / ROBOTIC EXPLORATION - HUMAN SPACEFLIGHT - SPACE TRANSPORTATION & RE-ENTRY TECHNOLOGIES - GENERIC TECHNOLOGIES - PILOT PROJECTS

Each activity is given a programmatic reference, which will remain unchanged until completion. Additional planning elements associated with each of the activities are:

Budget: The total Contract Authorisation (CA) values are given in KEURO, at yearly economic conditions.

Procurement Policy:

C Open Competitive Tender (Ref. Article 5.1 ESA Contract Regulations) C(1) Activities in open competition limited to the non-Large-System

Integrators (LSI). C(2) Activities in open competition, where a significant participation of non-

LSI is requested. C(3) Activity restricted to SMEs & R&D organisations, preferably in

cooperation. C(4) Activities in open competition, subject to SME subcontracting clause C(R) Competition is restricted to a few companies, indicated in the

"Remarks'' column; (Ref. Article 5.2 ESA Contract Regulations) DN/C Direct Negotiation/Continuation; the contract will be awarded in direct

negotiation being the immediate continuation of a previous activity with the same contractor (Ref. Article 6.1.C ESA Contract Regulations)

DN/S Direct Negotiation/Specialisation; the contract will be awarded by direct negotiation in implementation of a defined industrial policy or resulting from a sole supplier situation; (Ref. Articles 6.1.A, D, F ESA Contract Regulations)

Further details of the applicability of industrial policy measures can be found in documents ESA/IPC(2001)29 and ESA/IPC(2005)87,rev.4

ESA/IPC(2007)71

Together with the activity description the following information is reported:

Deliverables: Provides a short description of the tangible outcome, e.g., breadboard, demonstrator, S/W, test data. A final report is standard for every activity.

Further details regarding the activities, in what concerns TRL levels, duration, application and so on, can be found in the original document presented to IPC for the approval of the particular activity. In order to facilitate this process, in the last column of the tables in Annex I (“IPC Reference Document”), it is provided the reference document presented for approval to the IPC in which each activity is included.

ANNEX I

GSTP-4 Work Plan & Procurement Plan

List of Activities Approved

ANNEX I: Complete List of Approved Activities in GSTP-4 Work Plan / Procurement Plan

ESA/IPC(2007)71Annex 1, Page 1

Theme 1.- EARTH OBSERVATION

Data exploitation

GSTP-4 Title Budget (K€) Proc. Remarks (Company DN, IPC ReferenceReference 2005 2006 2007 2008 Policy etc.) Document

G104-11GD Data Base Generation System of 3D sceneries 500 C2

Output may lead toOperational SW for ESA(special attention oncontracts clause 42)

(2005)49,add.1

G104-14GD Cooperative EO Sensors 900 C (2004)49

G104-35GD Enhanced Services Infrastructure Technology (ESIT) 2,000 DN/C Spacebel, GIM, VITO (B) (2004)49,add.2

G104-36GD Semantic-web for Mediated Access Across Domains - SMAAD 800 C (2005)49,add.3

G104-37GD Use of ISEA (Icosahedral Snyder Equal Area) for EO Sensors 150 DN/S

GRIDS (CND)Output may lead toOperational SW for ESA(sub-clauses 42.8 and42.9).

(2005)49,add.2

G104-38GD Extension of ADAS (Advanced Earth Observation Data AcquisitionSystem) 1,500 DN/C

Alcatel Bell Space (B)Output may lead toOperational SW for ESA(sub-clauses 42.8 and42.9).

(2005)49,add.2

G104-39GD Preparation of Interferometric SAR processor - COISP 200 DN/C Technical University ofDenmark (DK) (2005)49,add.5

G104-40GD Application Module for UGEI (Universal Geometry Engine for EOImages) 125 DN/C Indra (E) (2005)49,add.6

G104-41GD Digital Urban Knowledge Engine (DUKE) 400 DN/S CS (F) + NavTeQ (NL) (2006)49,rev.1

G104-42GD Level 3 SAR processor for map production at continental scale 670 C1 (2006)49,add.3

G104-43GD Grid enabled Service Support Environment (SSE-Grid) 1,200 DN/S VITO (B) (2006)49,add.3

G104-44GR ADAS Evolution 2,500 DN/C Alcatel Alenia Space (B) (2006)49,add.3



Reference Title 2005 2006 2007 2008 P.P. Remarks IPC Ref. Doc.

G104-45SE Integrated EO based monitoring services for the Arctic region-IMSAR 400 C (2007)49, add.1

G104-46SE Enhanced oil slick drift forecasting 600 C (2007)49, add.1

Total Data exploitation 4,125 1,650 5,370 800



Microwave Instruments


G102-04EE High-power, low-loss feed array (development phase) 800 C (2005)49,add.3

G102-08ET Burst Synchronization for ScanSAR Interferometry 150 C (2005)49,add.3

G102-24EE Passive sub-array technological developments 500 C2 (2005)49,add.3

G102-25MC Ultra-stable structures for interferometric antennas 600 C (2005)49,add.7

G102-28ET Frequency Domain SAR Raw Data Compressor 500 C (2005)49,add.3

G102-30QC Evaluation of MMIC process for mm-wave space applications 250 DN/S Fraunhofer Institute (D) (2005)49,add.3

G102-32EE High Accuracy/Stability Reflectors for future EO missions 500 C (2004)49

G102-35ET PARIS Ocean Altimeter on GNSS Reflections 1,000 C (2005)49,add.3

G102-40EE European Antenna Modelling Component Library - EarthObservation 600 C2

Open Source SW (specialattention on contractsclause 42)

(2005)49,add.3

G102-41EE Medium-size unfurlable antenna for LEO (concept study) 200 C (2005)49,add.1

G102-42PS Verification of Self-Interference Free Receivers for HUT-2DRadiometer 100 DN/C HUT, Ylinen (FIN) (2004)49,add.2

G102-43PS SMOS Noise Injection Radiometer (NIR) Phase C/D 150 DN/C Ylinen (FIN) (2005)49,add.4

G102-44PY In-flight calibration of SIRAL altimeter 175 DN/S Technical University ofCrete (GR) (2005)49,add.5

G102-45MM Broadband Sources for Far-IR Power Generation 130 DN/CUni. Frankfurt/M (D), Uni.Erlangen (D), Athene e.V(D)

(2006)49,rev.1

G102-46EE Micromachined receiver 750 C (2006)49,add.3

G102-46ET GeoSounder MMIC 1,000 DN/S Omnisys (S) (2006)49,add.2

G102-47EE Integrated Antenna Feeds 500 C (2006)49,add.2

Total Microwave Instruments 250 3,080 4,575



Optical Instruments


G101-04MM Characterization of new calibration diffuser types 250 C1 (2005)49,add.3

G101-08MM Next generation solar-blind UV Lidar Detector 400 C (2005)49,add.3

G101-10MM Hollow Waveguide Space Instrumentation Applications 480 DN/S Qinetiq (UK) (2004)49

G101-12MM Imaging spectral signature instrument 300 C VTT, Specim (FIN) (2004)49

G101-13MM New Radiometer for Optical Calibration 300 C (2005)49,add.3

G101-14MC Advanced low temperature radiators for LEO 450 C (2005)49,add.3

G101-16MM Improved UV Grating Technology (IUVGT) 300 C1 (2005)49,add.3

G101-17MM High-efficiency Raman DIAL source 450 DN/S Passat Ltd. (CND) (2005)49,add.3

G101-25MM Hermetically sealed laser pump diode 500 DN/C Contraves (CH) (2005)49,add.3

G101-26MM Development of a 4-Mirror Anastigmat with a large Field of View 650 DN/C AMOS (B) (2006)49,add.2

Total Optical Instruments 1,430 750 1,900



Platforms/ Other Instruments


G103-03EE Steerable pencil beam X-band data downlink antenna 500 C (2005)49,add.1

G103-05ET ADIBEAM: Adaptive digital beamforming techniques for GNSSreceivers 350 C (2005)49,add.3

G103-06MC Low Temperature/Cryogenic CPL 400 C2 (2005)49,add.3

G103-07EC Micro Star Tracker and Baffle Technology Development 900 C1 (2005)49,add.3

G103-08ES Optimised CMG-based AOCS for Mini-Satellites 500 C2


(2005)49,add.3

G103-09ET 8PSK High rate design ( Bread board ) 1,000 C (2005)49,add.1

G103-13MM Adaptation of industrial motor technologies for space applications. 300 C1 (2005)49,add.3

G103-25ET Earth Exploration satellite ( EES ) Transmitter at Ka band 2,000 C (2005)49,add.3

G103-33MM Non explosive Hold-down Release Actuator 400 C (2005)49,add.3

G103-34ES Highly integrated full-custom autocorrelation spectrometer ASIC 500 DN/C Omnisys (S) (2004)49

G103-36ED Scalable Payload Computer (SPC) 600 C (2005)49,add.6

G103-37ET GPS Precise Orbit Determination (POD) instrument EQMdevelopment 1,500 DN/C Austrian Aerospace (A) (2006)49,add.3

G103-37MP Design, Development and Test of a Mini Ion Engine System 400 CQinetiQ (UK)EADS-ST/GiessenUniversity (D)

(2005)49,add.7

G103-38ED CCSDS IMAGE Compression ASIC 1,000 C2 (2007)49, add.2

Total Platforms/ Other Instruments 500 1,000 4,700 4,150



Theme 2.- SCIENCE / ROBOTIC EXPLORATION

Atomic Interferometer


G212-03EP Miniaturisation of very low power HV supply for microthrusters 400 C1 (2005)49,add.3

G212-04MM Parametric study on the absolute linewidth limit attainable for asemiconductor narrow linewidth laser 80 C3 (2007)49, add.2

Total Atomic Interferometer 80 400

AURORA


G213-01MM Combined Compact Raman Spectrometer & Microscope 400 C (2004)49

G213-08EE X/Ka-band High Gain Data Transmission Antennas 500 C (2004)49,add.2

G213-11MM Rover Autonomy Testbed 400 C Open source SW, specialattention on contractsclause 42

(2005)49,add.1

G213-13MM Planetary Robot Design, Generic Visualisation and VerificationTool 500 DN/C

Trasys Space (B)Output may lead toOperational SW for ESA(special attention oncontracts clause 42)

(2005)49,add.3

G213-14GM Laser Anemometer and Martian Dust Analyser 500 DN/S University of Aarhus,Innoware A/S (DK) (2006)49,add.2

Total AURORA 1,000 500 800



BepiColombo


G201-02MM Self-Lubricating Metal Matrix Composites (MMC) for mediumtemperatures in space 200 DN/C ARC (A), ESTL (UK) (2004)49

Total BepiColombo 200

Darwin


G203-02SC CRYOGENIC FRINGE SENSOR 500 C1 (2005)49,add.3

G203-03MM DARWIN laser metrology performance verification 300 C (2005)49,add.3

G203-06MM Lithographic manufacturing of Zero Order Gratings (ZOG) forinnovative achromatic IR phase shifters 400 DN/S Université Liège, CSL (B) (2004)49

G203-08ET RF Metrology Subsystem 1,500 C (2004)49

G203-09SC Test Harness for High Resolution Instruments 500 C (2005)49,add.1

G203-12SC Imaging Interferometer 800 C (2005)49,add.3

G203-13MM Index Guided Photonic Crystal Fiber for DARWIN 800 C1 (2005)49,add.3

G203-14MM QWIP Optimization for Darwin FIR Linear Array 250 DN/C ACREO (S) (2004)49,add.1

Total Darwin 650 1,500 2,900



Deimos Sample & Return


G211-01MM Sample and Return Systems for a Small Body (Deimos SampleReturn TRM) 250 C (2005)49,add.3

Total Deimos Sample & Return 250

Gamma Ray Imager


G206-01SC Gamma Ray Optics 500 C1 (2005)49,add.1

Total Gamma Ray Imager 500

Other Technologies (Th.2)


G214-02EE 650 GHz 5m Hologram Compact Antenna Test Range 300 DN/C HUT/MilliLab (Fin) (2004)49

G214-11EE Wideband Receivers 500 C (2005)49,add.3

G214-12MM Mercury Micro-rover end to end demonstration 160 DN/C SAS (B) (2005)49,add.3

G214-13SC Development of a miniaturized mass spectrometer for spaceapplications 620 C1 (2005)49,add.5

Total Other Technologies (Th.2) 300 1,280



Solar Orbiter


G202-01SC Development of light filters for solar radial velocity measurement 300 C1 (2005)49,add.3

Total Solar Orbiter 300

XEUS


G204-03SC High Resolution Low Mass Optics Petal 900 C2 (2005)49,add.3

G204-05MM Laser Radar with Submillimetre Accuracy 200 DN/C Riegl (A) (2005)49,add.3

G204-06MM Low temperature spectrometer array 500 C3 (2005)49,add.3

G204-07SC Optical Filters 450 C (2005)49,add.3

Total XEUS 700 1,350

X-ray Interferometer


G205-01EP Elimination of Corona Discharge in High Voltage FEEP Connectors 150 C (2004)49

Total X-ray Interferometer 150



Theme 3.- HUMAN SPACEFLIGHT

Advanced habitats


G301-01QM Investigation of the introduction of new surface treatmenttechnologies for space interior based on SAM polymers 570 C (2004)49

Total Advanced habitats 570

Automation and advanced robotic technologies


G302-02MM GLOBE: Gas-Lubricated Oil Bearings (Pre-Qualification Phase) 500 DN/C MARS CENTER (I), DTM(I) (2004)49

G302-03ES COTS based space borne computer 2 700 C (2005)49,add.6

Total Automation and advanced robotic technologies 700 500



Closed loop life support technologies


G303-03MC Regenerative Life support: Greenhouse Module 450 C (2004)49

G303-04MC MELISSA/BIORAT Genetic Stability Study (phase 2) 450 DN/C SCK (B) (2005)49,add.3

G303-05MC MELISSA Adaptation for Space - Phase 2 350 DN/C NTE (E) (2005)49,add.1

G303-06MC MELISSA : Fibres Degradation Unit 600 DN/C EPAS , UG, VITO(B) (2005)49,add.3

G303-10MC MELISSA : R.rubrum harvesting techniques 200 DN/C EPAS , VITO(B) (2005)49,add.3

G303-11MC Urine Treatment Unit (Phase A/B) 600 DN/C EPAS, VITO(B) (2005)49,add.3

G303-12MC Waste Collector Unit 450 C (2004)49

G303-16MC Advanced, Lightweight Membrane/Electrode Assembly forElectrolyzers 500 DN/C VITO (B) (2004)49

G303-17MC Additional characterization phase of the Waste compartment 150 DN/C EPAS (B) (2005)49,add.4

Total Closed loop life support technologies 500 1,150 1,650 450

Crew Health and Performance


G304-04MC Performance enhancements for trace gas monitoring (ANITA II) 300 DN/C K.T. (D), SINTEF (N) (2005)49,add.1

G304-05MM European Crew Personal Active Dosimeters (EuCPAD’s) forAstronauts 300 C (2006)49,add.1

Total Crew Health and Performance 600



Extra-Vehicular Activity (EVA) Suit Technology


G305-01MC Manikin Virtual IVA/EVA suit. 125 C2


(2005)49,add.3

Total Extra-Vehicular Activity (EVA) Suit Technology 125

Free-Flyers (Rendezvous and Docking, In-Orbit Assembly and Servicing)


G306-01MM Dynamic Parameters Identification 600 DN/C Trasys (B), Kripton (B) (2005)49,add.3

Total Free-Flyers (Rendezvous and Docking, In-Orbit Assembly andServicing) 600



Instrumentation for Life Science


G307-01MM Fluorescence based Biosensor for microbial /life detection 1,000 DN/S Inasmet (E) (2004)49

G307-04MM Peripheral Quantitative Computed Tomography 500 C2 (2005)49,add.3

G307-06MM Continuation Miniature Fluorescence Microscope. PC - MiMi 240 DN/C Dutch Space (NL), OIP (B) (2004)49

G307-07MM Facility - Glovebox Combination 560 DN/S Bradford Engineering (NL) +subcontractors (I, CH) (2004)49

G307-09MM Ozone Based Sterilisation Technology 250 DN/C Bradford Engineering B. V.(NL) (2006)49,add.1

Total Instrumentation for Life Science 1,240 250 560 500

Instrumentation for Physical Science


G308-01EM European Drawer Rack Simulator 400 DN/C SAS (B), ATOS (NL) (2004)49

G308-03MM High Resolution Diagnostics for Crystal Growth 300 DN/C Lambda-X (B), ULB/MRC(B), Jabberwock (NL) (2005)49,add.3

G308-08MM Differential Thermal Analysis 400 C (2005)49,add.3

G308-09MM High Temperature Sensors with self-calibration capabilities 500 C Vibrometer, EMPA, EPFL(CH) (2004)49,add.2

G308-10MM IMPACT related technologies 1,000 DN/C Kayser Threde (D) (2005)49,add.3

G308-11MM Development of single-walled sapphire cartriges 250 C (2006)49,add.2

G308-12MM X-ray Diagnostics for Space 500 C (2006)49,add.4

Total Instrumentation for Physical Science 1,550 1,800





G312-01EM Advanced payload laptop application 300 DN/C ATOS Origin, NLR (NL) (2005)49,add.3

G312-03MC Lightweight deployable structural protections against meteoroidsand space debris 600 DN/C Alenia (I) (2005)49,add.3

G312-04MC Membrane Gas Trap Technology Demonstrator for Columbus 250 C (2005)49,add.3

G312-05QQ Safety Risk Evaluation and Certification for use of Batteries inCOTS devices 350 C (2005)49,add.3

G312-06MM Optical modeling of corner cube retro-reflectors (CCRM) 250 C2 (2005)49,add.3

G312-08EZ ERASMUS Facility Responsible Centre Operational Environment 800 DN/C SAS (B) (2004)49,add.1

G312-09EM Operations Data File (ODF) Procedure Viewer 100 DN/C SKYTEK (IRL) (2004)49,add.1

Total Other Technologies (Th.3) 100 800 250 1,500

Payload Data Handling


G310-03MM Next Generation Telescience Support Unit 500 DN/S SSC(S) (2004)49

G310-04MM TSU ground network development 200 DN/C

Trasys (B)Output may lead toOperational SW for ESA(special attention oncontracts clause 42)

(2005)49,add.1

Total Payload Data Handling 500 200



Theme 4.- SPACE TRANSPORTATION & RE-ENTRY TECHNOLOGIES

Advanced Hot Structures and Thermal Protection Systems


G401-02MC Facetted Thermal Protection System (TPS) Panels 250 C (2004)49

G401-03MC Surface Protected Flexible Insulation (SPFI) 400 DN/S EADS ST GmBH (D) (2005)49,add.3

Total Advanced Hot Structures and Thermal Protection Systems 650

Advanced Liquid Propulsion


G402-01MM Advanced Ball Bearings for Expendable Cryogenic EngineTurbopumps 400 C (2005)49,add.3

G402-04MM Cost reduction of launcher valves 1,500 DN/S Techspace Aero (B) (2005)49,add.3

G402-05MM Electric actuators for fluid control in launch vehicles 1,600 DN/C Techspace Aero (B) (2004)49

G402-06MP Study on Flow Separation Phenomena in Rocket Nozzles 60 DN/S Univ. Di Roma (I) (2005)49,add.6

G402-07MP European 1N Hydrazine Flow Control Valve 1,400 DN/C Techspace Aero (B) (2005)49,add.7

Total Advanced Liquid Propulsion 1,660 1,400 1,900



Advanced Materials


G403-02MC Passive Damping of RLV Structures 300 C (2004)49

G403-03MC High Temperature Light Weight CMC Roller Bearing with LowCoefficient of Friction 400 C (2005)49,add.3

G403-04MC Layer by layer, low energy electron beam curing process forcomposite structures 500 C (2005)49,add.3

G403-05MC Visco-elastic Damping Embedded within a CFRP Panel 150 DN/S ARTEC (CND) (2006)49,add.3

Total Advanced Materials 300 150 900

Aerothermodynamics (ATD)


G406-01MZ Dedicated generally bi-disciplinary coupling of disciplines for spacevehicles 300 C (2004)49

Total Aerothermodynamics (ATD) 300



Avionics and GNC


G408-01ES GNC Design and Analysis Tool Environment for Reusable SpaceTransportation 300 DN/S GMV (E) (2004)49

G408-03QC Spacialisation of VTI SCA 600 MEMS accelerometers 300 DN/S VTI (FIN) (2004)49

G408-06MX Avionics Architecture for future Reusable Space TransportationSystems 700 C (2005)49,add.1

G408-09MX Man Machine Interface Technology Integrated Applications 1,450 DN/C

Space Applications,Spacebel (B)Output may lead toOperational SW for ESA(special attention oncontracts clause 42)

(2005)49,add.3

G408-10MP Advanced Flight Measurement Techniques forAerothermodynamics and TPS Re-entry Applications 2,100 C (2005)49,add.3

G408-11MP Tools for the study of dynamic stability of (re)entry vehicles in thetransonic/supersonic regime 200 C (2005)49,add.3

G408-12AO TMVS-AVKIT: TM avionics sub-system kit for TM transmission viasatellite links for launch-vehicle applications 4,000 DN/S Alcatel Espacio (E) (2005)49,add.5

G408-15MM TVC Hbrisc2 Software Environment Industrialisation 1,100 DN/CSABCA (B)Open SourceSW (special attention oncontracts clause 42)

(2005)49,add.6

G408-16AP SCARAB Software for Ariane Upper Stages Atmospheric Re-entryAssessment 500 DN/S HTG (D)Operational

Software (2005)49,add.7

G408-17MM TAS 3-E Flight Qualification (Extended Tri-Axial AccelerometerSystem) 280 DN/C Redshift Design and

Engineering (B) (2006)49,add.1

G408-18VL System requirements evolution impacts on P80 TVD Design 3,000 DN/C SABCA(B) (2005)49,add.7

G409-03EP Component technology for high power motor drive electronic forLauncher applications. 500 C (2004)49

Total Avionics and GNC 300 10,080 1,400 2,650



Health Management Systems (HMS)


G410-01ES Integrated Vehicle Health Management System Demonstrator 700 C


(2005)49,add.3

G410-02MM High Temperature, High Dynamic Range, Fast response PressureSensors for the spacecraft and launcher propulsion subsystem 300 C2 (2005)49,add.3

G410-03MM Fiber Optic Sensors for Structural Monitoring of the ArianeLauncher 500 C2 (2005)49,add.3

G410-04MM High Speed Tunable Laser Interrogator for Spacecraft HealthMonitoring 300 DN/S In-Tune Technologies (IRL) (2006)49,add.5

Total Health Management Systems (HMS) 800 1,000

Solid propulsion


G412-05MP Control of pressure oscillations in a cold flow model of solid rocketmotor. 300 DN/S

Von Karman Institute (B)Open source SW, specialattention on contractsclause 42

(2005)49,add.1

Total Solid propulsion 300



Theme 6.- GENERIC TECHNOLOGIES

Advanced Ground Station Technologies and Tracking Methods


G606-01GS Industrialization of Ka-band frequency converters 800 DN/C Alcatel Bell Space (B) (2005)49,add.3

G606-03GI Ground-segment engineering and operational configuration 250 C

Output may lead to ESAOperational SW (specialattention on contractsclause 42)

(2005)49,add.1

G606-04GI An Advanced M&C System for ESTRACK Ground Stations 250 C


(2005)49,add.3

G606-05GI Remote Monitoring and Control of Complex Systems 300 C


(2005)49,add.3

G606-06GI Generic Exchange Format and Interfaces Standardisation forGround Segment 300 C (2005)49,add.1

G606-07OF Improved approach to Verification & Validation on the SVF 200 C


(2005)49,add.3

G606-08GS Experimental High Data Rate Ka Band Down Converters for NearEarth Missions 350 C1 (2005)49,add.3

G606-09GS High performance 8-PSK-TCM demodulator in Generic Platform 300 DN/C BAE (UK) (2005)49,add.3

G606-10EM Fine grain traffic performance monitoring software tool 250 DN/C

AETHIS (B)Output may lead to ESAOperational SW (specialattention on contractsclause 42)

(2005)49,add.1




G606-11SW Advanced Traffic Performance Monitoring tool for time-criticalground communications networks 500 DN/C

Ubizen AETHIS (B)Output may lead to ESAOperational SW (specialattention on contractssubclause 42.8)

(2007)49, add.1

Total Advanced Ground Station Technologies and Tracking Methods 250 600 1,000 1,650



Avionics, GNC, Communications miniaturisation, with in mind bandwidth and power efficiency


G603-30ES High accuracy APS based ASTR 800 C (2005)49,add.1

G603-32ET GPS/Galileo Miniaturised Space Receiver (GAMIR) 500 C (2005)49,add.3

G603-34ES Reaction Wheel Electronics Interface Improvement 50 DN/S Stork (NL) (2005)49,add.1

G603-35ES On Board Computer for critical applications using system on a chipapproach 1,000 C (2005)49,add.3

G603-36ET Optical Link Demonstrator for end-to-end Deep Space Linkcommunications 450 C (2005)49,add.1

G603-37ES Computer for reliability oriented missions 300 C (2005)49,add.1

G603-42ED Advanced Avionics Architecture Development 450 DN/C Astrium (UK) (2005)49,add.4

G603-43ET Lightweight materials and technologies for reduction of microwavepassive equipment 800 DN/C Alcatel Espacio (E) (2005)49,add.6

G603-44MM Fast Wavelength Switching Optical Ring 160 DN/C In-Tune Technologies (IRL) (2006)49,add.2

G603-45EC Non-Linear Programming Solver for Space Trajectory Optimization 500 C


(2006)49,add.4

G603-46EC GNC Development Environment - GNCDE 420 DN/C GMV (E) (2006)49,add.5

G603-46ED Advanced Flexible I/O System 1,900 DN/S SES (S) and AAS (A) (2006)49,add.4

G603-47EC Reaction wheel product transfer support 1,500 DN/S Bradford Engineering NV(NL) (2007)49, add.2

Total Avionics, GNC, Communications miniaturisation, with in mindbandwidth and power efficiency 2,210 5,200 1,420



Basic Parts, Materials and Processes


G608-02QM Non-conventional matrix/carbon nanotubes reinforced compositefor Applications in Space 600 C (2004)49

G608-03QM High conductivity carbon fibre reinforced polymers 280 C (2004)49

G608-04QC Evaluation of Fe-RAM memory demonstrators 200 DN/C IMEC (B) (2005)49,add.3

G608-05QC Evaluation of Optic Fibre Cable Assembly 300 C (2005)49,add.3

G608-06QC Validation/Pre-Qualification of MEMS based Si pressure sensors 300 DN/C PRESENS (N) (2005)49,add.3

G608-09QC CTTB In-Flight Component Irradiation Test Data Analysis 400 C Open Source SW (specialattention on contractsclause 42)

(2005)49,add.3

G608-10QC Contactless Quality Control of Micro-parts 70 DN/S Upper Austrian Research(A) (2005)49,add.1

G608-11QC Enabling of High Q micromachined planar filters components 225 DN/S Reinhard (CH), IRCOM,Alcatel (F) (2004)49

G608-12ET Alternative Sources for Critical TWT Materials 400 C (2005)49,add.3

G608-13ES ASICs for space fabricated with Radiation Hardened by Designlibrary 450 C (2005)49,add.1

G608-14QM Development of new thermal control paints for Space andLauncher applications 250 DN/S MAP(F) (2004)49,add.2

G608-20QC Advanced development of III-N material for high powercomponents 1,400 DN/C IMEC (B) (2005)49,add.6

G608-21MP Digital Pressure Sensors for PRISMA satellite 370 DN/S Presens (N) (2006)49,add.2

G608-22MP Extended application range of the digital space pressure sensor. 500 DN/C Presens (N) (2007)49, add.1

G608-23ED SpaceWire Router ASIC Performance Characterisation 150 DN/C Austrian Aerospace (2007)49, add.2

Total Basic Parts, Materials and Processes 3,295 1,630 970



Extreme space environment technology (hot, cold, radiation..)


G602-08MP Modular & Multi-application Plasma Diagnostic Package (MMPDP) 500 DN/C LABEN(I), Proel (I) (2004)49

G602-20EM Proto-flight model of the Energetic Particle Telescope (EPT) 1,650 C (2004)49

G602-21EE MUSTANG: Muon Space Weather Telescope 75 DN/C University of Greifswald (D) (2005)49,add.2

G602-22QC Radiation Assessment of Deep Submicron CMOS Devices 400 DN/C IMEC (B) (2006)49,add.1

G602-23EE Development of standard plasma monitor 600 C (2007)49, add.1

G602-23QC Integrated Radiation Environment, Effects and ComponentDegradation Simulation Tool (Experimental Verification) 100 DN/C LIP (P) (2006)49,add.2

G602-24QC Verification of Enhanced Low Dose Rate Sensitivity 400 DN/S Seibersdorf Research (A) (2006)49,add.4

Total Extreme space environment technology (hot, cold, radiation..) 175 2,650 900



Lightweight systems (structures, propulsion, thermal etc)


G601-01MP Multiphysics Valve Model 200 C Open Source SW (specialattention on contractssubclause 42.10)

(2005)49,add.3

G601-04MC Thermal model reduction tool 200 DN/S

Alcatel (F), Astrium (F),+subsOpen Source SW (specialattention on contractsclause 42)

(2005)49,add.3

G601-05MC Thermal modeling of test chambers 150 DN/C ALSTOM (UK) (2005)49,add.3

G601-08MC VCHP thermal system-level modelling 125 C (2005)49,add.3

G601-09EM Data exchange methods for Space Environment Effects tools 100 C Open Source SW (specialattention on contractsclause 42)

(2005)49,add.3

G601-11MP Development of high current, voltage and temperature cablesuitable for Electric Propulsion 450 C (2005)49,add.3

G601-12MM Deployment Regulator Miniaturisation 300 C SENER (E) (2004)49

G601-13MM High Precision Linear Actuator 450 C (2004)49

G601-14MC Miniature Pyrotechnic connector/disconnector 300 C (2005)49,add.3

G601-15MC Acceptance Test Methods for Large Spacecraft 100 C (2005)49,add.3

G601-16MC NDE Techniques for Applications in Composites Manufacturing 250 C2 (2005)49,add.3

G601-17MC Folded Core Structures for Flat and Curved Sandwich-Panels 450 C (2005)49,add.3

G601-18MC Advanced RTM-Process for Manufacturing of CFRP SpaceStructures 300 C (2005)49,add.3

G601-19MC Composite flow Moulding Components for Spacecraft Applications 300 DN/S ICOTEC (CH) (2004)49

G601-20MC Piezo-Polymer Transducers for Non-destructive Testing and HealthMonitoring 400 C3 (2005)49,add.3

G601-21MC Payload adaptors with integrated shock & vibration damping 400 C (2005)49,add.1




G601-22MC Study on Carbon Fibre Tube Inserts-Extension 250 DN/C DLR (D), HUT (FIN), Patria(FIN) (2005)49,add.1

G601-23MC Shock response in spacecraft and equipment using combinedFE/SEA analysis 270 C1


(2005)49,add.3

G601-26MC 20-50K Pulse Tube cooler 400 DN/C Air liquide (F) (2005)49,add.3

G601-27MC Lifetime Extension of Small Rotary Coolers for Microsatellites andInterplanetary Missions 400 C (2005)49,add.3

G601-31MP Carbon Carbon Grids for Ion Thrusters 1,000 C (2005)49,add.3

G601-32MP Advanced Tank in composite material for Electric Propulsion 800 C (2005)49,add.3

G601-33MP Unified Propellant Management Assembly 400 C (2005)49,add.3

G601-34MP Ceramic Mounting Interfaces for Tanks 400 C (2005)49,add.3

G601-35MP Development and design verification of a 20N monopropellantthruster flow control valve 500 C1 (2005)49,add.3

G601-36MP Slow Acting Latching Valve 400 C2 (2005)49,add.3

G601-37MP Pump Pressurization of Propulsion Systems 100 C (2005)49,add.3

G601-38MM Study of a reaction sphere for attitude control using H-Brisc 2 400 C2 (2005)49,add.3

G601-41MC Lifetesting of New Concepts 200 C (2005)49,add.3

G601-42MP Development of an Electronic Pressure Regulator 500 C (2005)49,add.3

G601-43MC Mini TPL (CPL & LHP) Design Improvements and LongtermStability 200 DN/C Astrium (F) (2005)49,add.3

G601-44MP Development and Flight Qualification of a Solid PropellantMicropropulsion Module for Nanosat Application 300 C (2005)49,add.3

G601-46MP Low cost fabrication techniques for Titanium propellant tanks 130 C (2005)49,add.3

G601-48MC Advancement of multi-functional support structure technologies 750 C Inasmet (E), HTS (D) (2004)49

G601-50MM Rotary Piezoelectric Motor - Prequalification 450 C (2005)49,add.3

G601-51MM Small rotary actuator dedicated for Small antenna deployment andpointing operations 600 C (2005)49,add.3

G601-52EE Ka-band TM/TC for Telecommunications GEO satellites 300 C (2005)49,add.3

G601-53ES Essential Telemetry Support ASIC 800 C2 (2005)49,add.3



Reference Title 2005 2006 2007 2008 P.P. Remarks IPC Ref. Doc.G601-55MM Radiation Protection for Advanced Equipment Design 45 DN/C HUT (FIN) (2004)49,add.1

G601-56EE Ku/Ka-Band Multifrequency feeder 500 DN/S Rymsa (E) (2004)49,add.1

G601-57EC Next generation APS 1,100 DN/C Fillfactory (B) (2005)49,add.1

G601-57MM Optical frequency comb: critical elements pre-development 500 DN/S KT(D), Menlo Systems(D) (2004)49,add.2

G601-58PS Investigation on Optical Fiber Harness Technology 350 DN/C Contraves (CH) (2005)49,add.1

G601-63MC Deployment Simulation of Complex Antenna Structures 250 DN/S Samtech (B) (2005)49,add.5

G601-64MC Carbon Fibre/Aluminium Sandwich Panels Interconnection System 450 C (2005)49,add.5

G601-65MP Mechanical Cold Gas Regulator Development 150 DN/C Marotta (IRL) (2006)49,add.3

G601-66MC Metal Matrix Composite Based Flat Heat Pipes 300 DN/C Electrovac GmbH (A) (2005)49,add.7

G601-67EC MEMS Rate Sensor Development 2,000 DN/C SEA (UK) (2006)49,add.2

G601-68MP High accuracy spacecraft propellant gauging device using MEMStechnology 500 DN/S NanoSpace AB (S) (2006)49,add.4

G601-69EC Second Generation APS improvements for flexible low cost andmass sensors. 1,750 DN/S Cypress BV (B) (2007)49, add.1

Total Lightweight systems (structures, propulsion, thermal etc) 1,895 6,950 5,645 7,430



Modular Systems, including software


G607-01EM Standardisation and building blocks: open source softwarerepository 400 C2


(2005)49,add.3

G607-02EM Standardisation and Building Blocks: Maintenance and Evolution ofcomponents 300 C


(2005)49,add.3

G607-03EM Verification and Validation: Schedulability analysis environment 400 C (2004)49

G607-04EM System-software co-engineering: Frameworks process and tools 400 C2 (2005)49,add.3

G607-07EM Cross development environments: Operating systems - RTEMS 250 C2 Open Source SW (specialattention on contractsclause 42)

(2005)49,add.3

G607-09EM Cross development environments: Real-time and compiled JAVA 400 DN/CAstrium (F), Aicas(D),Linkoping University (S),Aonix (UK)

(2004)49

G607-10EM Real Time operating System (RTEMS) tasking monitoring tool 100 C Open Source SW (specialattention on contractsclause 42)

(2005)49,add.3

G607-11EM System-Software Co-Engineering: Architectural Language andTools 500 C (2005)49,add.3

G607-12EM System-software co-engineering: Data modelling technologies 300 C (2005)49,add.3

G607-13OF Generic and Automated Manufacturing and Operations System(GAMOS) 960 DN/C

RHEA(B)Output may lead to ESAOperational SW (specialattention on contractsclause 42)

(2005)49,add.1




G607-14EM Taxonomy of system FDIR principles and development process 350 COpen source SW, specialattention on contractsclause 42

(2005)49,add.1

G607-15ED SpaceNet: SpaceWire and Future Onboard Data-Handling 350 DN/C

University of Dundee (UK)Output may lead toOperational SW for ESA(sub-clauses 42.8 and42.9).

(2005)49,add.4

G607-16ED Advanced , Robust Processing Architecture (ARPA) 460 DN/C SEA (UK) (2005)49,add.5

G607-17ED Generic Fault Tolerant Software Architecture using SOIS forDistributed Applications - GenFAS 450 DN/C SciSys Ltd. (UK) (2005)49,add.5

G607-18ED Deployment demonstration of the CFDP standard in spaceapplications 600 DN/C Spacebel (B) (2005)49,add.5

G607-19SW ISVV process definition for auto-code generated software 250 C1 (2005)49,add.5

G607-20SW Open Image Generation System Phase II (OpenIGS2) 250 DN/CDuchSpace (NL),ATOS/Origin(NL)Operational Software

(2005)49,add.7

G607-21SW LEON-II (AT697E) simulator characterisation. 200 DN/C Spacebel (B) (2005)49,add.7

Total Modular Systems, including software 960 1,350 2,360 2,250

Other Technologies


G609-29MM Optical waveguides and micro-optical technology in silicon II 220 DN/C VTT (FIN), Modulight (FIN) (2005)49,add.7

Total Other Technologies 220



Other Technologies (Th. 6)


G609-02MM SMEAR II. (Radiation effects test protocol for optics) 150 DN/C SCK (B), Onera (F) (2005)49,add.3

G609-04MM High Resolution Optical Metrology System (HROMS) 600 C1 (2005)49,add.3

G609-05QC European mm-wave & sub-mmwave Reliability & Space EvaluationTest Centre 450 C1 (2005)49,add.3

G609-06MM Optical cements and adhesives for space use. (CEMOT II) 200 DN/C Leica (CH) (2004)49

G609-09MM Optical correlator for push-broom imagers 900 DN/C Technische UniversitaetDresden (D) (2004)49

G609-13MM MAPLE-BIOLIFT 2 - Technique for printing Microbioarrays 300 DN/C NTE (E) (2005)49,add.6

G609-17MM Target Projector for Videogrammetry (TPV) 400 DN/C CSL (B) (2005)49,add.3

G609-18MP Simulation of the Dynamics of Liquids in Partly Filled Tanks withMembrane-type Fuel Management Systems 100 DN/S NUMA (IRL) (2004)49,add.1

G609-20MM Laser diode technology developments at 779nm and 894nm 150 C (2004)49,add.2

G609-21EL In orbit demonstration of Digital Sun Sensor 100 DN/C TNO(NL) (2004)49,add.2

G609-21MM Advanced Slip-ring Solutions 300 C1 (2005)49,add.1

G609-22MM Distributed Feedback (DFB) Laser diode development at 894nm 300 C1 Modulight (FIN) (2005)49,add.1

G609-23MM Compact in-orbit optical image processor 300 C1 INO (CND) (2005)49,add.5

G609-24MM Design and development of extremely narrow band semiconductorDFB laser technology 200 DN/S ORC (FIN) (2005)49,add.5

G609-26EC Development of MEMS Accelerometer for Space Applications 600 C1 (2005)49,add.5

G609-28SR Sloshat FLEVO Post Flight Activities (Phases Fa and Fb) 200 DN/C NLR (NL) (2005)49,add.6

G609-30MM Laser diode device and measurement technology development 150 DN/S Observatoire Cantonale deNeuchatel - OCN (CH) (2005)49,add.7

G609-31ES Compatibility of the PPS5000 plasma Thruster with the newgeneration of Electric Propulsion Pointing Mechanism (EPPM) 120 DN/S Snecma (F) (2006)49,rev.1

G609-32ES Compatibility of the RIT-22 Grid Ion Engine with the newgeneration of Electric Propulsion Pointing Mechanism (EPPM) 120 DN/S EADS ST (D) (2006)49,rev.1




G609-33EP Development of an integrated resetable latching current limiter withtrip off time 1,000 C (2006)49,rev.1

G609-34MM Polishing of brazed optical quality SiC mirrors 350 C1 (2006)49,add.3

G609-34QC Technology Flow Evaluation and Qualification of SAW Filters 500 C (2006)49,add.2

G609-35MM Thermal IR Digital Holography for Non-contact Surface Metrology 800 DN/S CSL (B), MRC - UniversiteLibre de Brussels (B) (2006)49,add.4

G609-36MM Development of an Adjustable Large Range Viscous RotaryDeployment Damper 300 DN/S Austrian Aerospace (A) (2006)49,add.4

G609-37EE Terahertz Camera for Remote Detection of Material Defects andBiological and Chemical Substances 550 C (2006)49,add.4

G609-38MM Stepper Motor for Space Actuator Applications 100 C (2006)49,add.4

G609-39MM Voice Coil Motor Engineering Model 120 C (2006)49,add.4

G609-40MZ Flow-Structure Coupling for Hypersonic Flow Regimes 450 DN/C Open Engineering (B),Numeca (B) (2006)49,add.5

G609-41ET Multicarrier evaluation and advanced packaging for highlyintegrated RF SSPA 215 C (2006)49,add.4

G609-42SW Space System Database Development Platform 500 DN/C

Space Software Italia(I)Output may lead to ESAOperational SW (specialattention on contractsclause 42)

(2007)49, add.2

Total Other Technologies (Th. 6) 200 990 5,535 3,800



Power generation, storage and distribution efficiency


G604-01EP Development of materials for the thin film solar cells 1,000 C (2005)49,add.3

G604-02EP Development of a European Power Supply Controller 500 C (2004)49

G604-03ES Single Chip Advanced Data and Power Management System(SCADPMS) 600 DN/C Verhaert (B) (2005)49,add.3

G604-05EP Dynamic Modelling of multi-junction GaAs solar arrays 350 C (2004)49

G604-06EP Quality requirements for GaAs solar cells 500 C (2005)49,add.3

G604-08EP Commercial Off-the -shelf converter development 300 C1 (2005)49,add.3

G604-10EP Solar Cell Blocking Diode for High Temperature Operation 200 C (2004)49

G604-11EP Study, Development & Verification of a Planar Transformer 200 C (2004)49

G604-12EP Electrical network for thin film solar arrays (on flexible blanket) 500 C1 (2005)49,add.3

G604-13EP Improved optical modelling of solar cell assemblies 200 DN/S Thales (UK) (2005)49,add.3

G604-16EP Radiation studies for Next Generation Solar Cells 300 C2 (2005)49,add.3

G604-17EPTesting Method Definition and Failure Analysis for the ReliabilityVerification of the Multi-junction GaAs based PhotovoltaicTechnology

500 C (2004)49

G604-18EP Thin Film module pilot line and pre-qual 500 C (2005)49,add.3

G604-19EP Experimental Concentrator Solar Panel for Proba 2 - phase 2 450 DN/C CSL (B) (2004)49,add.1

G604-20EP Improved Manufacturing Technology for Ge Substrates 800 DN/C Umicore (B) (2004)49,add.1

G604-21MP Hydrogen Gas Storage in Space - Microspheres technology andapplications 50 DN/C E.T. (D) (2005)49,add.1

G604-22EP Multiple Output Low-Voltage DC/DC Converter Module 450 DN/C Austrian Aerospace (A) (2005)49,add.2

G604-23EP Solar array maximum power point tracking based on boostregulation for high power applications 300 C (2005)49,add.2

G604-24EP Analysis of Life-Cycled SAFT Li-Ion Cells 320 DN/C Saft (F) (2006)49,add.2

G604-24QC Robust Receiver Technology Optimisation 500 DN/C QinetiQ (UK) (2006)49,add.3

Total Power generation, storage and distribution efficiency 850 1,750 2,320 3,600



Technology to reduce the schedule and cost of System Design, AIV, Mission Control and Operations


G605-01EM Requirement Engineering: Requirements complexity and costanalysis 250 C


(2005)49,add.1

G605-04EM EGSE architecture 500 DN/C Siemens (A) (2004)49

G605-10MC Low cost platform for system simulation based on EcosimPro 100 DN/C Empresarios Agrupados (E) (2005)49,add.1

G605-11MP Development of an European Space Propulsion System Tool 600 DN/S

Iberespacio (E) +subcontractorsOutput may lead to ESAOperational SW (specialattention on contractsclause 42)

(2005)49,add.1

G605-13AC Concurrent Engineering of Space Instrumentation 300 C2 (2005)49,add.3

G605-15AC Concurrent Engineering and "Web Services" 100 C Open Source SW (specialattention on contractsclause 42)

(2005)49,add.3

G605-25EM In-flight validation of internal charging tools 250 C1 Open Source SW (specialattention on contractsclause 42)

(2005)49,add.3

G605-27EM Development of 3-D analysis tools for the Space ENVironmentInformation System (SPENVIS) 360 DN/C

BIRA (B), RHEA (B)Output may lead to ESAOperational SW (specialattention on contractsclause 42)

(2005)49,add.1

G605-29ES Microprocessor Simulator with Hardware Accelerator 250 DN/S Gaisler (S) (2005)49,add.3

G605-31EL Generic Ground Segment for Proba Microsatellites 700 DN/C Verhaert D&D (B) (2004)49,add.1

G605-32MP Kernel for turbine optimisation 300 C (2005)49,add.3




G605-39GI Advanced Monitoring for a Modern Generic Mission ControlSystem (Extension) 850 DN/C

Siemens (A)Operational SWfor ESA (Special attentionon contracts subclause42.8)

(2005)49,add.6

G605-40MC Active Payload Adapter 450 C (2006)49,add.4

G605-41SW Spacecraft Computer Basic Software Development and Validation 1,250 DN/S Saab-Ericsson Space (S) (2006)49,add.4

G605-42GI Re-engineering of Data Systems for European Ground SoftwareSystems 450 C


(2007)49

G605-43GI DTL/DML based Mission Control System (MCS) Demonstrator 550 DN/C

Siemens (A)Output may lead to ESAOperational SW (specialattention on contractssubclause 42.8)

(2007)49, add.1

Total Technology to reduce the schedule and cost of System Design, AIV,Mission Control and Operations 1,550 1,410 3,050 1,250



Theme 7.- PILOT PROJECTS

Special Projects


G703-01PT Support to Space Technology Transfer Finland 150 DN/S Turku Science Park Ltd(FIN) (2005)49,add.5

G703-03SR Symbiotic Sphere – an Interactive Space Station CommunicationInterface 200 DN/C Space Synapse Ltd. (IRL) (2006)49,rev.1

G703-04SR Definition of the VEGA-1 Payload (Step 1) 500 DN/S Contraves (CH), Verhaert(B) (2006)49,rev.1

G703-05SY Application domain of the PROBA platform 400 DN/C Verhaert and Spacebel (B) (2006)49,add.4

G703-06SYDevelopment, qualification, and flight manufacturing of theCryomagnet Self Protection (CSP) electronics for the AlphaMagnetic Spectrometer (AMS)

1,600 DN/S CRISA (E) (2007)49, add.1

G703-07ST National Technology Transfer Initiative (NTTI) 500 C (2007)49, add.1

Total Special Projects 150 2,300 900

ANNEX II

Detailed Descriptions of the Activities


Theme 1.- EARTH OBSERVATION

Ref. Number: G104-11GD Budget: 500 K€

Activity Title: Data Base Generation System of 3D sceneriesDescription: Design and prototype implementation of a system to automate the process of

generation of a 3D simulation database starting from correlated source data. Thebuilding of databases for simulation is a very time consuming task due to thefollowing factors: -The data flow required to generate the simulation databases isvery long. The simulation databases cover huge extensions that force to processhuge amount of data -The new simulation databases integrate satellite images toproduce a more realistic effect in order to produce a demanding simulationdatabase it is required a system able to store and reference all the source dataand to automate the generation process. The main objective is to reduce the timerequired for the 3D database compilation and consequently to reduce significantlyits production cost. The cost reduction in the production of 3D databases opensup new possibilities of application of this technology by addressing newcommunities such as: Urban planning, Emergency Disaster planning, MissionPlanning, Natural Resources Management, Tourism Advertisement (virtual flighton the web) and Environmental Monitoring. Due to the possible risk linked to theintroduction of new approaches and technologies in the development of thesimulation databases, the execution of the activity is proposed in two phases:-Feasibility analysis of the new technologies, identifying the bottlenecks in thegeneration of simulation databases and proposing solutions. -DBGS design andprototype implementation.

Deliverables: System architecture; DBGS prototype; Documentation; Sample simulationdatabase; Evaluation and demonstrator; Final report and presentation.

Data exploitation



Activity Title: Cooperative EO SensorsDescription: In several EO applications the users (value adders, service providers,

researchers, end users, etc) of EO products and services make a considerableeffort in exploiting EO information together with ground-based measurements. Inorder to avoid the burden of linking EO and ground data (e.g. wind speed anddirection, temperature, rain gauge, pollution measurements, motion detection, etc.) it is proposed to empower the EO ground Segment with "Cooperative EOSensors" which are able of directly accessing EO data in near real time, derive theEO product, extract the relevant information from the product, request neededground measurements from ground sensors and provide the combined EO highlevel product to the final user.The activity will be carried out in two phases. In the first one the availableelements from ongoing EO missions will be analysed and a virtual near real timeEO chain will be prototyped; the ongoing work on related subjects (see e.g.sensor web) and COTS shall be analysed and a sketch architecture for the wholecooperative EO sensors enabled ground segment identified; several candidate EOapplications (e.g. pollution, flood, landslide, volcano) will be analysed, togetherwith the application owners, in order to quantify and assess the benefits comingfrom the full integration of ground and space based measurements andprocessing. In the second phase two pilot applications will be selected and aprototype will be implemented and demonstrated

Deliverables: - Phase 1 (300 KE): Requirements; Conceptual design; Virtual NRT GS designand prototype implementation; Key trade-offs and prototypes; Evaluation of COTSand standards for ground based measurements; System architecture;Assessment and quantification of the benefits; Proposal for a scaled downprototype- Phase 2 (600 KE): Evaluation and Selection of the EO applications; Design ofthe prototype (EO GS and ground based); Implementation of the prototype of theCooperative EO Sensors enabled ground segment; Test, demonstration andevaluation with users


Ref. Number: G104-35GD Budget: 2,000 K€

Activity Title: Enhanced Services Infrastructure Technology (ESIT)Description: Previous work done in the MASS GSTP activity (MultiApplication Support Service

System) and in the ESA Service Support Environment implementation has shownthe advantages of exploiting technologies for harmonisation of service provisionmethods across providers. It was demonstrated that the instruments to support aneutral and open service-enabling environment permit a network of companieswith similarly and complementary skills to serve demands on larger scale e.g.promoting local or regional applications within a European environment withpotentials even for global perspectives. New large European projects (e.g.:GMES, TESI, etc.) are starting to pose new demanding requirements for serviceprovision, which need to be addressed.

In this regard this activity will aim for a new set of technologies which could solvethe forthcoming needs. These will be identified, prototyped and tested, for theircapabilities to:- support and exploit a wider services infrastructure- encompass EO and non-EO domains- provide seamless access to Earth Observation data and information, geographicinformation, geospatial data, …- permit an internet based telecommunication architecture supporting also mobility- offer more complete, complex and automated orchestration of services- improve the exploitation of existing and new EO facilities- extend even more the support to Service Providers in e-Commerce / e-Business- explore cooperation / e-Collaboration environments.

The activity will define the new services infrastructure’s architecture, trade-off theapplicable technologies, implement a prototype, prepare and run a demonstrationplan.

Deliverables: Software package (including COTS); Test data and environment; Documentation.

Justification for DN: The proposed activity is a continuation of an ESA activity (Contract no.15014, 2,500 K€ funded by GSTP-3 and EO programmes).

Article 6.1.c of the Contracts Regulations is applicable.



Activity Title: Semantic-web for Mediated Access Across Domains - SMAADDescription: This activity aims at identifying the methods to apply Semantic Web (and, as

mature, Semantic Grid) technologies for mediated discovery and access insemantic terms across ontologies of distributed sources of geo-referenced and notgeo-referenced data, products, information and services. So, the major objectivesare to identify and test Semantic Web / Grid Technologies permitting to:- Improve techniques for storage and retrieval of RDF and other types of data,considering distributed database approaches and specialised solutions forindexing, search and retrieval of geo-referenced data- Develop vocabularies / dictionaries to express multi-lingual thesauri such asgazetteers of geographic names, controlled vocabularies, etc. and providesolutions for their integration with other semantic data- Provide dictionaries / ontologies to support semantic interoperability between themost common metadata formats and offer simplified metadata vocabulary,compatible with full, standardised schemas, to allow easy and fast publishing ofdata by providers- Identify methods for thematic discovery and search, which uses cross mappingbetween user’s defined vocabularies and other documents’ vocabularies and/or toaugment / refine data search and retrieval (together with the use of contextualinformation about such, as user preferences, profiles and environments)- Assess the mediating technologies, which can permit to automatically crossrelate different ontologies, and to create active interfaces capable to suggestalternatives to the users from different domains

Deliverables: Requirements; new concepts and trade-offs; prototype applicable at least to theEO portal, including data, products, information and services; and prototypeevaluation and report (including potentialities and limitations).



Activity Title: Use of ISEA (Icosahedral Snyder Equal Area) for EO SensorsDescription: The Icosahedral Snyder Equal Area (ISEA) is a class of a Discrete Global Grid

Systems (DGGS) used to partition the Earth ’s surface into cells to whichapplication data can be associated for spatial search and visualisation. DGGSscan use different base regular polyhedrons.Preliminary assessments have been performed with an ISEA4H grid based on ahexagonal geometry and an average adjacent intercell distance of about 15 km,which copes very well with the observing geometry of medium / low resolutionsensors. They have provided promising results for use for the products of someEO sensors, SMOS in particular. However, real feasibility, benefits and fullpractical use have to be demonstrated. This requires some implementations andcomplete tests.In case of successful results, the outcome should be made operationally robust foreventual integration, for example, into the Earth Explorer Mission CFI, whichalready now provides unified services for mission planning and orbit calculation toEOP Ground Segments.This activity aims at demonstrating the feasibility of use of the ISEA as a DGGSwithin the SMOS framework and at preparing for its evolution for practical futureuse. Activities to be performed will include:- Development of an ANSI C/C++ library to generate ISEA grids of variableresolution and apertures (ISEA4H and ISEA3H) on sphere and ellipsoid.- Development of an ANSIC/C++ library to search / retrieve distance betweenpixels (e.g. given pixel X return all pixel indices within a certain distance, lat/longrange, etc).- Design of a visualisation library integrated in an open environment, in order toallow easy integration into ESA Earth Observation developments.Identification ofpotential applications in other domains and development of related componentsfor the most promising one (e.g.: market).- Documentation of above implementations.- Tests of selected implementations.- Identification of a semantically meaningful indexing strategy for grid pixels tosimplify all above activities.- Identify widely used global dataset (e.g. DEM like GTOP5 or GTOP30) andpossibility / methods to convert them to ISEA representation.

Deliverables: - Technical note on potential applications analysis- Software modules and library- Documentation- Test results

Justification for DN: GRIDS – Graphical Resources Integrated Data Solutions (CDN) havedeveloped the basic modules for the ISEA and own the relatedTechnology.Articles 6.1.a and d of the Contracts Regulations are applicable.



Activity Title: Extension of ADAS (Advanced Earth Observation Data Acquisition System)Description: Alcatel Bell Space has developed under the ESA GSTP-3 programme an

Advanced Earth Observation Data Acquisition System (ADAS), an improvementon the very successful Omnisat demodulator.

This activity contains further improvements to this development in order torespond to the evolutions in the space-to–ground data transmission standard andto include some novel features to ease the integration and operation of theequipment.

The activity will be devoted to perform the detailed design, implementation, andtest of the extensions required to support the new functions described below:

- Support of 8PSK modulation (8PSK is being accepted by most Agencies andindustries to improve spectrum efficiency)- Encryption of configuration files (ADAS is based on commercial equipment andsoftware to perform the signal processing, which makes it very easy to upgradethe equipment and to extend functions, but unfortunately also for non-authorisedusers, i.e. encryption of the configuration files will be required)- Generation of an antenna tracking signal (the ADAS equipment includes anX-band down converter, which is useful particularly for small Earth Observationstations; the availability of a signal strength output, to be used for antenna trackingpurposes, would be an additional asset for this type of station)- Provision of integrated measurement functions

Deliverables: Design and user documentation for all the functions, upgraded ADAS demodulator

Justification for DN: The proposed activity is a continuation of an ESA activity (Contract no.17122, 2,400 K€ funded by GSTP-3).Non-competitive tendering is justified according to Article 6.1.c of theContracts Regulations.



Activity Title: Preparation of Interferometric SAR processor - COISPDescription: An interferometric SAR processor has been developed under a GSTP contract.

The processor input is a collection of single-look complex images in ASAR format,while the output is made up of a single digital terrain model, displacement models,and auxiliary radar brightness and coherence images. In this regard the aim of thisactivity is to prepare this processor for operational use, further develop the errorprediction algorithm based on the experiences obtained with the present suite,and to identify and reduce performance bottlenecks. This shall be achievedcovering the following tasks:- ERS SLCI (Single Loop Complex Image) Interface. Design, implement, andvalidate an interface to the ERS.SAR.SLCI standard product. This would allowutilization of the existing ERS archive over small areas of interest.- Establishment of a strip facility. Large area processing may benefit significantlyfrom use of SLCI strips (> 300 km), due to simpler data administration and alsobecause calibration parameters may be propagated along the strips. Neither ERSnor ENVISAT standard SLCs are available as strips. However, ERS.SAR.RAWdata could easily be (re )adjoined to long continuous strips.- Atmosphere and GCP (Ground Control Point) error prediction. The present IP(Interferometric Processor System) includes an error prediction, which assumesthat errors at ground control points (GCPs) and at observation points (DEM –Digital Elevation Model pixels) are uncorrelated (also, the present error predictionmodel underestimates the errors when a large number of GCPs are present). Anew algorithm based on the atmosphere correlation structure (which is knownfrom the GPS and VLBI – Very Large Baseline Interferometry communities), isproposed for this task.- Improvement of robustness. Here the task is to identify the mechanisms thatcause large errors near data borders. Subsequently, a method to eliminate thoseerrors should be devised.- Performance optimization. Firstly, the processing algorithms will be optimized toobtain a reasonable balance between product quality and processing speed.Then, a more conventional optimization and parallelisation should be carried outto finally identify bottlenecks, which require future substitution of algorithms.

Deliverables: Interferometric SAR processor SW, upgraded with the features described above;user and maintenance documentation.

Justification for DN: The proposed activity is a continuation of an ESA activity (Contract no.12977, 350 K€ funded by GSTP and Corporate Budget).

Non-competitive tendering is justified according to Article 6.1.c of theContracts Regulations.



Activity Title: Application Module for UGEI (Universal Geometry Engine for EO Images)Description: The main objective of this activity is to verify that the Application Module I/F built

into UGEI (a currently running GSTP-3 activity) is adequate for the task, that itworks correctly, and to provide an example of the implementation of anApplication Module as a guide for further developments.

UGEI is meant to carry out in an organised way a number of tasks that are moreor less always required when preparing EO products for specific use(georeferencing, orthorectification, co-registration, etc.). So far these tasks arere-implemented in all the specific applications that are designed to prepare the EOproducts. UGEI implements the common tasks in such a way that the output canbe reutilised by a number of applications. It achieves this by providing a definedinterface to which the specific applications can connect to make use of thefunctions implemented in UGEI.

Hence this activity shall be devoted to design, Implement and test a sampleApplication Module for UGEI (in this case the application module will carry out theorthorectification of an EO image). This application module will have to bedesigned and coded. It will then need to be integrated with UGEI. A first stage oftesting will ensure that the integration with UGEI is behaving as expected; this willmost likely require adjustments both in the application module and in UGEI. Asecond change of testing will be required to unsure that the interface betweenUGEI and the application module is correctly abstracted and can be used by abroad range of application modules. The activity shall include the following tasks:

? Architecture and Detailed Design? Coding and unit testing? Integration with UGEI? Validation of integrated UGEI – Application Module

Deliverables: Design Documentation (ADD, DDD, ICD), Software Source, User Documentation,Validation data and report.

Justification for DN: This activity is the continuation of the work carried out by INDRA in theESA contract no. 18867 (budget of 400 K€, 200 funded by GSTP-3 and200 funded by the own company).




Activity Title: Digital Urban Knowledge Engine (DUKE)Description: The present activity aims at developing an innovative 3D database system

enabling the exploitation of very high resolution Earth Observation data, incombination with other sources of geographical information, for high fidelity,interactive 3D visualisation and simulation of urban environments. It will consist onthe development of a set of tools for retrieving, in an optimized way, the relevanturban information (buildings, roads, networks, etc.) from the different sourcesavailable (maps, footprints of buildings, DEMs, rasters, cadastre, 3D models,pictures, GIS, etc.), supporting the real-time rendering by a client application. Thismodule will combine a data pre-processor, for converting and compressingheterogeneous data to a form suitable for rapid view-dependent visual dataextraction, with an out-of-core querying subsystem that will exploit the potential ofcurrent commercial-off-the-shelf computational and visualization platforms. Such asystem would be used as a core to more complex applications for browsing,simulating or planning urban environment and training or monitoring operators incharge of their management.

In order to define this system several tasks are foreseen: definition of therequirements from target users and developers, including overview of currentstate of the art of complementary projects as CRIMSON, development of an initialbeta implementation and integration with the CRIMSON tool, and finallyrefinement of the specification and development of the final version and validationwith end users and data providers.

Deliverables: Prototype (beta and final), validated on real-life scenarios by a selected set ofcomplementary users. Envisaged scenarios will focus on subjects such as urbanplanning.

Justification for DN: CS (F) is currently developping the CRIMSON system (in the frame of anR&D activity funded by the European Commission), as an innovativeapplication using the latest Virtual Reality technologies for theinter-organisational preparation, rehearsal and management of urbancrisis.

The DUKE project is complementary to that CRIMSON project andaddresses the part of the creation of the urban database that was notincluded in the initial CRIMSON scope of work. To guarantee that theDUKE system is fully compatible with the original CRIMSON project, it isproposed to carried out the work with the same team that is developpingthe CRIMSON project, as CS (F) and NavTeQ (NL), as it is the only onewith the required experience and skills to guarantee the success of theproject.

Non-competitive tendering is justified according to the article 6.1.a of theContract Regulations



Activity Title: Level 3 SAR processor for map production at continental scaleDescription: The aim of this activity is to design and implement a high level SAR processor

(Level 3) for the automatic generation of seamless mosaics over very large areas(countries or continents) with high spatial resolution (<=20m) and applyingmultitemporal filtering techniques to achieve a superior radiometric quality(speckle reduction without loosing geometric detail).

In the frame of GMES land applications, it has been identified a gap for a mappingproduct capable to identify the growth of the urban areas on a yearly basis with adetail better or equal than 1 hectare over all the European Union (4,000,000 km2).So far, the mainstream has been making usage of optical data like SPOT-4 orLandsat to address this requirement and some small scale demonstrations ofproducts alike have been conducted in the frame of several GSE projects.However, this could be delivered inexpensively by making usage of today’savailable ENVISAT ASAR data. The technical advances during the last years inASAR data processing show that it is possible to generate geocoded SAR datawith a geometric and radiometric resolution much higher than that in the standardEnvisat products resulting in a level 3 product with a much betterphotointerpretability. The purpose of the proposed activity is to construct the L3processing facility which will be enabling infrastructure for mass application ofASAR in Land applications. In particular, the following tasks are identified:

• Building a SAR-L3 mapping facility capable to generate continental seamlessmosaics with a resolution better than 20m and improved radiometry bymultitemporal filtering• Demonstration of the facility operations over a limited area (700,000 km2) andnumber of scenes (1500)• Demonstration of the benefits of L3 production when directly accessing thearchive• Demonstration of how the Level-3 product can create new applications whendelivered to third parties• Preparation for future ground segments design• Preparation for a potential integration into ENVISAT current operations

In order to deliver the L3 SAR continental mosaic at an affordable price, thefollowing automatic processing schema is proposed:

- Advanced geocoding processor. Including the capacity to generate ASARorthoimagery without ground control points with a pixel localisation accuracy.- Superresolution image processor. Tool to generate temporally filtered imageswith a superior radiometric resolution (fighting speckle by time averaging insteadof spatial filtering).- Mosaicking processor. Tool to create seamless images without geometric orradiometric transition steps between images.- High level processing engine. Tool to orchestrate all data workflow, I/O datahandling and all the previous components.- Interface with end-users through ESRIN’s Service Support Environment(SSE-MASS) to enable the ordering and access to output products.- Interface with Envisat catalog through currently available SSE components- Interface with Envisat archive to enable electronic access to input data withoutphysical media handling.

Deliverables: Operating facility ready to address the processing over 1,000,000 sq km on ayearly basis; Validated L3 SAR mosaic over two or three countries or regions inEurope (700,000 km2); System documentation.



Activity Title: Grid enabled Service Support Environment (SSE-Grid)Description: The role of an SDI (Spatial Data Infrastructure) is to provide satellite data to

end-users. In practice the architecture of such SDI’s imply that these data-centresare continuously duplicating archives and moving large amounts of data aroundover limited internet lines. The available datasets of earth observation instrumentsare continuously growing in size, putting stress on this architecture. To avoid thisproblem, the Grid technology can be used. The idea behind the Grid technology isto bring the processing algorithms to the data instead of having to move largeamounts of data to the user’s processing site. The processing is done oncomputers in the data center, which have direct access to the data and only thefinal results need to be transported over the internet to the end-user.

The aim of this activity is to develop a Grid interface in SSE (Service SupportEnvironment) to operate and monitor a Grid. The interface should allow the user,e.g. a PI to submit a process" or "processing job" which is to be run on a Grid toprocess data available on the Grid. Alternatively, the user can select a processwhich already resides on this Grid as is done for the ESA MERIS (MediumResolution Imaging Spectrometer) grid service. The grid service itself should havea mode to run in historical mode (by reprocessing a historical archive andgenerating a bunch of products) but also in near-real time mode (the nearreal-time Grid service is a kind of subscription which starts automatically as soonas new data becomes available and generates the latest product). The Gridservice should publish an interface according to the Grid-On-Demand ICD byESA. The project will propose extensions to this interface if needed.

The tasks envisaged for this activity are:

- To set up an operational Grid-system around the VEGETATION centre and tomake the VEGETATION data available to the Grid- To incorporate the operational Grid at ESA/ESRIN into SSE and ensure to makethe MERIS and AATSR (Advanced Along-Track Scanning Radiometer) dataavailable to the SSE-Grid.- To offer the use of existing software components (e.g. SMAC, cloud detectionetc) by making them available in the Grid environment. These pre-builtcomponents can be directly used in a users own custom processing chain.- To add an "archive service" accessible from the SSE as a Web service, so thatprocessed results can be written on tape or DVD and ordered at nominal costs.- To integrate a delivery service to allow multicast of the grid service results via asubscription mechanism via the ESA DDS system.- Demonstration: run the GLOBCARBON multi-sensor processing chain on theSSE-Grid, taking inputs from VGT, AATSR and MERIS data and producing BurntArea Estimates products. This demonstrator should be run both in historical mode(processing data for 6 months) but also in near-real time (subscription) mode.

Deliverables: SSE-Grid software package; Operational VEGETATION and MERIS/AATSRGrids.


Justification for DN:

Taking into consideration that VITO's VEGETATION archive needs to beused for this activity and that the IT-infrastructure made available toSSE-Grid will consist of powerful processing units at VITO (linked to theESA ones), and a large data storage capacity, it is proposed to have VITOas the main contractor for this project. The SSE users will have directaccess to the VGT archive at VITO, and the AATSR or MERIS archive atESA. SSE users will have the opportunity to use existing software modulesmade available by VITO and ESA (e.g. from the Globcarbon project), andcombine them with their own modules to construct a custom processingchain. In addition, Spacebel (B) and DutchSpace (NL) are proposed assubcontractors as the first one masters the SSE, the second one has largerecognised experience in Grid (see GridAssist).

Non-competitive tendering is justified according to Article 6.1. a) of theContracts Regulations.

Ref. Number: G104-44GR Budget: 2,500 K€

Activity Title: ADAS EvolutionDescription: ADAS (Advanced earth observation Data Acquisition System) provides an

integrated earth observation data acquisisition system, able to process telemetryfrom radio frequency (X-band) to front end processing, supporting a wide range ofcurrent and future missions. The objective of this evolution is to guarantee thecompatibility of the ADAS system with upcoming Earth Observation missions,maintaining, at least, the present market share in the demanding high-end marketsegment, as well as to position ADAS also on the low-end market segment withan affordable, all-in-one solution for a complete data reception solution.

In particular, this activity covers the following aspects of the evolution of theequipment design:

- Extension of the equipment modulation and demodulation capabilities withchannel filtering algorithms for bandwidth limitation, efficient modulation anddemodulation schemes for higher information data rates and novel codingschemes for improved error rate reception. This, in line with the new generationtransmission standards, implies the evolution of the modem function withcompatibility with TCM encoder, SRRC, programmable filter shaping and GMSKmodulations for high data rate applications.

- The extension of the upper data rate limits in the same equipment by increase ofsingle carrier modulation/demodulation capabilities with a target of data rates upto 1 Gbps and the possibility to integrate in a single acquisition equipment amulti-carrier modulation/demodulation capability for at least 4 carriers and a totalthroughput of 2 Gbps. This capability includes the support of both high ratemonocarrier (1Gbit/s) and multicarrier transmissions.

- To position ADAS on the low-end market, by adding functions to reduce the costof the overall acquisition chain by further integrating in the ADAS system somefunctions otherwise requiring other equipment (for example, merging of the dataplayback function with the modulator function, FEP evolutions and extension ofthe front-end processing functions, inclusion of the antenna tracking loop controlcapabilities...)

- Extension of functional performances of the acquisition system by the addition ofnovel functions into the same industrial computer platform; extended monitor andcontrol functions improving cost of operation, autonomy in stations, and remotemaintainability, (automated self tests, data logging).


Deliverables: ADAS system including all new functions, validated and tested in an ESA EOstation; Project design documentation; Equipment documentation update(installation, maintenance and user handbook)

Justification for DN: The development proposed in this activity is continuation of the workdeveloped by Alcatel Alenia Space (B) under the ESA contract 17122("Development of an Advanced Earth Observation Data AcquisitionSystem - ADAS", funded by GSTP-3 and GSTP-4 with 3.3M€). As, thefunctions described in this activity are to be implemented within theexisting ADAS equipment, developed by Alcatel Alenia Space, it isproposed to carry out this development with the same contractor.

Non-competitive tendering is justified according to Article 6.1. c) of theContracts Regulations.

Ref. Number: G104-45SE Budget: 400 K€

Activity Title: Integrated EO based monitoring services for the Arctic region -IMSARDescription: The introduction of new SAR satellites and constellations of SAR satellites will

make the revisit time for arctic areas very frequent and hence tracking of shipsand icebergs/floes should be possible. In order to achieve this it is necessary tofind out the capabilities of the new X-band SAR systems and what featureextraction is necessary from the targets in order to make it possible to track themfrom image to image.

One of the biggest obstacles in introducing ship detection as a tool in fisheriesmonitoring and control in the arctic area has been the limit of use close to the iceedge (currently in the order of 20 m). Several demonstrations have shown that the(dynamic) ice edge creates many false targets, specially related to “ice tongues”(grease ice/new ice) extending from the ice edge. As fishing vessels quite oftenoperate as close to the ice edge as possible, ship detection has not been a usefultool for the fisheries monitoring and control. It is hence necessary to develop atool to mask the ice edge and it’s “tongues” so that these do not contribute withfalse ship targets.

The overall objective is to establish an operational satellite radar based monitoringservice providing updated and reliable information on ships, icebergs/icefloes, aswell as on wind and wave for the operational users in the Arctic region.

In this context, the activities to be performed include:

1. Discrimination of ships from ice-bergs and floes.SAR data acquired at the same time as in-situ observations of ice-bergs and floeswill be used to derive a set of rules and statistics that describe how ice-bergs andfloes differ from ships as targets in SAR data. The in-situ observations are fromIceCam systems onboard ships, hence both ships and ice-bergs/floes will bepresent in the same image under the same environmental and imaging conditions.The set of rules and statistics will be developed into an operational algorithm andincluded in the ship detection service.

2. X-band assessment and tracking of ships, ice-bergs and floes.Awaiting the launch of X-band SAR satellites preparational work will be done byliterature research, modelling of X-band SAR behaviour, and by using X-bandSAR data available from airborne campaigns. When real X-band SAR databecomes available from either TerraSAR-X or Cosmo-Skymed, a comparison withC-band SAR data will be done. Based on this assessment, any necessarydevelopment of the ship detection algorithm will be performed.

In order to implement tracking of objects over time it is first necessary todetermine which features need to be extracted from a target in order to make it


possible to track. Thus, a simulation of acquisition patterns of the relevantsatellites (Radarsat-2, Sentinel-1, Cosmo-Skymed, TerraSAR-X) will be performedin order to assess the most suited acquisition patterns for tracking. Based on thefindings, it is foreseen to implement and test a tracking algorithm.

3. Ice edge maskingUsing SAR images showing the ice edge and related “ice tongues” from a varietyof incidence angles, polarisations and resolutions develop a method to create anice mask that will be used to mask out areas in the ship detection. It might benecessary to integrate ice edge information from other sensors like RadarAltimetry and optical data in order to make the masking possible.

4. Wind retrieval from SAR and optical dataA prototype service providing wind speed and direction from Envisat ASAR data isbeing introduced. The wind information is extracted from the same data appliedfor oil spill, ship and the ice services. Improved and timely information on wind andwaves will be especially important for offshore operations. The developmentsinclude improving the wind extraction method and implementation and validationof a wave direction and –length service, also extended to utilise future missiondata e.g. from Radarsat and Sentinel-1.

Deliverables: Updated ship detection service classifying targets (as ship, ice-berg or floe) andutilising X-band SAR and providing tracking products for ships, ice-bergs andfloes; Updated wind and wave information service.

Ref. Number: G104-46SE Budget: 600 K€

Activity Title: Enhanced oil slick drift forecastingDescription: At present the capacity of national environmental protection agencies and coast

guards to forecast the evolution of large oil slicks from Prestige type accidentsremains limited. During the Prestige incident, this limited capacity resulted inerroneous predictions of which areas would be affected and environmental andecosystem impacts that could possibly have been avoided in French, Spanish andUK coastal areas.

Since this time, the state of the art in high resolution oceanographic modelling andsatellite based ocean observation has improved. Basic physical oceanographicmodels have undergone extensive development over the last 5 years and testshave demonstrated the positive impact such capabilities have in improvingforecasts of oil spill drift and evolution. However, many of these models retaincertain constraints that reduce their operational utility. Examples include:• Resolution and update times are targeted towards the open ocean at basin andglobal level. Oil drift forecasting requires faster, more localised, finer scaleupdates for a specific region• A model forecast may not be based on the latest EO data available leading toerrors in forecast and nowcast impact• Different regions are represented with varying degrees of quality and accuracy• Drift forecast models must be initialised with a sufficiently accuratecharacterisation of the location, extent and type of oil spilled.

There is therefore a need to better integrate the different data layers to ensure themost accurate timely information is available to support emergency responsedecisions. At the same time, the increased occurrence of pan-European responseto such disasters means common standards, interfaces and performance levelsmust be applied to ensure emergency response personnel make the mosteffective use of the decision support information

The objective of this activity is to establish benchmark best practices forintegration of EO (Earth Observation) data into state of the art oil spill drift


forecasting and impact assessment systems for decision support. This includes:

- Establish benchmark best practice for integration of EO data into state of the artoil spill drift forecasting and impact assessment systems for decision support: EObased oil slick characterisation, EO based oceanographic parameters for nowcastand forecast information layers, and EO based information for vulnerableecosystems, coastal land cover mapping, coastal zone characterisation.- Interfaces to other information systems: definition of interface protocols andformats for exchange of EO data and output data layers between serviceproviders and users.- Validation: improved HMI (Human Machine Interface) decision supportperformance through adoption of best practice and better integration of EO basedinformation layers; information exchange with European Maritime Safety Agency(EMSA) Safeseanet and DG Environment Civil Protection Unit Decision SupportSystem; compliance with on-going EC INSPIRE Data Format and Standardisationlegal requirements and developments; effectiveness of performance levelsthrough support to user organised spill response exercises.

Tasks to be executed:• Review present national systems for oil spill drift forecasting and response withrespect to: information layers presented to decision makers; perceived reliabilityand consequent utilisation of decision support information; modelling approachesand accuracy; input data layers and accuracy.• Review capacity of EO based information layers to improve drift forecastaccuracy, timeliness, temporal coverage and decision maker understandingduring crises response• Design interface protocols and data layer standards for information layersderived from EO data sources• Test performance levels with respect to integration of EO based information intothe overall decision support system, including both: direct information layers (egcoast line classification updates, oil slick information), and model outputinformation layers (eg Sea Surface Temperature forecasts, surface currentforecasts).• Review compliance of drift forecasting standards with system specifications ofSafeseanet and DG Environment Civil Protection Unit decision support systems• Review compliance of drift forecasting standards with appropriate Inspirestandards

Deliverables: • Interface protocols for EO data inputs, non-EO information layers, archivedinformation layers• Specification of data layer formats, content and performance levels forintegration with oil slick forecasting decision support systems• Prototype system for assimilation of EO derived information layers into driftforecast models• Best practice guidelines for integration of EO based information layers with oilspill drift forecasting decision support systems (including access to EO data sets,assimilation approaches etc)• Specification of requirements on information layers for oil spill drift forecasting toensure compliance with Inspire working group recommendations, Safeseanet andDG Environment Civil Protection Unit• Test and validation report for improved drift forecasting system


Ref. Number: G102-04EE Budget: 800 K€

Activity Title: High-power, low-loss feed array (development phase)Description: Reflector-based synthetic aperture radars (as opposed to active phased array

antennas) have shown a growing interest for cost reasons. To synthesise thedifferent overlapped shaped beams, high-power, low-loss feeds array arerequired. Similar needs are also identified to provide linguistic coverage in Ku- andKa-frequency bands. All these applications require high-power beam formingnetworks at focal plane level. Great care should be given to PIMP and multi-actionissues due to the high power levels involved. The inputs of this activity areexpected from the 2 parallel TRP-funded contracts on "Low-cost multi-feedantenna". The proposed activity would fund the demonstration phase of ahigh-power, low-loss feed array, suitable for an earth observation mission. Thisactivity will include the development of all critical items at feed array level and theRF power tests required to validate the design.

Deliverables: Feed array up to pre-qualification level.

Ref. Number: G102-08ET Budget: 150 K€

Activity Title: Burst Synchronization for ScanSAR InterferometryDescription: Burst synchronization would allow interferometry over much wider swaths than in

ordinary strip-map mode adding value to future SAR systems. This wouldconsiderably enhance the capability of the instrument making the data moreuseful for a wide variety of applications. The technique of imaging much widerswaths by repeatedly switching between beams, known as ScanSAR, has beensuccessfully demonstrated by both RADARSAT-1 and ENVISAT ASAR. Theadvantage of this technique is that a much wider effective swath can be imagedon the ground hence improving global coverage. The disadvantage, however, isthat with existing instruments it is not possible to realize repeat pass ScanSARinterferometry. This is because there is no synchronization between the bursts ofpulses transmitted in each beam for a given position around the orbit. The resultof this is that it is therefore unlikely for there to be any overlap of the Dopplerspectrum between acquisitions hence making interferometry between successivepasses impossible. The objective of the activity is to look at the feasibility andeventual system requirements for around orbit burst synchronization of ScanSARmodes in order to make wide-swath interferometry in ScanSAR modes possible.

Deliverables: Feasibility study into scanSAR interferometry identifying position/timingrequirements. From these requirements a system design shall be developed inorder to enable scanSAR burst synchronization. The system design shall beanalysed so that a cost estimate of the extra hardware required for realization ofburst synchronization may be established as well as the risks associated with theapproach taken.

Microwave Instruments



Activity Title: Passive sub-array technological developmentsDescription: This activity is dedicated to radiating subarrays for Synthetic Aperture Radar.

Despite large number of design performed by industries in C and X-band,innovative concepts and technologies are still required to reduce polarization feednetwork losses and to improve radiator efficiency over a wide frequencybandwidth These performances improvement are mandatory to allow an increaseof azimuth sub-array length in such a way to reduce the number of active controlson the antenna and induce a cost decrease. It is proposed to focus this activity ondual-polarisation subarrays which are much more critical due to the very limitedspace allocated to implement all the required components and to investigate lowlosses inter stages transitions to allow multi-layer integration and connection toT/R modules. Different concepts and technologies have to be traded-off(microstrip, suspended stripline, barline, waveguide.) for the feed networks andthe radiators. Calibration coupler included in the subarrays has also to beconsidered.

Deliverables: Sub-array detailed design and analysis report. Demonstration model of a SARsub-array.

Ref. Number: G102-25MC Budget: 600 K€

Activity Title: Ultra-stable structures for interferometric antennasDescription: Interferomteric instruments are currently being considered for a variety of EO

missions (e.g. SMOS). Two parallel TRP studies have taken place looking atGeostationary systems for Earth remote sensing. Observations from GEO havethe key potential advantage to provide continuous coverage of the same region,which is essential for nowcasting. Interferometric concepts that meet the productrequirements have been proposed considering frequency bands around 53, 118,183, and 380 GHz. This requires highly accurate and stable structures.

This activity deals with the trade-off and mechanical and thermal design of aninterferometric instrument. The particular concept at hand is based on aninterferometric receiver distributed along booms. Therefore the design drivers arethe mechanical scanning principle and structural stability and thermal design, all inrelation to the instrument requirements. It shall be noted that the proposedstructure should try to minimise the impact on AOCS and spacecraft propellant.Critical breadboarding shall serve to demonstrate the feasibility of the concept.The verification process shall be tailored to the novel instrument concept.

A two-phase approach is proposed. Phase 1 will end with a preliminarymechanical and thermal design of the Geo-sounder instrument. Phase 2 will bedevoted to the design, analysis, manufacturing and testing of an on-grounddemonstrator. Emphasis shall be placed on the verification of requirements andtheir consolidation for a future mission. A development plan for a full qualificationshall be established.

Deliverables: Demonstrator and critical breadboards. Technical documentation: Requirementsconsolidation, preliminary design and analysis of instrument, demonstrator designand analysis, test plan, test procedures, test results and correlation, developmentplan of qualification unit.



Activity Title: Frequency Domain SAR Raw Data CompressorDescription: Synthetic Aperture Radar raw data compression is today performed on board by

means of Block Adaptive Quantisation (BAQ). The BAQ allows for a relativelysimple implementation but the compression performance is limited and restrictedto integer numbers of bits per sample after compression. This is not sufficient formodern SAR systems, which in general generate a huge amount of data due totheir high resolution. An advanced method for SAR raw data compression hasbeen proposed, which provides better compression performance at the expenseof a higher processing effort. The block adaptive quantisation is performed in thetwo-dimensional frequency domain. This allows the elimination of the unusedspectrum, which is the result of over-sampling in azimuth and range. Furthercompression improvements are obtained by taking into account the apodisationfunction used during image processing and the use of entropy coding. Theimplementation of the frequency domain compression methods on board becomesfeasible with the availability of the next generation of digital signal processingdevices currently under development.The objective of this activity is the development of a hardware module optimisedfor frequency domain SAR raw data compression as one element of the on-boarddata-handling network. This includes also the development of the algorithm andthe demonstration of the compression performance.

Deliverables: Compression module breadboard compatible to the advanced scalable datahandling architecture and its complete validation in laboratory environment.


Ref. Number: G102-30QC Budget: 250 K€

Activity Title: Evaluation of MMIC process for mm-wave space applicationsDescription: Future atmospheric sounders (post -EPS missions) or imaging radiometer like the

EGPM have an urgent need of adequate evaluated MMIC suppliers capable ofeasily adapting to custom design and small volume production foundries specificto certain space programmes. Fraunhofer Institute (IAF) in Freiburg has recentlybeen identified in the frame of an ESA pre-development activity as capable ofoffering a 0.15 m pHEMT process potentially suitable for some of the future earthobservation developments in terms of achievable performance and in reasonablequantities. This evaluation will include 5 different Work Packages: WP1 willaddress the process documentation to make sure that processing route, materialsused, process description in terms of metal layers, passivation, passive and activeelements layout and construction and libraries are sufficiently documented; WP2will focus on the design of process representative Technology CharacterisationVehicle (TCV) and Dynamic Evaluation Circuit (DEC), the TCV will contain allbasic building blocs of the process (passive & active, transmission lines, metal tometal metal/dielectric interco the DEC will be an active transistor optimised andadequately matched for characterisation at mm-wave frequency. Packaging andMMIC mounting techniques will also be considered. Masks fabrication and wafersprocessing and acceptance tests will take place during WP3. At least 2 waferswill be processed to check process and performance repeatability. Reliabilitytesting and preliminary evaluation via the performance of high temperaturestorage (min 2 temperatures for activation energies calculation) and endurancelife tests (2 different bias) will be carried out during WP4 while WP5 will bededicated to reporting.

Deliverables: Process documentation and design manual, TCV & DEC descriptions. Reliabilityand evaluation testing definition and later report, final report 5 DECs and 5 TCVsfor ESA Constructional Analysis

Justification for DN: During the GSTP-3 activity “Modelling of Planar Schottky Diodes” (contractnumber 15820, 650 K€ funded by GSTP), Fraunhofer Institute (IAF) wasidentified as capable of offering a 0.15 m pHEMT process (including dualgate active devices) potentially suitable for some of the future earthobservation developments in terms of achievable performance and inreasonable quantities. It is therefore proposed to perform an evaluation ofthe most recent upgrade of that process.

Non-competitive tendering is justified according to Articles 6.1.a) and d) ofthe Contracts Regulations.



Activity Title: High Accuracy/Stability Reflectors for future EO missionsDescription: Antennas for future missions present a significant technology challenge,

especially because of the high gain, narrow beam and wide scan requirements.The mechanical stability of reflecting surfaces is a major limiting factor in largeantenna performances at very high frequencies. Critical areas, like pointingaccuracy (thermo-mechanical stability) and the high number of beams (overallcomplexity), will be addressed specifically in this activity. This activity will betargeted to the following main areas:-Study and pre-design of antennaarchitectures.-Address critical technological areas identifying potentialsolutions.-Perform critical breadboard development up to antenna level (shell,surface treatments, etc..)The activity will start with a carefull assessment on themechanical accuracy and stability requirements for different mission scenarios(LEO, MEO, GEO). This activity will identify and select the mechanical, thermaland technological solutions and antenna architectures required to achieve thenecessary accuracy and stability for reflector antennas. Thesesolutions/architectures will have to be demonstrated by critical breadboarding (asa minimum at electro and thermo-mechanical representative sample level). Amethodology for the coupled electrical and mechanical design, which can greatlyimprove the achievable performances of such antennas by allowing the closematching of the mechanical design to the electrical requirements, should alsocarefully be considered. Special focus should be given to large temperatureexcursions.

Deliverables: Performance analysis, Detailed design, Antenna hardware, inclusive of samplematerial.

Ref. Number: G102-35ET Budget: 1,000 K€

Activity Title: PARIS Ocean Altimeter on GNSS ReflectionsDescription: PARIS is an ocean altimeter based on GNSS reflected signals presently under

research within TRP PARIS-Gamma. This PARIS-Gamma activity includes anaircraft experiment, a definition of the critical technologies of a spaceborne PARISsensor and the manufacturing of an aircraft sensor to demonstrate some of thekey technologies. The results of the first two activities are really promising, whilethe breadboarding is now starting. The present activity is a follow-on ofPARIS-Gamma with a double objective: (a) consolidation of the key criticaltechnologies for a spaceborne altimeter based on the PARIS concept and (b)realization of airborne campaigns to consolidate retrieval algorithms and feedbackon hardware configuration.

Deliverables: Breadboard to consolidate critical technology. High altitude flight campaigns usingthe PARIS-Gamma aircraft sensor.



Activity Title: European Antenna Modelling Component Library - Earth ObservationDescription: Electromagnetic modelling tools are a key factor in the timely and cost effective

development of satellite antennas. The availability of well-established andvalidated tools has been proven to reduce costs and time to delivery by as muchas 30%. The present activity will aim at developing components specific to EarthObservation missions. In particular, it will be focused in two components: - Astructural component to ensure the background activity to pursuit the commonobjective of bringing forward antenna modelling technology and tools. It will focuson the Earth Observation-specific aspects of: electromagnetic modelling datadomain standardisation (to make tools interoperable); geometrical CAD tuned toelectromagnetic modelling needs (to reduce cost on initial geometrical modelling)for Earth Observation specific antenna configurations; and overall management ofthe development of the Earth Observation specific components.-A thematiccomponent, dedicated to specific needs and focused on: refinement of reflectorantenna analysis tools (for very high frequency instruments); and innovativemethods for array design. Further details on the contents of each developmentline are provided in the Antenna Modelling and Tools Validation Dossier.

Deliverables: Software component library with relevant documentation. Validation hardware(satellite and antenna mock-ups).


Activity Title: Medium-size unfurlable antenna for LEO (concept study)Description: Today, increased market request for large aperture reflector with small-stowed

volume has been experienced, while only small size (3m) fixed large reflectors areunder development in Europe (such as that for SAR LUPE made by SES). Toallow low cost instruments, Synthetic Aperture Radar instruments need reflectorswith diameters in the range of 3 to 7 meters. Two parallel contracts are on goingfor the design of primary feed array compatible with multi swath, but the reflectordevelopment still need to be funded. This development is mandatory to makepossible new missions. This activity deals with the study and trade-off of possibleinnovative concepts for an unfurlable or foldable medium-size offset reflectorantenna, in the range of 3 m to 7 m. The reflector antenna should have an in-flightsurface accuracy and stability compatible with instruments operating atfrequencies up to X-band in order to fulfil the RF requirements. The conceptshould be applicable to offset apertures with elliptical or super-elliptical rim,required for SAR applications. Moreover reduced storage volume is requested tobe compatible with the limited volume of low cost small launchers and makeenable new type of mission/applications either monostatic or bi-static (like thecartwheel concept).

Deliverables: Detailed design of alternative concepts


Ref. Number: G102-42PS Budget: 100 K€

Activity Title: Verification of Self-Interference Free Receivers for HUT-2D RadiometerDescription: The HUT instrument is a result of a Finnish national technology development,

which has been continued under ESA contract 18137 (GSTP-3). The HUT-2Dinstrument is a sophisticated first-of-its-class airborne L-band interferometer. Thepresent activity will cover the gap between the present manufacturing status of theinstrument and its full completion.

The objective of this CCN is to complete the HUT-2D hardware, including thosetechnological activities required to allow a short data processing cycle, namelyantenna pattern characterisation and aircraft attitude/position corrections. Thisactivity will cover the following:- Manufacturing of RF circuitry and antenna patches- Control and correlator software development- Data processor development- Instrument integration- On-ground characterisation- Performance verification measurements

Deliverables: On-ground Characterisation Report, Data Processor Description Report,Performance Verification Measurements Report.

Justification for DN: The proposed activity is a continuation of an ESA activity (Contract no.18137, 120 K€ funded by GSTP-3).

Article 6.1.c of the Contracts Regulations is applicable.


Activity Title: SMOS Noise Injection Radiometer (NIR) Phase C/DDescription: The NIR provides a source of absolute radiometric calibration for the SMOS main

instrument MIRAS (Microwave Imaging Radiometer with Aperture Synthesis), thepurpose of this being to perform measurements of soil moisture (SM) over landand ocean salinity (OS) over the seas. The NIR operates, in conjunction with anon-board calibration sub-system (CAS), developed by YLINEN for SMOS, toprovide a relative calibration between NIR and the 69 other receivers thatconstitute the MIRAS instrument.

The objective of this activity is therefore to complete Phase C/D design anddevelopment effort for the SMOS NIR, covering the following tasks:- The implementation of necessary design changes of NIR- The implementation of the increased manufacturing effort due to these changes- The ESA qualification of SMT (Surface Mount Technology) assembly line ofYLINEN- Additional PA work necessary to upgrade YLINEN’s PA procedures to therequired level

Deliverables: NIR Design/Manufacturing Documentation and PA Procedures.

Justification for DN: The proposed activity is a continuation of the phase B carried out under anESA activity (Contract no. 17950, 150 K€ funded by GSTP).



Ref. Number: G102-44PY Budget: 175 K€

Activity Title: In-flight calibration of SIRAL altimeterDescription: The Technical University of Crete (TUC), under EU funding, has established a

facility equipped with instruments that measure accurately and continuously thelevel of the sea in the area. In addition, an available transponder can be deployedon the site together with other precise localisation equipment. This set ofinstruments is ideal for calibration of radar altimeters.

The objective of this activity is to support the in-flight calibration of SIRAL radaraltimeter -which is embarked on Cryosat- by refurbishing and deployingspecialised on-ground equipment. This shall include:

- Re-setting and calibration of existing equipment on the island of Gavdos.- Improvement of the existing infrastructure, in order to deliver reliably the dataacquired by the different instruments. Data distribution shall be achieved inquasi-real time to any user located anywhere in the world.- Modification (if necessary) and deployment of the available transponder severaltimes during Cryosat mission below the satellite track. This requires thetransportation and installation of the transponder on the main island of Crete(several times during the mission and especially during the first 6 months afterlaunch).

Deliverables: Databases of processed calibration data acquired during the Cryosat mission,6-monthly activity reports, technical description of the instrumentation, of thecalibration methods and results.

Justification for DN: The objective of this activity is to benefit from the capacities available andto support Cryosat calibration activities immediately after launch and alsoperiodically throughout the 3 year mission. The launch date is currently setfor September 2005 and hence direct negotiation is proposed to speed upthe process. Moreover, the equipment to be used for this activity is part ofan existing infrastructure on the island of Gavdos (Greece) and TUC hasthe necessary expertise to carry out this activity (after the EU fundedcontract).


Ref. Number: G102-45MM Budget: 130 K€

Activity Title: Broadband Sources for Far-IR Power GenerationDescription: The aim of the activity is the development of novel photonic mixers for

submillimetre-wave and far-IR local oscillators operating up to 1 THz outputfrequency.

No compact power sources currently exist for the generation of Local Oscillatorssignals in the frequency range between 1-10 THz. However, this range offrequencies is interesting for numerous space and earth exploration experiments,for imaging and bioengineering applications, and for security applications. Theoptoelectronic sources based on photomixing are an attractive option due to thepotential to operate over a broad frequency range. The novel “nipnip” THzphotomixer concept developed in a previous ESA activity can overcome both RCtime constant and transit time limitations intrinsic to traditional design approaches,which are at the basis of poor power performances at higher frequencies. So far,results have shown the "nipnip" THz photomixer performance to be in goodagreement with theory. Issues related to device geometry and antenna couplingare believed to be the reason of the observed output power levels, which are oneor two orders of magnitude lower than expected.

In order to improve on the performance of this promising THz photomixer device,the proposed activity will, firstly, focus on identifying the causes of power couplingdegradation and, secondly, design and fabricate an improved device structure.Modified antenna coupling will rely on the previously developed large-signal modelfor the "nipnip" structure. The optimized antenna integrated devices will be fullycharacterized and their performance will be compared to predictions.

Deliverables: THz signal source with improved output power:- Integrated photomixer with integrated antennae;- Dual-color laser system used in characterisation setup not included.

Justification for DN: This activity is proposed in DN with these three entities which can providecontinuity to the technology development initiated in the previous TRPactivity. In particular, in that activity, (ESA contract number 16863, 223KEuro funded by TRP), this consortium demonstrated the proof-of-conceptfor the p-i-n superlattice THz photomixer and the tasks proposed for thecurrent activity should be considered a continuation of that initial work.

Non-competitive tendering is justified according to the article 6.1.c of theContract Regulations.



Activity Title: Micromachined receiverDescription: The schemes currently adopted for the fabrication of receivers do not address the

problem of incorporating the low/high pass filters and waveguide coupling circuitsthat are required for actual device operation nor how to combine differentwaveguide components such as subharmonic mixers, frequency multipliers andlocal oscillators on the same wafer. However, new developments in the field ofnano/micro-machining (photolithographic methods, surface/bulk micromachiningand LIGA) have lead to the production of components that have a near opticalsurface finish, near vertical walls and dimensions approaching a millimetre inheight. This is of direct relevance in the field of sub-millimetre technology wherethe waveguide and antenna structures used require such properties but until nowcould only be realised with the use of ultra high precision machining.

The objective of this activity is then to demonstrate that sufficient performance canbe obtained from a micro-machined receiver, and that it closely competes withexisting conventional designs. In addition, it will aim to demonstrate that a massproducible nano/micromachined submillimetre-wave receiver can meet thereliability and performance critieria required for space operation.

The activity will then be devoted to design, fabrication and characterisation of amicromachined high performance receivers for which the fabrication processlends itself to on-wafer production. The first phase shall emphasize on the designtasks. In addition, an intensive analysis of the insertion loss and Gaussianefficiency of the resulting antenna shall be undertaken. This analysis will try toidentify the origin of any losses and potential solutions that would minimise them.

The second part of the activity shall determine a design rationale and fabricationapproach that leads to the complete integration of a submillimetre-wavewaveguide receiver on wafer.

The third phase will consist on the manufacturing of a fully integrated on-chipmicromachined receiver, with the minimum number of interfaces.

Deliverables: Micromachined receiver hardware; complete processing description, proof ofreproducibility and mastering of technology; demonstrator; full performance report.



Activity Title: GeoSounder MMICDescription: The activity will consist on the design, breadboarding, qualification and testing of

MMIC (Monolithic Microwave Integrated Circuits) radiometers at 118 and 183GHz.

Microwave radiometers are used for atmospheric sounding of temperature andhumidity profiles on-board NOAA and METOP series of satellites on LEO.Observations from geostationary orbit can offer advantages for nowcasting, and amicrowave sounding instrument (GEO-Sounder) is currently being studied in aTRP activity for post-MSG missions. The proposed Y-shapedradiometer/interferometer requires a large number of calibrated correlationreceivers at mm-waves. In order to enable the mission, low mass and powerconsumption, as well as uniformity are required, implying the need of MMICreceiver front-ends.

In particular, the following tasks are envisaged:

- Study and prototyping of alternative feeds (lens/waveguide),- MMIC front-end design activities: Process evaluation and characterisation Subsystem design (LNA, mixer, multiplier)- Receiver without feed and with integrated feed- Test, evaluation and demonstration

Deliverables: Hardware, specifically MMICs at 118 and 183 GHz.

Justification for DN: Omnisys and Saab Ericsson Space are currently responsible for theGeo-Sounder TRP activity (contract 19449, 3.4M€ for phase 2A) where ademonstration system at 50 GHz is being built. The present GSTP activityaims to take the next step by developing MMIC receivers for the next twohigher frequency bands of the Geo-Sounder instrument. This work cannotbe done without the background of Phase 1 of the TRP activity and the fullunderstanding of the system aspects of the novel (patented) instrumentconcept. Moreover, development of the MMIC receivers has to be done inclose connection with the on-going TRP contract, in order to guaranteecompatibility and coherence with the demonstration system. Therefore,Omnisys is the only company suitable for the work.

Non competitive tendering is justified according to the article 6.1.a of theContract Regulations.



Activity Title: Integrated Antenna FeedsDescription: Most of today’s instruments have receivers that work with waveguide horn

antennas as receiving elements. They have traditionally been the most commonmicrowave antenna feed types, although the attenuation of fundamental-modewaveguides at (sub)millimetre wave frequencies is high and both the effect ofmetal tolerances and misalignments becomes more severe. However, the smallsize can be turned into an advantage when the dimensions and tolerancesrequired become compatible to those achieved by lithography. In recent years theadvancement of photo-lithographic techniques has resulted in a very reliable andrepeatable process for creating structures on dielectric substrates and thefabrication of very complex electronic structures with a high yield is now possible.This means that a viable alternative for waveguide-based front ends has emerged.

This activity comprises of trade-off, design, analysis, manufacture, and test ofintegrated antennas. The specific objective is to demonstrate that broadbandintegrated antennas can achieve competitive performance as compared to thetraditional wave-guide horn technology and that such antennas have highpotentials for higher frequency ranges. The following features are proposed: 1)suited for operation up to the frequency range of at least 1 THz; 2) betterperformance than the competing classical technologies.

The activity will include the following tasks:

- Investigation of design alternatives and establishing the baseline design- Assessment of different fabrication technologies for these feeds and differentexperimental verification techniques- Derivation by testing of the electrical performances of the integrated antennas- Analysis of the test results, providing explanations for the deviations of the testresults from the results predicted and correcting them wherever possible- Recommendations for future improvements.

Deliverables: Detailed design, performance prediction, Integrated Antenna feed hardware,process description, and full performance report.



Activity Title: Characterization of new calibration diffuser typesDescription: With the implementation of on-board calibration diffusers in space instruments

(MERIS, GOME2, Sciamachy) the list of newly available calibration standards isexpanding very fast (Spectralon, Fluorion, QVD). However, thorough andlong-term characterisation of their properties is hardly available and needs to beestablished. On-board calibration of radiometric measurements in remote sensinginstruments is often achieved by observation of a sun-illuminated reflectance ortransmittance secondary standard using prior calibrated reflecting or transmittingdiffusers. Furthermore, reflectance standards are also used in combination withcalibrated light sources to perform on-ground calibration to provide the so-calledkey-data. For both calibration procedures, accurate characterization of theBi-directional Scattering Distribution Function (BSDF) of the diffuser is needed. Inthis activity new diffuser types and materials shall be tested for their suitability assecondary calibration standard in space instruments. This shall include themeasurement of their BSDF at different wavelengths, tests on their susceptibilityto the spectral features phenomenon and degradation effects. Degradation shallbe quantified by means of BSDF measurements after exposure to UV radiation,contamination, thermal cycling and air-vacuum transition. A trade-off shall bemade to identify the most suitable diffuser type for calibration purposes.

Deliverables: Database containing list of new diffuser types and test/measurement results,diffuser trade-off.


Activity Title: Next generation solar-blind UV Lidar DetectorDescription: All Lidars are required to operate in an eye-safe spectral region. One solution

consists in the operation at UV wavelengths offering the advantage over alsopossible IR wavelengths of being "cleaner" of the Earth's albedo as wellbackground emission. However, to fully exploit this advantage, the detector mustbe "solar blind", i.e., inherently insensitive to visible and longer wavelengths.Wide-bandgap semiconductors are the primary choice as the photosensitivematerial for high-energy (i.e. short wavelengths beyond the visible: in the (EUV)photon detection. Thanks to a recent and on-going intense development effort, theGaN material is becoming mature enough to foresee an industrialization oftransistors by 2005. By its nature, GaN is insensitive to visible light, has a muchlower thermally induced dark current component, and is a direct-bandgapsemiconductor (as opposed to SiC). Furthermore, heavy ion radiation tests haveproven its virtual immunity to several Mrad level (limited by the source). Theactivity shall focus on the optimization of the Nitride material for detection, theoptimum detector structure (APD or PIN or even a PMT with a (Al)GaNphoto-cathode) manufacture and characterize a laboratory demonstrator of the(one or several) chosen structure(s).

Deliverables: Assessment of the most appropriate detector technology (APD, PM, etc); fullycharacterized laboratory model of a mono-pixel detector (or a small-format array)with requirements tailored for lidar applications.

Optical Instruments



Activity Title: Hollow Waveguide Space Instrumentation ApplicationsDescription: A new Hollow Wave Guide (HWG) technology has been patented, which provides

a low loss waveguide (<0.1dB/cm) formed by micromachining (based on deep dryetching of silicon-based substrates). The hollow nature of the guides means thatthey are capable of handling significantly higher power densities than conventionalsolid-core waveguides. Moreover, as the core is hollow, it is capable of operatingacross a broad band of wavelengths and has reduced losses to free space, asthere is no optical interface. This technology potentially allows low cost, rapiddevelopment and manufacture of optical functions integrated in a HWG platform.It allows simple integration of discrete components via co-aligned slots givingeased alignment tolerances as well as combining additional monolithic MMI and/orMEMS functions within an optical circuit. The miniaturised technology will reducesize and mass of systems allowing smaller instruments to provide resultscomparable with conventional, macro technologies and use in a broader range ofscenarios.This study will assess the feasibility of using this technology for space basedinstruments and two applications will be considered. First the HWG will beassessed as the basis of a compact lidar system. An optical circuit for a lidaroperating at 10 microns, based on using HWGs in a ceramic substrate to guideradiation between components, has already been demonstrated with coherentdetection efficiencies in excess of 90% of the theoretical maximum. Alternative IRwavelengths and components, as well as the application of siliconmicromachining, will be investigated as a means to reduce the size and weight ofthe lidar circuit significantly compared to conventional systems. A proof ofconcept HWG version of the lidar will be built and tested. The advantages andrestrictions of using the technology in space will be traded off against conventionaltechnologies and the application to lidar detection of CO2, ozone, H2O and otherspecies of interest will be assessed.Secondly HWGs will be investigated as the basis of a novel-sensing element forhyperspectral imaging based on Multi Mode Interference (MMI) re-imagingphenomena to split the image into its constituent wavelengths for spectralanalysis. A proof of concept HWG sensor will be built and tested. The advantagesand restrictions of using the technology in space will be traded off againstconventional technologies, including the mode of operation (2-D scan, line scan orstaring).

Deliverables: Design, build and test of a hollow waveguide lidar. Trade off of hollow waveguidelidar against conventional technologies with assessment for application toatmospheric sounding.

Justification for DN: The new hollow waveguide technology provides a low loss waveguideformed by surface micromachining (based on deep dry etching of siliconbased substrates). The proposed activity is based on this new technologyand will aim at assessing the feasibility of using it as the basis of a novelsensing element. As the basis technology to be used, the new hollowwaveguide, has been patented by Qinetiq Ltd (patent numbers: US5410625, 5379354, 5396570, 5428698, 5475776, 5917596) it isrecommended to award the contract to this company.

Non-competitive tendering is justified according to Article 6.1.d of theContracts Regulations.



Activity Title: Imaging spectral signature instrumentDescription: Hyperspectral pushbroom instruments on Earth observation satellites are able to

detect dedicated ground information by its spectral signature and to classify thecontent of the measured ground pixel. An elaborate ground processing of themeasured hyperspectral data cube usually performs this task. The proposedinstrument concept allows the optical on-board processing of the hyperspectraldata cube, identifying the ground pixels with a specific spectral signature andsaving thus time and cost for ground processing. The objective of this activity is tostudy the new instrument concept, which allows the on-board identification ofdedicated spectral signatures within the field of view of a pushbroom imager, todemonstrate its feasibility and to perform the proof of concept by breadboarding.The breadboard shall be self-contained and will consist consecutively out of animaging lens, a first spectrometer, an addressable spatial light modulator and asecond inverted spectrometer. The imaging lens images an object line on theentrance slit of a first spectrometer. This object line is sub-divided in spatial pixels,which will be dispersed by the first spectrometer into their spectral content andimaged on the spatial light modulator. This spatial light modulator can beaddressed with the spectral signature of the searched specific feature. A secondinverted spectrometer re-images the by the first spectrometer dispersed and bythe spatial light modulator transmitted flux into a line of pixels. In the cases inwhich the spectral content of the pixel is equal to the searched signature, itstransmission is maximum and can be therefore be identified in the final image by athreshold discrimination.

Deliverables: Functional self-contained Breadboard integrated and tested



Activity Title: New Radiometer for Optical CalibrationDescription: The ultimate objective of this activity is to increase the accuracy of radiometric

calibrations of optical space instruments. For (absolute) radiometric calibration ofoptical instruments, calibration standards are used. The output of these sourceshas a relatively large uncertainty (few percent). Furthermore these sources areunstable, resulting in a limited lifetime of the validity of their calibration. The initialradiometric calibration of the optical space instrument is, therefore, beforehand ofpoor quality. Improvement (to sub-percent level) of this calibration accuracy callsfor improvement of the initial calibration of these standards as well as an improvedand more frequent monitoring of the output during calibration of the instrument.In the scope of this activity, a portable system will be developed to perform on siteradiometric calibration and monitoring of radiance and irradiance sources. Thecalibration will be directly traceable to optical standards. Using this system it willbe possible to do cross checks between different institutes and instruments, inorder to improve consistency between the calibrations. Furthermore, models willbe developed to analyse the spectral properties of the calibration sources as wellas methods to correct for ageing. To validate and model the measured data, theradiometer system will be characterised in combination with commonly usedcalibration sources and measurement configurations. Finally an analysis will bemade of the improvement in terms of user data uncertainty.

Deliverables: 1) Design of the Radiometer system for measurement of radiance sources.2) Absolute calibration of the Radiometer system.3) Stability and reproducibility tests of the Radiometer system.4) Characterisation of the Radiometer system with FEL lamps (NIST standard).5) Analysis of the total error budget of the calibration sources.6) Aging tests of FEL lamps and diffusers with the Radiometer system.


Activity Title: Advanced low temperature radiators for LEODescription: Hyperspectral detectors in the short wave infrared (SWIR) require an operating

temperature of around 170K. Passive radiators, even in low earth orbits, canobtain this temperature. But these radiators are quite voluminous and theiraccommodation, specifically on small spacecrafts is difficult or not possible (e.g.Spectra). A potential way to reduce the volume of such radiators is to combinethem with Peltier cooler to increase the operating temperature of the radiator. Amajor design driver for this solution is the low performance of classical Peltierelements in the temperature range 170K - 220K. Recent developments in Peltiercoolers showed major improvements in the performance, by e.g. new materials(CsBi4Te6) with a better performance at 170K-250K or low dimensionalstructures. The expected gain is between 40%-100% in power consumption andheat to be rejected, which would be sufficient to use passive radiators instead ofactive cooling systems (e.g. Spectra) The objective of this study is to develop acompact low temperature radiator in combination with an advanced Peltierelement to cool down passively hyperspectral detectors (below -100 deg. C) inLEO for Earth observation. In the frame of this activity concepts shall beestablished for compact low temperature radiators and the performance of thePeltier coolers shall be optimised at this low temperature by e.g. using newmaterials or manufacturing technologies. The performance of the cooler shall thenbe verified by breadboard tests and the implementation of this technology in futureapplications shall be discussed.

Deliverables: Fully tested breadboard models, development and implementation plan



Activity Title: Improved UV Grating Technology (IUVGT)Description: Recent experience with UV gratings procured for the GOME-2 instrument

(METOP) has shown that there are still problems with the coating stability andtherefore performance of these critical components. This proposal addresses theissue by the development, test and qualification of a production process forhigh-line-density UV gratings with thin (nm level) reflective coatings. The goal is toensure that the entire process is understood, from design and modeling through toproduction and performance testing of the gratings (under representativeconditions and over the long term). All failure and degradation modes shall be fullyexplored, understood and mitigated against. Critical is that an ensured coatingstability be achieved such that component gratings shall survive longprocurement, AIV, calibration and storage cycles without degradation of (on-orbit)performance.

Deliverables: Detailed data-pack and grating samples demonstrating the compliance of the newprocess and the performance of the gratings.


Activity Title: High-efficiency Raman DIAL sourceDescription: Two major difficulties / challenges for space-borne differential absorption lidars

(DIALs) can be identified: 1) The generation of the wavelengths appropriate forthe species to be measured. 2) Generally a very poor wall-plug efficiency (on theorder of ~1%), which is increasingly problematic as the absolute power increases.The Raman laser is potentially an excellent candidate to generate the necessarywavelengths via the Raman shift and promises an increased efficiency. However,most often, a direct Raman-shift (especially Anti-Stokes) is very inefficient anddoes not provide a solution. While a direct Raman conversion is not considered asolution for DIALs, a proprietary scheme (RAMSES) developed by Passat Ltd. isvery promising and showed extremely encouraging results in the laboratory interms of wall-plug efficiency. Nevertheless, considerable challenges needaddressing (such as the required very high quality of the output beams) which isthe subject of this activity, together with the generation of 4 (quasi-) simultaneouspulses at the appropriate wavelengths (e.g. water vapour, or CO2 once the bestones for the carbon cycle will be established).

Deliverables: A fully characterized, diode-pumped, laboratory demonstrator of an efficientRAMAN laser source emitting at least two simultaneous wavelengths.

Justification for DN: As a result of the ESA contract number 16375 “Design, development andtest of a dual laser transmitter” (600 K€ funded by EOPP - EarthObservation Preparatory Programme), a trade-off between 3 technologieswas performed which included some level of experimental validation. Avariation of the Raman scheme developed by one of the sub-contractors,Passat Ltd., proved to be very promising, in particular wrt wall-plugefficiency. However, it was considered as industrially too risky by the primeto select the bread-boarding activity within that contract. This activity isnow warranted due to the fact that this alternate technical scheme, whichconstitutes intellectual property of Passat Ltd., circumvents thedisadvantages of the "classical" Raman scheme, and the potentiallydouble (or more) wall-plug efficiency translates to ~kW power savings inan operational DIAL system.

Non-competitive tendering is justified according to Articles 6.1.a) and d) ofthe Contracts Regulations.



Activity Title: Hermetically sealed laser pump diodeDescription: During the activity Core Laser Technologies, the cause for the very limited lifetime

of laser pump diodes in vacuum has most probably been found and a solutionformulated. The issue of lifetime is extremely serious and concerns the one mostcritical element (the pump diodes) in any space-borne laser system. The lifetimerequirements of pump diodes in each of the increasing number of ESA missionscarrying a diode-pumped laser will not be met unless an appropriately packagedpump diode is developed. The development of such a package is far from trivial:in addition to the thermo-mechanical properties of the package, the opticalproperties and reliability of the window are very critical and challenging, as is thehermeticity in the space environment. This activity aims to develop such apackage for single emitters, as well as addressing the critical areas for high-powerdiode stacks.

Deliverables: Hermetically sealed single-emitter pump diode (for NdYAG systems); detailedassessment & roadmap for solving the lifetime problem also for high-powerpump-diode stacks; and tests & results verifying the achievement of lifetimerequirements for most ESA laser-carrying missions.

Justification for DN: The present activity is a direct follow-on on the TRP contract number15129, “Core Laser Technology Development” (660K€ with ContravesSpace AG). The lifetime problem to be addressed in the present activityhas been discovered, analyzed and a solution formulated in the CLTcontract. The knowledge and infrastructure is readily available atContraves and can be used in the most efficient manner to address theurgent lifetime issue.




Activity Title: Development of a 4-Mirror Anastigmat with a large Field of ViewDescription: The objective of this activity is to cover the additional tasks to be carried out in the

development of an elegant breadboard of a 4-mirror anastigmatic telescope withrespect to the originally foreseen development of a 3-mirror anastigmatictelescope in the GSTP-3 activity currently running with AMOS (B).

In the current development of a three-mirror anastigmatic telescope with largefield of view it was found that the required optical performance can not beachieved with a three mirror solution. The activity shall cover all additionaldevelopments for the manufacturing of a four-mirror anastigmatic telescope ratherthan a three-mirror telescope. In particular, the activity shall cover the grinding andpolishing of an additional medium sized convex off-axis aspheric mirror and thedevelopment of a test set-up for a convex off-axis aspheric mirror requiring asophisticated stitching technique. Furthermore, the mass increase associated withthe introduction of an additional mirror requires a higher degree of lightweightingfor each of the individual mirrors. In order to prove this possibility it is proposed tomanufacture one of the telescope mirrors in SiC since this material has currentlythe best lightweighting possibilities without loss in optical performance. Finally, asuitable alignment algorithm shall be developed and applied in the alignment ofthe four mirror telescope.

The following tasks are foreseen:

1. Manufacturing of fourth mirror2. Development and manufacturing of test set-up for convex mirror using astitching technique3. Establishment of an alignment algorithm for a four mirror telescope

Deliverables: 1. Fourth mirror; 2. Stitching test bench; 3. Alignment algorithm; and associateddocumentation.

Justification for DN: AMOS S. A. (B) is currently executing the contract no. 18286/04/NL/PM,GSTP-3 activity "TMA telescope with large field of view" funded with 1M€.The proposed activity contains supplementary developments for anupgrade of the TMA to a 4 mirror telescope.




Activity Title: Steerable pencil beam X-band data downlink antennaDescription: Interference has been experienced when using X-band data down link antenna

because many users using wide coverage isoflux antennas share the samefrequency allocation. To avoid such interference, and increase gain, steerablepencil beam antennas need to be developed to provide spatial isolation. This willalso allow the use of the full X-band frequency allocation leading to a higher (350Mb/s) data rate and even more with other modulation schemes like 8PSK. Usingthis approach allow high cost saving thanks to the use of existing X-band groundsegment even for high data rate transmission. This activity deals with thedevelopment of X-Band steerable pencil beam antennas at X-band. It will coverantenna design and provide the main requirements for all the subsystems likeradiating panels, rotary joints and mechanisms. All critical subsystems will bedeveloped and tested except mechanisms that will be treated separately in adedicated activity.

Deliverables: Breadboard antenna RF demonstrator excluding mechanisms. Full antennasubsystems requirements.


Activity Title: ADIBEAM: Adaptive digital beamforming techniques for GNSS receiversDescription: The precision provided by current generation GNSS receivers together with the

use of sophisticated processing methods leaves multipath and interference as thedominant remaining error sources affecting GNSS performance. Moreover, theexperience gained in the use of adaptive antenna arrays in terrestrialcommunications can be incorporated in space-borne GNSS receivers aimed atmissions with very demanding accuracy requirements. The objective of thisactivity is to implement and test algorithms for adaptive digital beamforming in aGNSS receiver. Beamforming algorithms used up to now for antenna combinationare relatively simple. It is possible to apply more sophisticated algorithms, whichcombine in an optimal way the signal coming from different antennas. Given theincreased complexity of the hardware when several antennas are used, it is worthinvestigating new software algorithms that take full advantage of the hardwareavailable. The focus of this activity is on baseband signal processing algorithmsfor the combination / selection / estimation of the signals and parameters from thedifferent antennas. The goal is to arrive at techniques that may be consideredintelligent in the sense that use most of the information available in the receiverand to adapt the antenna array to the scenario.

Deliverables: Algorithms selection and design document; performance analysis and test resultsdocument; and ADIBEAM source and executable code.

Platforms/ Other Instruments



Activity Title: Low Temperature/Cryogenic CPLDescription: More and more instruments (Earth observation and Science) are using low

temperature/cryogenic sensors. Most of the current instrument designs are basedon concepts where the to be cooled sensor has to be located very close to thecryocooler or radiator to avoid too large temperature drops from source to sink.This implies very strong constraints on the instrument design and also S/C layout.Furthermore, there are applications where – even when reduced to a minimum –the remaining micro-vibrations of a cryocooler might affect the sensor. Atwo-phase loop will allow to physically decouple the sensor from the coolingsource, thereby simplifying to a large extent the instrument design and even thespacecraft lay-out, while at the same time, due to the very small temperature dropbetween source and sink, provide a very efficient thermal lay-out. As suchtwo-phase loops are typically made of thin tubings, an effective mechanicaldecoupling can also be realized between a cryocooler and a sensor. Furthermore,capillary pumped two-phase loops (CPL) will allow a temperature control of thee.g. sensor largely independent of the heat load to be removed. This activity aimsat developing low temperature/cryogenic two-phase loops to provide high efficientand flexible thermal tools to connect low temperature/cryogenic sensors with e.g.remotely located passive radiators and/or cryocoolers for an intended temperaturerange of 50 to 80 K.

Deliverables: Fully tested and functional breadboard model of a cryogenic CPL, includingdocumentation.

Ref. Number: G103-07EC Budget: 900 K€

Activity Title: Micro Star Tracker and Baffle Technology DevelopmentDescription: The contract shall examine designs for low performance, micro autonomous star

trackers and assess the feasibility and performance of the designs. The targetdesign is an extremely compact star tracker optical head with the option totransform the optical head into a stand alone ASTR by the addition of a singlePCB. The target applications are advanced future small, micro and nano-satellitesand s/c requiring distributed sensing. Each of the key aspects of the designconcepts will be demonstrated using dedicated breadboards and test samples. Inparticular, improvements in the following areas will be examined in detail: detector(particularly the LCMS APS detector currently being developed); optical system(including the use of a 3 lens only system and the possibility of plastic lenses);baffle design and construction (including new materials, paints and coatings, e.g.Deep Sky Black); mechanical system (including different materials and singlepiece construction); electrical system (including ‘single chip’ OH solution, ‘singlechip’ autonomy functionality via next generation FPGAs with embedded RAM andprocessing, miniature connectors, wireless data communication).

Deliverables: Final report and breadboard demonstration of key technologies.


Ref. Number: G103-08ES Budget: 500 K€

Activity Title: Optimised CMG-based AOCS for Mini-SatellitesDescription: For mini-satellites, on one hand, the present CMG-based AOCS is oversized in

terms of mass, power and volume budgets, cost and agile capacity (10-40 deg/s),and limited with regard to autonomy capabilities. On the other hand, the currentdevelopment have highlighted the lack of a standard methodology or framework tosimulate during the initial design phase the complete on-board SW simplifiedfunctionalities including not only AOCS control laws but also asynchronous taskssuch as guidance profile generation. The aim of the proposed activity is threefold:(i) to review and adapt in the most efficient and cost effective manner CMG-basedAOCS for mini-satellite platforms; (ii) to demonstrate the benefits and feasibility ofan autonomous agile platform operation and derive the corresponding verificationactivities for functions traditionally performed on ground; (iii) to define a frameworkfor SW prototyping of all the functions of the software with the aim to be able toeasily implement it on a representative target computer and validate the flightsoftware architecture concept.

Deliverables: Autonomous CMG-based AOCS software prototype; Documentation regardingmini-satellite mission needs, CMG sizing, CMG-based AOCS architecturedefinition and performance verification activities of the AOCS.


Activity Title: 8PSK High rate design ( Bread board )Description: The 375 MHz X-band frequency allocation is shared by more than one hundred

spacecraft, some of them with bandwidth occupancies as high as 350 MHz.Interference cases have been reported and their number will increase in thefuture. In order to mitigate the problem, the frequency authorities are consideringrestricting the band occupancy at X-band or imposing narrow beam requirementsand ban broadcasting for high rates. A number of Earth observation missionscurrently use X band for their high data rate downlink, using QPSK modulatione.g. Cryosat, Envisat. The 8PSK TCM modulation scheme has now beenstandardised by CCSDS and ECSS. CNES have already made use of thismodulation scheme and it will be flown on the DEMETER and PLEIADESmissions but only using a medium data rate of less than 200 Mbps. There is arequirement to be able to transmit TM data up to a rate of 600 Mbps, using the Xband frequency allocation. European Earth Observation satellites will require thishigh data rate TM downlink capability in the near future. This activity will providean architectural design and elegant breadboard of a high rate X band 8PSKtransmitter, which fulfils these future requirements. This breadboard shall be of amodular design, suitable for a variety of missions and shall be able to modulateTM data using 8PSK with rates up to 600 Mbps. The design shall ensure theoutput transmit spectrum conforms to ECSS standards and does not exceed theallocated frequency bandwidth at X band. System trade offs will be required tooptimise the 8PSK transmitter design and assess system issues including phasenoise and linearity, thus reducing spectral re-growth. The transmitter shall beimplemented using state of the art technology to obtain a compact, power efficientTX module.

Deliverables: A Breadboard of a high data rate transmitter will be developed. This will be of amodular design for data rate adaptability. This transmitter shall include all thenecessary data interfaces, modulator, baseband / analogue filtering, lineartransmit output stage etc? based on a stringent design specification. Thisbreadboard development is considered as a high priority for future Earthobservation and Earth exploration missions



Activity Title: Adaptation of industrial motor technologies for space applications.Description: The scope of the activity is to offer end users space suitable and/or space

qualified electrical motors based on COTS that proved their performances alreadyin industrial applications and are proposed to be upgraded to space standards.Current practices often yield questionable and costly results due to the lack ofspecific knowledge (e.g. space tribology, suitable materials, lifetime requirements,etc.). Such activities also represent a major, project-specific non-recurring costelement which is a barrier to use COTS technology. A hardware orienteddemonstration of the proposed motor upgrade initiative shall be performed and astatistically relevant number of motors of each type (brushed, brushless, stepper,piezo) shall be selected, screened, upgraded, inspected, tested in the frame of atest campaign defined on solid and unanimously accepted basis, with clear testobjectives and pass/fail criteria such as to establish a clear and unambiguousprocedure to upgrade COTS equipment to space standards, with full traceability,and confirmed performances.

Deliverables: Technical notes; breadboards, tested and inspected qualified items of hardware;relevant MGSE and EGSE (incl. software).


Activity Title: Earth Exploration satellite ( EES ) Transmitter at Ka bandDescription: With the increasing data download requirements of Earth Exploration Satellites

(EES), increased bandwidth is required and the use of Ka band becomes anecessity. Ka band technology is required to support high to very high TM datalinks. Ka band also allows the use of smaller diameter HGA onboard thespacecraft compared with similar communication performance at X band. Thisresults in a lower spacecraft launch mass and a ground infrastructure usingsmaller parabolic antenna ground stations. This Ka TX module is part of theroadmap presented in the technical dossier on transponders for TTC and is anintegral part of the TTC harmonization process. Basic RF technology exists in thisfrequency band due to previous developments on ENVISAT, but thesedevelopments were restricted to low data rate requirements. This Engineeringmodel (EM) shall be of a modular design, suitable for a variety of missions andshall be able to modulate TM data rates in excess of 1 Gbps. A suitable systemarchitecture for a high date rate Ka band TM transmitter, shall then beimplemented using state of the art technology to obtain a compact, power efficientTX module.

Deliverables: An Engineering Model (EM) of a high data rate transmitter will be developed. Thiswill be of a modular design thus providing data rate adaptability.



Activity Title: Non explosive Hold-down Release ActuatorDescription: This activity aims to identify a Non Explosive hold-down Release Actuator (NERA)

concept, to design and to manufacture a NERA model, functionally flightrepresentative, and to perform a complete qualification test campaign including itsexhaustive characterization. The need of a NERA product capable of performingthe release of a spacecraft appendage hold-down point without inducing a highshock has been identified. This product will decrease the cost of systems in whichthis type of devices is required.

Deliverables: Breadboards; tested and inspected qualified items of hardware; relevant MGSEand EGSE (incl. software)



Activity Title: Highly integrated full-custom autocorrelation spectrometer ASICDescription: Autocorrelation Spectrometers have been demonstrated in ESA and non-ESA

development contracts as being a very competitive alternative (in terms ofperformance to power, cost and mass ratio) compared to other spectrometertechniques, if designed as full-custom ASIC. The proposed activity, by furtherintegration in a state-of-the-art ASIC technology, is destined to ensure theavailability of Autocorrelation Spectrometers chips, improve their overallperformance and reliability, establish a qualification plan and to meet therequirements of future EOP and SCI projects. A chipset for a 128 to 1024 channelautocorrelation spectrometer (ACS) has been successfully developed in contract11211. A further integration of ADC and the digital correlators into an advancedCMOS technology eliminates the need of high-speed data/clock lines between twochips and therefore reduces complexity (a increased reliability) and powerconsumption. The proposed activity comprises the following tasks:-Integration ofADC and correlators on a single chip in advanced technology.-Inclusion ofadvanced readout features and correlation data pre-processing.-Selection of atarget application/mission, specification to be established considering therequirements of this application and general inputs from EOP and SCI projects.-Select appropriate chip technology.-Design and produce prototypes of thechips.-Build a prototype in cooperation with the target application. Prepare forqualification of the design. The prototype hardware shall be made such that aflight worthy spectrometer can be built, either by using components where spacequalified components exist, and/or by establishing a qualification plan.

Deliverables: ASICs, Spectrometer PrototypeDesign and Test ReportsReadout/post-processingsoftwareQualification Plan

Justification for DN: The proposed activity aims at ensuring the availability of autocorrelationspectrometers chips, improving their overall performance and reliability byfurther integration in a state-of-the-art ASIC technology. It can beconsidered as a continuation of the work performed by Omnisys underESA contract 11211 (“Digital Autocorrelation Spectrometer”, 1.5 M€,funded by EOEPP Extension, GSTP2, TRP, and EOEPP Extension 2). Onthose previous developments, Omnisys has demonstrated its uniquecompetence in full-custom designed autocorrelators, which ensures a highperformance vs. power and mass ratio, compared to competingtechnologies and semicustom correlator designs. Omnisys has,furthermore, a well known system know how, providing the appropriatedata processing for autocorrelation spectrometers with coarsequantisation. Thus, it is suggested to carry out the proposed continuationwith the same company.



Ref. Number: G103-36ED Budget: 600 K€

Activity Title: Scalable Payload Computer (SPC)Description: The main goal of this activity is the development of a scalable payload computer

(based on the newest generation of European processors for space) for a widerange of applications such as Instrument Control Unit (ICU) and/or payload dataprocessor.

It is the advent of the availability of a new generation of ESA developedprocessors and digital components for space (Leon2-RT, SpaceWire Router,SMCS332 SpW). Based on these components it is now possible to develop a newgeneration of payload computers replacing the previous generation that is basedon a processor that will soon become obsolete. The reference application for thisdevelopment is the Next Generation of Core Radar Electronic (NG-CRESS) whichis currently developed under ESA contract by EADS Astrium Ltd. There theScalable Payload Computer will perform a function as ICU and is intended toreplace a non European payload computer (MASS 486 by Maxwell).

Hence for this activity a Scalable Payload Computer (SPC) shall be developedwhich will be based on the newest generation of European processors for space,the Leon2-RT. The single board computer shall be usable to host the software tocontrol several simple or one complex instrument such as an advanced radar.There the Scalable Payload Computer shall provide the interface to the platformon the one side and on the other side command and control a number of modulesin the Radar Electronic and to the Front-end. For this it will have to provide anumber of interfaces such as SpaceWire, CAN Bus and MIL-STD-1553 bus.

The SPC shall be expandable with additional interfaces and co-processingfunctions by means of an expansion board which can be connected to the SPCvia a compact PCI interface. The SPC has to include a processing capability in theform of a single microprocessor and volatile memory, either rad-hard orEDAC-protected. To this end the activity shall cover the following tasks:

1.- Requirements Consolidation2.- Architectural Design3.- Detailed Design4.- Manufacturing3.- Test and Validation

Deliverables: Scalable Payload Computer prototypes plus test equipment.



Activity Title: GPS Precise Orbit Determination (POD) instrument EQM developmentDescription: The objective of this activity is to develop a GPS EQM POD (Precise Orbit

Determination) instrument for all Earth observation missions in low Earth orbitrequiring accurate geolocalisation. The key performance of this instrument will bethe low mass and low power consumption. The development is based on the GPSElegant Breadboard being developed for telecom missions under ARTESProgramme.

The proposed activity is based on the Elegant Breadboard of the navigationreceiver as developed in frame of the Innovative GPS Space Receiver activity fortelecom missions and comprises the completion and extension activities to arriveat an EQM of a complete POD instrument.

The performance requirements on data products of a POD instrument are ofcourse more stringent than the ones for a pure navigation receiver, therefore theperformance driving aspects need special attention. The main impact on theperformance of a POD receiver stems from the antenna (multipath, gain pattern)and the RF-front-end. Thus, the antenna has to be adapted to the specific needsand the RF-front-end cannot be reused directly from the GPS navigation receiver,but has to be redesigned. In addition, codeless tracking of the GPS P(Y) ismandatory for a POD receiver, since only dual-frequency signal processing is ableto support the POD accuracy requirements and the number of available civil L2signals-in-space is still too limited for such a purpose.

The following tasks are foreseen:

1) System level: System engineering, Performance and Verification aspects dueto POD functionality.2) Hardware level: Antenna Implementation for POD applications, Redesign of theRF front-end, Design and mechanical & thermal analysis of complete box3) Software level: Implementation of codeless tracking (Y-code), Improvement ofstart-up mode and I/F command handling,4) Equiment manufacturing and testing (including environmental tests)5) Software development and verification.

Deliverables: GPS POD Instrument EQM; documentation.

Justification for DN: The proposed development of a GPS POD instrument is based on theInnovative GPS space receiver being developed by Austrian Aerospace inthe frame of the ESA ARTES-5 contract no.: 16353/02/NL/US. Combiningthis innovative development with the experience and heritage within theSaab Ericsson Space group in GPS based meteorological instruments(GRAS instrument on METOP, GPSOS instrument for the US NPOESSsystem) generates an unique consortium to develop this very compact andperformant ‘Precise Orbit Determination’ (POD) GPS receiver. It is thenrecommended to award this contract to the consortium composed ofAustrian Aerospace (A) and Saab Ericsson Space (S).



Ref. Number: G103-37MP Budget: 400 K€

Activity Title: Design, Development and Test of a Mini Ion Engine SystemDescription: The fundamental advantages of electric propulsion have already been

successfully applied to a variety of applications including TelecommunicationSatellites (ARTEMIS/ALPHABUS), Earth Observation (GOCE) and ScienceSpacecraft (SMART-1/BepiColombo). Concerns about global warming and climatechange have resulted in a growing requirement to measure the Earth’s upperatmosphere on a regular basis. The instruments for such missions, DIAL Lidarsand cloud measuring radar, function most effectively at low altitudes. To achievestable positioning of a Spacecraft at these altitudes, low thrust electric propulsionis required to compensate for the atmospheric drag effect. Another emergingmarket need is the exploitation of large distributed aperture instruments throughprecision formation flying. This is particularly important at low altitudes where therobust ion engine design and inert xenon propellant are little affected byenvironmental and atmospheric effects such as atomic oxygen. In order torespond to the specific propulsion and control needs of these missions,downscaling of existing thruster technology is required.

A miniaturised thruster will be designed using scaling relationships to demonstrateperformance of the new system. Identification and trade-off of potentialMiniaturised Electric Propulsion System (MEPS) capabilities will be performedwith reference to existing ESA Earth Observation (EO) missions that may use thistechnology (such as Earthcare) and the mission requirements of futureinterplanetary small spacecraft applications. Establishing of power converter andcontrol requirements shall be made taking account of system/performancetrade-offs and considering a variety of mission scenarios. A breadboard systemdesign will be defined to encompass required performance over a range ofapplications, taking account of system/performance trade-offs. A breadboardsystem shall be manufactured comprising of a prototype miniaturised thruster, anexisting power supply and control equipment, prototype xenon propellant systemand existing electric propulsion test facilities. Based on breabboard systemcharacterisation an updated system design for a proto-flight system shall beundertaken.

Deliverables: System design; Breadboard design and requirements; Breadboard system testreport; System design definition documents

Justification for DN: The measure C1 is in line with the conclusions of the harmonisation ofelectrical propulsion technologies (2004 - 2005)

The electrical propulsion subsystem allow for specification ofperformances and interfaces as independent building block of thespacecraft. The scale factor derived from the freedom of making thetechnology available to a large number of clients (LSI) and the fact thatonly few players are viable in this domain would recommend toconcentrate the public research funds for electrical propulsion inspecialised equipment suppliers. There are noticeable industrialrationalisation movements among the existing equipment suppliersproviding electrical propulsion. It seems reasonable that the publicinvestment supports these movements.


Ref. Number: G103-38ED Budget: 1,000 K€

Activity Title: CCSDS IMAGE Compression ASICDescription: The CCSDS 122.0-B-1 standard defines a particular payload image data

compression algorithm that has widespread applicability to many types ofinstruments. The compression technique described in the CCSDS standard canbe used to produce both lossy and lossless compression. The presentRecommended Standard differs from the JPEG2000 standard in several aspects:a) specifically targets use aboard spacecraft;b) a careful trade-off has been performed between compression performance andcomplexity;c) less complex, it can be fully implemented in either hardware or software;

The objective of this activity is to develop a radiation hardened ASIC thatimplements the CCSDS 122.0-B-1 standard for Image Data Compression. Thecompressor described in the standard consists of two functional parts, a DiscreteWavelet Transform module that performs decorrelation, and a Bit-Plane Encoderwhich encodes the decorrelated data. Since the compressor consists of twomodules, the development of two separate ASICs could be considered and atrade-off analysis shall be performed. The device interface shall be generic, inorder to be easily adapted to any future mission in Earth Observation, although aparticular attention shall be given to the SENTINEL-2 requirements, since thismission could be the first candidate to use the ASIC if it is available in due time. Abreadboard shall be developed as well in order to test and validate the device.

This activity is a reorientation and replacement for the GSTP3 activity "DataCompression ASIC" (G00/B38.ETD-045).

Deliverables: 20 ASIC Compressors plus prototypes and test equipment.

Justification for DN: The capabilities needed to implement in ASIC an image compressionstandard are quite widespread, but considering the integration of the ASICin future space instruments, the collaboration and supervision of LSI canbe an important asset.


Theme 2.- SCIENCE / ROBOTIC EXPLORATION

Ref. Number: G212-03EP Budget: 400 K€

Activity Title: Miniaturisation of very low power HV supply for microthrustersDescription: In the last few years the Field Effect Electrical Propulsion (FEEP) has been

optimized as the only technology able to meet stringent requirements in terms ofaccuracy, resolution and low noise. Such requirements are essential for missionwhere drag compensation, formation flight and accurate maneuvers are required.At the moment the FEEP micro-propulsion is the selected technology for theGOCE mission (drag compensation), it is the strongest candidate for SMART-2mission (formation flight in the frame of the LISA technology packagedemonstrator) and is the selected technology for the CNES MICROSCOPEmission. A further step in high voltage integration technology is needed to furtherreduce the size of the Power Conditioning Unit (PCU) for future programmesusing very low thrust and to have a PCU size in line with the size of the satellite(e.g. microsatellite) and the rest of the electrical propulsion system. UnfortunatelyFEEP technology imposes stringent requirement to the associated power unit:high voltages (up to 12kV), high efficiency, fast reaction time, accuracy andresolution, which impose an internal optimized ion loop, and a compact design areamong the most important design drivers. It is proposed to develop an elegantbreadboard of a FEEP PS and to test is it with existing FEEP thrusters. The FEEPPS shall be made of the following main functions: emitter and accelerator powersupply, stabilization loop, emitter and accelerator electrical parameter telemetries,etc. Key requirements of the development are: compact design, high efficiencywith a “flat” characteristic w.r.t. thrust level, thrust accuracy and resolution(stabilization loop), fast reaction time.

Deliverables: Microthruster Power Supply Elegant Breadboard and design data package. EGSEand test reports.

Atomic Interferometer



Activity Title: Parametric study on the absolute linewidth limit attainable for asemiconductor narrow linewidth laser

Description: Diode pumped solid state lasers (DPSSL), diode pumped fiber lasers (DPFL) andsemiconductor lasers (SCL) are competing in many space applications wherenarrow linewidth emission and frequency tunability are critical issues. Both DPSSLand DPFL reveal narrow linewidth for short averaging time but they lack forreliability and efficiency and they are sensitive to harsh environment. On the otherhand, SCL are well renowned for their reliability and efficiency and are much lesssensitive to environmental changes. They also are easy to tune over broadfrequency range. However their linewidth (degree of coherence) has to beimproved to be a good challenger to the first two types of lasers. The goal of thisactivity is to identify the limiting factors to spectral linewidth of these three kinds oflasers and to look at ways to improve on the SCL performances. The currentstate of the art in narrow band diode lasers has converged at the 1 Hz level (USA)and this represents a device in laboratory conditions. In Europe this performanceneeds to be verified and reproduced in the lab. Additionally a verification model(this activity) needs to reproduce the performance prediction of the bestdeveloped device/s. Nevertheless the theoretical lower limit is orders of magnitudelower than the value of 1Hz. In order to access the potential of Ultra long livedtransitions (optical), which have an ultra narrow linewidth, the development of anultra narrow linewidth source needs to be achieved to probe these atomic (neutraland ionic) transitions.

The objective of this activity is to provide a lower limit to the linewidth achievablefrom single frequency semiconductor diode lasers. It will include a theoreticalstudy (modelling study) to determine the absolute limits attainable for asemiconductor diode laser for implementation in a manufacturing/hardwaredemonstrator. The linewidth goals will be set at the <<sub Hz level in order tomeet the expected requirements for implementation in future Optical Atomic Clock(OAC) demonstrators. The modelling study shall identify all the limiting factors thatcould prevent the achievement of the required goals and propose novel means tocircumvent these barriers by design and novel technology implementation.

The following tasks are envisaged:

1.-Comparative survey on typical features of commercially available narrowlinewidth lasers.2.-Mathematical formalism of single frequency laser optical spectrum3.-Methods to improve the semiconductor laser linewidth4. Measurement methods of laser linewidth5.Performance evaluation in a specific application (TBD)

Deliverables: Technical notes and final documentation.

Justification for DN: Non-LSI have recognised experience and capabilities and there areexpectations of spin-in from domains where SME and R&D centres haverecognised expertises.



Activity Title: Combined Compact Raman Spectrometer & MicroscopeDescription: Develop a compact, fibre optic delivered, combined system for microscopic

Raman spectrometry and microscopic imaging for use on future planetarymissions operating in the range 100-4000cm-1. The sensor head shall allowsurface scanning compatible with the microscopic resolution for the Ramanspectrometry within the microscopic field of view. The head for the instrumentationwill be delivered via a surface penetrating mole, necessary due to oxidisation ofthe surface layers by solar UV radiation. The connecting tether will containfibre-optic cables to irradiate the target area and return microscope images andspectra to lander based analysis instrumentation. Calibration is envisaged via adiamond film deposit on the probe end, which would allow Raman spectra to becompared against constant reference peaks. The scanning microscope functionwill allow spectral versus spatial information to be obtained. The work will identifysuitable detectors, for instance InGaAs, which operates to 3.5 micron. Laserpump sources at wavelengths avoiding auto-fluorescence, and providing goodresolution, must be traded-off; wavelengths >850nm provide spectra frombio-molecules of interest, whereas lower wavelengths are more suited to metaloxides. Fibre optic cables need to be identified with viable transmission losses atthe required wavelengths. Environmental compatibility will be considered.Trade-off for inclusion of LIBS, desirable but considerably increasing mass andvolume of the instrument will be considered. Analytic computational techniquesfor the deconvolution of spectra need to be developed. The study will build andtest a laboratory breadboard device.

Deliverables: Trade-off of detectors, laser pumps sources, fibre optic cables. Design, build andtest of a Compact, Fibre Optic Delivered Raman Spectrometer/Microscopebreadboard. Environmental compatibility assessment. Assessment of analyticcomputational techniques for deconvolution of spectra. LIBS inclusion trade off.

AURORA



Activity Title: X/Ka-band High Gain Data Transmission AntennasDescription: Future planetary missions will move from the current S/X frequency bands to

X/Ka-bands for the data downlink antennas. Dual-frequency, 1.5-mdual-reflector-based antennas with dichroic sub-reflectors are normally used forthese applications. It is important to reduce their development time by havingoff-the-shelf designs that can be fine tuned for a specific mission. Although thereis a good background work in Europe on dichroics, there is an interest inimproving the dichroic performance in terms of frequency bandwidth by using newtechnologies for both capacitive and inductive concepts. The activity will becarried out in two phases:

The first phase will concentrate on trade-offs for antenna concepts that can beused for X- and Ka-band data transmission from science exploration probes. Dualreflector systems that use sub-reflectors with tailored dichroic phase reflection andtransmission functions, used together with the sub-reflector surface shaping, maybe used to optimize the overall antenna gain. The trade-offs of the overall antennaperformance shall also include the use of coaxial feed (handling both frequencybands).

The second phase will concentrate on manufacturing a demonstratorcorresponding to the antenna concept selected from the trade-offs performed inphase 1. The combined optimization of sub-reflector shape and tailored dichroicphase reflection and transmission functions will be done to optimize the overallantenna gain.

Deliverables: Phase 1: Antenna concept suitable for manufacturing and pre-qualificationPhase 2: Pre-qualified antenna


Activity Title: Rover Autonomy TestbedDescription: Robots autonomy is being improved by maturation of “high level” technologies like

vision control or decision processing techniques. A study “Mobile Robot ControlArchitecture” MORCA has been performed at ESA 10 years ago, anticipating suchimprovement in the autonomy of robots. Since then, major bricks of a rovermission have been developed like the autonomous navigation system of CNES.The aim of this activity is to refresh MORCA, and implement in this controllerframework, the latest software technologies in terms of autonomy and decisionmaking capabilities into a software testbed. The work will be focused to otherautonomy aspects than navigation, which is fully handled by the CNESapplication. The testbed shall be linked to this application. Then the Contractorshall demonstrate the maximum autonomy achievable for a planetary rovermission, typically based on AURORA programmes, with an ideal target of fullrobot autonomy.

Deliverables: S/W controller implementation based on MORCA and S/W autonomy modulesintegrated to the controller.



Activity Title: Planetary Robot Design, Generic Visualisation and Verification ToolDescription: The objective of this activity is to extend the robotics simulation package 3DRM

with planetary rover simulation functions, covering rover dynamic and optimizedion. In the context of the RESCUE project, it was developed a CAD environment,so called 3DRM, that allows optimizing the robot arms and their workingenvironment, the dynamic and control simulation, and the validation of typicalrobotic tasks such as pick and place an object. The s/w environment is based onthe new Java 3D technologies that provide a license-cost-free portable system,with good optimized ion environment. This activity shall extend the 3DRM tool tocover planetary exploration missions. The following aspects will be at leastcovered: the optimization of different kinds of mobile robots (e.g. rovers, spinestructure) as articulated mechanisms including their kinematics/dynamicscharacteristics; the possibility to specify, graphically, mobile robots navigationtasks and to validate their execution; the import of 3D elevation maps of theterrain; and the optimization of mobile manipulators, on the rover base or not, andthe specification/validation of the corresponding tasks.

Deliverables: Visualisation, dynamic and control simulation software package for robot androver systems, that can run on different h/w platform

Justification for DN: In the context of the RESCUE project (contract number 15922, 300 K€funded by GSTP), TRASYS developed a CAD environment, so called3DRM, for the modeling of robot arms, their dynamic and control, theirworking environment, and the validation of typical robot arm tasks. 3DRMshall be complemented with a module enabling to model and simulate arover system dynamic behavior on a planetary like terrain.

Non-competitive tendering is justified according to Articles 6.1.c) of theContracts Regulations.


Ref. Number: G213-14GM Budget: 500 K€

Activity Title: Laser Anemometer and Martian Dust AnalyserDescription: The goal of this activity is to develop, manufacture and test an Engineering Model

(EM) for a wind measurement experiment on a Mars mission.

Wind measurement on the surface of Mars is of great interest to the scientificcommunity, particularly given what can be learnt about dust transport anddeposition. Such investigation will not only give an insight into the environmentand meteorology of Mars, but also help in the design and development of otherinstruments and systems for use on Mars. Past work on a Laser Anemometer andDust Analyser (LAMDA) has already led to the development of a breadboard ofthe sensor. As this instrument has been included as part of the MEDUSA(ExoMars-Pasteur Dust Analyzer ) science payload package for launch on boardthe ExoMars mission in 2011, it is necessary to continue the development of thisinstrument to an Engineering Model for further system level testing and to identifythe relevant interfaces to other elements of the payload package, and to theExoMars system as a whole. The EM design and development shall be done inclose coordination with the on-going development of MEDUSA, in particular forwhat concerns possible mechanical, electrical and data interfaces between the 2instruments and the management of the relevant mission operations(measurement startegy/timelines, data sharing, etc.).

The EM to be developed in this activity shall be a self-contained unit in whatconcerns power and signals. The EM shall be comparable in form, fit and functionto the envisaged flight model. The power interface shall be the standard 28 V busand the data shall be in a form that can be transmitted to Earth (via the servicemodule) without any conditioning in the service module. To the extent possible,the EM shall be built using the same materials, same generic component typesand same processes and procedures as are envisaged for the flight model. TheEM shall be environmentally tested for both thermal cycling and vibration tests(sine, random, acceleration), according to the environment requirements proposedby the Agency.

The activity shall cover the following tasks:

1. Design/Development: Will take current concept, and develop designs of thesensor, electronics, software, mechanical and thermal systems for theEngineering Model.

2. Manufacturing: of mechanical and electrical systems, as well as othernecessary components.

3. Testing: The EM will be subject to a variety of tests. Some will involve verify thescientific operations of the instrument. Other testing on components will also becarried out in terms of thermal cycling, vibration, etc.

Deliverables: Technical Reports (Design, Breadboard test results, etc.). Engineering model.

Justification for DN: The tasks proposed are the continuation of the work performed, up to levelof breadboard verification, at national level by the team formed by theUniversity of Aarhus and Innoware (DK). In addition, the Mars wind tunnelat the University of Aarhus is the only facility known that will allow for thetesting of the proposed instrument in a realistic Martian atmosphere. Giventhe special competences and the unique facilities available in this team itis proposed, to carry out those tasks with these two entities.

Non competitive tendering is justified according to the article 6.1.a of theContract Regulations.



Activity Title: Self-Lubricating Metal Matrix Composites (MMC) for medium temperaturesin space

Description: This activity proposes to finalise the development of a dry lubricant based onpowder metallurgy technology, specifically the main goal of this activity is toqualify a self-lubricating composite based on Bronze and MoS2, to be used as adry lubrication for space application under medium (20 Deg C) and high (300 DegC) temperatures. The first main application can be Bepi Colombo Ball bearingscages or bushings but may be suitable for all mission where mechanisms shall beactuated under high temperature (up to 350 deg) Liquid lubrication for spaceapplication shows very good results under normal range of temperature (-30 degC to + 80 deg C). Outside this range and typically for high temperature (up to 300deg C) the only lubrication solutions should be dry lubrication. Presently, ballbearings cages for high temperature application are manufactures of lead bronze(e.g. LB9) combined with MoS2 coatings. However, at temperatures of 300 deg C,zinc and lead may sublimate. The lubrication is then lost and the sublimatedproduct would contaminate other devices or lead to electrical shorts. ARCS (AT)have recently developed an innovative production process (from powdermetallurgy) to manufacture this Bronze based MMC (Metallic Matrix Composite).This Bronze based MMC shows low friction and wear at 20 deg C and 300 deg C,while combining high mechanical properties (260 MPa at 300 deg C). Based onthese promising first results, a continuation of this project propose to go up to ballbearing and bushing tests. The project will start with the requirement survey. Thesecond part of the project will be dedicated to the identification of the best MMCcandidate (thanks to detailed tribological tests) for further tests as ball bearingcages. The third part of the project will be dedicated for ball bearing and plainbearing (bushes) tests under medium (20 deg C) and high (300 deg C)temperatures and under air, nitrogen and vacuum.

Deliverables: MMC samples, ball bearings and bushings samples and associated test results.

Justification for DN: This is a continuation of previous ESA activity No.15870 (190 K€ fundedby the Corporate Budget). The present ESA activity is focusing onpolymers and this activity proposes to finalise the development of a drylubricant based on powder metallurgy technology.


BepiColombo


Ref. Number: G203-02SC Budget: 500 K€

Activity Title: CRYOGENIC FRINGE SENSORDescription: In order to control the optical path differences between telescope pairs of the

DARWIN interferometer below the tolerated differences of some 10s ofnanometers, the actual path length is measured using stellar light, in a banddifferent from the science signal. The metrology band is taken out and sent to adedicated fringe sensor unit, before the light in the science band is combined anddetected. The fringe sensor operates at a wavelength of below 4 um. Theobjective of the activity is to design and develop a fringe sensor operating in acryogenic environment. The unit shall be integrated and tested in the CryogenicInterferometry Facility.

Deliverables: Breadboard of the sensor for further testing and characterization.


Activity Title: DARWIN laser metrology performance verificationDescription: The aim of this activity is using the ViRGO gravitational wave detection facility to

test the High-Precision Optical Metrology (HPOM) systems developed for theDARWIN mission (and its precursor mission SMART-3). ViRGO will enable HPOMsystem verification at the nominal distance between satellites of the DARWINconstellation.Within the frame of High-Precision Optical Metrology (HPOM), twoabsolute-distance measurement interferometers (a frequency scanninginterferometer and a dual-wavelength interferometer) and a fine lateral sensor arebeing developed. The HPOM systems are required to maintain the extremegeometrical accuracies required in the DARWIN satellite constellation overdistances between 25 and 250 meters.To meet the accuracy requirements of the DARWIN technology demonstrationmission SMART-3, it is necessary to measure distances with nanometricaccuracies. Thus the optical path stability of the distance measurement systemneeds to be in the order of 10E-12. Such stabilities can only be demonstrated invery long vacuum tubes, because the transmission properties of a medium otherthan vacuum (such as optical fibers) will fluctuate by several orders of magnitudestronger than the measurement accuracy requirement.

Deliverables: Detailed test report on the HPOM system performance over working distances,which correspond to the nominal DARWIN operational distance. Analysis ofremaining noise sources and subsequent improvement of the HPOM hardware tooptimizes the performance. Recommendations for the design of HPOMengineering models and flight hardware.

Darwin



Activity Title: Lithographic manufacturing of Zero Order Gratings (ZOG) for innovativeachromatic IR phase shifters

Description: The Back Sided Zero Order Grating (ZOG) Achromatic Phase Shifter is a new andoriginal optical component, which is intended to provide flexible and performingsolutions in particular in the field of nulling Interferometry, for instance DARWIN,where stringent characteristics are required in order to achieve very high rejectionratios. The use of a ZOG in total internal reflection (TIR) induces a diffractionefficiency that closely approaches 100%. The ZOG concept allows to accuratelycontrol the homogeneous and anisotropic optical properties of this layer in order tocompensate for the natural dispersion of the transparent blank material. A nearlyperfect achromatic vectorial phase shift (phase shift takes place between the sand p polarisation components of the light) can be reached. The simulatedperformance of such a component is very promising: equivalent rejection ratios upto several tens of millions over broad wavelength ranges (spectral resolution lessthan 2). The implementation in an interferometer is quite immediate and elegant.Considering two identical components rotated by 90? From one another, weretrieve for each state of polarisation the "designed" achromatic phase shift. So itworks with natural light. Thanks to reactive plasma etching (RPE) processes, thegrating structure can be etched into the substrate. The monolithic approach isoften required for space applications with extreme temperature range and harshenvironment: for instance, it ensures that no CTE mismatch could occur. It is amajor advantage over any multi-layer devices. Summarizing, in this activity thefollowing work shall be performed: optimisation of the physics-chemistry of theRIE to IR materials, like ZnSe or CdTe; manufacturing of prototypes in thespectral range 6-11 microm; metrology with microscopy (AFM+SEM); andperformance assessment on an IR bench: measurement of the induced phaseshift.

Deliverables: Reports, documentation, performance assessment and prototypes.

Justification for DN: The Back Sided Zero Order Grating (ZOG) Achromatic Phase Shifter(APS) is a new and original optical component, which is intended toprovide flexible and performing solutions in particular in the field of nullingInterferometry. A preliminary study on APS concepts for DARWIN showsthat the ZOG concept might be the best solution, not only due to its opticalperformance but also because of its simplicity of implementation. Thisactivity will aim at optimising the lithographic manufacturing of ZOG to IRmaterials. As there is an existing patent on ZOG for Phase Shifters by theUniversité de Liege, and this institution has the previous knowledgenecessary for the success of this activity, it is recommended to place thenew contract as direct negotiation with this university.

Non-competitive tendering is justified according to Article 6.1.d of theContracts Regulations.



Activity Title: RF Metrology SubsystemDescription: Formation flying of several spacecraft is required for space interferometers with

large and variable baselines. In the absence of GPS signals from systems,intended for signal reception on ground, a local metrology system needs to bedeveloped. Due to the fact that the GPS frequencies are protected, receivers andtransmitters operating at a different frequency band need to be developed.Themetrology system should perform range measurements between antennae in thesatellite formation. Based on these range measurements relative position andattitude can be computed. The objective of this activity is to design and develop a3-node metrology system based on elegant breadboards of transmitters, receiversand associated processing tools. The system will be based on GNSS-like signals,taking into account that the system shall be operate in non-near-earth orbits. Thedeveloped breadboard RF Subsystem will be used on ground to validate formationflying and demonstrate the performance requirements.

Deliverables: In this activity a double frequency RF metrology for formation flying missions shallbe designed, breadboarded and tested. The elegant breadboard developed underthis activity shall be representative of the SW and HW functionally and electricaldesign of the final flight unitt. It shall be developed in a single board, minimizingsize and mass and it shall consist of two and three nodes, allowing end-to-endperformance demonstration of Smart-3 and Darwin missions.


Activity Title: Test Harness for High Resolution InstrumentsDescription: Future science and earth observation missions call for instrumentation with higher

spatial resolution than what is practical to provide with a single aperture. This isdue to the law of diffraction having the effect that aperture size needs to beincreased to achieve higher spatial resolution. However, the higher resolution canbe obtained by combination of light collected by separated apertures. Thistechnique is called aperture synthesis or interferometry, i.e. the combination ofseveral beams generating a composite signal, providing the needed higher spatialresolution. There are already scientific ground based facilities exploiting thistechnique, e.g. ESO’s Very Large Telescope Interferometer (VLTI) in Chile. Thisactivity will include the following tasks: definition of general requirements to testhigh resolution instruments; survey of the principle and technique of multipleaperture generation (collimator, beam splitter, holographic grating, corner cubes,Darwin Beam combiner design, FO coupling, micro optic); elaboration ofpreliminary designs; trade-off analysis and selection of the most appropriatedtechnique; investigation of market needs for such test facility; detailed design;critical design analysis (identify risks, feasibility); design justification; marketsurveys of the critical components; required breadboard activities to achieve therequirements; trade-off between aperture generation in or outside the cryogenicenvironment and trade-off between radioactive or conductive cooling.

Deliverables: Design of a general purpose test facility for high spatial resolution instruments,based on aperture synthesis techniques, including breadboarding ofkey-elements.



Activity Title: Imaging InterferometerDescription: This activity aims at deriving the optical design of an imaging space interferometer

with up to six separated input apertures. The architecture of the imaging beamcombiner shall be based on phase-referencing, supporting simultaneousobservation of the science object and an off-axis reference target for OPDstabilization purposes, alternatively a high performance metrology system. Inorder to have a wide co-phased field of view homothetic mapping interferometerswill be assessed, e.g. pupil zooming should be investigated as one design option.

Deliverables: Selected design manufactured and tested in a representative environment.


Activity Title: Index Guided Photonic Crystal Fiber for DARWINDescription: Darwin, GENIE and their preparatory missions require special wavefront filtering

devices as part of nulling interferometers in a broad spectral range from 4 to 20micrometers, operating at 40 K and resisting hard radiation as expected for thespace applications. Index guided photonic crystal fibers are the most promisingsolution for single mode guiding in the wide wavelength range. The unavoidabledifficulties in matching the different materials at the core/ cladding boundary andits very small diffraction index difference can be circumvented. The new basicfiber technology will be started from the simulation of nano-structures and will leadto the fabrication of new fibers with unique optical properties. Nano-structuredphotonic crystals to be designed & fabricated will enable either for single modewave guiding or for IR-image guiding by quasi-gradient index or by multi-corefibers – in optimal coupling with other optical elements and tailored to specialapplications. This activity will comprise: software development of radial symmetric& 2D nano-structures for simulation of index guided photonic crystal fibers,crystal/glass optimize growth with a specific structure, fiber fabrication with thedesired parameters in a wide spectral range, and fiber performance testing inproper space environment condition.

Deliverables: Index guided photonic crystal fiber operating in the spectral band from 4-20micrometers.



Activity Title: QWIP Optimization for Darwin FIR Linear ArrayDescription: The TRP activity “Far IR Linear Detector Array” concerning ESA’s DARWIN

mission, currently on-going, has so far achieved QWIP (Quantum Well InfraredPhotoconductor) state-of-the-art performance at 16 µm, with good response andoperating temperature but with dark current values exceeding Darwinrequirements by several orders of magnitude.

The main objective of this GSTP activity is then to obtain dark current optimisationin order to achieve lowest possible dark currents, QWIP energy level fine-tuningand dark current reduction by 4 to 5 orders of magnitude. This shall include thefollowing:

- QWIP energy level fine-tuning. QWIP excited level adjustment by processingfine-tuning down to molecular monolayer; Optimisation of size and shape ofquantum well “horn”; Optimisation of multilayer structure.

- QWIP dark current reduction. Barrier material purification, crystal lattice defectminimisation and bulk sample test; Study effect of barrier thickness variation overentire detector; Change electron injection (electrode doping); Investigate surfacecurrents on new (lower) level of dark currents (with eliminated photocurrent –reflections from cold walls inside the cryostat); Investigate inconsistency in thedependence of dark current on the barrier thickness.

Justification for DN: This GSTP activity will serve as a continuation to the previous work byACREO (SE) under an ESA contract (No. 16427, funded by TRP with 750K€).




Activity Title: Sample and Return Systems for a Small Body (Deimos Sample Return TRM)Description: The objective of this activity is to assess the feasibility of and to identify critical

technologies for a mechanism that enables a micro spacecraft to rendezvous witha small body, obtain a sample and return to its orbit. The study shall exploreseveral options for different key subsystems, such as sampling mechanisms, andprovide trade-offs. The sample mass should be commensurable with a Soyuzclass sample return mission, in the region of 1kg. The sample should consist, atleast partly, of subsurface material. Additionally, the system should be able tooperate with a high degree of autonomy.

Deliverables: Technical report covering key aspects such as trade-offs between severalsampling methods, landing/rendezvous mechanisms, and sample return systems.Elaborated conceptual design of sampling devices, including acquisition, transferand retrieval.

Deimos Sample & Return



Activity Title: Gamma Ray OpticsDescription: The most promising approach will be selected for developing the optics to cover

the requirements of the Gamma Ray Imager Technology Reference Mission (GRITRM). The GRI may require more than one gamma ray optics technologies, dueto the large range of gamma ray energies of interest. Layered synthetic structuresas well as crystal optics in Laue or Brag configurations shall be considered. Inorder to properly evaluate the gamma ray optics technology, samples will beproduce for testing and evaluation. The results of these measurements will beused to guide the iterative process of developing the necessary optics elements.

Deliverables: Optics element prototypes for laboratory tests and evaluations at ESTEC andexternal facilities. Technical documentation describing the technologies andprocesses involved, as well as the performance predictions and measurements.

Gamma Ray Imager



Activity Title: 650 GHz 5m Hologram Compact Antenna Test RangeDescription: The second half of 2003 will see the successful conclusion of TRP contract

13096/98/NL/SB "Submillimetre Wave Antenna Testing Using a Hologram CATR".The principal of the Hologram CATR is to replace the conventional reflectors of acompact antenna test range with a transmission element to produce the quietzone antenna testing. The advantages of the technique are: relaxation ofmanufacturing tolerances by an order of magnitude; relatively low cost; andportability, if required. The current TRP activity is the first large Hologram CATR tobe manufactured and can be considered as a first generation item. Parallel workunder the activity to develop the concept of a compact dual reflector feed systemfor hologram illumination will allow for improved illumination of the hologram with aconsequent simpler hologram design making it more amenable to largerholograms at even higher frequencies. The HUT Radio Laboratory/SMARAD andMilliLab propose a 16 month research and development project to further developthe hologram based CATR at 650 GHz. This project aims to a test program inwhich the Herschel telescope could be tested at the lowest HIFI band (480-650GHz) (as well as the Planck telescope) by the end of 2005 (or early 2006) under aseparate ESA contract. The proposed R&D project should start as soon aspossible in 2004 to take advantage of the experience gained under the currentTRP effort to produce, evaluate and apply a 3m-diameter hologram formeasurements at 322 GHz. Its key study areas are: development of hologrammanufacturing techniques towards a 5m x 5m hologram using a mylar film of 25micron thick with copper layer of 5 micron thick together with Saueressig GmbH;optimising a DRFS (Dual Reflector Feed System) system for 650 GHz for a 5m x5m hologram; development of measurement instrumentation towards betterdynamic range and improved measurement accuracy at 650 GHz

Deliverables: By the completion of the activity, the capability of operational testing of theHerschel Telescope will be possible at frequencies up to 650 GHz. This applies tothe Palack telescope as well. There will have been demonstrated an antennameasurement capability of large aperture sub-millimetre antennas at 650 GHzwith the knowledge that it can be extend at least up to 1000 GHz.

Justification for DN: The Helsinki University of Technology is the originator of the concept ofthe Hologram Compact Antenna Test Range and has undertakendevelopment over the last ten years. ESA entered its support for thetechnique in addressing the problems associated with the testing of largeaperture antennas at millimetre and submillimetre wavelength frequencies.With the creation of the ESA External Laboratory, MilliLab, in the 1990's, aconcerted effort was made under ESA TRP to consolidate the knowledgebase and produce an operational hologram range at 322 GHz. The currentGSTP proposal would build on this unique foundation and the running TRPcontract (no. 13096, budget of 520 K€).

Non-competitive tendering is justified according to Article 6.1. a) and c) ofthe Contracts Regulations.




Activity Title: Wideband ReceiversDescription: The objective of the work of this activity is to advance the European state of the

art in the subject of broadband mm and sub-mm-wave receivers, and todemonstrate by breadboarding the mastering of the analysis, modelling andtesting tools. The first part of this activity should be devoted to design of highperformance wideband receiver concepts and topologies. Emphasis will be placedon at least the following main areas: system requirements, system concept,instrument topology, technological risk, and fabrication issues. The second part ofthis activity should determine a design rationale and fabrication approach thatleads to the complete integration of a submillimetre-wave wideband receiver. Thiswill be followed by a phase where the critical items will be breadboarded andtested.

Deliverables: Performance prediction, Wideband receiver hardware, demonstrator, fullperformance report


Activity Title: Mercury Micro-rover end to end demonstrationDescription: In the past years ESA has developed a scenario for geochemistry investigation on

planetary surfaces. In this scenario a micro-rover (named Nanokhod) carrying ageochemistry instrument package is delivered on a planetary surface by a smalllander. The microrover departs from the lander to apply the instruments toselected soil elements. In its initial phase, the ESA Bepicolombo mission toMercury intended to implement the microrover scenario. Consequently severalBepicolombo technology activities were initiated to bring the elements of thescenario to a level of readiness adequate for mission use. Unfortunately due tobudgetary reasons the Bepicolombo lander was later cancelled. However thetechnology developments were kept going, as it was perceived that thetechnology there produced would be valuable for a possible future mission toMercury. These developments are now reaching completion. Therefore the needof bringing together all these elements in a complete end-to-end demonstration,which would target the specifics of a mission to Mercury. The activity hereproposed aims at re-elaborating those technologies to adapt them to the specificsof Mercury (higher autonomy, night operation) and at adapting the end-to-endcontrol chain to operate with the deliveries of the Bepicolombo technologyactivities, demonstrating the end-to-end operation.

Deliverables: System model demonstration in a relevant environment.

Justification for DN: In the past years ESA has developed a scenario for geochemistryinvestigation on planetary surfaces. In support of this scenario, the TRPactivity (300K€) “Payload Support for Planetary Exploration (PSPE)”,contract number 13501, developed a first demonstrator of an end-to-endcontrol system. The work, led by Space Application Services, producedgroundbreaking technology to allow to remotely commanding autonomousmicrorover operations. It is thus proposed to complement that initial workwith the tasks included in this activity.

Non-competitive tendering is justified according to Article 6.1.c. of theContracts Regulations.



Activity Title: Development of a miniaturized mass spectrometer for space applicationsDescription: The measurement of the chemical composition of gaseous, liquids and solids is

fundamental to the in-depth understanding of the given sample. Thus chemicalmeasurements play a key role in the exploration of planetary bodies in our solarsystem. The chemical composition is vital to the description of the discoveredmaterial and to decipher its formation. By means of mass spectrometry theseresults can be obtained with a sufficient precision. However, such instrumentationhas to satisfy the strict requirements of robotic space exploration which are: 1)availability of extremely low resources; 2) rugged design; 3) harsh spaceconditions like vacuum, large temperature range, radiation; and 4) fullautonomous working modes.

The task of this activity shall be to miniaturize a technique well known fromlaboratory applications (Quadrupole mass spectrometry is widely used in industrialand scientific applications). The eventually developed breadboard model shalldemonstrate its scientific capabilities and suitability for a deployment in the harshenvironment of alien worlds.

The output of this activity shall be a fully functional breadboard modeldemonstrating it suitability for planetary exploration missions. This requires:- Fully integrated design of the mass spectrometer (ion source, filter, detector).- Miniaturisation of drive electronics, signal processing and power supply.- Miniaturisation of vacuum system- Testing according parameters dictated by the requirements of space missions,vibration, mechanical shock, thermal vacuum and radiation damage.

Deliverables: One breadboard model and Technical notes.



Activity Title: Development of light filters for solar radial velocity measurementDescription: Solar radial velocities measurement is usually performed using sets of Michelson,

Lyotfilters, magneto-optical, Fabry-Perot or Mach-Zender type filters. These filtersanalyze the solar spectrum with a resolution of at least 50000 over a narrow rangecentered on a Fraunhofer absorption line in the visible. They should be tunableover a few 100 mAngstrom. These filters should be able to make images of theSun with a resolution of about 0.5 arcsec from 1 AU. Up to know, these filtershave been developed for space-based application using a combination ofMichelson and Lyot filters. These latter are rather heavy when it comes to built alight instrument such as the one envisaged for Solar Orbiter. At present there aretwo possible alternatives that are rather light: Fabry-Perot and Mach-Zenderinterferometers. The former is based on Lithium Niobate or vacuum spaced withpiezoelectric spacers. The second alternative uses the full sun spectrum (i.e.manyFraunhofer line) for deriving the solar radial velocity. The purpose of thestudy is to trade off the various solutions for space applications, and to build ademonstrator that will be tested in solar observatories.

Deliverables: Reports and demonstrator.

Solar Orbiter



Activity Title: High Resolution Low Mass Optics PetalDescription: An optical model petal shall be produced, demonstrating the optical performance

and resource requirements for high resolution imaging for space sciencemissions. It is envisaged; that a future space based optical system would bemodular, constructed from optical petals based on the result of this TDA. While itis considered as sufficient to produce one single optical petal to demonstrate thetechnology, the compatibility with alignment systems and modular build-up have tobe considered already at this stage. Pre-cursor test samples as sub-assembliesare expected to be tested at ESTEC and external facilities, supporting theselection of the optimal design and production processes. The optical petal will beevaluated in terms of its specification and performance before and after thedelivery to ESTEC.

Deliverables: High-resolution low mass optics petal with test result reports. Detailed technicaldocumentation describing the technologies and processes involved, as well as theexact specification of the actual optics petal.


Activity Title: Laser Radar with Submillimetre AccuracyDescription: The objective of this activity is to improve the current range accuracy of Lidars

time of flight measurements from one cm to the sub-millimetre range. In order totackle the mm-barrier a prototype rangefinder shall be developed using noveltechnologies (short pulse laser, high resolution time to digital converters, etc). Themeasurement of roundtrip time with pulsed laser radars yields very attractive andcompact sensor devices with low complexity and low data processing effort.Today's time-of-flight technology achieves range precision in the order of one cm.For sub-mm accuracy other measurement techniques like laser basedtriangulation or fringe projection or stereovision systems have to be used. Allthose methods are limited in measurement volume and target distance; needco-operative targets or a special surface texture or illumination. Laser radarsmeasuring the roundtrip time of a short laser pulse shall overcome all theserestrictions and offer a high dynamic range in addition. This activity shalldemonstrate the feasibility of innovative laser radar technology, boosting therange precision capability of pulsed laser radar systems to sub-mm accuracy, as itis required for space missions to control formation flying satellites (e.g. XEUS,Darwin) or short range detection, robot manipulation and surveillance on the ISS.

Deliverables: Rangefinder breadboard with sub-millimeter range accuracy.

Justification for DN: This activity follows the previous developments made on Laser Radarsand Imaging Lidars by Riegl. Specifically it is a continuation of the TRPactivity “Imaging Sensor for Scientific Mission” (200 K€), under contractnumber 14333. Based on the previous experience of Riegl in this area andon the availability of hardware, it is recommended to continue this workwith Riegl Company.


XEUS



Activity Title: Low temperature spectrometer arrayDescription: The objective of this activity is to develop an optimized x-ray detector array based

on microcalorimeters with Transition Edge Sensors (TES) as thermometers,matched to the requirements of the NFI-2 instrument proposed for XEUS. Thisinstrument will consist of a 32x32 element array of cryogenic detectors, with apixel size of ~250x250 mm2 and a filling factor of 95%. The requirements forthese detectors are to provide a detection efficiency of 90% (0.5-15 keV), anenergy resolution of 2 eV at 1 keV and 5 eV at 7 keV, and an effective timeconstant of <100 ms at 15 keV. In addition, the design of the array should be suchthat electrical and thermal cross talk between pixels is minimized to the extent thatthe above requirements are still met for all pixels across the array. Theperformance should be demonstrated with a representative read-out scheme for a2x2 element sub array.

Deliverables: Detector arrays for laboratory tests and evaluations at ESTEC and externalfacilities. Technical documentation describing the technologies and processesinvolved, as well as the performance predictions and measurements.


Activity Title: Optical FiltersDescription: Future detectors for science missions, both planetary and astrophysics missions,

are, due to their increasing efficiency, often becoming more sensitive to irradiationby photons outside the desired detection range. By using suitable filters,transmitting only in the required detection band, while blocking the undesiredradiation, the detectors can be better optimized and their efficiency improved. Thedevelopment of optimized filters is therefore very relevant to provide the requiredperformance on instrument level. Filters with selective transmission bands are tobe developed for applications in photon detection instruments for planetary andastrophysics missions. Also cryogenic detectors have to be considered, requiringoperation of the filters at low temperatures. The transmission band of interest shallbe transmitted with least possible losses, while the adjacent energy bands mustbe efficiently blocked. Not only technologies relying on synthetic layeredstructures and thin films shall be considered, but also micro- and nano-structuresof proper geometry made of suitable materials.

Deliverables: Filter prototypes for laboratory tests and evaluations at ESTEC and externalfacilities. Technical documentation describing the technologies and processesinvolved, as well as the performance predictions and measurements.



Activity Title: Elimination of Corona Discharge in High Voltage FEEP ConnectorsDescription: Fine control using electric propulsion makes use of Field Emission Electric

Propulsion (FEEPs) driven by small power supplies with low currents but voltagesas high as 14kV. Current users include GOCE, and future users shall includesatellites that fly in formation, such as XIM. Due to the low thrust involved eachsatellite may contain many FEEPs and hence miniaturisation is of an essence.Nevertheless, project usually requires that, once integrated on board the satellite,the FEEP power supplies are tested one last time to ensure they are working. Totest they must be disconnected from the FEEP itself, which cannot be fired in anormal satellite integration environment. The use of a connector between supplyand FEEP to facilitate this test leads to a later danger of corona discharge sincethe connector provides insufficient insulation under partial pressures - which canoccur for example due to a single-point failures such as a leakage in the onboardfluid feed subsystem (e.g Xenon in the case of GOCE). Current approach hasbeen to take the chance that no single-point failure of the Xenon subsystem willoccur. To eliminate the risks mentioned above, this study calls for thedevelopment of suitable connector or of a potting tool, which may be used at theend of satellite AIT. This TRP-funded study would be split into two parts, the firstof which would study possible solutions to the problem taking into account typicalapplications and typical venting analysis. Second part of the study would be thedevelopment of the connector or tool as appropriate. This study has beenproposed in agreement with TOS-MPE.

Deliverables: Qualified samples of manufactured solution (eg potting tool or connector).

X-ray Interferometer


Theme 3.- HUMAN SPACEFLIGHT

Ref. Number: G301-01QM Budget: 570 K€

Activity Title: Investigation of the introduction of new surface treatment technologies forspace interior based on SAM polymers

Description: During the investigation it shall be identified if the relative new and innovativeSAM (Sustainable Active Microbial) polymer technology is capable to protect thespacecraft inner surface and installed elements of microbiological contamination.Offering permanent protection against mildew algae and bacteria, SAM polymersrepresent a completely new class of biocites based on special functionalizedpolymers. These polymers can be incorporated into paints, dyes and plasticsequipping them with microbiacidal action. Based of today's knowledge thetechnology works by electrostatic surface interaction between the polymers andthe microorganism; due to this interaction the metabolism of the microorganismwill be disturbed.

Deliverables: Project Plan, Test Plan; Lab Test results; Requalification Results; CoatingProcedures; Final Report

Advanced habitats



Activity Title: GLOBE: Gas-Lubricated Oil Bearings (Pre-Qualification Phase)Description: The basic idea of GLOBE is to make liquids work as gas-lubricated bearings and

as vibration isolators in microgravity, where the smallness of the loads bearableby surface tension is not a too severe limitation. Non-wetting liquids behave asideal bearings because they are able to work in the virtual absence of staticfriction, do not undergo wear, do not produce debris nor noise, do not requireexternal sources of lubricant nor alignment procedures, and are not subjected toany relevant resistive torque. GLOBE is a space application-oriented projectaimed at demonstrating a new and original technology based on the fluid dynamicphenomenon of the permanent inhibition of wetting by means of thermocapillaryconvection. MARS and DTM Technologies, under the responsibility of MARS,have already successfully completed a first phase of this project, under the aegisof ESA, producing a breadboard model of the hardware and results from anumber of tests. The two teams are now ready to team up again and build apre-qualification model of the hardware.

Deliverables: GLOBE Engineering & (Pre-)Qualification Model, with full technicaldocumentation.

Justification for DN: The initial GLOBE development was performed under TRP contr.14332/00/NL/PA by MARS Center (I) and DTM (I). As the know-how onthe utilised fluid physics, the derived technology, and already existinghardware is very specific, only the proposed contractors would be capable(and interested) to perform the intended pre-qualification towards apotential flight demonstration.


Automation and advanced robotic technologies



Activity Title: COTS based space borne computer 2Description: The main goal of the activity is the specification, design and prototyping of COTS

based computers for three kinds of mission: satellite, Fault Tolerance (ATV type),high computing (Payload type).

The use of COTS components for the design of on-board computers is not newbut has always been considered on a case-by-case basis. Use of COTSprocessors is now mandatory to get fast access to high computing power.Converging technologies between space and non-space industrial domains,mainly aircraft and automotive, demonstrate that COTS-based solutions arefeasible and can be applied also to space. Evolution of the system designtechniques is also rendering possible the use of robustness by design techniquesbetter than intrinsic robustness by radiation hardening. This activity hence isdevoted to achieving some solutions towards space borne COTS basedcomputers and to assess their efficiency and usability for space missions in theaim of using them in operational projects.

A functional specification and validation plan are prepared for three domainswhere COTS based Computer Systems (CoCs) will be used; i.e. Highly ReliableCoCs, Highly Available CoCs and High Processing Power Payload CoCs. Thedetailed design of each of the inner building blocks shall be performed.Executable models of the design shall be built for early verification.The selectionof the COTS components to be in the CoCs is performed and justified. Thequalification of the CoCs must be performed according to existing ESA flightqualification rules. The method for prediction and evaluation of the CoCsperformance is defined allowing the assessment of the reliability and added valuewithin a system, including programmatic and cost. The prototyping of two CoCs isperformed; i.e. a platform oriented CoCs and a payload oriented CoCs, they aremanufactured at the level of Engineering Models.The CoCs test means aredefined to allow validation and assessment of the fault tolerance properties. Ademonstration application featuring a deep space mission is implemented, it willbe used to stress the CoCs and will serve as final assessment of the technology.

Phase 1. The study phase features the demonstration of critical technology issuesfor building CoCs.- WP1: Functional Specification of the CoCs- WP2: CoCs definition and building block level specifications- WP3: Selection of the COTS technology: CPU, memory- WP4: Specific design for the Reconfiguration Module and Safe GuardManagement- WP6: Detailed design of the Building Blocks

Phase 2. The implementation phase aims at prototyping and assessing thecomputing systems.- WP5: Evaluation methods for reliability, availability, performance andassessment of added value within a system- WP7: Prototyping of the CoCs. Two prototypes at Engineering Model level arerequested.- WP8: Overall CoCs assessment through a deep space science type ofapplication.

Deliverables: Specification package for CoCs; Design package and justification file including theexecutable models; COTS Selection data package including justification;Evaluation method specification and design; Prototype specification, design andmanufacturing (includes 2 Hardware devices, 1 Software and 1 EGSE);Assessment report including programmatic aspects.



Activity Title: Regenerative Life support: Greenhouse ModuleDescription: Study the concept and design of greenhouse module for a planet base. Taking

into account current ESA studies in structure, the concept of the greenhousemodule will be studied. Depending on the mission scenario (i.e. transit or planetbase), a trade-off addressing the structure, material selection, and design will beperformed. Within this study the constraints of life support processes (selectedcrop, hydrodynamics, thermal control, humidity control, pressure control, lightutilization, plant harvest, water recovery ?) as well as the space one (reducedgravity, mass, radiation effects,..) will be considered. Preliminary tests on materialwill be performed. When possible, the production process of the material selectedwill be described. When appropriate, in situ resources utilization will be considered(i.e. CO2 ). Based on the results.

Deliverables: Technical documentation, test reports, drawings, final report


Activity Title: MELISSA/BIORAT Genetic Stability Study (phase 2)Description: Development and validation of instrument for genetic and proteomic stability

follow-up in the MELISSA compartments. In this phase it is proposed to focus onthe genetic instrumentation for MELISSA compartments II and IV. Based onprevious results, specific probes to follow the genetic evolution will be studied,designed and developed. When necessary, complementary proteomiccharacterization of the microbial communities will be performed. The technologywill be validated during a long-term culture (over 1000 generations) in MELISSAcompartment II and IV. In parallel, equivalent activity will be run for the axenicitymonitoring. Whenever appropriate, countermeasures to the evolution andcontamination will be discussed and preliminary guidelines will be given.

Deliverables: Deliverables include: breadboard, validation test plans, result and analyses.

Justification for DN: This activity follows the previous phase 1 carried out by SCK (B) forMELISSA/BIORAT (contract number 15680, 450 K€ funded by GSTP-3).


Closed loop life support technologies



Activity Title: MELISSA Adaptation for Space - Phase 2Description: Establishment of an industrial team and performance of the "ground work" to

support exploitation of the research achievements of the MELISSA joint venturefor future manned space missions. The work of Phase 2 which is expected to lastfor about 2 years will cover essentially system-level design and analysis focus onpreliminary evaluation of mass, volume, energy and accommodation for a Marsbase scenario. Validation of these preliminary estimations will be compared withvalues of the MELISSA pilot Plant.

Deliverables: Deliverables will include specifications, and analysis reports, drawings, finalreport.

Justification for DN: This activity will serve as a follow on of a previous ESA contract (No.15671, budget of 300 K€, funded by GSTP) successfully performed byNTE.



Activity Title: MELISSA : Fibres Degradation UnitDescription: Development of continuous or semi-continuous fibres degradation unit including

its instrumentation and interfaces with the first compartment of the MELISSAprocess (bioreactor, filtration, specific treatment). The proposed activity willexploit the experience of previous ESA contracts to develop a system forsemi-continuous fibres degradation unit. The object of the proposed activity is todevelop a breadboard, which allows fulfilling the ground demonstration of theMELISSA loop.

Deliverables: Deliverables will include design reports, drawings, test data, developed hardware.

Justification for DN: Follow on activity on ESA contracts 14719 and 15689. The contract14719, “A total converting and biosafe liquefaction compartment forMELISSA”, was funded by the European Participation in the InternationalSpace Station, with an amount of 500 K€, and done by the University ofGhent. The contract 15689, “Melissa Engineering of the WasteCompartment”, was funded by GSTP-3, with an amount of 750K€ anddone by EPAS and VITO. This activity is the continuation of both contractsand then requires the participation of the three companies involved in theinitial activities.




Activity Title: MELISSA : R.rubrum harvesting techniquesDescription: The task proposed concerns the harvest technologies for the second

compartment. Any closed life support system is now based on the association ofphysico/chemical processes and biological processes. During the last 15 years allspace agencies have been working on the processes characterization. It is nownecessary to study the technology to link these processes. The harvest of theproduced biomass is a key element of the photosynthetic compartment.Unfortunately the technologies are specific of the considered microorganisms andthe extension of previous studies on compartment 4 cannot be extended tocompartment 2. Study the harvest technologies for the MELISSA secondcompartment. Review of potential technologies, trade-off, selection,breadboarding, test and validation.

Deliverables: Deliverables include analysis reports, design report, final report.

Justification for DN: This activity follows the previous work carried out by EPAS and VITO (B)for MELISSA (contract number 15689, 830 K€ funded by GSTP-3).



Activity Title: Urine Treatment Unit (Phase A/B)Description: The use of selected microbial strains to remove contaminants from water is

extensively explored in terrestrial wastewater treatment plant. Urine is a majorconstituent of liquid issue from the crew with the peculiarity of a very high saltscontents. Technology to transform urine in potable water as distillation or reverseosmosis are very efficient but high energy consuming and don't take benefit of thesalts. It has been demonstrated that direct utilization of urine could present majorinterest for hydroponics cultures of higher plants. However ammonium shall betransform in nitrates and Na concentration shall be considerably decreased.Current space urine recycling systems use physico-chemical methods for waterproduction. Simpler transformation of urine for HP cultures promises higherrecycling percentage, greater flexibility/adaptability and lower power consumption.A development model will be manufactured and subjected to extensive testing toexplore the inherent performance of the system.

Deliverables: Developed hardware, test results, and final report.

Justification for DN: Follow on activity to a previous contract in GSTP-3, number 15652,“Microbial Water Treatment”, with both companies (EPAS, and VITO), andfunded with an amount of 660K€. As a direct continuation of that contract,it is proposed to award this contract to EPAS and VITO in order tocontinue with the tasks described in this activity.




Activity Title: Waste Collector UnitDescription: It is well accepted that future manned missions will need a high percentage of

metabolic consumables. Current life support hardware does no consider wasterecycling possibilities. Consequently the crew wastes are simply stored and burnduring re-entry. All tested waste recycling technologies have demonstrated theneed of a pre-treatment. It is now necessary to study and develop the technologyfor a new waste collector unit, the associated pre-process and transportationmode up to a waste recycling unit. Study and development of a waste collectorunit and associated treatment. The proposed activity will consist to:- Study the requirements of a new waste collector unit- Review and study critical technologies,- Propose a preliminary design- Manufactured and assembled the proposeddesign,- Test the assembled hardware- Propose a roadmap for future development.

Deliverables: Deliverables will include design reports, drawings, test data, developed hardware.


Activity Title: Advanced, Lightweight Membrane/Electrode Assembly for ElectrolyzersDescription: This activity aims at improving the polymer membrane technology. After

development work on membranes for fuel cells, nickel-hydrogen batteries andelectyolysers, further significant improvement can be achieved by developing anEDE manufacturing process, where both electrodes and membrane are castedtogether in a direct manufacturing run. This will enable significant reduction inmanufacturing cost, mainly aimed for terrestrial application, but also increasereliability of the product (e.g. improved sealing) and weight reduction, both veryimportant for space application. This activity will also study the transfer of currentlydeveloped membrane technology towards larger scale production andimprovement of performance for space applications. The finalmembrane/electrode assembly will then be tested in a realistic (full-scale)electrolyzer.

Deliverables: Electrolyzer membrane (fully tested in realistic electrolyzer) and associateddocumentation

Justification for DN: Direct follow-on of a previous GSTP activity (Contract 16065, budget of800 K€ funded by GSTP-3). Vito emerged from the previous governmentBelgian agency SCK and has very strong background in polymermembrane technology and has worked on ESA contracts since HERMES.This activity means a significant improvement of membranes for fuel cells,nickel-hydrogen batteries and electyolysers, by developing an EDEmanufacturing process.




Activity Title: Additional characterization phase of the Waste compartmentDescription: MELISSA (Micro-Ecological Life Support System Alternative) has been conceived

as a micro-organism and higher plant based ecosystem intended as a tool forunderstanding the behaviour of artificial ecosystems. The work performed underall the previous contracts by all the MELISSA Parties has demonstrated thevalidity of the MELISSA concept: a controlled compartmentalised system. Thisconcept implies a high degree of process characterisation and modelling andwaste management control. Over the last few years, a very high attention hasbeen devoted to the understanding of the waste compartment (compartment 1).Regarding compartment 1, the major part of the previous activities has beendevoted to the preliminary modelling (i.e. mass balance) as well as onrecommendations for the pilot reactor design.

During the past years, MELISSA research was performed to biodegrade efficientlythe organic wastes produced during long term manned space missions. Thecurrent efficiency of this waste processor is between 55 and 70% dependent onthe process conditions. Nowadays, the major part of the non-biodegradablefraction consists of fibrous components. From preliminary investigations,assuming a good solid/liquid separation as well the use of edible white-rot fungi, itcan be concluded that a significant higher efficiency can be reached. Theseparation technology must also function as a hygienic barrier. Microbialevaluation to detect the presence of different bacteria of the two compartmentsand the presence of pathogens is needed. This detection has been performed byclassical, already existing, techniques.

The objective of the present activity is the further development of a continuous orsemi-continuous waste compartment (i.e. liquefacter + fungi compartment)including its instrumentation and interfaces with the second steps of the MELISSAprocess (bioreactor, filtration, specific treatment).

Deliverables: Breadboard model and Technical notes.

Justification for DN: The proposed activity is a continuation of an ESA activity (Contract no.15689, 913 K€ funded mainly by GSTP).




Activity Title: Performance enhancements for trace gas monitoring (ANITA II)Description: The ANITA enhancements are HW and analysis related activities in support of the

ANITA II TGM system development for ISS. Specifically will be focused on lowweight and long-term stability designs for the modulator, mirrors and gas cell (e.g.use of CFRP) and long duration performance testing. HW improvements are alsoaimed at improved system sensitivity (e.g. IR source an detector). The HWoptimization will be support by performance Analysis. Topics for study andanalysis are transfer of calibration models between similar (not identical) FTIRsystems or the effects on the calibration models if HW ages (changes),temperature variation in the environment (i.e. gas cell).

Deliverables: HW pre-developments, calibration models, test-, design and analysis report.

Justification for DN: The ANITA enhancements are Hardware and analysis related activities insupport of the ANITA II TGM system development for ISS. Kayser-Threde(D) and SINTEF (N) form a consortium that have performed all the TGMtechnology development work since 1990 under ESA contract 15743 (totalbudget of 2,400 K€ funded by GSTP and ISS Utilisation programmes),including the TD (ANITA I), to be manifested for a flight on ISS.


Crew Health and Performance



Activity Title: European Crew Personal Active Dosimeters (EuCPAD’s) for AstronautsDescription: Exposure monitoring for Astronauts by personal dosimeters has not been

performed by Europe on ISS until present, despite a vast field of radiationmeasurements conducted. The passive European Crew Personal Dosimeter(EuCPD) project, initiated in spring 2005 for STS-116 and STS-121 is the firstpresent astronaut individualised monitoring so far undertaken by ESA utilisingEuropean technology on ISS. These particular missions call for personalmonitoring, as some 15 to 20 hours of EVA are planned for ISS assembly, andalso long flight duration is foreseen, enabling delta exposure and long termmeasurements.

Low Linear Energy Transfer (LET) for ionising radiation has been measured in thepast quite accurately. However, the contribution of secondary particles of highbiological efficiency such as neutrons are not yet sufficiently characterised. AJapanese experiment to measure neutron spectra in space using Bonnerspheres was inherently constrained since its sensitivity to neutrons with energieshigher than approx. 10 MeV was very limited, apart from being inappropriate forpersonal dosimetry due to mass and volume excess. Unambiguous energy andspectrum categorisation and differentiation of the different types of radiation,namely electrons, protons, alpha particles and heavier particles from galactic andsolar origin and secondary products produced in interaction with shielding materialand the human body, such as thermal to high energy neutrons, still forms today asevere challenge. Due to budget and time constraints the EuCPDs are passiveand, consequently, do not deliver time resolved medical operational data whichare in addition delayed to the event of exposure.

Hence, there is a need for a development of a European active personaldosimeter ( EuCPAD’s) for European Astronauts covering the contribution of allthis radiation types to astronauts exposure. Some of the reasons for such adevelopment include the following:

• EuCPAD’s need to be calibrated using representative sources with well definedspectral characteristics.• EuCPAD’s are needed in more rugged and compact form with improved EMCcapabilities (avoidance of spurious alarms), to withstand mechanical shocks.• Mechanical failures of commercial active dosimeters. Experience shows in caseof power plants drop-outs per week are unacceptably high. The proposed activitymay improve the overall reliability of active devices.• The directional response of EuCPADs needs to be improved and optimized.Presently, most (neutron) dosimeters do not fulfil ISO or DIN requirements.• Differentiation between Protons and Neutrons needs dedicated attention, aspresent commercial dosimeters developed for radiation field mapping werepredominated by sensitivities to one radiation type only or by mixed neutronGamma fields• Space EuCPAD’s need to be sensitive for high energy neutrons.• Realised commercial dosimeters with neutron sensitivity from thermal to 70 MeVneed more efforts on miniaturisation as they are presently around 800g.

Deliverables: Phase 1 covers the review. After completion of all phases an active dosimeterfollowing specification will be produced with as far as possible COTS components



Activity Title: Manikin Virtual IVA/EVA suit.Description: In general the Virtual design environment is providing more and more support in

all phases of design and verification (Virtual Spacecraft Design activity). Inmanned space activities it is obvious that the human should be in the loopimmediately at the start of the design and verification processes. By doing this inthe virtual environment of the design, it will be possible to identify human factorrelated problems and solutions early in that process. In the cases where humanstravel to and live in space with and without suits for EVA (Extra VehicularActivities) or IVA (Intra Vehicular Activities) there are specific needs andlimitations that need to be introduced into the design process. This will have animpact on the Spacecraft design as well as for a future European need to developspace suits, for instance for autonomous European crew transport capabilities.The objective is to provide a parameterized database of space-suit andenvironmental suit classes that can be used in combination with virtual manikinsfor design, human factor analysis and verification, and in future for education andtraining.

Deliverables: HW pre-developments, calibration models, test-, design and analysis report.

Extra-Vehicular Activity (EVA) Suit Technology



Activity Title: Dynamic Parameters IdentificationDescription: Novel robotic control scheme does make use of the robotic structure dynamic

knowledge to optimize the control performances and robustness. To enable this, itis required to have an accurate model of the robot dynamic parameters, of whicha CAD model, when it exists, may provide only an initial, but not sufficientapproximation. In addition, novel applications, like Geo Servicing, requireinteracting with a non-cooperative satellite of only partially known dynamicparameters, due to partially deployed flexible appendage, and un-accurateknowledge on the propellant remainder. In order to optimize the controlperformances, it is required to identify accurately, the dynamic parameters, suchas mass, centre of mass localization, inertial parameters, of the completestructure. Different approaches exist for that such as the use of local or globalidentification, while exiting the structure with known motion profile and deriving therelated dynamic parameters. This activity shall develop the necessary s/w andsensors to perform identification of the complete dynamic parameters for open/closed kinematic structure and test of the s/w on different robotics structure.

Deliverables: Dynamic identification software for open/closed kinematic topologies and relevantsensors set to support the identification

Justification for DN: Trasys together with Krypton has developed for ESA a robotics softwarepackage (contract 16592), for calibration of open/closed kinematicstructures, called ROCAL. This package is based on pre-existing workwhich is Intellectual Property of Krypton.

The proposed activity aims at complementing the ROCAL with roboticdynamic parameters identification. Krypton is a world leading expert inrobotics parameters identification and robotics dynamic metrology. Trasyswas the integrator of the ROCAL package. The proposed procurementpolicy is justified on the base of: the unique expertise of the proposedcontractors; the issue of Intellectual Property part of the ROCAL whichlimits the ability of other parties to modify the existing software.

Non-competitive tendering is justified according to Articles 6.1. c. and d. ofthe Contracts Regulations.

Free-Flyers (Rendezvous and Docking, In-Orbit Assembly andServicing)


Ref. Number: G307-01MM Budget: 1,000 K€

Activity Title: Fluorescence based Biosensor for microbial /life detectionDescription: The improvement of degradative capabilities of microorganisms increases the

possibilities of development of biodeterioration processes on ISS materials.Resistance of materials to microbial deterioration becomes an issue spacecraftdesigners must take into account. The purpose of this activity is to develop newtools to study microorganisms in space conditions. In this way, microbialdeterioration testing would provide new guidelines for the selection of spacecraftmaterials. Several fluorescence-based biosensor for in situ measurements ofbacteria, fungi, chlorophyll (generic and specific bio groups) have already beendeveloped and actually they are being used for buoys and heritage buildings. Theproposal intends to develop these sensors to be used in space (manned missionand space laboratory as COF facilities, Habitats in Moon, or for the detection ofpotential exolife microorganism on planet exploration.

Deliverables: Fully functional breadboard of sensor

Justification for DN: INASMET has developed and patented fluorescence based biosensor forin situ measurements of bacteria, fungi, clorofila (generic and specific biogroups). The proposal intends to develop these sensors to be use inspace.

Non-competitive tendering is justified according to Article 6.1. d) of theContracts Regulations.


Activity Title: Peripheral Quantitative Computed TomographyDescription: Determining the effect of prolonged microgravity on bone histology is identified a

key scientific objective. This will require analysing inner and outer structures of legand arm long bones, in complement to wrist and heel bone assessment. Importantadditional data can also be yielded from bone marrow analysis, to get informationon bone cell activity. Based on the results of the related TRP activity " pQCTpreparation study", the aim of this activity is to specify, build and evaluate ademonstrator of an ISS-compatible pQCT (peripheral quantitative computedtomography).

Deliverables: Documentation, space-compatible pQCT technology demonstrator, evaluationreports, preliminary design of an ISS p-QCT and -possibly - of a breadboard forimaging small animals.

Instrumentation for Life Science



Activity Title: Continuation Miniature Fluorescence Microscope. PC - MiMiDescription: The aim of the activity is to complete the development of the Fluorescence

Microscope from the previous contract to achieve full scientific performance andintegration of all subsystem in the BIOLAB Experiment Container. The activity willbe focused on two major areas: The light path for the fluorescent mode inparticular for high magnification will be improved. This includes the redesign of theillumination optics adapted to the Laser light source and avoiding speckleformation due to coherence of the source. Additionally a miniature x,y,z movementsystem for the sample holder will be implemented (this was for budget limitationsnot included in the previous contract). This modifications and additions will beincluded in an overall optimised design, based on the lessons learnt during thedevelopment and testing in the previous contract.

Deliverables: Miniature Fluorescence Microscope demonstration model. PC+ operation S/W,Documentation

Justification for DN: The aim of this activity is to complete the development of the FluorescenceMicroscope to achieve full scientific performance and integration of allsubsystem in the BIOLAB Experiment Container. The FluorescenceMicroscope was initially developed, by Dutch Space and OIP, under ESAcontract 15656 (“Fluorescence Microscope”, 300 K€, funded by GSTP-3programme). Due to the specific know-how developed on the system aswell as the competences acquired by this team during the previousactivity, it is suggested to carry out the proposed continuation with thesame pool of companies.



Activity Title: Facility - Glovebox CombinationDescription: Life (and Physical) Science Facilities with an open life support system or critical

samples may require a permanent isolation from the cabin air loop. Neverthelesssamples and materials may have to be inserted in /extracted from the facility. Apotential solution for this problem is the integration of facility and gloveboxtechnology as a functional unit. A typical example is the Small Rodent Habitat(MISS). The aim of this activity is to develop a demonstrator combining the twotechnologies to one functional unit. Particular emphasis will be required on the(partially contradicting) requirements on life support, pressure difference, thermalenvironment etc.

Deliverables: Fully functional demonstrator of a facility glovebox combination (full functionalityonly required for the subsystems in question)

Justification for DN: Bradford Engineering is specialised in the supply of gloveboxes to theAgency and other customers. Bradford Engineering’s unique experience inthis field makes them the perfect choice for solving the problem of theintegration of facility and glovebox technology as a functional unit.




Activity Title: Ozone Based Sterilisation TechnologyDescription: The Biolab Glovebox (BGB) sterilisation system was the first Ozone based

sterilisation system to be used in space. This early development - despite itsqualification for Biolab - still leaves room for improvement. The main objective ofthis activity is to improve the Ozone sterilisation process and to develop a conceptfor a modular portable Ozoniser. Based on the experience with the previousBiolab Glovebox Ozoniser and the presently available technology, the designconcept for a Portable Ozone Steriliser will be established.

Specifically, the following tasks are foreseen:

1- Review of the state of the art of commercial Ozonisers, the lessons learnt fromthe Space Ozoniser development (BGB Ozoniser) and the range of potentialapplications.2- Concepts and practical demonstration via breadboarding of technologiesrequired for the Ozone sterilisation process3- Establishment of a space oriented design concept for a Portable Ozoniser(POROZ)4- Identification of the market potential of the portable Ozoniser concept andrequired modifications for specific commercial applications.

Deliverables: Concept for a Portable Ozoniser

Justification for DN: Bradford Engineering has developed the Ozone Sterilisation Technology(contract 12547, 2 MEuro funded by the Microgravity Facilities forColumbus programme) for the development of the Biolab Glovebox(including around 300 KEuro for the development of the Ozoniser). Thisproposed activity should be considered as a continuation of the initial workcarried out there.

Non-competitive tendering is justified according to Article 6.1c of theContract Regulations.


Ref. Number: G308-01EM Budget: 400 K€

Activity Title: European Drawer Rack SimulatorDescription: This activity shall have as an objective to enhance the simulator of EDR+PCDF

developed in the frame of a GSTP activity (PCDF Virtual Model and SoftwareSimulator) in order to render it fit to support maintenance of the EDR and PCDFflight software and to integrate future class-2 payload models other than PCDF.The main tasks will be-enhancement of subsystem models-integration of thesimulator into the CD-MCS operational environment-integration of OBC ERC32emulator able to run the real flight software-integration of flight software.

Deliverables: Simulator of EDR+PCDF integrated with an OBC emulation and the flightsoftware; Simulator integrated in the CD-MCS operational environment, to supporttraining of ground crew using the real operational consoles

Justification for DN: It is proposed to base this activity on an existing simulator of the EuropeanDrawer Rack and Protein Cristallisation Diagnostics Facility developed bythe consortium of SAS and ATOS Origin (Contract no. 16662, budget of700 K€ funded by GSTP-3). Therefore these companies not only have agood knowledge of this product but also have developed expertise on EDRand PCDF system and the adequate simulation techniques, which isessential for the simulation work.

Non-competitive tendering is justified according to Articles 6.1. a) and c) ofthe Contracts Regulations.

Instrumentation for Physical Science



Activity Title: High Resolution Diagnostics for Crystal GrowthDescription: A thorough understanding of the growth process of crystals requires real

simultaneous three-dimensional in situ measurements of the concentration field(s)within the boundary layers around the crystal(s) and of the shape(s) of thecrystal(s). To study crystal growth also in status nascence, it is of interest toobserve the growth matrix with highest possible resolution, to discover as early aspossible first concentration changes. Therefore it is the aim of this activity tocombine High Resolution Optical Tomography with Digital Holography to acompact microscopic optical diagnostic tool, where each tomographic view byDigital Holography will also be processed with respect to Visual Observation atdifferent focal planes. The activity therefore also must include the adaptation ofthe tomographic reconstruction algorithm to the projections created by DigitalHolography. An additional Digital Holography optical path might be addedperpendicularly to the tomographic planes to support the three-dimensionalreconstructions with additional information. The activity shall focus on the design,manufacture, integration, calibration and test of a breadboard demonstrator withthe potential to be converted into space hardware. The activity shall be finalisedby representative measurements on a Model Experiment.

Deliverables: Calibrated Operational Demonstrator of the new combined diagnostic tool. Newsoftware to derive the required 3D-matrix and shape data from the measureddata. Final Documentation containing the representative measurements, themanual for the instrument including its calibration and the s/w description.

Justification for DN: This activity follows on a previous TRP activity, “Fluid Science StimulationTechnology”, (contract number 15262 and 182 k€ of budget). As this teamof companies represents a single specialised source, it is proposed toaward the contract to it.

Non-competitive tendering is justified according to Articles 6.1. a. and c. ofthe Contracts Regulations.


Activity Title: Differential Thermal AnalysisDescription: The ESA topical team supporting the Material Science Lab (MSL) formulated the

demand for a specific insert for the MSL utilizing the Differential Thermal Analysistechnique. The method is appropriate to check complex phase changes as usualin ternary and even quaternary melt systems. Such systems are often industriallyrelevant as for example perovskites (High temperature superconductors!) andgarnets (Laser host crystals!) reveal with certain compositions such complexbehaviours. The proposed activity shall relate to a feasibility analysis as to howsuch this technique can be applied within the MSL as a dedicated insert. Furtherthis activity will deliver breadboards on the technology needed for such an insert.

Deliverables: Differential Thermal Analysis technique demonstrated with breadboards.



Activity Title: High Temperature Sensors with self-calibration capabilitiesDescription: Isolated technical solutions for temperature sensing at temperatures in the range

1500 – 2000 ºC have been studied in previous/on-going TRP studies (AdvancedTemperature Sensing, Improved Thermocouple Measurement). The performanceand lifetime of future high temperature furnaces will be limited by the temperaturesensor operational range and lifetime. At present no satisfactory solution exists forSQF (Solidification and Quenching Furnace, operating temperature 1800 ºC).Current commercial sensors suitable for LGF (Low Gradient Furnace )/SQF(Solidification and Quenching Furnace) type furnaces have severe problems withmeasurement drifts and saturation phenomena due to a breakdown of theelectrical resistance of the refractive insulator materials and problems with thethermo-mechanical stress. Furthermore, a built-in self-calibration capability byimplementing miniaturized carbon-metal eutectics are deemed necessary formonitoring accuracy vs. time. Potential Users include: Microgravity Facilities forColumbus, Materials Science Laboratory, SQF, LGF, future facilities for MaterialProcessing.

Deliverables: Sensor development effort (depending on outcome of on-going studies), testfurnace development/modification, sensor testing and inter-calibration, elegantsensors breadboard system.


Activity Title: IMPACT related technologiesDescription: The aim of this activity is to develop technologies required in conjunction with the

scientific operation of IMPACT (International Microgravity Plasma, Aerosol, andCosmic dust Twin facility). This includes: dust handling; cleaning procedures;diagnostic tools; dust/plasma-controlled manipulation via Laser, inductive orcapacitive manipulators. Critical technologies will be tested under short-termmicrogravity conditions e.g. parabolic flights.

Deliverables: Breadboards, procedures etc.

Justification for DN: Kayser-Threde was the prime for the “Phase B0 for an ICAPS/IMPFResearch Facility”, contract 17742, funded with 1,200 K€ in the ELIPSprogram. As the proposed activity is a direct continuation of that contract, itis proposed to select Kayser-Threde for the implementation of the tasksdescribed in this activity.




Activity Title: Development of single-walled sapphire cartrigesDescription: The objective of this activity is to produce 2 instrumented fully equipped prototype

single-walled sapphire cartriges with representative sample and fixation structure.

The science requirements for the Material Science Lab (MSL) at any timedemanded high processing temperatures at some 1,500 °C, with excellenttemperature stability together with high accuracy and rotating magnetic fieldapplication. The modular design of the MSL lead to two presently availablefurnaces inserts not fully covering these requirements. For example, the maximumoperational temperature is lower and the high temperature stability requirementsare achieved with some limitations only and also lower field strengths prevail atthe sample due to shielding issues. Also these two inserts do not allow for thepreformance of Zone Melting experiments, which necessitates viewing thephase-boundary between the melt and the crystal. Therefore saphire-cartridgesare needed.

The Floating Zone Furnace with Magnetic Field (FMF) developed by DLR, as aMSL insert copes very well to these requirements: ultra stable temperature controle.g. is performed via optical fibres, optical access to the sample via a borescopecamera arrangement was demonstrated and operational temperature andgradients are compliant with above established requirements together with theachieved higher magnetic field strength leading to the potential fullfillment of amuch broader experimental programme. Also this furnace enables the zonemelting process so far not available for ISS experimenters. The highertemperatures and the solved optical access issues for the FMF require use ofsapphire cartridges. Although a double-walled sapphire cartridge was usedsuccessfully in the FMF programme, its use calls for additionalrevisions/optimisations and component developments relating to e.g. thehermetical sealing, the applicable junction techniques for high temperatures andthe sample fixation, and tackling of thermal and shock loads together with the highthermal conductivity.

An identified sapphire/metal bonding technique shall be further developed,iteratively optimised, and verified. Hereto instrumented test cartridges (on COTSlevel) shall be manufactured and tested under realistic thermal conditions(preferably in the FMF-LM which should be available by mid 2006 at FreiburgUniversity). The major test objectives, whereas such testing needs therepresentative furnace configuration, would be to verify the bonding technique andto determine the temperature profile inside the cartridges. This will further lead tothe production of fully equipped and instrumented prototype cartridges, i.e. with arepresentative semiconductor sample and fixation structure, which shall bemanufactured and tested in the FMF-LM.

Deliverables: Newly developped and tested and verified for FMF(-LM) ready to useinstrumented saphire cartridges, enabling high processing temperatures withoptical thermal control and camera access.



Activity Title: X-ray Diagnostics for SpaceDescription: In the frame of the TRP contract "X-Ray diagnostics of Opaque Media", a

breadboard of a X-ray in-situ analytical system has been developed and tested todefine the performance and the range of applications. This developmentdemonstrated a good multidisciplinary applicability in Physical and Life Sciencesand the objective of this activity is the development of a technology demonstratorfor in-situ diagnostics of metallic processes (directional solidification of alloys) andverification of scientific performance (resolution, contrast, ...).

The development of this technology demonstrator includes a monochromaticX-ray source with high intensity and the imaging system. The technologydemonstrator will be already designed with an application on a sounding rocket inmind i.e. it will be a ruggedised system with a first optimisation on powerconsumption and mass. The performance of the technology demonstrator will beverified by application of the system to real scientifc set-ups with emphasis on thedirectional solidification, but not excluding interdisciplinary applications.


1.-Update of requirements from the previous TRP activity and potentialapplications; preliminary design concept

2.-Flight Design concept and technology demonstrator detailed design

3.-MAIT of Technology Demonstrator

4.-Scientific performance verification.Deliverables: Fully functional technology demonstrator for in-situ X-ray diagnostics; Test results

of scientific performance testing (including selected Life science applications)



Activity Title: Advanced payload laptop applicationDescription: Development is under way for the next generation on-board ISS procedure

viewer, the iPV. This development is partly funded by GSTP-3. The proposedactivity will take the current web-based iPV framework and extend it to fit in areal-time payload operations scenario. Extensions will be made so iPV cancommand and control an ESA payload accommodated in the European DrawerRack. Operational content for flight and ground operations (such as proceduresand displays) will be developed. Finally all SW and data will be integrated andtested against EM and/or FM of the selected payload. Current target is PCDF(protein crystal diagnostics facility) a drawer payload.

Deliverables: A complete set of ECSS-E40 documentation; software for the payload laptop;procedures and displays for the payload laptop.

Justification for DN: This activity is the continuation of the “Crew Informatics Technology”,contract number 12737, funded previously with an amount of up to 965 K€by the European Participation in International Space Station and theGSTP-2 and GSTP-3 programmes. Atos Origin has been involved indefinition and demonstration of laptop based operational interfaces, andthis company also has experience programming the ESA ISS real-timepayload controller, the SPLC. Thus, this company is ideally positioned toextend the iPV framework with an SPLC real-time connection. NLR haslong experience in preparation of operational products for payloadoperations, and ground payload operations. It is then proposed to awardthis contract to both companies, ATOS Origin and NLR.





Activity Title: Lightweight deployable structural protections against meteoroids and spacedebris

Description: The development of Columbus led to a double bumper protection with Nextel andKevlar materials used as second bumper. The enhancement of this protectionhas been investigated through the TRP contract 15512 with Alenia. The resultingconfigurations have reached the limit of the physics of protection. Newapproaches are needed to ensure the safety of space vehicle for long durationmissions. The objective is to assess the performances of different lightweightdeployable protections against meteoroids and space debris. The aim of the workis to achieve a 30 percent mass reduction for a protection able to defeat aprojectile with 100 KJ kinetic energy, compared to state-of –the-art protections (31kg/m2 including main structure).

Justification for DN: The enhancement of this protection has been initially investigated in theTRP contract 15512, “Material Procurement and Sample Manufacturing”(323K€), with Alenia. The resulting configurations have reached the limit ofthe physics of protection. New approaches are needed to ensure thesafety of space vehicle for long duration missions. As this company hasthe required experience and this activity is the continuation of the previousquoted contract, it is proposed to award this contract to Alenia.



Activity Title: Membrane Gas Trap Technology Demonstrator for ColumbusDescription: Under ESA contract, an MGT has been developed and tested against Columbus

water loop degassing performance requirements. The technology looks verypromising. However, the achieved performance was only at 33% of the flow. Theproposed activity is a follow-on activity covering the development of a MGT gastrap TD in form, fit and function (FFF) meeting the Columbus water loopdegassing requirement. The technology demonstrator shall include all Columbusimposed safety features and shall also be subjected to environmental testing(vibration test) and extended lifetime performance testing (resistance to microbiological growth) using the real coolant water quality.

Deliverables: 1 MGT TD unit, spare membrane modules, Design and Test documentation.


Ref. Number: G312-05QQ Budget: 350 K€

Activity Title: Safety Risk Evaluation and Certification for use of Batteries in COTSdevices

Description: This study will assess the risk impacts on the use of batteries in COTS deviceswith respect to dependability, safety, and PA requirements, and collect all theresults in an ESA Handbook for Safety certification of batteries in COTS. In orderto reduce costs for re-certification, the approach for Safety certification of Batteriesin COTS will take into consideration a Probabilistic Risk Assessment (PRA)methodology. The study should include considerations regarding the impacts ofemerging technologies of possible wide use in few years. Exchange of data withNASA should be envisaged.

Deliverables: Technical Notes (addressing the expected tasks) and the ESA Handbook forSafety Certification of Batteries in COTS.


Activity Title: Optical modeling of corner cube retro-reflectors (CCRM)Description: During the production of retro reflector targets for the ATV rendezvous and

docking navigation systems (optical), the need has arisen for the accurate testingand modellisation of the optical performance of corner cubes both as singleelements and when combined in arrays. This study will address that need with theproduction of a rigorous approach to the problem and the formulation of aparametric high fidelity model compatible with existing commercial optical raytracing software (Code5 and Zemax).

Deliverables: Rigorous raytracing algorithms incorporating geometric, diffraction,thermo-mechanical and straylight effects. Hardware test and validation of theoutput from the software under realistic conditions with representativecomponents.


Ref. Number: G312-08EZ Budget: 800 K€

Activity Title: ERASMUS Facility Responsible Centre Operational EnvironmentDescription: As a continuation of the activities currently on-going under GSTP-3 concerning the

ERASMUS FRC (Facility Responsible Centre), it is proposed to extend and tofinalise the following products and services needed by this facility as part of itsOff-line and On-line Operational environment.a) Off-line Operational environment:- Archiving. The ERASMUS FRC and the B-USOC will define the utilisation modeof the EDR (European Drawer Rack) and EUTEF housekeeping and experimentsdata archive (long term archive, science data archive). The work will consist in theintegration, test and initial operation of the archive.- Planning tool. A tool to plan the operational experiments of the PCDF (ProteinCrystallisation Diagnostics Facility) and the resources of EDR will beimplemented. The work will include integration, test and initial operation.- Simulation Facilities. Following Phase 1 of the EDR Software Simulator activity,the cost to completion estimate has been reviewed. In addition to the completionof the developments foreseen under Phase 2, the need for commissioning (Phase3) of the EDR and PCDF Virtual model and Software Simulator has beenidentified. The commissioning phase shall start after the Phase 2 development ofthe EDR and PCDF Flight model is completed and shall consist in the validationand updating of the simulation models against the delivered flight units of EDRand PCDF. A training programme of the ERASMUS FRC and B-USOC personnelby means of the Simulator shall be defined and initiated.- EDR and PCDF Multimedia Site. A multi media Server providing future users ofEDR, PCDF and EUTEF with technical and programmatic data shall be created.The work shall include content provision and maintenance of the Server.- EDR Ground Support Equipment (EXGSE). The EXGSE will provide interfacesand resources compatible with the EDR to allow development, interface testing,and operation of EDR payloads on ground. The work will consist in the installationand maintenance of a self-standing EDR environment at the B-USOC byinterfacing the EXGSE to the PCDF Engineering Model.

b) On-line Operational environment:Voice Keysets, on-line archive, front-end workstations and facility operationsdisplays shall be installed in the ERASMUS FRC and B-USOC infrastructure asrequired.

Justification for DN: The proposed activity is a continuation of the following 3 GSTP activities:G00/H70.EZ-001 - EDR Drawer/Locker GSE; G00/H70.EZ-002 - PCDFVirtual Model and Software Simulator; G00/H70.EZ-003 - EDR Class2Payload Operation Test (ESA Contracts no. 16662, 16710 and 16728respectively, with an overall ESA contribution of 1,900 K€).




Activity Title: Operations Data File (ODF) Procedure ViewerDescription: The International Space Station (ISS) will be operated in flight by a multi-national

crew. The astronauts will follow instructions that are prepared by the experts onthe ground with “procedures”, grouped into the “Operations Data File” (ODF).They will operate the many complex systems and scientific elements and deviceson-board following these instructions, which will be presented to the crew onlaptop screens with an ODF viewer. ISS partners are jointly maintaining astandard for the structure and format of manual interactive crew procedures foreffective in-flight operations, the ODF Standards.

n this regard the proposed activity will cover work to finalize the implementation ofthe multilaterally agreed baseline of the ODF Viewer (iPV – internationalprocedure viewer) on ISS flight laptops and ground control stations. Technologyused for this Web-based interactive documentation application includes UML,XML and Java. This phase of the development (which is a joint ESA/NASAundertaking) will see the Viewer mature to flight product status. Activities requiredto reach this goal include:

- Modification and adaptation of Viewer based on feedback from operational useof the software in ground simulators and control centres.- Establishment of facilities for sustaining engineering of the software products.

Justification for DN: The initial phase was implemented through a D-MSM funded contract withAstrium (D) with Skytek (IRL) as subcontractor, awarded after an opencompetitive tender procurement process. This phase was concluded in2002 with a formal delivery of the preliminary version of the ODFprocedure authoring tool and associated ODF procedure templates.Subsequent riders merged that output with achievements made inprevious GSTP activities so a capable Viewer of the procedures could beproduced. That effort led to the multilateral decision to fund the new ODFViewer for ISS via GSTP (see ESA/IPC(2003)4). Hence, the activity willserve as a continuation to the previous work mentioned above (ESAcontract no. 14464, funded by ISS programme with 1,245 K€ and 555 K€from GSTP).




Activity Title: Next Generation Telescience Support UnitDescription: The Telescience Support Unit (TSU) is a self-contained unit that consists of a data

handling and transmitter/receiver assembly that is able to acquire, process, andtransmit microgravity experiment data to the ground. It was previously flown onthe Foton capsule, where it was in use by the Fluid Physics Facility (FluidPac).More experimenters on Foton express their wish to take advantage of the TSUfunctionality, but the TSU can only support one user at a time. This activity shallproduce a redesign of the Telescience Support Unit to support multiple users,acquisition of high-resolution video images and an increase in downlink capacity.To accomplish this, a distributed architecture is proposed. Such architecture shallconsist of data/video acquisition units, located near the different experimentcontainers, communicating directly with the respective experiment controller orcamera. A central data handling and management unit collects and distributesdata between the acquisition units.

Deliverables: A breadboard of a redesigned TeleScience Support Unit to demonstrate thetechnology.

Justification for DN: Since the beginning of the Telescience Support Unit project, in 1995, theSwedish Space Corporation has been prime contractor for this ESAdevelopment. During this time they have shown extensive knowledge andexpertise regarding the technologies involved in this field. At the presenttime this is the only known company in Sweden working on similartechnologies for space applications.

Non-competitive tendering is justified according to Article 6.1.a of theContracts Regulations.

Payload Data Handling



Activity Title: TSU ground network developmentDescription: The Telescience Support Unit (TSU) is a self-contained unit, consisting of a data

handling and transmitter/receiver assembly that is able to acquire, process, andtransmit data from a spacecraft to the ground. It is currently used during the Fotonmissions. Data from the Foton experiments are transmitted via TSU to PrincipalInvestigators located at the Esrange ground station and at the User Home Bases(UHB). For the Foton M3 mission the TSU will undergo a complete overhaul toallow all the payloads of the mission to be served by it. TSU will also adoptCCSDS space communication standards, which will allow the use of differentground stations. Telescience will finally be possible to the extent that PrincipalInvestigators sitting in their UHBs will have the ability to interact with theirpayloads several times a day having their data/commands being seamlesslyrouted through the ground station in sight of Foton. This proposal suggests usingthe DREAMS software to distribute data/collect commands between the Fotonreceiving ground stations and the Principal Investigators. DREAMS is a genericsoftware package that contains most of the functionality needed to distribute anddisplay data/collect and verify commands over a network. DREAMS has beendeveloped in the frame of the GSTP and used in some ESA activities, where ithas proven user-friendly and reliable. The work includes the definition of therequirements for data distribution/command processing from the TSU groundsegment; the design of an architecture for the TSU ground segment; theimplementation of that design; and the demonstration of the implementation.

Deliverables: System model demonstration in a relevant environment.

Justification for DN: This proposal deals with using the DREAMS software, developed byTrasys (B), to distribute data/collect commands between the Fotonreceiving ground stations and the Principal Investigators. DREAMS is ageneric software package that contains most of the functionality needed todistribute and display data/collect and verify commands over a network.DREAMS has been developed in the frame of the GSTP (JERICHODEVELOPMENT AND INTEGRATION, Contract no. 12522 with a totalbudget of 1,200 K€, funded by the GSTP and Corporate funds) and usedin some ESA activities, where it has proven to be user-friendly andreliable. Based on this unique experience and know how, and on there-use of elements from previous projects, the company is in a position tofulfil the proposed objectives of the activity in a very effective way.



Theme 4.- SPACE TRANSPORTATION & RE-ENTRY TECHNOLOGIES


Activity Title: Facetted Thermal Protection System (TPS) PanelsDescription: Within the last 20 years in Europe several different TPS types have been

developed and at least ground-qualified. The assemblies are used to insulate thecold vehicle structure from the high external aerodynamic heat loads during there-entry phase and to keep them within their temperature limits. The TPS designgenerally has to consider the outer mold line of the vehicle, which is usuallydefined by the aero-thermodynamic design. Consequently the TPS has a curvedand sometimes complicated three-dimensional shape, where basically each panelis unique. This requires e.g. complex tooling and drives considerably the cost ofthe TPS. A system with a small family of in them identically shaped facetted TPSpanels approximating the outer mold line might have the potential of considerablyreducing the effort and cost for the Taste objective is the development of afacetted TPS system consisting of identical small panels with a limited number ofdifferent shapes. The facetted TPS system shall be based on already existingTPS assemblies, e.g. CMC standoff panel TPS. A possible demonstrator vehiclemight be the German Shefex demonstrator.

Deliverables: Study reports and demonstrator design.


Activity Title: Surface Protected Flexible Insulation (SPFI)Description: The SPFI (Surface Protected Flexible Insulation) has been developed and partly

already qualified in recent years as a Thermal Protection System (TPS) for thewindward side of re-entry vehicles. It consists of a CMC cover plate with aninternal flexible insulation blanket underneath. Different techniques have beendeveloped and tested to mount the cover plate directly to the insulation blanket.These include bonding as well as the use of a standoff system. The objective ofthe activity is the further improvement of the existing SPFI system, in particular: 1.Reduction of mass by replacing the current 4-layer CMC protective cover by anew cover using the 2.2 D weaving technology; 2. Reduction of maintenance andrepair effort by improvement of the fixation system in order to simplify theexchange of individual SPFI panels; 3. Reduction of the integration effort by thedevelopment of large (600mm x 600mm) panels together with a suitable sealingtechnique.

Deliverables: Status, study and test reports. Test samples.

Justification for DN: The technology to be used for this activity has been already pre-developedat EADS ST GmBh (D). This company is therefore found to be the onlyone capable of doing such a job within the budget and schedule foreseen.

Non-competitive tendering is justified according to Article 6.1.a. of theContracts Regulations.

Advanced Hot Structures and Thermal Protection Systems



Activity Title: Advanced Ball Bearings for Expendable Cryogenic Engine TurbopumpsDescription: In order to improve the reliability and performances of cryogenic TurboPumps

(TP) ball bearings for future expendable engines and, based on outcomes of lastdevelopments performed on bearings (Cronidur-30 rings + Silicon Nitride balls),this activity is intended to investigate 3 identified further developments axes:-Optimisation of inner rings heat treatments; Heat induction or nitride solution willbe investigated in order to achieve the optimum performances of the Cronidur-30material between, the fatigue of the ring, wear and Stress Corrosion Crackingresistance.- New cage material, design and dynamics; Design, manufacture andtest of several bearing cages under cryogenic environment. Materials, such aspure Teflon, Rulon or Salox, having superior lubricating and wear properties thantraditional ones will be investigated and integrated in a specific cage frame.-Investigation of Hybrid bearing configurations; Assessment of roller bearingssuitability for requirements of TP environment. A Hybrid bearing configurationconsists on combining pure axial pure radial load bearings. Then, stiffness,dynamics and load capacity are improved. In addition, this configuration leads tointegration time reduction and assembly phase simplification.

Deliverables: Technology samples (bearings for full scale testing) + relevant documentation +test results.


Activity Title: Cost reduction of launcher valvesDescription: Based on a valve market survey, the most promising valve type/size currently in

serial production at Techspace Aero will be selected for assessment of design andmanufacturing enhancements leading to a substantial cost reduction atcomponent and integration level. Considering the cost reduction to be achieved inthe manufacturing process, min. 30 % is expected, the design and assemblyprocess will be optimized and resulting design and technology modificationimplemented in the valve. For example, the following promising concepts for costreduction will be assessed: mechanical elements such as cryo compatible boltlocking, metallic equipment vibration dampers, sliding seals, new valve bearingtechnology and use of new (metallic and non-metallic) materials. Newtechnological concepts are verified by test and analysis at component level. Theflow part will be optimized using existing analysis tools and real scale tests. Theactivity will result in a demonstrator model that is functionally and environmentallytested and can be prepared for serial production. Upon demonstration of theidentified cost reduction in the study potential cost reduction for other valve typeswill be identified applying the above methodology.

Deliverables: Breadboard of enhanced rocket valve including actuator.

Justification for DN: Techspace Aero is the main manufacturer of Ariane launcher valves inEurope and their expertise and valve technology is essential for thesuccessful implementation of the proposed activity.


Advanced Liquid Propulsion



Activity Title: Electric actuators for fluid control in launch vehiclesDescription: In the frame the GSTP-2 and GSTP-3, Techspace Aero has designed,

manufactured and tested the valve specific elements of an electrically actuatedregulation valve of butterfly type. The actuator is of rotary type. Other valve types(poppet, ball) using linear and rotary actuators based on hydraulic/pneumaticsources need to be replaced by electric actuators as well. The proposed activitycovers: Requirement specification, design, manufacturing, assembly and testingof a valve demonstrator. After classification of technical specifications ofpneumatic actuators for valves and selection of future candidate applications,electrical actuator concepts for launcher valves are selected. Breadboard modelswill be designed, manufactured and tested for cold and hot temperatureapplications (20 K and 1000 K). Extreme temperature tribology and vibrationcontrol are covered in the development and testing. Dynamic sealing is ofparticular concern for safety reasons.

Deliverables: Breadboard model of electric-actuated valve

Justification for DN: Techspace Aero has gathered extensive experience for electricallyactuated valves. In addition, they currently execute a valve tribologyresearch programme. This activity is a continuation of previous activities inthe GSTP-2 and 3 programme (contracts numbers 11244, 16491 and17250). Techspace Aero has designed, manufactured and tested the valvespecific elements of an electrically actuated regulation valve of butterflytype.The actuator is of rotary type. Other valve types (poppet, ball) usinglinear and rotary actuators based on hydraulic/pneumatic sources need tobe replaced by electric actuators as well.The proposed activity covers: Requirement specification, design,manufacturing, assembly and testing of a valve demonstrator.




Activity Title: Study on Flow Separation Phenomena in Rocket NozzlesDescription: The objective of this activity is to investigate the basic characteristics of the

phenomena inside the nozzle divergent section, and the physical origin of the sideloads in classical nozzle configurations. In particular, the possible generation ofthe "inviscid separation phenomenon", and its role on the occurrence of regimesof "free" and "restricted" flow separation will be addressed.

During the nozzle operations in overexpanded regime, a flow separation in thedivergent section may take place, whose asymmetric character can yield sideloads on the nozzle wall, with consequent major structural problems. Thesephenomena may also occur during the flight because of the buffeting effectscaused by the re-circulating flow at the launcher base.

A numerical campaign will be performed for TIC nozzle geometry. The runs willconsider both the basic nozzle shape and several cut shapes, obtained bytruncating the basic nozzle at different lengths. Moreover, also different PR will beconsidered. The choice of the shapes, truncation lengths and PR will be selectedsuch to allow comparison with the experimental data available. The comparisonwith experimental data will allow to validate the CFD approach and also willprovide important information on the role of turbulence and its modelling on theflow structure. Based on the results obtained in Part 1, a numerical campaign willbe performed considering the basic nozzle shape at different pressure ratio, tounderstand the possibility that a flow reattachment takes place because of theexistence of the flow re-circulating region in the divergent core. In particular, it willbe studied if such a region is able to trigger the transition from free shockseparation to restricted shock separation, which represents the worst condition forthe generation of high side loads.

Deliverables: Technical Reports.

Justification for DN: The proposed activity is a continuation of a previous GSTP3 activity(Contract 16301, 180 k€) with Univ. di Roma. Moreover significant work insimilar areas has been carried out by Univ di Roma.


Ref. Number: G402-07MP Budget: 1,400 K€

Activity Title: European 1N Hydrazine Flow Control ValveDescription: The objective of this activity is the development of a 1 N Flow Control Valve,

together with the testing and qualification of a hydrazine compatible valve for useon scientific/navigation spacecraft.

The activity will be split in three Phases, covering the following tasks:

Phase 1. Technical requirements from thrusters manufacturers, adaptation of thedesign done in the GSTP3 activity, tailored to TA requirement specification, takinginto account Galileo needs and existing thrusters interface requirements (Snecma,EADS ST, Ampac), up to a concept review. Critical technologies, samplesmanufacturing and testing, valve breadboard manufacturing and testing, tests ofBB at thrusters manufacturers facilities, test means studies up to PDR review.Phase 1 Deliverables: PDR datapack including test results as presented above,market analysis and specifications.

Phase 2: EM (2 models) manufacturing and tests. End of phase with valve CDRwith agreement to proceed to valve Qualification.Phase 2 Deliverables: CDR datapack including development test results used tojustify the design, Manufacturing and Inspection plans, Qualification test plans,design justification with analyses or reference to testing as appropriate.

Phase 3: Valve qualification testing with concluding with Qualification review.Qualification test programme including life cycle testing, environmental testing,and valve performance characterisation. Mounting of the valve onto a thrusterchamber and nozzle assembly for flow performance testing including live firing inboth pulse mode and steady state conditions.Phase 3 Deliverables: QR datapack including full set of performancecharacterisation and life cycle test results.

Deliverables: See deliverables per phase as specified above.

Justification for DN: This activity is a continuation of the work developed by the contractor inthe GSTP-3 activity "Development of a Propellant Flow Control Valve for1-20 N Thrusters" (contract number 18247, 350K€). It is recommended tocontinue the work with the same contractor.




Activity Title: Passive Damping of RLV StructuresDescription: For future reusable spacecraft structures containing composite materials vibration

loads are safety critical, mass relevant as well as lifetime reducing. During theforeseen long life of a reusable launch vehicle (RLV) the structural stresses andstrains caused by dynamic loads can be reduced by a targeted increase ofmechanical damping. The purpose of this activity is the development, design andexperimental testing of passive damping methods, which can be applied for awide range of composite (and other) structures. The here proposed activities arefocused on concepts where friction elements are integrated between the layers ofsandwich panels. It is foreseen to verify the functioning of the damping devices inexperiments as well as to apply and develop methods to predict the attainabledamping effects. Further possibilities for application in future RLV technologies,mass saving as well as life-span extension potential of such passive dampingdevices are subjects of investigation. It is well thinkable to transfer the technologyto further application in aircraft- or automotive engineering.

Deliverables: Reports of the development, design and experimental testing of the passivedamping methods.


Activity Title: High Temperature Light Weight CMC Roller Bearing with Low Coefficient ofFriction

Description: CMC sliding bearings developed for X-38 body flap show high coefficients offriction (COF) resulting in high wear rates, heavy load introduction and highactivation forces. Considering this technology at the basis of any movable controlsurface for future space transportation systems (attachment and movement of hotcontrol surface like body flaps, rudders and elevons), it is considered of utmostimportance to investigate in this innovative direction. The objective of theproposed activity is to develop and manufacture a CMC high temperature rollerbearing with low COF and experimental qualification in a thermo-mechanical test(max. 1600 ºC in air) with dynamic movements.

Deliverables: CMC high temperature roller bearing and qualification results.

Advanced Materials



Activity Title: Layer by layer, low energy electron beam curing process for compositestructures

Description: There is a growing interest of European and US aerospace communities for curingprocesses based on Electron Beam Radiation. This interest is mainly focused onthe manufacturing of large and thick composite structures, due to the mainfollowing advantages: low cost tools can be used due to limited thermal risesduring curing, very low production of volatile compounds, Energy savings. Theobjective of the activity proposed is to develop out of autoclave processes forcomposite structure curing by optimising and developing the layer-by-layer lowenergy curing process. The activity will include also an economical analysis basedon the evaluation of materials, tooling and machines to be used (tow placementcoupled with low energy electron beam mobile accelerator).

Deliverables: Reports and economical analysis.



Activity Title: Visco-elastic Damping Embedded within a CFRP PanelDescription: The aim of this activity is the development, analysis, design and testing of

visco-elastic damping devices integrated within a CFRP sandwich structurerelevant to space structures. The embedded visco-elastic device shall reduce thevibration foreseen throughout the lifespan of the structure. The damper shall becapable of reducing vibration amplitudes from both acoustic and dynamicenvironment but excluding shock, transient vibrations and to some extendvibroacoustic effects. The main objective of this activity will be to test abreadboard model with the integrated visco-elastic damper and to compare theadvantages and disadvantages of this technology with other type of embeddeddamping device such as Coulomb friction based damping. The improvement indamping will be measured against parameters such as added mass, complexity,cost...etc, so that future ESA projects can take educated decision upon whichtechnology to select in order to fullfill their mission objectives.

The following tasks are envisaged within this activity:

• Design and analysis of the demonstrator breadboard(s), materials selection,manufacturing and breadboards testing. Each breadboard shall constitute acomplete structural system that allows evaluation of the benefits of the designmaking use of passive damping. In addition, test coupons shall be manufacturedwhere development tests, relevant to the breadboard(s), are required (e.g.bonding strength test).Testing shall as far as possible simulate the relevant flightloads and environment. If feasible/applicable, it shall include testing of a similarstructure like breadboard(s), but without the integral passive-damper device as adirect comparison.• Based on the outcome of the breadboard testing campaign, possibleimprovements of the design shall be considered/proposed and the developmentand evaluation plan updated as far as integration of the demonstrator into a biggerstructure is concerned. The result of this evaluation is to obtain a more optimiseddesign as input for the concluding study of this technology support program.• Finally, a dedicated application study shall be done, addressing such points suchas the impact of environmental condition “Space”, potential difficulties inmathematical treatment of non-linearities of such devices including properprediction of the mechanical characteristics, impact on damping characteristicswhen using long-term (e.g. booms or antenna in orbit), tuning to differentfrequencies.

Deliverables: Technical Notes, and test reports.

Justification for DN: The SPADD (Smart Passive Damping Device) technology, proposed to beused in this activity is patented by ARTEC (CND). This technology isbased on visco-elastic material, and it has been space-qualified andmounted onboard various satellites such as Stentor, Intelsat, Inmarsat,Integral, Métop, W3A and Amazonas. It has also been used on Arianne toreduce the vibrations generated during launch phases. Hence, ARTEChas a quite relevant experience in this area as well as a patented product,with flight heritage, that could be embedded within honeycomb panels toreduce the vibration level on ELV, RLV and spacecraft. It is then proposedto carry out the tasks of this activity in direct negotiation with ARTEC(CND).

Non-competitive tendering is justified according to Articles 6.1. a) and d) ofthe Contracts Regulations.


Ref. Number: G406-01MZ Budget: 300 K€

Activity Title: Dedicated generally bi-disciplinary coupling of disciplines for spacevehicles

Description: The proposed work concerns the bi-coupling of disciplines to provide experiencesand solid test cases of industrial interest. The different proposals (each for theamount actually needed, the sum given here is the estimate for a steady-stateproblem) shall correspond to the different coupling opportunities. It is, however,not excluded that e.g. two parties tackle the same problem if they use differentapproaches to be able to compare the efficiency and success of employedapproaches. The work may also include the derivation of reduced modelling usefulfor one-dimensional analysis tools or concurrent design work (e.g. in ESTEC'sCDF). The problem of validation by means of experiments needs to be addressedas well. Selected considered flow cases are expected to become potential testcases for the use of the generic multidisciplinary tool suggested to be developedin the frame work of a parallel TRP project. The Agency would provide mutualvisibility of the parallel TRP and GSTP progress. Parties are invited to apply forthe different projects as suitable.

Deliverables: Sample cases for coupling 2 (or depending on in-house developments more)disciplines. Comparison of experiences in carrying out such coupling. Test casesfor a generic more general tool allowing for the addition of more disciplines.Possibly modelling relations for use in one-dimensional or CDF environments.

Aerothermodynamics (ATD)



Activity Title: GNC Design and Analysis Tool Environment for Reusable SpaceTransportation

Description: A typical reusable space transportation system mission profile consists of severalbranches, such as take-off, ascent, orbital/sub-orbital phase, entry, terminal areaand landing. The performance of the vehicle in each branch influences thesubsequent branch in terms of initial conditions and vehicle parameters. In thelight of the preceding, to analyze the influence of the different mission parameterson the studied branch, and subsequent ones, a software tool for analysis ofmission sensitivity and derivation of critical GNC requirements shall be developed.The tool will be derived based on existing analysis tools and already developed byGMV S.A. The tool shall enable the sensitivity analysis of the mission parameterson the mission profiles, supporting the selection, design and analysis of vehicleconfigurations and reference missions. The tool shall contain a library withdifferent vehicle configurations, whose flight dynamics capabilities can beanalysed for several mission scenarios, as well as an extensive set ofrepresentative sensors, actuators and GNC algorithms for RSTS. In addition, thetool shall be capable of generating 6DoF closed loop real-time and faster thanreal-time simulation runs, and able to accept as a guidance profile an optimaltrajectory or trajectory arc coming from the ESA optimizer ASTOS. The planetaryenvironments targeted are the Earth and Mars.

Deliverables: - GNCLAU new release and associated documentation (user's manual); -Documentations (technical notes, final report and abstract) on, but not limited to,GNCLAU enhancements for sensitivity analysis of each mission arc of typicalRSTS mission

Justification for DN: Different mission profiles and vehicle configurations are under evaluationas baseline for future reusable space transportation system. To identifymission capabilities of each proposed configuration, a mission sensitivityanalysis tool allowing proper derivation of GNC requirements is required.

GMV S.A. has developed and upgraded recently for the European SpaceAgency a software tool called GNCLAU for GNC analysis of advancedreusable launchers. GMV S.A., due to their in-depth knowledge in thedevelopment of GNCLAU and reputation in mission analysis and GNCdesign for launchers, is in the best and unique position to successfullysupport the Agency for enhancing the capabilities of the above tool withinthe time and effort foreseen in this activity. It is then suggested to placethe new contract as a direct negotiation with GMV S.A.


Avionics and GNC



Activity Title: Spacialisation of VTI SCA 600 MEMS accelerometersDescription: The smart sensors realised using MST (micro-System Technology) have already

proven the great interest in the other fields of applications like automotive,medical, geophysics, etc. Today, some of these devices are commerciallyavailable, and they have shown great advantages in terms of reduction of mass,on board power, to give higher performance and probably lower overall costs.These devices are often referenced as MOTS (MEMS Off The shelf), are thecommercial devices that are not specifically designed and fabricated for use inspace harsh environments but which can be "spacialised" with minimum technicaland financial efforts. This is the case of the VTI SCA 600m accelerometer chipseries addressed in this proposal. Strong collaboration between VTI and EADSST (Les Mureaux) will be encouraged. Some tests like vibration, shock, thermalcycling, radiation, etc have already been initiated by EADS ST and the test resultswill be communicated to VTI; they should confirm the reliability of the SCA 600devices.VTI will start by investigating the amount of efforts required for a"spacialisation" of the SCA 600 accelerometers to launcher applications. Afteragreement with ESA the necessary development and manufacturing for upgradingthe accelerometers will be performed. It is anticipated that this will certainlyinclude development of adequate hardened or suitably shielded read outelectronic. Adequate testing will then validate the space upgrading of the SCA 600series. A commercial evaluation will be perform to investigate and possiblyenlarge the scope of the spacialisation exercise to other space applications(AOCS, science, etc)

Deliverables: Reliability status of the SCA 600 accelerometers series. Spacialisation &validation testing programs, commercial evaluation, final report. 5 Space GradeSCI 600 accelerometers for ESA analysis.

Justification for DN: ESA and EADS ST are presently investigating possibilities to reduceoverall launcher and space vehicles costs by using MEMS Off The Shelf(MOTS) for producing miniaturised sub-telemetry units. The SCA 600accelerometer chip series from VTI Hamlin in Finland have been identifiedas the most potential suitable European candidate to compete with state ofthe art US accelerometer and easily upgradable to launcher application.This activity aims at confirming the reliability of the devices and atpreparing it for possible application on Ariane V. As the SCA 600accelerometer chips series have been developed by VTI, this companyhas a unique and complete knowledge of the system and it is likely to bethe best group to efficiently carry out the tasks included in this activity.



Ref. Number: G408-06MX Budget: 700 K€

Activity Title: Avionics Architecture for future Reusable Space Transportation SystemsDescription: In support of future reusable space transportation systems, the following avionics

technology elements shall be analysed: an integrated fault-tolerant avionicssystem architecture, which guarantees safety and reliability at low maintenancelevel, a modular system concept approach to achieve low-cost maintainability anda high degree of commonality between future reusable space transportationprogrammes (crew transport and RLVs), advanced space-qualified avionicscomponents, in particular standardized fault-tolerant network elements, whichmeet the performance requirements and which are available during the life of theprogramme, as well as standardized avionics software services, designed formulti-platform applications, to streamline the software qualification andmaintenance process.

Deliverables: Analysis report of Avionics Architecture for future Reusable Space TransportationSystems

Ref. Number: G408-09MX Budget: 1,450 K€

Activity Title: Man Machine Interface Technology Integrated ApplicationsDescription: This activity aims at updating the mission and vehicle design achieved in a

previous activity done in this area and the MMI requirements baseline. Also, it willinclude the design and implementation of the cabin mock-up; the development,refinement and implementation of the MMI technologies to provide a high quality,seamless and integrated MMI user experience; the set up and the establishmentof the mission simulation; an extensive evaluation in simulated mission scenarios;and the performance of human factors analyses and demonstration of safetyimprovements obtained. Finally it will try to Iteratively improve the MMIexperience.

Deliverables: Requirements baseline; technical specification; mission definition; missionsimulator; cabin mock-up; design definition file; design justification file; MMIsoftware and user manual; test and evaluation plan.

Justification for DN: Both companies have established the process for developing high qualityMMI for manned space vehicles and have developed and tested MMI inflight tests and in vehicle simulations under contract no. 16778 (1,350 K€funded by GSTP).




Activity Title: Advanced Flight Measurement Techniques for Aerothermodynamics andTPS Re-entry Applications

Description: Development and improvement of techniques for in-flight measurement of criticalaerothermal properties, TPS characteristics and specific flow variables, bothon-board and off-board hypersonic vehicles are key elements required for thefuture demonstrator vehicles. Smaller and more accurate sensors, as well asadvanced non-intrusive measurement techniques are to be developed. Thedevelopment concerns detailed numerical sensitivity analysis as well as prototypeassembly activities leading to integrated subsystem testing in relevant hypersonicwind tunnel and plasma facilities. The following scientific instrument (payloads)and their integration into the TPS are proposed:1. Flush air data systems and Nose heating sensors such as Raflex and Pyrexintegrated into NOSE cap.2. Instrumentation associated with flap efficiency and heating such as C-SiCdeveloped pressure sensors, high temperature thermocouples integrated ontogeneric flap elements. Embedded IR or other non-intrusive techniques.3. Advanced intrusive and non-intrusive techniques for measurement of catalysisand oxidation of samples integrated into TPS4. New TPS methods and approaches such as UHTC, Phase change techniquesor cooled TPS methods having reached a sufficient TRL level for in flightdemonstration and qualification on potential follow up EXPERT flights.5. Non-intrusive and miniaturized laser technique developments for real gaschemistry measurements in the shock layer such as emission spectroscopy(RESPECT) and LIF (Laser Induced Fluorescence)6. Reflectometers for signal attenuation measurements (black out)7. Other temperature, pressure or gas surface interaction measurementtechniques

Deliverables: FTM developments, qualification results, wind tunnel models and flight hardware;emission spectroscopic data; improvements of pyrometry and infraredthermography methods for ground based facility and flight testing; improved andextending pressure range for EBF (Electron Beam Fluorescence); qualifiedsensors for nose cap and flap region Schedule; reflectometers; advanced TPSmethods qualified for flight prototype testing


Activity Title: Tools for the study of dynamic stability of (re)entry vehicles in thetransonic/supersonic regime

Description: The objective is to develop improved tools to characteristic the dynamic stability ofre-entry vehicles based on lessons learned. The objective is to apply these free totumble techniques for re-entry vehicles such as EXPERT and planetary probes ;typically the free to tumble technique is very advantageous for configurations withlarge base and where the sting ( used with classical forced oscillation techniques) perturbs the dynamics of the wake. It will focus in the design andimplementation of experimental set-up in a transonic / supersonic facility in orderto characterise the dynamic stability of (re)entry vehicles. Specifically, it willinvolve the following tasks: development of forced oscillation mechanism;development of free to tumble mechanism; implementation of force balanceadapted to the new environment; and application on a well-known vehicle forvalidation of the set-up and methodology


Ref. Number: G408-12AO Budget: 4,000 K€

Activity Title: TMVS-AVKIT: TM avionics sub-system kit for TM transmission via satellitelinks for launch-vehicle applications

Description: The advantages of using satellite links for launch vehicles TM transmission hasbeen identified in terms of operational flexibility, low cost and launcherperformance. This application requires a specific TM sub-system kit able tooperate in the launch environment and to transmit, in a continuous way, the wholelauncher TM through satellite links.

The development of such a sub-system can be split in three parts: Avionicsdevelopment and ground tests; In-flight demonstration; Integration in alaunch-system for operational use.

This activity is initiated in GSTP upon request of D/LAU and is focused on the firstof the three parts mentioned above: avionics development and on-ground tests,specifically in the development and qualification of a TM subsystem kit (i.e.:transmitter, power amplifier & antenna) for TM transmission via satellite links forlaunch-vehicle applications. The “kit” feature is an essential goal of thedevelopment in order to ensure an easy implementation and multi-userapplication. The following main tasks are foreseen:

1.- transmitter adaptation/development compatible of launch-vehicle environmentand requirements;2.- power amplifier adaptation/development compatible of launch-vehicleenvironment and requirements;3.- antenna adaptation/development compatible of launch-vehicle environmentand requirements;4.- subsystem integration and qualification/acceptance tests;5.- simulated demonstration test (using ESA ARTEMIS S/C).

Once this activity is successfully accomplished, several in-flight demonstrationopportunities can be envisaged either within the frame of the GSTP programme oras part of a launch-system programme. In any case, that should be implementedat launch-system level, covering the integration of the kit in the launch vehicleavionics bay as well as all the necessary launch-system analysis and tests.

The use of satellite links (i.e.: ARTEMIS, ATV) has already involved thedevelopment of similar equipments. However, its application for launch vehiclesrequires the adaptation and/or development of equivalent avionics with respect tothe specific launch environment and compliance with the associated performancerequirements. The “L-Stars” study (under ESA contract no. 13590 in the frame ofthe GSP programme) identified the main requirements and constraints as inputsfor the design of the TM kit for launch vehicles applications.

Deliverables: Engineering models; qualification models; industrial products definition files;subsystem qualification file; kit user’s manual; associated software (operatingsystem and application software).

Justification for DN: The mentioned company has a unique experience on this type of avionicsand application, which was developped during its participation assubcontractor in the a prevoius development. (i.e.: development in theframe of the ESA Contract 12010/98/NL/AB - ATV Flight Segmentdevelopment) Moreover, the short time available from now until the 1stintended application (2nd ATV launch) requires a diligent approach.

Non-competitive tendering is justified according to Article 6.1.a fo theContracts Regulations.



Activity Title: TVC Hbrisc2 Software Environment IndustrialisationDescription: The objective of this activity is threefold: to reduce the costs of validation and

operation of the TVC (Launcher Thrust Vector Control) SW; to increase theconfidence in the produced TVC SW; and to enhance the competitiveness of theVEGA operational phase and future Ariane electrical TVC.

Benefiting from two previous GSTP-2 and GSTP-3 activities: “Integrated MotorController for Mechanisms (IMCM)” (covering the development and qualification ofthe HBRISC2 micro-circuit and of the first generation of development tools); and“HBRISC2 Tip-tilt mechanism (TTM)” (covering the command of a tip-tiltmechanism with HBRISC2), the present GSTP-4 activity shall cover the following:

1- Development of Synthesizer Plus. Evolution of the SW development tooldeveloped by GSTP-2 (Synthesizer) resulting in Synthesizer Plus SW(executable) with design & validation documentation and user manual. Theapplication range of this generic tool covers present and future TVC for Launchersbut is not limited to those applications. Over the existing tool, the main progressesof the Synthesizer Plus are the capacity of generation of multiple binaries from asingle model and an increased confidence in the produced code. 2- SERACQ Board. To develop a reliable HSSL acquisition system (a PCperipheral board with embedded control SW); for which there is an urgent need(according to the VEGA TVC SW PDR, its use is now foreseen also during systemand stage level tests).

3- Automated SW test bench. To develop an auxiliary tool for SW validation,namely low level (HW tight) MACRO's.

Deliverables: Each SW tool with design & validation documentation and user manuals; 4 Itemsof SERACQ Boards with relevant cabling.

Justification for DN: The proposed activity is a continuation of two previous GSTP activitiescarried out by SABCA (B), contracts numbers 13492/06 (200 K€ funded byGSTP-2) and 18242 (500 K€ funded by GSTP-3).



Ref. Number: G408-16AP Budget: 500 K€

Activity Title: SCARAB Software for Ariane Upper Stages Atmospheric Re-entryAssessment

Description: Scarab is an integrated software package developed under ESA for the analysisof uncontrolled re-entry and destruction of satellites, space debris and otherobjects in the atmosphere (re-entry trajectory; thermal, structural loadscomputation). This software package is regularly used as one of the worldreferences in the frame of operational mission analysis (i.e. the MIR re-entryanalysis).

The initial analysis performed for Ariane covered the analysis of the central corestage of Ariane 5 (EPC) re-entry phase as a validation step with a comparisonwith information available from re-entry observations. In the framework of the ATVlaunch scenario, the destructive re-entry analysis of the composite EPS-VEB wasanalysed. The analysis of the re-entry scenarios of the new cryogenic ESC-Astage is on-going with a fully loaded stage with two satellites and supportingstructures.

During these studies, it turned out that the re-entry analysis of launch vehiclestages demands a modelling and an analysis of special phenomena and featureswhich are not required for satellite re-entry scenarios. Obvious differences tosatellites are: extreme high ballistic coefficient, high fuel loading (cryogenic orhypergolic) higher than the empty launcher mass in non-nominal scenarios,danger of tank bursting and/or explosions, etc … Those aspects were treated onrequest but independently from each others. This leads to useful analysis resultsbut relying on different software codes (explosion break-up model, re-entry codefor explosion fragments …) not directly linked to each others. This situation makesthe scenario analysis and assessmen complex and cumbersome due to therequired processing of data between the different codes.

Therefore, it is needed to clean up completely the software developed so far andto make it fully traceable, to verify the individual new models introduced, to takeadvantage of all new features introduced in the SCARAB version 3.0, as well as amore friendly user's interface to introduce and define particular requirements.Implementation of a full 3 phase material database and thermal analysis for liquidpropellants, which includes the freezing and vaporisation state (vaporisationalready included) is needed. Stochastic rather than deterministic analysis shall beintroduced to be selectable when and where necessary. A better knowledge andmodelisation of the behaviour of specific material used in the launcher design(composite materials) shall be also introduced. The software shall be tested orre-run with real test cases.

Deliverables: Software package fully validated, with the associated documentation, asrequested by ESA. Dedicated technical notes on specific developments (explosionmodelling, tank bursting, characterisation of materials, …)

Justification for DN: The basic software code of SCARAB is an integrated software packagedeveloped under an ESOC contract (15756) with HTG (HyperschallTechnologie Göttingen) in Germany. Taking into consideration that thiscompany has led the SCARAB development since 1995, and based ontheir unique expertise, only HTG can fulfil the proposed tasks within thegiven budget and time allocation.




Activity Title: TAS 3-E Flight Qualification (Extended Tri-Axial Accelerometer System)Description: This activity aims at qualifying the extended version of the Tri-Axial Accelerometer

System (TAS 3), capable of acquiring, processing and storing acceleration dataalong three orthogonal axes.

TAS 3-E is the extended version of the TAS 3 acting as a complete stand aloneinertial monitoring system capable of measuring, processing and storingacceleration and vehicle attitude, thanks to additional sensors implemented inextension modules. Subject to mission requirements, these modules couldaccommodate one or several sensors, like Magnetometer, MEMS Gyro, MEMSAccelerometer, GPS, ...

TAS 3 has successfully flown on the Foton M 2 mission. The Foton M2 missiondemonstrated that TAS 3 measurement bandwidth can be extended from 10mHzdown to 0.1mHz by data post-processing (incl. calibration for magneticdisturbance). The measurement of the magnetic field, performed inside the Fotonre-entry capsule by another subsystem were used to determine the attitude of thespacecraft (angular rate accuracy ±0.01°/s, angular position accuracy ±1°), whichdemonstrates the feasibility of the approach.

The Flight Qualification of TAS 3-E system will :

- Extend the Foton-M3 inertial characterization from vibration measurement toquasi steady acceleration measurement (bandwidth 0.1mHz to 10mHz; resolution0.01µg); attitude measurement (accuracy ±1°); and angular rate measurement(accuracy ±0.01°/s).- Flight Qualification of the TAS 3-E for launch and re-entry vibration and shocks;orbital phase micro-vibration characterization; characterization of short durationevents (e.g. separation phase, 0.2s) with angular rate accuracy < 0.3°/s andattitude change accuracy < 0.5°; and orbital flight characterization (similarperformances expected as on Foton-M3).

The activity will include the following tasks:

1.- Preliminary design: block schematics, component selection, evaluation ofengineering budgets2.- Procurement of the magnetometer sensors3.- Detailed design: electronic and mechanical design of TAS 3-E I/F boardaccommodating the additional sensors.4.- Manufacturing and performance test of an EM TAS 3-E.5.- Manufacturing and test of a FM TAS 3-E suitable for the Foton M3 mission.

Deliverables: TAS 3-E System performance demonstration report.TAS 3-E FM with 3 magnetometer sensors suitable for the Foton M3 mission.

Justification for DN: The work to be carried out in this activity is continuation of thedevelopment of the Tri-Axial Accelerometer System done by Redshift (B)under ESA contract 18291, and funded with 610K€. It is then proposedthat the same entity develop the tasks proposed in the description of thisactivity.

Non-competitive tendering is justified according to Article 6.1c of theContract Regulations.


Ref. Number: G408-18VL Budget: 3,000 K€

Activity Title: System requirements evolution impacts on P80 TVD DesignDescription: This activity covers two major issues:

• to refine the TVC subsystem performances to follow new system requirementsand to resize TVC components accordingly.• to implement ESA standard EEE parts procurement policy customized for theVEGA application, for the digital and power electronics of a 35 kWelectro-mechanical actuation system.

The Nozzle actuation system (TVC) dynamics is tightly coupled to the LV systemdynamic and flight control loop. It is a typical problem in this field to early definethe system requirements for TVC dynamic performances that are sizing for theTVC S/S. This task is even more complex when electro-mechanical actuators areconcerned due to the intrinsic non linearities and low damping of suchservomechanisms. Another difficulty exists concerning the way to specify dynamicperformances and the kind of S/S analyses outputs that fits system levelverification needs. VEGA project has achieved such tasks but the relevant effortcould not be well estimated at the time. On the other hand the evolution of the LVmechanical design and configuration studies have lead to a redefinition ofmechanical interfaces and equipment packaging.

Equipment packaging is also constrained by the second major tasks of theproposed activity: the implementation of ESA standard EEE Parts ProcurementPolicy. The initial P80 TVC contract was based on the re-use of the contractor(SABCA) heritage based on the development of similar application in theaeronautic business domain where the use of commercial EEE parts is a normalpractice. Afterwards, VEGA developed a tailoring of standard ESA EEE PartsProcurement Policy called VG-SG-1-C-032-SYS Issue 5/1 that was madeapplicable to the P80 TVC development program. This has lead to a significantre-definition of the TVC electronics equipment and to associated costs to managethe procurement of higher quality parts.

The activity shall carry out the following tasks:

Dynamic Performance tuning: to refine the P80 TVC S/S dynamic performanceanalyses, tracking the evolution of the system needs consistently with the fact thatthe system analyses and design are run with anticipation with respect to S/S ones.This includes the investigation of different approaches for requirementsspecification and verification.

Dynamic Performance verification: to finalize and tune the TVC S/S simulationmodels; to perform a significant amount of simulations in order to give the systema set of performance data in a format consistent with system analysis tools andmethods.

TVC equipment's design refinement: to rework IPDU (Integrated PowerDistribution Unit) and EMA (Electromechanical Actuator) design to fit the newsystem level requirements; to release manufacturing updated IPDU and EMAB/B's.

IPDU re-design: IPDU is the electro-mechanical TVC electronic controller. Itincludes a digital module (DCM) and a Power Module (PM) and its preliminarydesign was based on commercial items. Passing to standard parts leads tore-design because of different available components packaging andperformances. Also, the re-design activity has to be based on refined TVC overallperformances and new mass/volumes/interfaces definition as a result of the abovementioned refinement of system needs.


Implementation of SG-1-C-032-SYS Issue 5/1 EEE Parts Procurement policy: Toestablish the policy and manage the EEE Parts Procurement and the applicableESA rules for PCB manufacturing and parts soldering.

To achieve this the activity shall be split among the following tasks:1.- Participate to working meetings with the system design authority with thepurpose to refine and tune the TVC performance that cope with system needs andto define a common framework that enable exchanging needs and data betweensystem and sub-system team and tasks2.- To perform simulations to verify the system performance requirements and tofinalize TVC components sizing (e.g. power and energy budgets, IPDU powerdrivers, batteries, EMA electrical motor, EMA mechanism components like rollerscrew, gears, etc.)3.- Re-design of the IPDU4.- Procurement of the EEE Parts5.- Manufacture of the redefined IPDU B/B and EMA B/B6.- Increase of the IPDU models to be built

Deliverables: Validation of TVC S/S performances;Validation of TVC S/S simulation models;TVC S/S Transfer functions for System level Analyses.Updated EMA B/B Definition and Configuration files.Updated IPDU Definition and Validation files.EEE Parts Procurement Plan, PAD's, etc.IPDV and EMA

Justification for DN: This activity is a continuation of the work developed by the contractor inthe GSTP activity related to the development of the P80 (contract number15919, 11,600K€). It is therefore recommended to continue the work withthe same contractor.



Activity Title: Component technology for high power motor drive electronic for Launcherapplications.

Description: Electrical Thrust Vector Control (TVC) for the next European launchers need veryspecific components, both for control purpose and for power devices. Suchcomponents can be specific integrated controllers, or high power devices. Suchpower devices can be 1200V/300A modules or 200A precision current sensors.Those components are not currently available in Europe with the properqualification level, suitable for civil launchers and space applications. The aim ofthis activity is to define and validate a qualification roadmap for European existingcomponent compliant with the power TVC specifications. The perenniality aspectis major in this process.

Deliverables: Power electronic components



Activity Title: Integrated Vehicle Health Management System DemonstratorDescription: An activity to design, develop and test prototype Vehicle Health Management

(VHM) software's for reusable space transportation system (RSTS) has beeninitiated. The main outputs of this activity will be prototype health management onand off board software's, and a vehicle health management testbed, withhardware in the loop capabilities, for real-time performance assessment of thebaseline HMS software prototype(s). At the end of the above activity there will bea proven concept of an Integrated Vehicle Health Management System as well asassociated on & off board software prototype(s) for reusable space transportation.However, some necessary development steps are required to extend the existingapproach in various directions: -Development of a multi-domain object-orientedmodelling environment tool for the development of model-based diagnosis (on andoff board), from requirements analysis to auto code generation, based onmodelling standards such as Modelica;-Definition of a common, softwarereference architecture for IVHM system to reduce development and integrationcosts;-Performance benchmarking of the multi-domain object-oriented modellingenvironment tool-Detailed investigations on safety procedures validation and(semi) automatic assistance to ground operations in case of contingency ordecision over complex multiple constraints, and maintenance approach forcomplex and recurrent vehicle system-Reconfigurable control and faultidentification system demonstrator, i.e. combined IVHM and GN&C systemsintegrated and tested in the reusable space transportation software prototypingreal-time testbed with hardware in the loop.

Deliverables: Multi-domain object-oriented modelling environment tool; Reference S/Warchitecture for IVHM on-board and off-board; Reconfigurable control and faultidentification system demonstrator; Related Technical Notes and Test Reports.


Activity Title: High Temperature, High Dynamic Range, Fast response Pressure Sensorsfor the spacecraft and launcher propulsion subsystem

Description: The requirements for pressure sensing in the combustion chamber and nozzles ofspace launchers shall be defined and a special pressure sensor operating in hightemperature (2000 C), with high dynamic range and with fast response shall bedesigned, developed and tested under pragmatic tests conditions. The workprogram of this activity will involve the definition of the sensor requirements and ofthe conditions of operation (operational temperature, range of pressuremeasurements, accuracy of temperature measurements etc); the development ofa sensor device and the performance of initial tests including assessment of thematerials to be used; the manufacture of the sensor prototype; the·implementation of the interrogation unit with redundancy·; and the test andassessment of the performance of the sensor arrangement in a relevantenvironment.

Deliverables: A prototype of a high temperature, high dynamic range, and fast responsepressure sensor.

Health Management Systems (HMS)



Activity Title: Fiber Optic Sensors for Structural Monitoring of the Ariane LauncherDescription: This activity shall define the sensing requirements of the Ariane launcher and shall

design, develop and test a fiber optic sensor system for health monitoring of theAriane launcher. The work program shall involve the definition of the specificationsin terms of the environmental conditions and the required sensor performance; theadaptation of suitable fiber optic sensing techniques according to performancerequirements and operation environment; the design of the distributed networkbased on the launcher layout; the design of the multiplexing technique in order toachieve optimum balance between high degree of multiplexing, complexity andredundancy; the manufacturing of the sensors prototype and of the interrogationunit; and the verification through testing in the structure of Ariane.

Deliverables: A prototype system of a fiber optic sensor Health Monitoring System along with allrelated reports, designs, simulations and videos.



Activity Title: High Speed Tunable Laser Interrogator for Spacecraft Health MonitoringDescription: The main objective of this activity is to develop an interrogator suitable for

dynamic measurement of a large number of multiplexed sensors that is suitablefor operation in harsh launch vibrations.

Monitoring of various parameters in modern spacecraft (satellites, launchers,probes) is required to provide necessary information on the condition of thespacecraft and its various subsystems (AOCS, thermal, propulsion, power,mechanisms etc). As an example, the Ariane 5 launcher requires the monitoring ofover 1,000 sensors during qualification flights. This places a high demand on thereliability and performance of the sensing system which must provide accuratedata in a very harsh operating condition. Fibre optic sensors, and in particularFBG (Fiber Bragg Grating) technology, has proven itself to be a very reliablemethod of monitoring a number of parameters including strain, temperature andpressure providing high quality readings that are immune to EMI (ElectroMagneticInterference). In addition the optical fibres themselves offer a low loss, low masssignal harness which means that the interrogation can be made at a largedistance from the measurement point. These advantages and the ability tomultiplex large numbers of sensors on a single strand of optical fibre lead to thepossibility of creating an effective health monitoring system for large spacecraft.Currently several interrogator systems exist that use various detection principles,including CCD (Charged Couple Device) detectors, tunable lasers or arrays ofband pass filters, however these are generally limited in either the multiplexingcapability and or dynamic performance.

Hence this activity proposes to design and build an interrogator based on fasttunable laser which shall fullfill the monitoring needs of a large spacecraft such asa launcher. Emphasis will be placed on producing an interrogator that is robustand suitable for operation in the launch environment. In addition the contractorshall address the multiplexing requirements of such a large structure examingways in which several hundreds of sensors can be interrogated simultaneously.The interrogator shall also be suitable for measuring accelerometers and strainsensors where the data is of a dynamic nature requiring the measurement systemto have a high measurement bandwidth. The following tasks shall be carried out:

1.- Establish the interrogator specifications2.- Perform preliminary design and tests to verify performance3.- Build representative unit optimised for mass power and designed in such away as to be suitable for use in the launch environment.4.- Test demonstrator according to approved test plan (vibration, shock andthermal).5.- Analyse results6.- Conclusions and further recommendations

Deliverables: Interrogator and technical documentation.

Justification for DN: Are the only European manufacturer of FBG interrogator based on tunablesemiconductor lasers. This technology is seen as a very promising forreaching the multiplexing and dynamic range required in large spacestructures while being suitable for operation in the launch environment.

Non-competitive tendering is justified according to Article 6.1.a) of theContracts Regulations.



Activity Title: Control of pressure oscillations in a cold flow model of solid rocket motor.Description: The process of fluid/structure coupling in real, hot engines cannot be studied and

observed experimentally because of the hostile gas environment. Therefore cold,simplified set-ups are needed to understand the basic principles. The cold gasfacilities allow a clear understanding of the driving parameters and are needed toidentify the best possibilities of passive control of the oscillations. Suchidentification in real hot engines would be much more expensive. The obtainedresults form a database for future validation of numerical models and hence theprediction of pressure oscillations in real engines.

Deliverables: Proposal for passive control of the pressure oscillations in a model simulating theaeroacoustics and fluid/structure coupling phenomena present in solid rocketmotors; generation of internal flow field and related acoustic field typical for solidboosters.

Justification for DN: In the framework of the A5 solid booster design, VKI (Von KarmanInstitute) was asked previously by CNES to investigate and identifyexperimentally on a cold test bench, the origin of vortices within thecombustion chamber and their acoustic coupling with the cavities locatedat the base of the solid rocket engine. Hence, VKI have gained a uniqueexperience in the particular difficulties linked to boosters and also relatedto its simulation on a cold test bench. Moreover,VKI has the necessarycombination of windtunnels, measurements techniques and experienceavailable to easily extend and adapt their previous experimentalinvestigation towards the present study. VKI has already set-up a modifiedwindtunnel and tested an adapted measurement technique for slagaccumulation.


Solid propulsion


Theme 6.- GENERIC TECHNOLOGIES

Ref. Number: G606-01GS Budget: 800 K€

Activity Title: Industrialization of Ka-band frequency convertersDescription: High performance prototype Frequency converters have been designed for Deep

Space applications. Deep Space Ka-band allocations are from 31800 to 32300MHz for the downlink and from 34200 to 34700 MHz for uplink. The main RFperformance improvements that have been achieved, respect to commercialconverters, are the following: very low phase noise characteristic, mandatory fordeep space application; phase stability in the order of 7 electrical deg/Kelvin,mandatory for deep space ranging; breadboards of one 3-channel down converterand one channel up converter have been developed by means of TRP contracts,with excellent technical results. The developed breadboards shall be completedwith a proper monitor and control interface. Ad-hoc analysis shall be performed inorder to reduce the components costs by maintaining high performance, asrequired by Deep Space missions. Integration, maintainability, interface shall beoptimised, to come to a product fully deployable in ESA tracking station, as well asin any other third party station.

Deliverables: One 3-channels Ka-band down converter and two Ka-band single channel upconverter. Relevant industrialization design documentation.

Justification for DN: This activity is the continuation of the previous research done by ESA forthe development of high performance frequency converters. In this sense,Alcatel Bell Space has successfully designed and manufactured aprototype Ka-band down converter, contract number 17143, (430 K€funded by the Scientific Programme) and has a done a study for aprototype Ka-band up converter, under contract number 17460 (250 K€funded by TRP). It is thus proposed to continue the development of highperformance frequency converters, with the industrialization processdefined in this activity.


Advanced Ground Station Technologies and Tracking Methods


Ref. Number: G606-03GI Budget: 250 K€

Activity Title: Ground-segment engineering and operational configurationDescription: The complexity and the variety of the ground-segment components augment

regularly. The difficulty to centralise the overall ground-segment engineering andoperational configuration in terms of services, configuration items, operationalconfiguration, network configuration, increase operational and engineering risks interms of reliability. The study shall provide the Agency with a suitable architectureand recommendation for automatic operational and engineering configurationreporting mechanisms. In particular the study shall:-Review and analyse the ESA ground-segment elements such as to derive theconfiguration components that belongs to individual elements (e.g. Operatingsystem version and patches, Communication configuration, Applicationconfiguration). The analysis should also include a review and a definition of theprovided services.-Specify a generic configuration format that covers all identified configurationitems of the various ground-segment elements.-Elaborate a system architecture able to retrieve the configuration reports of thevarious ground-segment elements-Investigate the best technology approach for the configuration format and itsreporting to a possible central system.-Investigate the impact of such an approach on the various concernedground-segment elements.

Deliverables: Technical reports and Final Study Report covering:-Configuration file format to be implemented on the various subsystems-Architecture of the future configuration report system.-Evaluation of existing tools on the market.-Related recommendations for technology choices and standardisation activities.-Impact analysis of this new system on the existing ground-segment components.



Activity Title: An Advanced M&C System for ESTRACK Ground StationsDescription: In the next future, ESTRACK ground station operations will be faced with a

number of challenges that reflect an increased number of spacecraft using thestations, a much denser utilization pattern, increasing demands on automationand introduction of new services. Some examples of these new challenges are:support of 'lights-out' routine operations in the GFCC; automation ofuplink-handover between ground stations; automated activation of backupequipment in the ground stations; direct access to telemetry data-streams at theground station by ESA- and non-ESA mission customers; etc. The objectives ofthe study phase for the proposed activity will be to:-Determine the impact of these challenges on ground station M&C-Derive user-level requirements for the next generation of M&C systems-Specify services to be exposed by the M&C system-Define workflows for groundstation operations (i.e. sequences of service-request, internal functions andservice-response)-Define a functional architecture for a future M&C system.Then, in the definition phase the activity will be devoted to:-Identify enabling technologies from the IT-marketplace (such as e.g. softwareagents, open distributed systems, e-business and web services, ManufacturingExecution Systems MES, security systems) which promise adequate, economicand durable solutions-Demonstrate automation potential for M&C operations by implementing selectedrequirements in a demonstrator on the basis of recommended technology

Deliverables: -A comprehensive collection of user-level requirements covering conventionalM&C functions and the forthcoming M&C challenges.-An outline architecture for a new M&C system for ESTRACK ground stations.-Specification of M&C services and of related operations workflows.-Analysis of enabling Information Technology and implementationrecommendations.-Implementation of a demonstrator for M&C automation.


Activity Title: Remote Monitoring and Control of Complex SystemsDescription: There are different situations in which it may be necessary to monitor and control

remotely the behaviour of complex software systems composed of severalmachines and tasks running in parallel. For instance, it is very common that themission and science control systems are physically located in different places, andthey require two dedicated teams. In addition, future big multi-mission systems willrequire the control of a high number of machines and tasks. The aim of thisactivity would be the design of a control system based on current infrastructure(SCOS-2000) to be used for the monitoring and control of other systems, such asseparated science data processing systems, or multi-mission systems. Theproposed approach is:-Centralised SCOS-2000 mission control system for the processing and filing ofdata received from different heterogeneous systems-Multi-platform agents (possibly using SNMP protocol) running on the differentmachines gathering information to be sent to the central monitoring system, andresponsible of the execution of commands sent from the server-Fully configurable system to be used for different applications

Deliverables: System requirements; system design; SCOS-2000 based prototype.



Activity Title: Generic Exchange Format and Interfaces Standardisation for GroundSegment

Description: At present, every new mission defines their own exchange formats for theinterface between the different systems as part of the ground segment. As thedata volume and complexity of most of the subsystems within the ground segmentincrease, an efficient and homogeneous data description, storage and transfermechanisms is becoming mandatory at different levels. The exchange of datathrough complex interfaces has traditionally been a drawback, which has oftenrequired specific implementations for each different mission or scenario.Furthermore, current trends and initiatives at European level have detected agrowing need for information sharing from several and multiple sources. Tosupport that demanding scenario, the starting point must be the definition ofcommon representation paradigms that allow sharing the information and thereuse of subsystems. Initiatives for standardisation, based on XML have beenlaunched in several fields. This activity will have 2 Phases:Phase 1:The aim of this activity would be the definition and prototyping (usingSCOS-2000) of a standard format (possibly based on XML) for the exchange ofdata between systems, including: -Database information, to share the contents ofthe spacecraft database, -Telemetry data exchange, so external systems accessto telemetry data, -Telecommanding requests exchange, so external systemsrequest the execution of commands in the spacecraft -Events and messages,-Scientific data, considering different types of missions (earth observation,astronomy, etc.)Phase 2:The aim of the proposed activity would be the definition of a multipurposelanguage, XML based, that allows for describing as metadata (catalogue) theinformation stored in the archiving systems for EO data; describing a querylanguage that supports broadcasting the queries to several databases assuringthe same search criteria in different environments; provide well defined andstructured formats standardising the way in which the data is delivered; definitionof intermediate file format to exchange data between different archiving facilities,which do not employ the same processing systems.

Deliverables: -Exchange format definition, -management tools, -libraries implementation,-Language definition, -Prototype Tools, -SCOS-2000 prototypes


Ref. Number: G606-07OF Budget: 200 K€

Activity Title: Improved approach to Verification & Validation on the SVFDescription: This study deals with the problem of test writing on the Software Validation Facility

(SVF). The study shall evaluate and demonstrate the use of PLUTO and ASE forTesting on the SVF. The SVF provides a test bed for OBSW anomalyinvestigation and for the validation of changes to the OBSW. Tests on currentSVFs are specified in languages such as TERMA's Sil. Due to the low abstractionlevel of the test writing language, the writing of tests is complicated andtime-consuming, limiting the OBSM engineer to simple and narrow-lined tests withthis potentially powerful facility. There is a need for more convenient and morepowerful ways of writing tests on the SVF. Additionally, ESA has initiated a trendtowards harmonization between check-out systems and mission control systems,with one of the results being the definition of the Procedure Language for Test andOperations (PLUTO). PLUTO is supposed to be used for specifying procedures tobe run during satellite checkout on the EGSE as well as for specifying operationalprocedures to be run during mission operations. Important part of the PLUTOconcept is the Space System Model (SSM), which is a model representation of theelements PLUTO operates on, making PLUTO general and independent from theactual facilities for which procedures are specified. The Automatic SchedulesExecution (ASE) Framework is a PLUTO-compliant procedure executioninfrastructure, aiming at the automation of Mission Control System procedure.ASE offers powerful ways of specifying schedules of PLUTO procedures. Thegeneral idea is to have the user specify SVF test procedures with ASE andPLUTO, with the interface to the SVF being encapsulated in the SSM. The SSMmight include models of the SVF (testing language) facilities with which the testwriter interacts as well as a model of the OBSW and OBSW environment. Aspecific set of OBS functionality (Onboard Schedule operations, for example) willbe selected and used to provide a concrete environment for the comparativeevaluation of the current and proposed approaches to test specification andexecution.

Deliverables: A demonstration and an evaluation of, the usage of Pluto & ASE on the SVF toperform testing in the selected functional area.



Activity Title: Experimental High Data Rate Ka Band Down Converters for Near EarthMissions

Description: Missions requiring very high data rates will use the 25.5 - 27 GHz band for thedownlink. Alternatively the 37-38 Ghz band will be used. A frequency converterwith specific performances for Near Earth (up to 2*106 Km), very high data rateoperation is required to allow the operation of this band. Some performances shallbe driven by the specific characteristics of the mission that will employ this band.This study will cover the technological trade-off and the design and building of aprototype suitable to be deployed on a ground station and establish theperformances of this band. Critical design issues will be: -Frequency plandefinition avoiding interferences with the existing units.- Trade off between filteringand linear distortion for wide bands (up to 1.5 GHz)- Linearity of output stageswith the higher levels imposed by the high data rates and the fixed Eb/N0.- Phasestability, noise and spurious. A prototype will be manufactured to validate thedesign performances and allow the future experimental validation in an ESAstation of the link. Potential users of this technology are missions like Lisa, Gaiaand Darwin

Deliverables: Reports including trade-offs, design justification and design definition; prototype ofa 26 GHz very high data rate down converter.


Activity Title: High performance 8-PSK-TCM demodulator in Generic PlatformDescription: To study and implement a High performance 8-PSK-TCM demodulator (lower loss

but medium bit rate < 8 Msps) in a Generic Platform, as the GDSPs of the IFMS.This would allow ESTRACK to cover the full ECSS-E-50-05A. RF & mod.Standard, once the GMSK is implemented. Losses should be less than 0.3 dB atthe selected rates, in order to take the maximum advantage of this efficientmodulation scheme. Higher rates than 8 Msps would be interesting, but are notfeasible within the IFMS, and are probably also difficult to implement in a genericplatform. The development shall be complete, fully tested and also includingmonitoring and control, in order to be incorporated in the operational ESTRACKnetwork.

Deliverables: Development reports. Test Procedures and results. Prototype in IFMS andpreparation for deployment in operational IFMS.

Justification for DN: The proposed contractor has developed the platform that should be usedfor this development, in the frame of the contract 18081 (funded with 2 M€from the General Budget) and it is thus the only company that has therequired knowledge to successfully accomplish the tasks described in thisactivity.




Activity Title: Fine grain traffic performance monitoring software toolDescription: Ground segment real-time systems that were up to now confined in a single

location tend nowadays to be geographically distributed. This implies the use ofsecure and highly available wide area communications links near the limit of theirperformance capabilities. It also imposes stringent requirements for both shortand long term service performance levels. The proposed activity aims at building aspecific traffic monitoring tool that extends the capability of classical (long term)network performance measurement systems towards providing fine grain (shortterm) analysis of time-critical traffic, down to the packet or message level. Thesoftware tool will combine existing technologies of non-intrusive (passive) trafficinspection with distributed monitoring functions (in order to characterize thesource data flows). Both types of data will be combined by a reporting and alertingsystem, which will also be able to take into account security and encryptionaspects, in order to compute the required metrics.

Deliverables: Requirements and architectural design documents; pilot software tool for finegrain traffic performance monitoring; reports; demonstration of the tool on a typicalESA ground segment communications network.

Justification for DN: Ubizen Aethis has successfully completed activities under GSTP-2(Integrated network management for future ESA operational network –IMS, contract no. 12245 with a budget of 250 K€), and its continuationunder GSTP-3 (Integrated Network and security management forOPSNET – SIMS, contract no. 13948, budget of 475 K€). The resultingdeliverables have been rolled out in ESOC for both the IGS(Interconnection Ground Subnet) testbed and for OPSNET, in particularlong term performance monitoring software tools for network devices,computer systems and perimeter security components. The proposedactivity is a continuation of this technology into the domain of managementof highly time critical networks.



Ref. Number: G606-11SW Budget: 500 K€

Activity Title: Advanced Traffic Performance Monitoring tool for time-critical groundcommunications networks

Description: Applications supported by ground stations networks are becoming more dynamic,inducing feedback loops and interactivity in telemetry/telecommand applications.Their communications will therefore imply needs that prevail today in real-timeenvironments: supporting ground networks will not only be driven by long term(macroscopic) availability, performance and security requirements, but will alsohave to offer short-term (fine grain) quality of service.

Fine grain traffic performance monitoring software tools, able to measure the shortterm performance of these networks, are therefore required. In this sense, theprototype software tool TrafMon was done under a previous GSTP contract. Thattool combines existing technologies of non-intrusive (passive) traffic inspectionwith distributed monitoring functions to characterise the source data flows. Bothtypes of data are then combined by a reporting and alerting system in order tocompute the required metrics.

The objective of this activity is to enhance and validate the current TrafMonprototype in order to develop a pre-operational pilot version of an easy-to-use toolfor the traffic performance monitoring of time-critical communications links. It willprovide fine grain (short term) analysis of time-critical traffic, down to the packet ormessage level, as an extension of the capability of classical (long term) networkperformance measurement systems. The current available prototype is focusedon the core issues of raw data acquisition, centralisation and processing but, dueto limited resources, does not yet tackle adequately data anaylsis, reporting andpresentation aspects. It needs to be further enhanced and validated in a real-lifeenvironment in order to reach sufficient functionality, usability, maturity, scalabilityand robustness to be deployed and operated in ground segments communicationsnetworks control centres.

The following tasks are identified in the two phases of this activity:

Phase 1.- to build a real-life validation and demonstration environment using an ESAground segment subnet;- to increase scalability and robustness of the different modules of the TrafMonsystem (probes, central processing engine, database and report generator);- to support precise GNSS based time-synchronisation between the source anddestination sites;- to build a report writer with additional functions such as on-the-fly aggregation ofraw data in the database, provision of near real-time automated reports, detectionof abnormal events, generation of proactive warnings and alarms upon deviationfrom the performance baseline, attractive graphical user interface adapted tonetwork operators.

Phase 2.- to develop extra plug-in adaptors to support additional protocols andapplications;- to develop additional analysis modules, such as baselining and latency profilecorrelation, service level management for data link providers, support to linkqualification procedures, support of secure networks.

Deliverables: Technical data and reports; Pre-operational pilot TrafMon software tool ready forinstallation in ESA ground communications networks; Test reports on thevalidation and demonstration on a typical ESA network.


Justification for DN: The tasks proposed in this activity are a direct continuation of the work forthe TrafMon technology already developped in the contract 19203, "FineGrain Traffic Performance Monitoring Software Tool" (funded by GSTP-4with 250 K€). Ubizen Aethis (B) has successfully completed this contract,leading to a tested prototype version and to its installation at ESTEC in theGalileo communications networks test laboratory.

In addition, Ubizen AETHIS has built over the last years a wide expertisein the monitoring of complex and heterogeneous operationalcommunications networks. More specifically, the company has acquiredknow how and experience in the combined area of monitoring andmanagement of secured networks, and in implementing distributedmanagement software. It is recommended to place the contract in DirectNegotiation with Ubizen Aethis (B) .

Non-competitive tendering is justified according to Articles 6.1, c) and a) ofthe Contract Regulations.



Activity Title: High accuracy APS based ASTRDescription: This is the final development identified in the harmonisation road map. Using the

HAS APS detector from Fillfactory - developed by ESA specifically for thispurpose, an ASTR will be designed, manufactured and tested that providessub-arcsecond performance (1 sigma). Robustness (against SEU and shock) willalso be included. The target mass and power is 1.5Kg and 5 Watts (comparedwith 3.0Kg and 12Watts for current comparable CCD based Star Trackers). Theunit shall also be designed to be ITAR free.

Deliverables: Final Report and E(Q)M hardware


Activity Title: GPS/Galileo Miniaturised Space Receiver (GAMIR)Description: The objective of this activity is the design, development and testing of an

engineering model of a GNSS receiver, integrated in a single board, compatiblewith LEO and GEO missions. GAMIR will bring to space a high degree ofminiaturisation and very low mass and power consumption, with excellentnavigation performances. The receiver will be designed to receive any of the newsignals available in the coming years (EGNOS, modernised GPS in 2006, andGALILEO in 2008). Two new chips are required to cope with the new signals: achip in charge of the base band processing and a second chip for the RFfront-end. The receiver will implement the newest techniques for signal and dataprocessing, for example TCAR, BOC acquisition and tracking, fast-unaided coldstart based on FFTs and pilot signal processing.

Deliverables: GAMIR engineering mode; related design; development and testingdocumentation.


Activity Title: Reaction Wheel Electronics Interface ImprovementDescription: Qualification of a MIL STD 1553 B interface incorporated in the Wheel Drive

Electronics of a Reaction Wheel Unit. The existing MACS bus will be replaced,while all functionality will be maintained. An FPGA will be used to incorporate allthe glue logic as well as the Remote Terminal functionality. The Unit will bequalified to ADM Aeolus specs.

Deliverables: Qualification report

Justification for DN: Stork is a Dutch company with background in space projects (A5 starterigniters, VEGA igniters, ERA hinges). Stork took over the reaction wheelbusiness from Astrium UK. These Reaction Wheels have an impressiveheritage in ESA science missions (SOHO, XMM, Integral, Rosetta). Storkcould expand the business to telecom satellites, after building their namein this market and thus establish a position as second source supplier forwheels in Europe, with a leading position in high-end wheels for ESAmissions.

Non-competitive tendering is justified according to Articles 6.1.a and c ofthe Contracts Regulations.

Avionics, GNC, Communications miniaturisation, with in mindbandwidth and power efficiency


Ref. Number: G603-35ES Budget: 1,000 K€

Activity Title: On Board Computer for critical applications using system on a chipapproach

Description: The objective of the activity is to develop an on board computer for criticalapplications such as S/C controller using the LEON IP core in a system on a chipapproach that shall include on the same chip additional functions traditionallyimplemented on a separate board such as I/O (buses, discrete, packet wire,…),management functions (timers, reconfiguration handshake..), system accelerators(dual port RAMs, caches,…). A first phase will include the design and a firstiteration (simulator, FPGA) whilst the second phase shall consist into the designand development of the System on a chip and its integration on a flightrepresentative board to be tested in realistic functional and performanceconditions.

Deliverables: On Board computer implementing system on chip, based on Leon.


Activity Title: Optical Link Demonstrator for end-to-end Deep Space Link communicationsDescription: The overall objective of this proposal is to achieve feasibility demonstration of an

optical link for deep space applications. It shall include the development of ademonstrator for an end-to-end deep space communication based on an opticallink. This demonstrator shall include a breadboard of the on-board terminal, andthe testing of the end-to-end link performances. This activity is strictly derived fromthe outcomes of the Deep Space System Trade-off Study, in particular: linkdefinition based on possible mission(s), modulation and coding formats, laserwave-length, signal dynamics (amplitude variation, Doppler, Doppler rate, etc);overall TT&C subsystem definition; and optical sensor requirements. Theon-board terminal architectural trade-off shall be performed, in order toconsolidate the design for the optical sensor and for the RF and base-band signalprocessing and to assess the overall link definition and performance evaluation.The demonstrator shall include the onboard terminal breadboard and the groundfunctions needed for the end-to-end demonstration.

Deliverables: Design documentation of the onboard terminal breadboard; end-to-enddemonstrator; end-to-end test results; design development plan including all theindications in terms of flight technologies, risk, schedule and costs.



Activity Title: Computer for reliability oriented missionsDescription: Due to the increasing requirements in computing power, new powerful computers

need to be developed to replace the current generation of computers based onERC 32 or 1750 microprocessors. The application domain includes the on-boardcomputers for Science, Earth Observation, Navigation and Telecommunicationmissions. The major requirements for having this new computers developed are:-The increase in computing requirement, the availability of the radiation hard LEONmicroprocessor makes it possible with 100 Mips raising to 200 Mips- The need tosupport the development process and in orbit fault diagnostic process in a way ascomplete and non intrusive as possible- The drive to integrate the microprocessorwith other functions in a system on a chip approach (SOC)- The desire tointegrate in one unit as many avionics functions as possible so as to reducerecurring cost. This integration includes mass memory, ACNS sensor interfacesand even complete sensors such as GPS- The push to use COTS interfacestandards as much as possible. This extends from CAN to Wireless networks-The need to increase the back plane bandwidth and to improve its reliability- Theneed to operate such computers as part of a distributed system in new missionssuch as formation flying The activity includes the following 3 types of actions:-Development of a highly integrated LEON based computer technology. Thisincludes hardware development for SOC, context saving, auto recovery,advanced debugging support etc. This also includes relationship with otheractions such as the implementation of standard basic S/W, mass memory,communication interfaces and the implementation of interfaces for ACNS sensorssuch as the Fibre Optic Gyro, APS star sensor interfaces, and AGGA based GPSboards- Adaptation of the computer to specific missions such as:Telecommunication applications, Low cost data system application, Distributedcomputer system consisting of a few nodes, needed for formation flying missions-Investigation and prototyping of advanced computer technology including highperformance, high reliability back plane, possibly optical.

Deliverables: -Specification of the reliability oriented computer- Development of a highlyintegrated LEON based computer technology. This includes hardwareDevelopment for SOC, context saving, auto recovery, advanced debuggingsupport etc. -Specification of adaptation of the computer for Telecommunicationapplications, Low cost systems and Distributed system consisting of a few nodes,needed for formation flying missions. -Specification and prototyping of advancedcomputer technology including high performance, high reliability back plane,possibly optical. -Final report



Activity Title: Advanced Avionics Architecture DevelopmentDescription: The avionics architecture developed for Unionics provides a processor

architecture that is more efficient and flexible than traditional approaches basedon redundant processors. The approach taken is to inter-connect the processingnodes using a SpW network and Routers. This means that it is possible todistribute SW processes to any available processor on the network.

The purpose of this activity is to take the Unionics architecture from its currentstatus as a Demonstrator system to a flight proven system. The work will build onthe Unionics development and will take forward a detailed analysis of the overallsystem and FDIR (Fault Detection Isolation Recovery) architectures, build abehavioural model of the preferred FDIR approach, and verify the system levelbehaviour of a target system. The activity shall then cover the following tasks:Building block definition; FDIR analysis and modelling; HW and SW SystemArchitecture development; System level integration; System Test Facility selectionand definition.

Deliverables: A complete Unionics-based system for a realistic application. The proposedapplication is a prototype for the ExoMars Rover.

Justification for DN: The proposed activity is a continuation of the Unionics developmentfunded by BNSC.




Activity Title: Lightweight materials and technologies for reduction of microwave passiveequipment

Description: Alcatel Espacio manufactures a variety of electronic equipments for satelliteplatforms and payloads such as S-Band Transponders, Modulators, Passivefilters, Imuxes, On-Board Data Handling Units. All these equipments have ametallic housing usually made by aluminium that represent between 30-35 % forDigital Electronic Equipment to 90-95% for Passive Radiofrequency Equipment; Inthe Active Radiofrequency Equipment the housing represents 55-60 % of totalmass.

Mechanical designs of Alcatel Espacio have the objective to minimize theequipment mass by achieving smaller thickness, elemental shapes, highintegration. One identified and significant step in the reduction of mass is themanufacturing of the mechanical parts with a lighter-than-aluminium material.

With this objective, Alcatel Espacio has carried out a number of studies anddevelopment activities, such as an ESA contract in a consortium with Inasmet,with the aim of applying Inasmet’s magnesium alloys to the manufacture ofPassives filters. In base of these, Alcatel Espacio has as lightweight materialbaseline the use of Magnesium Alloys.

The Magnesium Alloys allow a mass reduction of 20 to 35% compared withconventional solutions. In addition, the following aspects need to be considered:• no major impacts on definition of parts (same basic concept of Aluminium Alloys)• no major differences between Aluminium and Magnesium Alloys on Mechanical& Thermal behaviour.• manufacturing process of mechanical parts is similar to Aluminium Alloys.

The activity will consist of the following main work packages:Step 1: Selection of the Magnesium alloys. This part will be based on criteriadefined on “Data for Selection of Space Materials and Processes”(ECSS-70-71A). Some of selection criteria could be: Manufacturer andProcurement Limitations; Mechanical/Thermal/Electrical Characteristics;Cost/Delay/Market Forms.

Step 2: Definition of the Surface Treatments. The foreseen surface treatments areChromate Convertion and Silver Plating. The definition should include asminimum for each required treatment Minimum Thickness of Surface Treatment;Operating Maximum Temperature Range Required; Electrical Characteristics ofTreatment.

Step 3: Definition of several different pieces to be tested in order to determine:Limits of Manufacturing versus to Wall Thickness / Dimension Tolerances / Depth/ Thread; Stability of Manufactured Parts versus to Thermal Cycling / ChemicalAttacks (foreseen material used on Production Phase) / Packaging / Stockage;Torque values versus Screw Material / Temperature limits of use.

Step 4: Stabilisation of industrial processes for each Surface Treatment.

Step 5: Selection of pieces that will be demonstrated in tests, representative of theforeseen manufacturing (including surface treatment) and use of mechanicalstructure.

The results foreseen for this activity are processes of:• Procurement and manufacturing of the Magnesium Alloys.• Manufacturing of representative mechanical parts, e.g. IMUX• Process, mainly related to surface treatment of parts• Definition of potential application areas of new technology


Deliverables: One three-channel (TBC) Ku-Band Input Multiplexer engineering qualificationmodel.

Justification for DN: This activity is the continuation of the work previously done by AlcatelEspacio under the National Space Programme funded by CDTI.



Activity Title: Fast Wavelength Switching Optical RingDescription: The objective of this activity are: to demonstrate new ring based optical

networking technologies; to compare them with AWG (Array Waveguide Grating)based star topologies; and to investigate their network performance for use inspace.

Future On-board Telecom processors are expected to have aggregate traffic ofsome Tbps, and require 1000s of interconnects running at Gbps, theserequirements are leading to severe design limitations given current electricalinterconnect design rules. It has therefore been seen as necessary to investigatehow novel optical techniques in particular WDM (Wavelength DivisionMultiplexing) can improve this situation. As has been found in terrestrialapplications, the introduction of ever more powerful ASICs (Application SpecificIntegrated Circuits) and MCMs (MultiChip Modules) is resulting in aninterconnection bottleneck, due to the increased processing capacity, theshrinking feature sizes and the ever increasing processing speed in these chips,requiring the transfer of huge amounts of data in and out of these devices at veryhigh data rates. An optical backplane is widely seen as a possible solution to thisproblem, offering with the use of WDM a virtually limitless bandwidth over a singlelink. Other advantages offered by adopting an optical backplane are: greatpotential for scalability; low cross talk of optical links; reduced electromagneticinterference; low loss optical fibres; simplified test and integration; and thepotential for mass and power reduction.

In the proposed activity the contractor will build a three node system optical burstnode network demonstrator that explores the distributed switching capability ofpassive wavelength addressed optical networks in a ring configuration, operatingat an aggregate capacity of 10Gb/s per node – bidirectional. For intra satellitecommunication applications, the need for low size, weight and power equipmentare priority needs as well as ensuring the technology exceeds incumbent electricalswitch technology, and its future proof in the sense of meeting the capacity andthroughput data transmission requirements of future space missions. To this end,it is the intent of the current activity to perform a suite of comparison test resultswhich allow comparison between this proposed ring network topology and theAWG star pass optical back-plane switch, studied in a previous ESA activity. Incontrast to the centralised nature of the that activity, the current one focuses onthe specific physical performance metrics of a distributed switch implemented viawavelength addressing at the source. In addition to the specific physicalperformance metrics, the current study wishes to draw conclusions with respect tothe scalability, data latency performance, data granularity, and benefitsattributable to a distributed, as opposed to a centralised, switch for spacedeployment. The tasks to be carried out include:

1.- Build demonstrator and propose test plan.

2.- Test demonstrator according to approved test plan. Analyse results and makea comparison with those achieved in the Multigigabit Optical BackplaneInterconnections activity.


3.- Conclusions and further recommendations.

Deliverables: Technical Notes (according to the 3 tasks described above).

Justification for DN: In-Tune Technologies has successfully carried out the related tasks forcontract 17884, "Multigigabit Optical Backplane Interconnections", (activitylead by IMEC - BE, total budget of 530 K€ funded by GSTP-3) and thisactivity can be considered as direct continuation of those tasks.

No competitive tendering is justified according to article 6.1.c. of theContracts Regulations.


Activity Title: Non-Linear Programming Solver for Space Trajectory OptimizationDescription: The objective of this activity is the analysis, design, development, test, and

evaluation, of a mathematical NLP-solver (Non-Linear Programming solver). ThisNon-Linear Programming (NLP) mathematical solver will be based on SequentialQuadratic Programming (SQP) algorithms and should be the inner gear fortrajectory optimization problems in the future.

Currently, ESA optimizer ASTOS (AeroSpace Trajectory Optimization Software),and in general any trajectory optimization tool currently in use in Europe, use NLPmathematical solvers such as SLSQP, SLLSQP, NPSOL, and SNOPT. Thesesolvers use Sequential Quadratic Programming (SQP) mathematical algorithms tofind the solution of the non-linear programming problems in trajectory optimization.SLSQP and SLLQP (developed in Germany) upper parameter limit is at about 500optimization parameters. NPSOL and SNOPT (developed in USA) is a sparseSQP method capable to solve problems with several thousand parameters.Trajectory Optimization problems become increasingly complex due to thedemand for branched trajectories for rockets and entry vehicles, weak stabilityboundary (WSB) trajectories as well as trajectories for space vehicles withextremely low thrust propulsion. For numerical methods which are based ontranscribing the continuous optimal control problem into discretized problems(either for the control functions only such as in direct shooting or for both thecontrol functions and the state as in collocation) this demand results in thenecessity to solve extremely large nonlinear problems with the number ofoptimizable parameters from 1,000 up to 300,000 (as an example, around200,000 for VEGA). The current available commercial solvers cannot handle sucha big number of constraints and e.g. ASTOS requires segmenting a full analysisinto small pieces or mission arcs. Hence, the development of mathematicalalgorithms, and the corresponding transcription method implemented in a moderncomputer language will provide ESA with the ability to deliver optimization resultsin a bigger range of problems, in a shorter period of time, and in a more reliableform.


Task 1. Analysis and Definition:• Definition of requirements for an advanced NLP software capable of solvinglarge, sparse NLP problems, in particular with respect to efficiency, robustness,flexibility, user interaction, industrial standards.• List the existing methods and software which have the capability of solving thesetype of problems.• Identify actions to be undertaken (new methods to be developed, softwareimplementation issues).• Establish a series of work packages and a schedule for generating and testingthe desired software.

Task 2: design and Development:• Design and development of the preliminary NLP-software core covering as well


performance verification, robustness and benchmarking aspects.• Detailed design of the NLP problem test bench cases to be used for verificationand validation.

Task 3: Testing and Validation

As a final step, this NLP European solver shall be included in ESA trajectoryoptimization tools (e.g. ASTOS).

Deliverables: Technical notes, performance databases, and trajectories.


Activity Title: GNC Development Environment - GNCDEDescription: Rapid prototype development of GNC systems using commercially available

computer aided design and auto coding tools is incresingly used in spacetechnology and spacecraft projects. The establishment of a GNC DevelopmentEnvironment (GNCDE) using such commercial tools, together with extendedmodels and special functions libraries for spacecraft GNC and together withtemplates for closed loop simulations, will provide means to further reduce thedevelopment time and effort.

During phase 1 the overall framework for GNCDE as well as the GNCrequirements and concepts were defined. For phase 2, the GNCDE prototype forone chosed mission template (RVD) and the definition of all the others have beenperformed and all critical issues identified and solved. The prototyping of all thesurrounding tools has also been performed.

During phase 3 the detailed development of the tool, with full implementation of allfunctionalities and templates will be carried out and the GNCDE completed andtransferred to an operationalstate. This will bring the tool to commercial level maturity. The tools will includestatistical and covariance analysis, control analysis and synthesis, autocoding andmonte carlo, 3D visualization, CAD and guidance analysis tools.

Deliverables: Complete suite of commercial quality level tools and associated documentation formaintenance and use

Justification for DN: This activity is a direct continuation of the contract C14320, funded byGSTP-2 with 530 K€. In this initial contract phases 1 and 2 of the GNCdevelopment environment were successfully developed with GMV. Thecurrent activity is intended to cover the phase 3 of this development.

Non-competitive tendering is justified according to Article 6.1.c) of theContracts Regulations.


Ref. Number: G603-46ED Budget: 1,900 K€

Activity Title: Advanced Flexible I/O SystemDescription: The purpose of the activity is to develop a prototype for the new generation of

standard I/O interfaces such as defined in the new ECSS-E50-14, for datahandling systems with centralized I/O or RTUs (Remote Terminal Units). Inparticular, it will be focused on flexible standard I/O parts of the CDMU (commandand data management unit) / OBC of a spacecraft to ensure in the near futurere-usability between programs requesting these types of systems.

The activity will start by the review of a current state of the art system close toflight readiness (such as the Aeolus CDMU) and assess the impact on thephysical budgets (power, mass, volume) of the I/O system when using thepreviously developed M2 ASIC. It is expected a significative reduction in powerconsumption as well as lower mass and volume (a preliminary assessment showsthat a significant reduction in power consumption (25 W to 10 W) and mass (9.5Kg to 5 Kg) can be exptected).

The objective of the activity is to develop two I/O boards based on the M2 ASIC,as I/O controller, with built-in flexibility to cater for differing I/O budgets.Specifically the following two configurations should be addressed:

- One board type for standard I/O (thermistor acquisitions, analog measurements,relay acquisitions etc),- One board type for AOCS I/O (propulsion, magnetorquers, magnetometer..).

In addition, a generic tester for the I/O part of the data handling units will be alsodeveloped. The tester shall also allow test of individual I/O boards.

This activity will be phased as follows:

- Phase 1. Design and breadboard of I/O system- Phase 2. Development of the engineering model of I/O system- Phase 3. Design test for board and unit- Phase 4. System demonstration and tests.

Deliverables: EM Flexible I/O boards included in an EM I/O system demonstrator

Justification for DN:The boards to be developed in this activity are based on the currentlyexisting SES-M2 ASIC. As this M2 ASIC was developped by and it isproperty of this consortium, it is proposed to carry out this activity in DirectNegotiation with SES (S) and AAS (A).

Non-competitive tendering is justified according to Article 6.1. a) and d) ofthe Contracts Regulations.


Ref. Number: G603-47EC Budget: 1,500 K€

Activity Title: Reaction wheel product transfer supportDescription: Following the pull out of Stork of the space industry and the sale of its reaction

wheel product line to Bradford Engineering, a specialised support and qualifcationprogramme is required before the wheels can be supplied for flight by Bradford,due to the complex and skilled nature of reaction wheel design and assembly.

The unique selling points of these Reaction Wheels are:- Well known and guaranteed micro vibration spectrum;- High resolution wheel speed measurement;- Fixed, fast torque realisation (i.e. 80 ms);- Digital MIL 1553 interface

In addition the wheels also benefit from

- Demonstrated high tolerance to zero wheel speed crossings;- Capability to run at low RPM rates for a very long time;- Separate electronics and wheel – lower thermal and duty cycle restrictions

This transfer of knowledge (from Stork to Bradford) was initiated under Dutchnational PEP2006 funding with good progress. The objective of this activity is tocontinue with this transfer process, and to successfully transfer all design,manufacture and test know how for the complete RWU (reaction wheel unit).Bradford need to import all design information into their design tools (mechanicaldesign, thermal design and electrical design) and reperform the unit analyses. Theactivity will also include the demonstration of the successful transfer andunderstanding of assembly and test procedures. In particular, an existing wheelshall be stripped, rebuilt and re-tested. To finalise the transfer all required designupdates (e.g. for component obsolecence and rationalisation and supply chainchanges) must be performed and a single channel Qualification Model reactionwheel unit manufactured assembled and tested.

Two main phases are envisaged:- Transfer of the knowledge and technology and demonstration of the criticalprocess- Design update and supply chain management; reaction wheel production andqualification; and EGSE modernisation

Deliverables: Reaction wheel unit (including also the drive electronics); Technical notes.

Justification for DN: Bradford Engineering are the purchasers of the manufacturing rights andtherefore the only company able to perform the tasks.

Non-competitive tendering is justified according to Article 6.1. a) and d) ofthe Contracts Regulations.



Activity Title: Non-conventional matrix/carbon nanotubes reinforced composite forApplications in Space

Description: This activity will consist of the following phases: Phase 1: Target definition: - Meritfactors in relation with applications under consideration - economical perspectives;Definition of Raw material: - Functionalisation screening - identification of best ofclass material/blend; Semi-product definition/processing: - optimisation ofprocessing methodology and equipment - definition of basic process families (1, 2or 3D) - identification of influence of processing conditions - morphology ofsemi-product -process performance - selection of most promising process -definition and realization of pilot semi-product processing unit; Test andcharacterisation of semi-product: - definition of experimental plan - samplesproduction - GSE definition and manufacturing - test campaign (physical,structural, outgassing, dimensional characterisation) - most promising samplesidentification; Definition of validation prototype application. And Phase 2comprising: Detailed study of validation prototype - design and concept –manufacturing – testing; Techno-economical conclusions. The conclusions ofPhase 1 would lead to the definition of Phase II by identifying the most promisingapplication. This phasing approach is necessary due the applicability of thematerial, which is very large. Such a definition has to be made to focus thedevelopment on most promising application. After that Phase 2 will lead to therealization of a prototype.

Deliverables: -Technical notes. Phase 1: Semi-product samples, fully characterized for spaceapplications. Phase 2: Prototype selected after Phase 1.

Basic Parts, Materials and Processes



Activity Title: High conductivity carbon fibre reinforced polymersDescription: For solar panels, efficient cooling is required to maintain photovoltaic efficiency. At

present, Al or better Carbon Fiber Reinforced Plastics (CFRP) are a substrate forthe solar cells. Replacement of normal CFRP by high conductivity CFRP allowsbetter cooling and so a higher PV efficiency when using concentration. It will alsoavoid thermo-elastic waviness of the panels. The advantage is still greater whenunidirectional properties are put forward: pitch fibres and high conductivity in thethermal gradient direction and normal fibres and better toughness in the 90ºdirection. Different core materials have to be assessed: Aluminum, C/C, etc. invarious sizes and thickness to check the compatibility of the different materials.The present proposal focuses on developing low weight, high thermal conductivitysandwich panels for specific high value application in satellites. The structuralmaterials in satellites are chosen to have a high stiffness to weight ratio and thelowest thermal expansion coefficient to thermal conductivity ratio. The thermalconstraint is particularly important for observation and mapping satellites but alsofor high temperature panels such as those used for inner planet exploration orhigh power equipment. Generally speaking, each location where the thermalgradient has to be limited is a potential application: antenna reflectors, high powerelectronics boxes and panels, hot structures, solar generators with concentration,etc. Especially for solar concentration ratio (typically 8-10) for advanced solarpanels presently under study in IES2 ARTES 5 program, the use of highconductivity CFRP is a major issue and a possible go/no-go for high concentrationratio.

Deliverables: Part 1: Material selection and according to the state of the art and ECSS-Q-70and thermomechanical characterization. Part 2: Identification of benchmark(patented design), manufacturing and testing. Part 3: Evaluation of benefit forantenna reflector


Activity Title: Evaluation of Fe-RAM memory demonstratorsDescription: Ferroelectric memories hold the promise for dramatic improvements in the speed,

endurance, and power consumption of non-volatile semiconductor memories. Thisactivity will be the continuation of previous activities funded under GSTP:Development of a Ferroelectric Memory Technology", phases I, II and III. Theprogram of work consists in the reliability assessment of the manufacturedFe-RAM demonstrators. In particular radiation testing, high and low temperaturetests, environmental tests are planned to be performed on the delivereddemonstrators to characterize this novel technology and identify criticality (if any)with respect to the space environment.

Deliverables: Radiation test report; high/low temperature test report; and environment testreport.

Justification for DN: This activity will be the continuation of the initial “Development offerroelectric memory technology”, funded with 400 K€ by the GSTP2 andGSTP3 programmes (contract number 13579).




Activity Title: Evaluation of Optic Fibre Cable AssemblyDescription: The main objective of this activity is to prepare the MEMS Based Si Pressure

sensors for formal industrial qualification by final users in the horizon 2007. It isexpected that this validation/pre-qualification exercise will allow this technology toachieve a technology readiness level 4 (ready for flight) after formal industrialqualification. The activity will be divided into 2 phases. During phase 1 thefollowing tasks will be done: QA approach for complex-systems suppliers;definition of micro-systems pre-Qualification model(s); validation/pre-qualificationdefinition. The results of phase 1 will be used during phase 2: QA structuralorganisation; manufacturing of pre-qualification model(s);validation/pre-qualification testing.

Deliverables: QA documentation; FMECA report; ESA audits reports; manufacturing andperformance verification reports; validation/pre-qualification testing report; finalreport. At least one complete pre-QM


Activity Title: Validation/Pre-Qualification of MEMS based Si pressure sensorsDescription: The main objective of this activity is to prepare the MEMS Based Si Pressure

sensors for formal industrial qualification by final users in the horizon 2007. It isexpected that this validation/pre-qualification exercise will allow this technology toachieve a technology readiness level 4 (ready for flight) after formal industrialqualification. The activity will be divided into 2 phases. During phase 1 thefollowing tasks will be done: QA approach for complex-systems suppliers;definition of micro-systems pre-Qualification model(s); validation/pre-qualificationdefinition. The results of phase 1 will be used during phase 2: QA structuralorganisation; manufacturing of pre-qualification model(s);validation/pre-qualification testing.

Deliverables: QA documentation; FMECA report; ESA audits reports; manufacturing andperformance verification reports; validation/pre-qualification testing report; finalreport. At least one complete pre-QM

Justification for DN: PRESENS is developing a space version of its MEMS based Si pressuresensor in the GSTP-3 activity “Combined high pressure and temperaturesensor” (300 K€), with contract number 16557. It is now proposed tocontinue the development with the performing of the componentvalidation/pre-qualification, in order to bring the technology to a TRL 4ready for industrial qualification.

Non-competitive tendering is justified according to Article 6.1.a and c ofthe Contracts Regulations.



Activity Title: CTTB In-Flight Component Irradiation Test Data AnalysisDescription: The CTTB is an in orbit component characterisation tool for recurrent deployment

(first planned flight is on the GSTB-V2). In short, the CTTB performs an in-flightanalysis of the radiation induced component parameter degradation. The CTTBcontains 6 experiment boards each carrying a number of technologies andcomponents. The total data volume generated by the CTTB is extensive andrequires a considerable data analysis effort. The purpose of the proposed activityis to collect, in near real time, the generated CTTB data and perform the followingtasks: compile and present the CTTB data; analyse component parameterdegradation with respect to the radiation environment, temperature andoperational conditions; correlate the in-flight analysed data with existing groundbased irradiation data on components from same lot as in-flight devices; assesssuitability of new technologies for flight on Agency missions; investigatecomponent radiation damage physical mechanisms and develop models suitablefor implementation in the GEANT4 toolkit. Based on all analysed data, assesscurrent radiation evaluation / qualification engineering approaches and suggestimprovements. The following technologies and component families are planned tobe flown: memory experiments (SRAM, DRAM, PROM, EEPROM, FLASH,memory cubes), GSTB-V2 specific solar cells, photonics (Opto-couplers, CCDs,APSs), linear devices, power devices, GSTB-V2 related components. Othertechnologies (i.e. MEMs, novel materials, etc.) are foreseen for investigation forfuture recurring CTTB experiments.

Deliverables: Irradiation test report for each component generated according to ESA standards;technology demonstration reports for technology demonstration experiments; finalreport; an Internet web page presenting the CTTB analysed data as soon asavailable.



Activity Title: Contactless Quality Control of Micro-partsDescription: Quality control plays a vital role in the prototyping and later processing of IEEE

components and even more specifically during MEMS fabrication. However, ifquality control is well implemented for standard IC circuitry novel and techniquesmethod are still required for evaluating MEMS overall quality and which willconsider the very specific nature of micro-systems. Optical CoherenceTomography (OCT) is a relatively new imaging technique capable of recordingcross-sectional images of transparent and turbid structures with micrometer-scaleresolution. Originally developed for biomedical imaging applications, thistechnique has also a great potential for non-destructive material characterisationand testing. In parallel, Laser Ultra Sound (LUS) technique may be used formaterials where light cannot penetrate. Short laser pulses of some nanosecondsinduce ultrasonic pulses within the sample. These pulses are travelling throughthe sample, are reflected and scattered at interfaces and at the backside of thedevice. This activity proposes to study the possibility to use LUS and OCT tocharacterise and image cross-sections of (raw) materials and MEMS componentswith resolutions in micrometer range. The study will start with a thoroughclassification of the proposed optical techniques (LUS and OCT) for inspectionand testing of MEMS (which parts and materials are suitable for which method,requirements for future testing, etc). This will be followed by experimental work:the OCT method will be experimentally evaluated for the characterisation ofsemitransparent raw material and as inspection and testing tool for suchsemitransparent miniature parts (e.g. precision moulded polymer componentsplanned for use in micro-turbine for example). The same programme will beapplied to LUS for non-transparent materials and parts, especially compositematerials as for example composite materials being studied for future re-entryvehicles for space transportation. The requirements for future testing andinspection procedures will be evaluated together with the findings of theexperimental study and the two methods (or an alternative one) will be improvedand developed (e.g. regarding: measurement speed, operation of set-up andhandling of inspected materials and components, data processing, developmentand definition of quality criteria). The activity will be carried out in 3 phases: 1)Classification study of the proposed optical techniques (LUS and OCT) forinspection and testing of MEMS; 2) The OCT method will be experimentallyevaluated; 3) The LUS method will be experimentally evaluated. Future testingand inspection procedures will be evaluated together with the findings of theexperimental study of the two methods.

Deliverables: Classification report of LUS and OCT techniques for inspection and contact lesstesting of Micro-systems. OCT & LUS evaluation reports Commercial EvaluationFinal Report including OCT & LUS user guide and set up and procedure detaileddescription

Justification for DN: The Upper Austrian Research has developed a unique experience inOptical Coherence Tomography (OCT) and Laser Ultra Sound (LUS). Thevalidation of both techniques for MEMS will require significant efforts andknow how achievable only by a company with this level of existingexperience. The total cost of the activity is 100 Keuro but the AustrianSpace Agency has proposed to co-manage and co-fund this activity withan internal budget of 30 Keuro. Additional funding may be expected fromthe European Commission through the 6th framework, which will alsobenefit ESA and ASA.

Non-competitive tendering is justified according to Articles 6.1. a) and e) ofthe Contracts Regulations.



Activity Title: Enabling of High Q micromachined planar filters componentsDescription: The ultimate goal of this study is to transfer to an industrial source Reinhardt

MicroTech (RMT) and validate for space use, a technology process used tofabricate membrane supported millimeter-wave filters. This technology appearshighly strategic, performance wise, for high frequency application, starting in the20-30 GHz band up to millimeter wave frequencies (118 GHz). The potentialdomains of application range from space telecommunications to earth observationMissions and applications in scientific payloads are not excluded. More precisely,this technology transfer is strongly supported by Alcatel Space for its low tomedium volume applications and Thomson Multimedia (TMM) has also beenidentified as a second potential final user seriously considering this technology forits new generation Rx/Tx interactive satellite TV ground terminal (previouslly, theprocess had been developed at IRCOM (university of Limoges, France) throughAlcatel Space funding.

With this updated activity the tasks originally proposed are optimised and maturedto reach a sufficient industrial throughput and process reproducibility. IRCOM isfully involved in the project and increases the chances of success (e.g. a processengineer from IRCOM will be staying at RMT to ensure in situ technologysupport). Moreover, the budget increase will also allow the incorporation ofadditional in line process control which will improve process stability andreproducibility. Additional measurements during processing will also enhanceprocessing accuracy and the understanding of process margins. After these steps,improved devices are manufactured by applying the regarding design rules andthe process tolerances are then established. Assessing the reliability of devicesand validating the design rules will form the concluding works. Finally, a workpackage for process identification documentation (PID) will summarize all requiredprocess documentation.

Deliverables: Deliverable 1: Specification of the filter to be fabricated. Deliverable 2: Detailedprocess flow of existing process at IRCOM. Deliverable 3: PHS MEMS optimizedprocess flow and validated design rules for implementation of high Qmicro-machined components. Deliverable 4: Alcatel Space Assessment report(inc. matrix of compliance) Deliverable 5: Commercial Evaluation from PHSMEMS with emphasis on instrumentation and automotive potential market.Deliverable 6: Filter components for analysis within ESA components laboratory.

Justification for DN: The objective of this proposal is to prototype through an industrial MEMSfoundry high Q micro-machined planar filters components initiallydeveloped in an open research (CNRS-IRCOM) laboratory under fundingof Alcatel Space (one of the expected final users). This activity will not onlycontribute to guarantee the independence with respect to the US market inPHS MEMS but also intends to explore the suitability of the filtercomponents for other grand public applications such as instrumentationand automotive. It is also expected that the participation of a final usersuch as Alcatel Space will guarantee a rapid transference into satellitepayload. It is suggested to award this contract to this pool of companies.




Activity Title: Alternative Sources for Critical TWT MaterialsDescription: The objective of this activity is to identify European suppliers for critical TWT

materials and to realise an evaluation and pre-qualification programme for themost sensitive ones. The fabrication of space-standard TWTs involve a largenumber of materials and processes, some of which come from a single sourceoutside Europe or are subjected to possible exportation control. This situation isconsidered to be perilous, especially in view of the current strong position ofEuropean industry in this domain. To mitigate the associated risks, it is thereforerequired to identify alternative sources (in particular European sources) for a set ofcritical materials (ceramics, metals and alloys). This activity will first concentrateson the review and identification of critical materials and possible suppliers.Second, selected suppliers will be contacted and partnerships will be settled.Finally, a set of critical materials will be evaluated and pre-qualified according tothe specific requirements.

Deliverables: First, an extensive inventory of critical TWT materials and processes, as well aspossible non-US suppliers. Second, an evaluation and pre-qualification report ofthe most critical items.


Activity Title: ASICs for space fabricated with Radiation Hardened by Design libraryDescription: This activity is meant to give continuity, make use and profit from the tools and

services created in previous Radiation Hardened by Design developments. Theactivity would consist in defining, designing and ultimately fabricating complexASICs with a commercial process line and the Radiation Hardened by Designlibraries which have been developed, characterised, and tested in previouscontracts. This will include the usual design phases of an ASIC, as explained inESA's internal "ASIC Design and Manufacturing Requirements". The design(s) tobe implemented is not the main driver of this activity and is yet to be determined. Itcould either be: a) an already known design to ESA (e.g. AGGA3, LEON,SCTMTC, NAPAL-FEIC, FFT), and thus use this activity to have a second sourceproduct (back up solution in case of failure/delay of first source foundry, usuallyATMEL). b) A new design for space that finds more suitable the RHBD fabricationapproach (because of better radiation hardness, better price, better assemblychoices and/or better lead-time) than the other manufacturing alternatives.Radiation tests should be planned, executed and results documented, as part ofthe continuous validation of this RHBD technology. Whenever appropriate,comparisons with respect to area, speed, power consumption and design flowaspects between this RHBD development and a similar one of a competitortechnology should be established and documented to continue the evaluation ofthis technology against the few existing alternatives (mainly Atmel).

Deliverables: ASIC development documentation: specifications, verification and HW validationreports; radiation tests plans and results ASIC (FM) samples; reports about theexperiences of using the RHBD libraries and associated new design methodologyaspects.



Activity Title: Development of new thermal control paints for Space and Launcherapplications

Description: Future trends in paint development are geared towards a higher stability (longermissions, more extreme temperature profiles), and there is also a need to modifycomposition because of more stringent International Safety and pollutionregulations (e.g. use of chromates as primer will need to be abolished and use ofsolvent decreased). The main objectives of this activity are the following:- Develop new primer to replace chromate-based primer.- Most primers, such as Phosmap 11 and PS, are based on chromates. Newprimers need to be developed and qualified. Compatibility with the differentsubstrates and paints need to be evaluated.- Reduction/change of solvent needed for present applications.- The more stringent requirements regarding emission of volatile organiccompounds have a direct impact on the paint solvents regularly used in spaceapplications. Reduction of this emission or replacement by less harmful solventsneed evaluation.- Industrialization of new coatings (e.g. high temperature white coating, FSR-C,RSR-C).

Deliverables: - Development + qualification of different Substrate/Primer/paint combinations- Methodology for reduction of emission, and/or qualification of replacementsolvents- qualification of industrial application techniques on different substrates.

Justification for DN: MAP is the only European company making space proven thermal controlpaints.



Ref. Number: G608-20QC Budget: 1,400 K€

Activity Title: Advanced development of III-N material for high power componentsDescription: The objective of this activity is to develop high quality hetero-epitaxial growth of

nitride heterostructures and to establish a dedicated GaN wafer supply route thatcan be accessed by European (space) companies. High quality low defect densityAlGaN/GaN HEMTs have previously been developed within the GSTP-3 activityATHENA on sapphire and SiC substrates. Further developments are required toimprove material quality and provide continued support to the also ongoing ESAactivity Epi-GaN (from the GSTP-3 Announcement of Opportunities).

The following tasks are planned:

(i) Optimisation of growth transfer: Continued support will be given to theoptimisation of process growth in transferring from the small research reactor tothe newly purchased 7x2” MOVPE reactor (acquired through the Epi-Gan project).

(ii) Investigation of alternative substrate materials: At present the majority of powerdevice work ongoing in Europe is based upon GaN/AlGaN growth on SiC wafersubstrate material. This approach gives excellent power capability and goodthermal management albeit at a relatively high cost/mm2 of die area. Initialemphasis will be placed on developing improved devices grown on SiC (andsapphire) material in order to address immediate user needs and to rapidlyestablish commercial market penetration through the Epi-GaN facility. This will befollowed by continued investigation of improved material growth on Si substrates,with expansion from 2” to 4”, and possibly 6”, diameter wafers since this offers theultimate low cost solution. Also, if suitable quality free standing GaN wafersbecome available material growth investigations will be undertaken. It is alsoplanned to assess the reliability of devices manufactured using these differentsubstrate materials.

(iii) Transfer from HEMT to power HEMT devices: The Athena project has beenextremely successful with high power density RF devices demonstrated (e.g.4W/mm on sapphire, for a 0.6mm gate width device). However, in order todemonstrate higher levels of absolute power, further work is planned to optimisedevelopment and fabrication of large power bar devices with large gate periphery(i.e. moving from sub-mm gate width transistors to devices with several mm’s ofgate width).

(iv) Power switching devices: Development of GaN components for high powerswitching applications will be investigated. An important breakthrough for reducingswitching losses would be the development of vertical type of transistors onconductive substrates. Permeable-base vertical GaN transistors will be developedfor high power switching applications and a component evaluation made.

The primary output from this activity will be a commercial source of GaN wafermaterial. Wafers will be grown on more conventional SiC/sapphire substrates, butend-users will also be offered a low cost Si wafer option. In the long term thisfacility will become self-supporting since IMEC have plans to set up a commercialspin-off company. The choice of substrate provides scope to address both thespace and terrestrial markets.

Deliverables: Technical Reports, Hardware for external evaluation.


Justification for DN: This activity is the continuation of the work previously done by IMEC in theESA contracts 14205 ("Development of Advanced technologies forLow-Defect Hetero-epitaxial Growth of GAN and INGAAS Layers", 2.35M€ funded by TRP and GSTP-2) and 18297 ("EPI-GAN: A market orientedactivity", 1 M€ funded by GSTP-3 and an additional amount of 1M€co-funded by IMEC).



Activity Title: Digital Pressure Sensors for PRISMA satelliteDescription: The main objective of this activity is the development and qualification of Digital

Pressure Sensors for PRISMA (international satellite technology demonstrationprogram). This will include the design, fabrication, test and qualification ofEngineering and Fligh Model digital pressure sensors for the MEMS-basedmicro-propulsion sub-system for the PRISMA satellite. The micro-propulsionsub-system requires the development of both a 5 bar and 250 bar full-scale digitalpressure sensor. The solution proposed should include a major focus onminiaturisation and a digital interface circuit should be included in order to improvefunctionality, accuracy, reliability and size for the digital pressure sensor withrespect to the analogue version. The mechanical sensor housing will be optimisedfor the PRISMA application, but the solution will be relevant for a wide range ofspace propulsion applications. Two main phases are envisaged:

- Engineering Model design, fabrication and test.- Flight Model fabrication and qualification.

Deliverables: Engineering Models for the micro-propulsion sub-system and 4 flight models forthe PRISMA satellite.

Justification for DN: The proposed contractor is Presens (N) as this development should bebased on the analogue pressure sensor developed by Presens under ESAcontract 16557/02, which is property of this company.




Activity Title: Extended application range of the digital space pressure sensor.Description: Presens (N) baseline technology is a piezoresistive silicon MEMS pressure sensor

developed for full-scale measurement from 10 bar to > 1000 bar for high-precisionoil & gas subsea applications. Presens is currently involved in developmentactivities within GSTP in order to adapt and pre-qualify the proprietary siliconMEMS technology for satellite applications.

Now, new technology at Presens involves the development of silicon MEMSsensor technology for low-pressure (aerospace applications) and differentialpressure applications (sub-sea flow measurements) and hence the presentactivity is proposed. The main objective of is to implement processes andtechnology for precision digital pressure sensors covering a wide range of spacepressure sensor applications, both for satellites and for launchers: the outcome ofthe activity shall be a sensor solution competitive for fuel tank and fuel supplypressure applications in satellite propulsion systems, as well as for launchertelemetry applications.

The activity shall cover the following areas in order to enhance the digital spacepressure sensor products and capabilities from Presens for a wide range of spaceapplications:

• Establish Electron Beam (EB) Welding infrastructure and qualify processes fordigital space pressure sensor. EB-Welding is a key process in fabrication ofsensors, and enables for integration of sensor functions into more complex andcompact sub-systems.

• Establish technical requirements and implement the silicon MEMS sensingelement design for a digital low-pressure sensor for space applications. Newtechnology involves the development of silicon MEMS sensor technology forlow-pressure (aerospace applications) and differential pressure applications(sub-sea flow measurements). Including the low-pressure silicon MEMStechnology will enhance the Digital Space Pressure sensor portfolio to coverfull-scale pressure range from 0-100 mbar to 0-350 bar.

• Establish sensor housing design and assembly processes for a digitallow-pressure space sensor.

• Reducing the contamination risk of the propulsion system. Rough mediumcompatibility is obtained by using metal separation diaphragm and sensor cavityliquid filling. The present solution is based on silicone oil, with a contamination riskof the propulsion system interior. The risk of contamination can bee reduced byincreasing the reliability of the sealed sensor compartment or by replacing fillingfluids with more compatible materials. Both options will be considered. Onealternative is to replace Silicone oil with Fluorinert™ liquids (these liquids havethermo-mechanical properties similar to Silicone oil, but the contamination risk issignificantly reduced).

• Measurement redundancy will be implemented for the Digital Space Pressuresensor by including several sensing elements. This is feasible due to the smalldimensions of the silicon MEMS sensing element, and thus will not contribute tosignificantly increased size for the complete sensor.

• Digital interface circuits based on Silicon-On-Insulator (SOI) semiconductortechnology is a promising alternative to the technology based on Bulk-CMOS. TheSOI technology is suitable for high-temperature capabilities, which is particularlyrelevant for sub-sea and downhole oil and gas applications (and also for spaceapplications). This will include early stage radiation testing of pressure sensorconcepts with digital interface circuitry based on SOI-technology in order to


evaluate the radiation hardness capability. Also, the evaluation of R&D-suppliersand the industrial supply chain for interface circuit components will be carried out.

• Consider technical requirements and implement the silicon MEMS sensingelement design on a SOI technology process for an increased temperature rangein space applications. Temperature range for present technology is limited to 125°C. New technology by introducing SOI material for the silicon MEMS sensingelement will improve the temperature capabilities significantly, up to 350-400 °C isfeasible.

Deliverables: • EB-welding infrastructure and documented processes.• Low-pressure engineering model delivery and pre-qualification.• Report on technology capability for radiation hard space ASICs based onSOI-technology.• High-temperature pressure sensor demonstrator for space applications.

Justification for DN: This activity is a continuation of the work already done under ESA contract16557, "Digital Pressure Sensors for PRISMA satellite" (funded byGSTP-3 and GSTP-4 with 470 K€). It is recommended to continue thedevelopment with the same company, Presens (N).

Non-competitive tendering is justified according to Article 6.1, c) of theContract Regulations.


Activity Title: SpaceWire Router ASIC Performance CharacterisationDescription: The objective of this activity is the characterisation of the SpaceWire Router ASIC

Prototypes with respect to its timing parameters, power consumption figures andoverall perfomance. This is a key electronic component for the implementation ofSpaceWire standard compliant network for high speed data interconnection onboard of satellites, and its characterization has to be done in order to produce anddistribute the SpaceWire Router ASIC as Application Specific Standard Produce(ASSP) and to use it in flight applications. Within this activity the timingparameters of the I/Os and the power consumption figures for idle, typical andworst case use scenarios shall be measured. The results of this characterisationwill be fed into SpW Router ASIC data sheet. An additional objective of thisactivity is to gain more experiance with the usage of this component and toprepare future applications.


1.- Preparation of detailed Test Plan2.- Timing Parameter and Power Consumption Characterisation3.- Device testing in representative Application Environment

Deliverables: SpaceWire Router ASIC Performance Characterisation Report

Justification for DN: Austrian Aerospace (A) has performed the detailed design of the SpWRouter ASIC as part of the industrial team in the contract 15803,"SpaceWire Router ASIC" (funded by TRP with 1.3 M€). With this directlyapplicable background they are most suited to perform the work proposedin this activity and it is proposed to procure this activity in DirectNegotiation with Austrian Aerospace.




Activity Title: Modular & Multi-application Plasma Diagnostic Package (MMPDP)Description: Compact Packages for the in-flight monitoring of the Electric

Propulsion/Spacecraft interactions have been successfully developed in therecent years for ARTEMIS, STENTOR and SMART-1 satellites by LABEN/Proel.They were dedicated to the monitoring of the charge-exchange ions generated bythe gridded ion engine (GIE) operation (ARTEMIS) and to primary & secondaryions and relevant contamination arising from the Hall Effect Thruster (HET)operation (STENTOR and SMART-1). The objective of this proposal is thedevelopment of a new and versatile instrument, identified as Modular,Multi-application and reconfigurable Plasma Diagnostic Package (MMPDP)conceived according to a modular architecture and capable to cover severalissues and aspects of plasma diagnostics/monitoring for different applicationscenarios, such as; -In-flight validation of Electric Propulsion Technologies (GIE,HET, FEEP)- In-flight validation of Electric Propulsion Technologies (GIE, HET,FEEP) and assessment of their possible interactions with the spacecraftenvironment, -Earth ionosphere and magnetosphere study, deep spaceexploration and planetary science (characterisation of the plasma environmentsurrounding a celestial body, including earth), -Electro-static and Electro-dynamicexperiments and relevant technologies validation in the frame of applicationsbased on the ISS and on Tethered Space Systems deployed from the ISS. Thedevelopment will start considering achievements of ARTEMIS, STENTOR andSMART-1 plasma packages. The proposed activity is articulated in 2 phases andincludes the study, design, development, manufacturing and testing of MMPDP atEngineering Model level, fully representative of a possible instrument FlightModel. The design will be conceived according to a modular philosophy,reconfigurable, where functions/performances could be implemented by changingin the MMPDP general architecture hardware (and software) modules.

Deliverables: Design, manufacture and tests of MMPDP.

Justification for DN: LABEN/Proel has gained their unique experience in Diagnostics Packagesand Plasma Diagnostics through their work on ARTEMIS, STENTOR,SMART. Compact Packages for the in-flight monitoring of the ElectricPropulsion/Spacecraft interactions have been successfully developed inthe recent years for ARTEMIS, STENTOR and SMART-1 satellites byLABEN/Proel. They were dedicated to the monitoring of thecharge-exchange ions generated by the gridded ion engine (GIE)operation (ARTEMIS) and to primary & secondary ions and relevantcontamination arising from the Hall Effect Thruster (HET) operation(STENTOR and SMART-1). Laben/Proel is therefore the best suitedcompany to place this contract with.


Extreme space environment technology (hot, cold, radiation..)


Ref. Number: G602-20EM Budget: 1,650 K€

Activity Title: Proto-flight model of the Energetic Particle Telescope (EPT)Description: The EPT will measure the high-energy particle fluxes with very good energy,

angular and mass resolutions. It measures the energy deposited by chargedparticles into twelve sensitive elements and processes the information to identifythe particles (0.2-10 MeV electrons, 4-300 MeV H and 16-1000 MeV He ions) andto determine their energy spectra and angular distribution. The EPT consists oftwo "particle telescopes" placed in series separately adapted to low andhigh-energy ranges. The low-energy section consists of two silicon detectors. Thehigh-energy section is a so-called "range telescope? in which the thicker silicondetector is used as a (DE) sensor and a stack of absorbers and scintillator-baseddetectors produce a digital measurement of the total energy (E).The EPT overalldimensions are 205 mm x 205 mm x 190 mm. Its weight is about 6 kg, with theelectronic readout included. The power consumption is lower than 6 Watts. Themaximum energy-dependent geometrical factor of the detector is ~1.5 cm2sr.The radius of the EPT circular aperture was set to a diameter of 35 mm. Theresulting maximum field of view angle is 50 Deg. Due to the widely varyingfluences of electrons, protons and heavy ions within the radiation belts, it wasfound necessary to provide this instrument with a stunning in-flight particlediscrimination capability. This was achieved by performing a thoroughcharacterisation of the EPT by an intensive Monte-Carlo simulation usingGEANT4 software. With this optimised design procedure we get background-freecounting, even in the channels devoted to particles of very low abundance inspace.

Deliverables: -EPT engineering model; -EPT proto-flight model; -Technical notes describing theEPT mechanical assembly, electronic system, operating modes, thermalproperties, mechanical vibrations and acoustic noise test results for the proto-flightmodel


Activity Title: MUSTANG: Muon Space Weather TelescopeDescription: The objective of this activity is the upgrade of the ‘prototype Muon Space Weather

Telescope’ (MUSTANG) to a fully functional ‘initial operational capability’ includingthe scientifically interesting ‘directional measurement capabilities’.

The scientific and commercial user community are eagerly waiting for a real globalMUON-measurement 24/24 hours network, to which the MUSTANG is essential inclosing the “European northern hemisphere gap”. In addition, some of the ESAsatellites in charge of solar flare measurements will probably end their operationallife by that time (e.g. SOHO, Ulysses).

Deliverables: ESA hardware “MUSTANG telescope” to be located and transferred to Universityof Greifswald.

Justification for DN: The proposed activity is a continuation of an ESA activity (Contract no.18835, 200 K€ funded by TRP).




Activity Title: Radiation Assessment of Deep Submicron CMOS DevicesDescription: This activity aims at investigating the effect of the space radiation environment

(Total Ionising Dose and Displacement Damage) on novel sub-micron devices.Technology trends in downscaling is progressing very fast and smaller than 90nmtechnology nodes will soon be commercially available. The rapid technologydevelopment and the increasing trend to employ COTS devices in spaceapplications make it essential to characterise these state-of-the-art technologiesenabling identification and selection of the appropriate technology for spacemissions.

Thus the activity will consist of two main parts:

- Irradiation characterisation of 65nm devices including initial gamma irradiationcharacterisation followed by detailed proton irradiation characterisation. Gammacharacterisation is performed to verify whether the observed catastrophic gateleakage current increase (in 90nm and 65nm proton irradiated devices) is due tosurface effects (total ionising dose) or bulk effects (displacement damage). Thegamma characterisation is followed by detailed proton irradiation characterisationof these devices under various operating and environmental conditions.

- Determination of the radiation behaviour of advanced gate concepts, high-k gatedielectrics, strain engineering and/or high mobility substrates. Devices selected forirradiation testing are from the 45nm technology node.

The activity will also include the following tasks:

Wafer fabrication of CMOS test samples earmarked for irradiation test campaign(65nm and 45nm technology)Manufacturing of measurements systems to characterise test samplesManufacturing of test jigs for irradiation of test samplesPurchase of beam time at irradiation test facilities

Deliverables: D1: Technical report on the gamma radiation assessment of the IMEC 65 nmhigh-performance CMOS technology.D2: Technical report related to the systematic proton radiation testing of the IMEC65 nm CMOS technology.D3:Technical report related to the investigation of thermal annealing on thepost-irradiation performance of IMEC’s 65 nm CMOS technology.D4: Technical report related to the radiation assessment of 45 nm CMOS deviceswith advanced gate concepts such as e.g. FinFETs.D5: Technical report related to the radiation assessment of high-k dielectricsintended to be used in low power deep submicron CMOS technologies Thephysical mechanisms involved in the observed radiation effects will be discussed.D6: Technical report related to the radiation hardness of CMOS devicesprocesses on high-mobility substrates.D7: Summary report on the radiation activities performed in the two Activities andgeneral guidelines concerning radiation effects in potential semiconductor devicesfor future space applications. This report will be considered as the Final Report ofthe activity.

Justification for DN: The work to be carried out in this activity is the continuation of the contract14924, funded by GSTP, with 500K€. In addition, IMEC is the only entitywith the required expertise to ensure an efficient and cost effectiveexecution of the activity.

Non-competitive tendering is justified according to the Articles 6.1.a and cof the Contract Regulations.



Activity Title: Development of standard plasma monitorDescription: This activity aims at developping a standard, low resources monitor to measure

the plasma and UV environment in space. The detector shall be able to work asstand alone or as part of a larger package of space environment monitors.

Sensors to measure the plasma environment in space are needed for manypurposes as: studying the plasma in space (solar-terrestrial, interplanetary andaround other planets) in scientific missions, monitoring of the plasma environmentaround application spacecraft (e.g. to study spacecraft charging and the effects ofelectric propulsion), for space weather applications and to support thedevelopment of improved space plasma modelling and simulation tools. Existingsensors are still rather complex, large and specialised for a given, usuallyscientific, application with specific requirements for the range of plasmaparameters measured. There is an opportunity for an innovative, small, light andlow resources plasma detector which can be flown as standard detector ondifferent types of spacecraft and orbits.

The detector shall be able to measure the charged particle environment over theenergy ranges (0 -- 30 eV and 10 KeV- 300KeV) as well as the solar EUV fluxesof interest to be derived from measurements of photoelectrons resulting from EUVexposure The densities and energy distribution for ions and electrons shall bemeasured. New technologies and materials shall be assessed to significantlyreduce the weight and power consumption of the monitor and to combine differentmeasurement techniques for the different energy ranges. The target is a detectormass below 1 kg and a power consumption of less than 5 Watt.

The plasma monitor shall be designed with a flexible interface that does allow theimplementation into different spacecraft with little or no modifications. Integrationinto a package with other environment monitors shall be foreseen as well. Therequirements will be established with the potential user programmes.

Deliverables: A laboratory prototype together with the related software, electrical ground supportequipment (EGSE), design and development documentation and test reports



Activity Title: Integrated Radiation Environment, Effects and Component DegradationSimulation Tool (Experimental Verification)

Description: This activity is a continuation of a previous development of a Martian RadiationEnvironment Model and models for radiation effects in EEE (Electrical,Electromechanical, and Electronic) Components based on the Geant4 particleTransport Toolkit. The Mars Radiation Environment Model was successfullydeveloped and internationally recognised. This tool is indispensable for predictingthe radiation environment of ESA and other Mars lander mission types. The MarsRadiation Environment Model development was carried out in parallel with thestudy and development of new models or methods to predict radiation effects incomponents to improve currently employed prediction methods. The proposedactivity aims at extending the radiation effects prediction models to include protoninduced SEE (Single Event Effect), generalisation of the models and verify themodels by Heavy Ion and proton irradiation tests campaigns.

The first part of the activity aims at developing proton induced degradation modelsin a predefined SRAM type. The results already obtained in the previous activitytogether with experimental results from ESA's SEU (Single Event Upset)reference monitor will be employed to develop and implement the model. Thesecond part aims at generalising the developed model to include other SRAMtypes. The generalised models are tested employing existing SEU rate predictiondata in the literature. Finally, in part three of the activity, the model is verified byselecting novel SRAM devices, performing SEU rate prediction and verifying theresults with experimental data from irradiation test campaigns.

In particular, the following tasks are envisaged:

- Study of transport and diffusion of electron-hole pairs mechanism in SRAM- Implementation of model- SEU rate prediction (employing model) and comparison to experimental data- Generalisation of model to include different SRAM types- Implementation and functional verification of generalised model- SEU rate prediction of novel SRAM types.- Irradiation test campaign of novel SRAM types and comparison with predictedvalues.

Deliverables: D1: Technical notes including model description. D2: Proton / SEU models. D3:Technical note including study report and model description. D4: Generalisedmodel. D5: Irradiation test plan. D6: Irradiation Test Report. D7: Verificationreport. D8: Final Report

Justification for DN: Results obtained from a previous contract with LIP (contract number18121 funded with 100K€) provided the Agency with valuable tools topredict the radiation environment on Mars. Additionally the activityprovided valuable knowledge of SEU modelling in SRAMs induced byHeavy Ions subsequently leading to improved SEU rate predictionmethods. The proposed activity is a natural continuation of that contract,improving SEU modelling capabilities of great importance to the Agency.Considering the work already performed on the previous activity by LIP, itis proposed, in order to guarantee the success of the project, that LIPcontinue the development.

Non competitive tendering is justified according to the article 6.1.c of theContract Regulations.



Activity Title: Verification of Enhanced Low Dose Rate SensitivityDescription: Traditionally, Total Ionising Dose (TID) qualification of components is performed at

high dose rates reducing test time at irradiation facilities and hence cost. The doserates employed are significantly higher than experienced by components in-flight.Enhanced Low Dose Rate Sensitivity (ELDRS) has been observed and reportedin the literature and considered to be of serious concern. ELDRS mainly affectsbipolar technologies. The results reported indicate that the ELDRS depends onseveral parameters such as biasing conditions, operating temperature devicestructure etc, complicating its characterisation. Current ELDRS test methods aretime consuming and costly, hence accelerated and practical ELDRS test methodsare required. The current ELDRS test procedure requires testing of EEEcomponents at a dose rate of 36rad(Si)/h. Thus, the irradiation test time forprojects such as Galileo, with Total Dose Requirement in eccess of 100krad, mayreach 4 to 6 months. The facility cost (approximately 200 to 300 Euro/hour) andproject schedule impact may be significant. The proposed new method potentiallyprovides a considerable reduction in the above mentioned test time (by 5 to 10times).

The objective of this activity is to further develop and verify a new radiation testmethod / technique to assess Enhanced Low Dose Rate Sensitivity (ELDRS) ofbipolar technologies and to implement the new techniques in the Agency TotalIonising Dose test method and guidelines and ESCC standards. The input of thisactivity shall be based on Agency guidelines and recommendations detailed bythe Component Technology Board's (CTB) Radiation Working Group. The activityis initiated by a study phase where the ELDRS effects in general and theproposed accelerated ELDRS test method is studied in detail. Subsequently, thetest method is analysed and a verification and implementation plan generated.The implementation plan shall focus on further development of the method to amaturity level suitable for application as a test method standard. The verificationand implementation plans shall be discussed and optimised at an ELDRS relatedworkshop at ESTEC, (organised by the Contractor). Following the workshop theverification phase is initiated by procurement of ELDRS sensitive EEE parts ofdifferent type from different manufacturers. Based on the accelerated ELDRS testmethod and ESCC22900 guidelines test plans shall be generated and testcampaign initiated. The results from the test campaigns shall be analysed andemployed to verify the suitability of the test method. Based on the analysed testdata, the test method shall be further refined. Finally, the outcome of the activityshall be presented to the CTB Radiation Woking Group. During the activity, awebpage shall be maintained to improve exposure and PR of the activitycontaining general information and activity status.

The test and verification work performed in this activity may lead to a test methodplan to be implemented in the European irradiation tests standards.

Deliverables: Verification test and implementation plans; radiation test plan and radiation testreport (including test method / procedure description suitable for inclusion inESCC test standards); final report.


Justification for DN: The availability of the novel ELDRS test method is required by the Galileoproject due to the high cost associated with the traditional low dose ratetest methods planned performed in the framework of the IOVdevelopment. Given the very specific nature of this activity, requiringextensive knowledge of radiation effects in EEE components and a verygood understanding of radiation tests facilities operation and use, it isconsidered that Seibersdorf Research has a unique experience in thisarea. In addition, Seibersdorf Research has available its test facilitieswhich is a major advantage in order to implement this activity. Taking intoconsideration those factors, together with the limited funding and timeavailable, it is considered crucial for a successful result of this activity toimplement this activity in Direct Negotiation with Seibersdorf Research.




Activity Title: Multiphysics Valve ModelDescription: The objective of this activity is to acquire functional models for all types of valves.

This will enable the valve designer to reduce the design lead-time. The activity willconclude with the development of a concurrent (stage/engine/equipment)engineering tool. The activity can be defined as follows: i. Functional modelling for engine/stage modelling; actuator parameters andperformance; simplified flow equations. ii. Flow control investigations; analysis of hydraulic torque in ball valves;pressure drop database for space valves; engine level integrated flow controlstrategy.

Deliverables: Experimental database related to flow control tests; flow control and actuationmodels for several types of valves and regulation equipment.


Activity Title: Thermal model reduction toolDescription: The objective of this activity is to establish a general technical specification for the

development of a thermal model reduction tool. It will also include the descriptionof the procedures/steps that have to be followed by the sub-system suppliers andthe system when using model reduction e.g. number and location of nodesrequested for the reduced model, criteria for the correlation with the detailedmodel. Some software requirements will also be considered at this stage, such asthe need to interface with the ESA thermal analysis tools ESARAD and ESATANand/or STEP TAS-NRF. Additionally, it will also intend to develop a thermal modelreduction tool and prepare its commercial distribution and to produce guidelinesfor thermal model reduction in order to help thermal engineers and to ensure theproper use of the techniques developed (thermal models reduction procedures,acceptance testing, information to be compulsorily provided with a reducedthermal model, possibilities of modification of a reduced model for use at systemlevel etc.).

Deliverables: A thermal model reduction tool, interfacing with the ESA thermal analysis toolsESARAD and ESATAN and/or STEP TAS-NRF and available at completion of theactivity for immediate use by the thermal community.

Justification for DN: Alcatel and Astrium-SAS are currently developing an original thermalmodel reduction method within the frame of the Large Platform Mission.The approach followed is generic and can be extended to address thegeneral issue of thermal model reduction. It is therefore proposed tore-use the experience gained by Alcatel and Astrium as much as possiblewith the goal of having an industrial commercial tool in place in 2005.


Lightweight systems (structures, propulsion, thermal etc)



Activity Title: Thermal modeling of test chambersDescription: Test chambers need to be modelled in order to correlate and validate a thermal

model with tests on a physical model (thermal balance tests). In the currentversion of ESARAD, test chambers cannot be modelled correctly, due for instanceto the fact that non-parallel (simulated) solar radiation cannot be taken intoaccount. This situation is not satisfactory and it is the objective of this activity toimplement major enhancements in ESARAD to improve the simulation and greatlyimprove the efficiency of such modelling. Modelling of both parallel and divergentbeams of single and multi-point sources are required as is non-uniformity of theflux within the beam. For obtaining the relevant requirements and validation of theresulting software an experienced test engineer needs to be involved as well asan experienced thermal engineer. Furthermore, for actual validation, a number ofactual chamber tests need to be performed with an estimated cost of 20kEurosper day.

Deliverables: Extensions of the current ESARAD program to allow thermal chamber simulationusable in the way of working of the thermal engineer.

Justification for DN: The proposal describes a modification and extension to existing software(ESARAD) that is developed and maintained by Alstom under the controlof ESA (contract no. 13908), funded with an amount up to 590 K€ throughdifferent budget lines (TRP, General Budget, Scientific Program).Furthermore ALSTOM holds the IPR on this software.

Non-competitive tendering is justified according to Article 6.1.c and d. ofthe Contracts Regulations.


Activity Title: VCHP thermal system-level modellingDescription: The objective is to develop a generic software module to carry out the analysis of

Variable Conductance Heat Pipes (VCHPs) at system-level. The module shall beused to simulate the impact of VCHPs on the overall Thermal Control System(TCS) of a spacecraft. This will thus require simulating in a simplified yetrepresentative manner the interaction of VCHPs mathematical models with a(large) Thermal Mathematical Model (TMM). The module shall be compliant withESATAN either as a pre-processing tool generating ESATAN language, or as atool interacting directly with ESATAN at run-time, or as an ESATAN subroutine orsubmodel template.

Deliverables: A VCHP system-level module, which shall be compliant with ESATAN.



Activity Title: Data exchange methods for Space Environment Effects toolsDescription: Space environment analysis often requires coupled treatment of geometry and

orbit (e.g. computing atomic oxygen fluencies, debris impacts, contamination,radiation, solar UV). Reliance on custom tools is very expensive and inefficient.New non-space technologies are being developed, especially based on Standardfor Exchange of Product Model Data (STEP, the casual name for ISO 10303),which offers a way to develop space-specific applications with maximum use ofcommercial tools. To get the most out of the available resources it is important tomake use of these new technologies. Also because the area of spaceenvironment analysis is continuously evolving it is important to do so with an openand modular approach. The use of these technologies will greatly enhance theefficiency in exchange of models and data between different kinds of analysis anddifferent disciplines. It also facilitates the harmonisation among tools, avoidingduplication of common functionalities in the various tools. Under a current activitythe data structures required for space environment analysis tools are studied, abasic implementation, using STEP, is being defined, and the necessary softwareis developed implementing the protocol. This work also include a prototypeapplication of the protocol in an existing space environment analysis tool namelyESABASE. In order to achieve the full benefit of the STEP based exchangefacilities it must be properly applied in a range of space environmental tools. Thisrequires both works on the exchange protocol itself (the inclusion of additionaldata) and on the application of the protocol in the various tools.

Deliverables: Updated step protocol and associated software implementing the protocol. Theapplication of the protocol in a number of specific space environment tools.


Activity Title: Development of high current, voltage and temperature cable suitable forElectric Propulsion

Description: One of the critical technologies to the further enhancement of Electric Propulsiontechnology in Europe is the availability of space qualified cable that can be usedfor EP applications requiring high temperature, high current and high voltagecapabilities (<300C, up to 2000 V, > 20A). In case of a geostationary applicationthe harness also has to cross the dynamic interface imposed by a pointingmechanism, this demands the additional feature of flexibility in the selected cable.To date cable insulation has been limited to PTFE, kapton etc. Although theseinsulation materials have excellent dielectric capabilities they are fundamentallylimited to operation at temperatures below approximately 200 degrees Celsius.Qualified wires will greatly simplify EP thrusters’ thermal and electrical design andqualified electrical connectors are mandatory to ease thruster implementation onspacecraft. There are two principle objectives of the proposed activity: The firstone is to identify and investigate the most promising insulation materials that couldbe used in the manufacture of high temperature and high voltage cables. Someterrestrial applications already demand wire that would satisfy the requirementsfor EP applications, but were not designed with the specific requirements of thespace environment (compatibility) or design goals (minimising mass and volume)and are therefore not suitable for space flight. The second one is to manufacturesample lots of the cable, subject it to thermal, vacuum, dielectric strength andvibration testing with the ultimate objective of eventual space qualification.

Deliverables: Identification of candidate cable insulation technology and selection of mostpromising; design of cable meeting space environment requirements; manufactureof sample cable lots and environmental testing for qualification.



Activity Title: Deployment Regulator MiniaturisationDescription: A product capable to regulate an appendage (reflector, panel, boom) spring driven

deployment, making the end deployment shock negligible, being simple, compact,reliable and cost effective would be very attractive to be used in the nextgeneration of Telecommunication satellites, mainly if it is adequate for a widerange of temperature. No European product is at the time being available in thisproduct category. A mechanism like that has been designed, manufactured, andsuccessfully tested being used in a Low Cost Deployment Mechanism that wasdeveloped under a TRP contract. This deployment regulator is based on theprogressive melting of a band cylindrically disposed made of a low meltingtemperature metal alloy. That mechanism is even adequate for systems requiringsequential deployment of its different constituents, such as big deployable foldedantennas, multi-panel folded solar arrays, tri-dimensional structures, etc. Theactivity proposed is to design and built a totally flight representative model ofsmaller size to fit better in the application requiring input torque in the order of aquarter or a half the capacity of present existing design, performing a completequalification test campaign.

Deliverables: -Miniature Deployment Regulator Qualification Model. -Complete qualification testcampaign.


Activity Title: High Precision Linear ActuatorDescription: The conversion of a rotary motion into a linear motion is generally obtained via the

Screw- Nut mechanism concept. One of the two elements is restrained intranslation and when it rotates, allows the translation of the other, which is fixed inrotation. One complete turn corresponds to the lead value for translation. Theminimum lead for the roller screws is 1 mm (medium efficiency) and 2 mm for theball screws (high efficiency). A new concept developed by SENER reduces thelead to less than 50 microns keeping the efficiency as in the roller srew concept.The innovative concept is based in the deformation of the screw through a specialbearing. A breadboard model is already manufactured to demonstrate theconcept.

Deliverables: Linear actuator QM


Activity Title: Miniature Pyrotechnic connector/disconnectorDescription: Miniature pyrotechnic initiators have been demonstrated in recent contract

activities. The objective of this activity is to develop miniature connectors /disconnectors according to user needs. This will include the definition ofrequirements and design; and as a second step the manufacture and theperformance measurements.

Deliverables: Miniature connectors/disconnectors



Activity Title: Acceptance Test Methods for Large SpacecraftDescription: Due to the complexity of very large Ariane 5 payloads, the integration of such

payloads is usually performed at sub-system or main subassembly level beforefinal assembly of the complete spacecraft. Acceptance testing of the completespacecraft is then complex and is generally performed at a very late state. At thisstage handling and logistic operations are very time consuming, accessibility tothe spacecraft is often limited and it is very difficult to perform modifications to thehardware in case of problems. In view of these difficulties to perform acceptancetesting on large Ariane 5 launched spacecraft (compared to typical satellites) it isproposed to perform a systematic study with the objective to identify specificacceptance test methods/approaches for these large SC. The objective of thisactivity is to define specific acceptance test approaches for large Ariane 5payloads. This shall cover the identification of acceptance test objectives atdifferent levels and the investigation of the selection/definition of the most suitableapproach to achieve the objectives. A typical example of a large Ariane 5 payloadshall be used to support the study. Logistic/operational constraints (e.g. S/Stesting/assembly testing, possible testing during integration/local tests) shouldalso be investigated.

Deliverables: Acceptance test approaches, objectives and methods.


Activity Title: NDE Techniques for Applications in Composites ManufacturingDescription: In recent years, the Non-Destructive Evaluation (NDE) of structures has proven

beneficial in the improvement of manufacturing processes as well as in theassessment of the integrity of structures. While many of the available NDEtechniques are capable of assessing a homogeneous component on a qualitativelevel, research is still underway in the area of NDE for improving the capability ofquantifying subsurface flaws in terms of orientation and size.The objectives of thiswork are summarized as follows:1.The initial phase of the project will involve the exploration of computed x-raymicrotomography (micro-CT) as an NDE technique for composite materials. Theobjectives of this exploration will be to investigate the use of micro-CT for directdetection of micro-cracking and debonding in composite structures, and todevelop micro-CT as a research tool in the development of a coupledexperimental and computational non-destructive testing methodology forassessing subsurface fractures within structures.2. The next phase of the project has the objective of developing an analyticalmodel relating surface displacements to subsurface flaw size and shape incomposite structures. This would be an extension of current work thatconcentrates on using such methods for characterizing embedded flaws such assensor for monitoring cracks in homogeneous materials.3. The final phase of this project will be to combine these tools into anon-destructive evaluation technique capable of assessing the integrity ofcomposite structures and improve health monitoring in composites manufacturing.Description of sub-activities and Planning: Technique of monitoring of the integrityof the structure in field conditions especially in the launch environment will beaddressed.

Deliverables: Report on analytical model, Report on evaluation technique.



Activity Title: Folded Core Structures for Flat and Curved Sandwich-PanelsDescription: The IFB ("Institute of Aircraft Design") developed during the project LuFo II a

process of manufacturing lightweight core structures by folding thin planematerials. Those structures are candidates for future passenger airplane bodiesas spacers for a planed double-skin concept. This technology possesses a highcost-reduction-potential for sandwich-materials compared to e.g. honeycombs. Aspecialty of folded core structures is, that material properties like longitudinal,width-wise or perpendicular stiffness and strength can be tailored for a plate orshell by calculating a fitting geometry. In that way the core structure can be fittedto a specific loading-case. Almost every foldable material like thin metal sheets,paper, etc. can be folded with the same machine. Today folded core structurescan be manufactured for applications like panels, lightweight wall constructions,etc. The objectives of this activity are to further develop the process for spacecraftaeronautical structures and components and materials; to investigate inspectionmethods (NDE) for CRFP structures with folded cores; to manufacture and test ademonstrator panel; to develop and test methods to introduce inserts into panelswith foldable cores; and to develop analysis guidelines and failure criteria forfolded core structures.

Deliverables: Flat demonstrator panel; identification and testing of inspection methods; costestimation for structural panels with folded cores; performance comparison offolded cores to honeycomb cores.


Activity Title: Advanced RTM-Process for Manufacturing of CFRP Space StructuresDescription: Standard manufacturing process for spacecraft and launcher structures is the

autoclave technique using prepreg-technology, even though the limitations suchas those regarding the development of complex 3D-curved CFRP (Carbon FibreReinforced Plastic) structures. Meanwhile resin injection processes based onRTM (Resin Transfer Molding) have been established in aircraft and automotiveindustry due to economical and performance reasons. Further developments onadvanced RTM processes like DP-RTM (differential pressure RTM) and SLI(single line injection) use a combination of advantages of both classical RTM andautoclave technique to reduce mold costs and better control the manufacturingprocess. First attempts for qualifying RTM process have been made and weresuccessful, as RTM process allows for new material combinations, lowerproduction costs (specially for small series), simple pre-manufacturing of complexdry semi-finished components, etc. In this regard the objective of this activity is thedemonstration of advanced RTM process to manufacture more cost-effective andhigh-quality composite structural components than the conventional compositetechnology.

Deliverables: Process qualification program; technology demonstrator identification;demonstrator design & test plan; demonstrator test and test evaluation.



Activity Title: Composite flow Moulding Components for Spacecraft ApplicationsDescription: Composite materials are offering advantages over conventional materials when

applied in spacecraft structures. The fiber and resin materials used in compositestructures are in general strong and durable, and it is therefore often themanufacturing process that dictates the properties and quality of the finalproducts. The Composite Flow Moulding (CFM) process patented by ICOTEC(CH) seems to be a revolutionary improvement over conventional manufacturingprocesses. Not only is the process well controllable, but it also allows themanufacturing of very complex shapes, such as threaded fasteners. In a currentGSTP study composite fasteners manufactured using this process are beingscreened for space suitability. Basic material tests are being performed and somemechanical characterization on "standard" fasteners is done. The objective thereis to show that the process and materials meet space requirements. This is Phase1 of a three-phase proposal. Phases 2 and 3, which are proposed here, build onthe results of Phase 1. Phase 2 would cover the qualification of "standard"fasteners for space use. In addition, in Phase 2 application specific componentswith special material property requirements (e.g. very low thermal conductivityfasteners, electrically conducting or isolating fasteners) could be manufacturedand qualified for use on spacecraft. Selection of a specific component could resultfrom the Phase 1 work. Finally, the aim of Phase 3 would be to integrate thedeveloped components into an application. The details of phase 3 depend on theactual application and are not part of this activity.

Deliverables: Space qualification of fastener standards, application specific components

Justification for DN: In the ESA contract 17613 (Composite Flow Moulding Components forSpacecraft Applications – Phase 1, with 178 K€ funded by GSTP3),composite fasteners manufactured using this process are being screenedfor space suitability. Basic material tests are being performed and somemechanical characterization on "standard" fasteners is done. The objectiveof this activity is to continue that work, covering the qualification of"standard" fasteners for space use, and the manufacture and qualificationof specific components with special material property requirements (e.g.very low thermal conductivity fasteners, electrically conducting or isolatingfasteners). Due to the specific know-how developed on the system as wellas the competences acquired by this team during the previous activity, it issuggested to carry out the proposed continuation with the same company.

Non-competitive tendering is justified according to Articles 6.1. c) and d) ofthe Contracts Regulations.



Activity Title: Piezo-Polymer Transducers for Non-destructive Testing and HealthMonitoring

Description: The piezo-polymeric transducers present many advantages, the most significantof them are:- production cost: due to the intrinsic low cost of the polymer support and of theprocess of shaping the transducer (by " laser scribing" process on apiezo-polymer film metalized with gold or other conductive metals)- conformability: due to the elasticity of the polymeric structure of the support thistype of sensors can be adapted (glued, bonded) to the body under test also inconcave or convex surfaces- reliability and mechanical robustness: due to the intrinsic polymer characteristics- direct coupling without the necessity to use other matching materials- wide spectrum of applications compared to piezo-ceramic transducers.Piezo-polymer Transducers can be developed to be used during the all phases ofspace missions. This activity aims at developing new piezo-polymer sensorssuitable to generate and receive acoustic guided waves in composite materials,employed in structures, elements or components for space applications (such astanks, boosters, parts of launchers, elements of a spacecraft or of a spaceinfrastructure, large antennas).This activity will include the engineering, manufacturing and validation of PPT's(both at engineering model level and at proto-flight model level) for defectsdetection/monitoring on composite Materials, first in simulated launch / spaceconditions and later during a selected space mission or within an in-flightexperiment on the ISS. Due to the different environment conditions, different typeof transducers and different type of coupling to the Composite Material could beimplemented and validated during a dedicated test campaign. It could also beevaluated the possibility of embedding this kind of sensors directly into theComposite Material during the manufacturing phase according to differentproduction processes.

Deliverables: Design refurbishment, manufacturing and validation of a piezo-polymer transducerat engineering model level; design finalization, manufacturing and "in situ"validation at proto-flight model level.


Activity Title: Payload adaptors with integrated shock & vibration dampingDescription: Payload adaptor is a key element to reduce and filter shock and vibration

excitation inside the spacecrafts with an associated cost and mass saving atsatellite level. Some developments are presently running in this area, but aremore S/C oriented. Main idea of the present proposal is to develop a fullyintegrated adaptor, which includes the attenuator device. Relative displacementsbeing larger on the adaptor side, this solution exhibits in theory a better potential.This payload adaptor will reduce the induced excitation levels at the spacecraftwith the associated cost and mass saving at satellite level by a passive system.Description of sub-activities and Planning: -Trade studies to select the mostadequate mechanical configuration. -Modification of a standard adaptor to adddamping capabilities by a passive system. -Qualification by test of the adaptor toverify the shock / vibration attenuation capabilities.

Deliverables: Study Report for selecting the most adequate mechanical configuration, - Modifiedstandard adaptor, Qualification Test Report



Activity Title: Study on Carbon Fibre Tube Inserts-ExtensionDescription: The innovative carbon fibre tube insert design that was developed and used for

the ROSETTA Lander is currently subject to a more thorough and generalinvestigation and qualification. However, it is already clear that not all interestingdesign modifications and load cases can be analyzed and tested with thenecessary statistical significance within the given time and budget framework. Anextension of the study is needed to cover cyclic and thermal loads. The objectiveis to assess the mechanical properties and fields of potential use for all interestingdesign / load combinations of the carbon fibre tube inserts and to implement thefindings in the ESA Insert Design Handbook (extension and completion of thealready ongoing work).

Deliverables: Study Report, Updates for the ESA Insert Design Handbook

Justification for DN: The innovative carbon fibre tube insert design, that was developed andused for the ROSETTA Lander, is currently subject to a more thoroughand general investigation and qualification under ESTEC/Contract no.16822 (budget of 200 K€ funded by GSTP). The innovative carbon fibretube insert design promises to be generally lighter than standard designs,under equivalent load-bearing capabilities. This activity is a continuationand completion of the already ongoing work.



Activity Title: Shock response in spacecraft and equipment using combined FE/SEAanalysis

Description: InterAC has developed enhancement of SEA modelling of complex structures byusing FE model to provide SEA parameters. This technique called Virtual SEA isable to post-process classical FE results into SEA network. It was developed forautomotive application (modelling car chassis SEA subsystems) to compensatethe inability of analytical equations to provide reliable representation of the true 3Ddynamic complexity. Localized structural complexity can thus be modelled usingsets of small FE models and translated into SEA parameters. The full SEA modelof the payload, built in general software such as AutoSEA, can thus be widelyimproved after importing these parameters in the AutoSEA network. A key issue,in translating FE results into SEA parameters is the substructuring process (i.e.portioning a domain into a set of 'weakly coupled' dynamic smaller systems). Ithas been solved by developing intelligent routine able to re-organize FE nodesinto subsystems from forced FE response results. Depending on the choice of acentral frequency band, a frequency band-dependant portioning can beautomatically derived from FE results. It is well known that SEA portioning isdependant on frequency (i.e. on the wave length of vibrations at that frequency).The number of subsystems required for good prediction of mechanical energytransfer is increasing with frequency. Now the portioning can be fitted to thetargeted frequency band.

Deliverables: Study reports and Software



Activity Title: 20-50K Pulse Tube coolerDescription: European coolers already existing or under development currently cover the

temperature range 50-80K and below 20K. Cooling in the temperature range20-50 K is required to improve the performance of scientific and earth observationdetectors and would also enable the use of the recently discovered lowtemperature superconductor (LTS) MgB2.The objective of this activity is then thedevelopment of a long life EM Pulse Tube cooler to provide a heat lift of 400mWbelow 25K and capable of surviving the launch and space environment. Theactivity covers the design, manufacture and test of an engineering model of a20-50K Pulse Tube cooler based on the previous work on the large heat lift40-80K cooler and on the developments for ground applications. The buildstandard will be such as to support full cooling performance evaluation and toverify capability to survive launch and operate in either a Space Station or satelliteenvironment.

Deliverables: Tested EM and documentation.

Justification for DN: The team of Air Liquide, CEA and Thales is currently developing a 30Kpulse tube for terrestrial applications, funded by the EC, which makes useof the Thales "tactical" compressor technology heritage. This compressoris being upgraded for use with the 80K Cryosystem deep freezer and willform the basis for the compressor of the Large Heat Lift 40-80K cooler,which shall be the baseline for the now-proposed 20-50K cooler. CEA hasan established expertise in the 2-stage cold-finger development needed toextend operation from 80K down to 20K. The activity is a continuation ofthe contract 14896, “Miniature 50-80K pulse tube cooler”, funded with 420K€ in TRP.

Non-competitive tendering is justified according to Article 6.1.a) and c) ofthe Contracts Regulations.


Activity Title: Lifetime Extension of Small Rotary Coolers for Microsatellites andInterplanetary Missions

Description:Propose design changes to coolers, which would increase lifetime without majorincrease in cost, mass or required power. Modify cryocoolers and undertakeperformance characterisation of the cooler.

Deliverables: Prototype small rotary cooler with associated documentation.



Activity Title: Carbon Carbon Grids for Ion ThrustersDescription: The acceleration grid of current ion thrusters show an excellent life performance,

but special care has to be given for large grid diameters, so that the grids are ableto withstand launch loads and operational temperatures without criticaldeformation. Erosion measurements on various material samples, showing anexcellent stability, allow the conclusion that Carbon-Carbon (CC) should be theoptimum candidate for future large thrusters. It is not clear if CC grids withdiameters above 20 cm can meet the strong requirements to thruster grids likeflatness, alignment, sputter effects, stability and wall thickness. Consequently thefeasibility to build such grid has to be investigated, and limited life testing shouldbe performed. The following tasks will be included: design of a large grid (>20 cmdiameter) based on CC material, selection of CC raw material, manufacturing ofbase material, manufacturing of grids, manufacturing process optimisation;manufacturing and integration of a grid package and a thrusters; performanceverification testing; design review / update-manufacturing and integration of a gridpackage and a thrusters; performance verification testing; durability test.

Deliverables: Grid package manufactured; test results; functional test of structural and thermalmodels.


Activity Title: Advanced Tank in composite material for Electric PropulsionDescription: Electric Propulsion (EP) is nowadays considered a strategic technology that is

rapidly becoming available for commercial applications both in the GEO and LEOsatellites market. The most significant EP tasks foreseen on medium/high sizecommercial satellites concern the orbit transfer from the parking orbit to theoperational orbit and the orbit control, once the operational orbit has beenachieved. In addition, the EP applications for planetary exploration are nowgaining a strong momentum. In view of a massive utilization of EP on near futurecommercial satellites (e.g. based on Alphabus platform) and scientific spacecraft(ref. BepiColombo mission), the availability of low cost, low weight, high produceability EP components will play a key role for the definitive EP use. In this regard,the tank for the containment of the propellant gas (Xenon) is identified to be a keycomponent of an EP sub-system. This activity aims at improving themanufacturing, at a high throughput rate, of Xenon composite tanks for EPapplications (although this shall also provide opportunity to manufacture tanks forChemical Propulsion), without using autoclaves and ovens for composite curing.The activity will address in particular the tank technology based on an internalliner fabricated with light material and an external vessel realized in compositematerial filament wound around the liner and polymerized, layer after layer, with alow energy (about 300 keV) electron beam accelerator. The potential advantagesidentified are: no practical limitation in the final thickness of the tank; lower cost oftank manufacture; homogeneity in material growth; possibility to lay theimpregnated fibres along "non-geodetic" lines; freedom of choice of the optimumpatterns for maximizing the product mechanical strength; and production of smallpressure vessels.

Deliverables: Pre-development tests for a preliminary "tuning" of the process parameters;detailed design of a tank prototype, to be manufactured with the new proposedprocess; fabrication/procurement of a liner prototype; manufacturing of the tank;characterisation of the tank sample/s; assessment and critical analysis addressingthe manufacturing of a tank at flight-model standard and the "industrialisation"issue.



Activity Title: Unified Propellant Management AssemblyDescription: An integrated or Unified propellant Management Assembly (UPMA), employing a

mechanical based HPR could reduce overall system mass, increase reliability andallow for full EP system testing at Thruster Module Assembly (TMA) level. Theobjectives of the proposed activity are to identify and investigate the mostpromising technologies available for implementing a UPMA. This would includeHPT and LPT's, Isolating pressure regulators, pressure sensors, flow meters andthermo-throttles. A breadboard should then be constructed and characterised forenvironmental compatibility and operational performance leading to themanufacture of a Qualification Model designed to take the UPMA and associatedtechnologies to a high Technology Readiness Level.

Deliverables: Identification of valve/HPR/flow controller technology and options, UPMAmanufacture, cost prediction, UPMA performance and lifetime prediction;breadboard UPMA manufacture and experimental characterisation; QMmanufacture, environmental testing, and life test.


Activity Title: Ceramic Mounting Interfaces for TanksDescription: The mounting brackets of satellite tanks are presently made of titanium. The use

of fibre reinforced ceramic material can improve the mechanical and thermalinterface of the tank with the spacecraft, by providing a higher stiffness and byacting as a thermal barrier. Brackets made of ceramic material have beendeveloped for several applications. This activity will be devoted then to adapt thistechnique to the requirements of satellite tank mountings. It will include themanufacturing and development testing of mounting brackets with an existing tank(including vibration, shock and determination of thermal behaviour).

Deliverables: Reports; requirements specification; development plan; manufacturing anddevelopment testing of mounting brackets with an existing tank.


Activity Title: Development and design verification of a 20N monopropellant thruster flowcontrol valve

Description: Availability of European Flow Control Valves for European thrusters is consideredstrategic in order to avoid export restrictions of non-European components, whichaffect the competitiveness of European thrusters and propulsion systems. Theproposed activity shall cover the development of the flow control valve, and thedesign verification testing (including environmental and life testing) of a flightrepresentative model. Special attention shall be given to physical, chemical,mechanical and magnetic characteristics of materials; magnetic actuationperformance; welding parameters selection; sealing and valve seat resistance;particles contamination limits; avoidance of sliding surfaces; compatibility withspace environment; reproducibility of valve performance; reliability; single pointfailure modes; low cost manufacturing; and possibility to use commercial pieceparts. The performances of the final design shall be compared to that onesrelevant to the valves to be replaced.

Deliverables: CDR Data Package. Design Verification Test Report. Flight representative modelused for design verification testing.



Activity Title: Slow Acting Latching ValveDescription: Availability of European Latch Valves is necessary in order to avoid export

restrictions of non-European components, which affect the competitiveness ofEuropean propulsion systems. By developing a latching valve with slow actuationcharacteristics it will be possible to overcome the pressure transient problems atpropulsion system priming and during operational life. This activity shall includethe specification for a slow acting latching valve, the establishment of the basicdesign and development test plan, the development of the valve and, finally, thedesign verification testing (including environmental and life testing) of a flightrepresentative model. The performances of the final design shall be compared tothat ones relevant to the valves to be replaced.

Deliverables: CDR Data Package including development report, design verification test report,and flight representative model used for design verification testing.


Activity Title: Pump Pressurization of Propulsion SystemsDescription: The activity will consist of a study of application of pumps for pressurisation of

propulsion systems for spacecraft, with the objective to identify the benefits interms of performance, mass, volume, cost, etc. It will include an assessment ofS/C propulsion systems with pumps, usage of pumps, effect on propulsion systemdesign and operations, foreseen effect on other S/C subsystems (e.g. power);definition of pump driven propulsion system concepts for selected missions;assessment of pros and cons, and ultimate benefits; and identification of requiredtechnology and hardware development.

Deliverables: Survey results, concept definitions for selected missions, assessment report androadmap.


Activity Title: Study of a reaction sphere for attitude control using H-Brisc 2Description: Attitude control systems (ACS) traditionally need (at least) three reaction wheels.

The orientation of the satellite can be changed by reaction at the acceleration ofthe appropriate wheel. Another traditional approach is to use a control momentgyro consisting of a rapidly rotating wheel held by a gimbal. Applying torques onthe gimbal joints changes the satellite orientation. The proposed approach is touse one unique reaction sphere. The sphere is held in position by magneticlevitation and can be accelerated in any direction by asynchronous motors. Thecontrol of the 3D levitated sphere is very demanding for processing power. Thegoal of the study is to demonstrate the feasibility of this ACS sphere concept withtoday available new controller technologies. The proposed controller will be basedon a recent high-power space-qualified processor: H-BRISC2. This activity willcover the following aspects: attitude control system , asynchronous motors, andmagnetic levitation (magnetic bearings) plus high performance microcontrollers.

Deliverables: Demonstrator showing the feasibility of the ACS sphere concept.



Activity Title: Lifetesting of New ConceptsDescription: The objective of this activity is to assess the long-term behaviour of the new

generation of two-phase loops through a dedicated lifetest programme. Theactivity shall start with the design and manufacturing of the appropriate number oftwo-phase loops for a comprehensive lifetest programme, taking into account allmaterials which will be used in real loops, the design and manufacturing of theappropriate test set-up, the definition of a lifetest programme and the execution ofthis programme.

Deliverables: Fully life-tested two-phase loops and associated documentation.


Activity Title: Development of an Electronic Pressure RegulatorDescription: Despite the advances in "high tech" propulsion, many missions still require cold

gas (or warm gas) nitrogen or xenon systems. Typically these systems usemechanical pressure regulation, often from US sources. For example CRYOSATuses a mechanical regulator from Mu Space Components. The objective of thisactivity is therefore the development of a European source for the regulator. Theactivity will result in the development of a European source for the regulator withthe following characteristics: electronic "bang-bang" regulation has benefits as thecontrol pressure and hence thrust levels can be varied; the use of Polyflex'sSV-14 series valves will give a mass reduction on mechanical regulators (eachvalve weighs around 45 grams); low cost design and manufacturing.

Deliverables: CDR documentation and breadboard model.


Activity Title: Mini TPL (CPL & LHP) Design Improvements and Longterm StabilityDescription: The objective of this activity is to further improve and optimise the design of

miniature two-phase loops:-Further reducing the design in order to reduce the power range and the volume.-Building appropriate demonstration models based on this improved design takinginto account on-going activities to further reduce the diffusion and leak rate.-Performing a performance test and long-term stability (lifetest) programme.

Deliverables: Fully performance and life-tested demonstration models with associateddocumentation.

Justification for DN: This activity represents a continuation of a previous ESA/CNESharmonised activity (a successful development was done at Astrium -co-funded between ESA and CNES, leading to very promising firstresults): ESA contract number 14021, 175 K€ funded by TRP.




Activity Title: Development and Flight Qualification of a Solid Propellant MicropropulsionModule for Nanosat Application

Description: A technology for micropropulsion based on the combustion of an energeticmaterial stored in a micromachined chamber of silicon or Foturan has beendeveloped. Currently, the solid propellant technology has reached a good level ofmaturity. This technology presents evident capabilities for micropropulsionapplication. For low dV impulse requirements, solid propellant thrusters offer manyassets: low power consumption, no moving parts, low fabrication cost, simpledevice so minimizing the risk of failure, easy operability and safety requirement,different thrust levels possible in one matrix. This activity shall be devoted then tothe development and Flight Qualification of a Solid Propellant MicropropulsionModule for Nanosat Application and to validate the technology in spaceenvironment by the participation to a NANOSAT validation flight.

Deliverables: Flight hardware and flight qualification report.


Activity Title: Low cost fabrication techniques for Titanium propellant tanksDescription: The current technology for the manufacturing of propellant tanks made of titanium

6AlV4 is based on relative thick forgings (25mm) machined to the final wallthickness (0.8 - 2mm) and welded to form a complete tank. The objective of theactivity is to avoid forging and machining by forming of sheet material to tankdomes and cylinders. This avoids nearly every machining operation except theweld area and the ports integration. Optimisation has to be done to reach the finalrequired wall thickness by careful analysis of the pre-contour. This activity willinclude a trade-off study between the forming technique and the classicalforged-machined technique in respect of cost influence depending on thedimensions, mass influence depending on the tolerances, and technical influencedepending on the PMD configuration.



Activity Title: Advancement of multi-functional support structure technologiesDescription: Further miniaturization of satellites requires not only the accommodation of all

subsystems in the very limited volume inside the satellite but also significant masssavings. As a result, separate functioning of relevant spacecraft subsystems (thecase for conventional satellite designs) can no longer be maintained but a highlevel of integration of the different subsystem functionalities needs to beenvisaged. These requirements can only be met by advanced structuretechnology concepts such as multifunctional support structures (MFSS), whichintegrate e.g. structural and thermal control design, radiation shielding andelectronics. Basic MFSS technology developments are currently performed withina GSTP-3 activity. However, further efforts are needed to extend the applicabilityof such technology and to achieve an industrial application level. Then theutilisation of advanced MFSS has the potential to significantly improve the overallsatellite mass and system performances. Building on the relevant technologyactivities already started the complexity of the MFSS designs shall be enlarged.The design and manufacturing concepts shall be demonstrated by hardwareverification tests. Final objective of this activity shall be to provide a detaileddesign concept of a MFSS prototype for an in-flight demonstration.

Deliverables: Detailed design concept of a MFSS prototype and test results.


Activity Title: Rotary Piezoelectric Motor - PrequalificationDescription: The proposed activity is aimed at designing, manufacturing and pre-qualification

testing of a European ultrasonic piezo motor (rotary piezo-electric actuator) forspace applications. The work shall comprise: -identification of present technologystatus and critical design features- conceptual design update- development testingon critical design features- detailed design of a qualification model -testing toqualification levels, Critical issues identified before include: -suitable friction layermaterials for the required temperatures- piezo components/material qualification -miniaturised and low-power drive electronics.

Deliverables: Qualification model and technical data package.



Activity Title: Small rotary actuator dedicated for Small antenna deployment and pointingoperations

Description: The proposed activity main goal is to develop and qualify a small rotary actuatordedicated principally for small Antenna Deployment and Pointing Mechanism(ADPM). Targeted deployable and steerable beam antenna reflector size andmass are: 80cm to 100cm; <3kgAt least two actuators are required at ADPM levelto allow full deployment and pointing functions. The actuator design shall takeadvantages of the recent new European technology improvements in the field ofReducer (Harmonic Drive), Lubrication (Fluid), Sensor (Potentiometer). Emphasisshall be put on decreasing the mass (7Kg) of the existing ADPM (today designedto drive big antenna reflectors). Mass saving concerns the actuator itself, but mayalso concern the Hold-Down and Release Device (HDRD), where for such smallantenna mass and inertia, it should be possible to achieve this function at actuatorlevel (preloaded system during launch) instead of using dedicated HDRD attachedto the reflector.

Deliverables: Small ADPM EQM and associated tests results.


Activity Title: Ka-band TM/TC for Telecommunications GEO satellitesDescription: Telecommunications GEO satellites only using Ka-band are expected in the

medium term. They will require TM/TC antennas working in the same frequencyband. This activity is concerned with the development of Ka-band TM/TCantennas for geostationary satellites. Conventional concepts of using fixed lowgain antennas will likely need to be reviewed bearing in mind the high atmosphericlosses at Ka-band and this may lead to new antenna architectures andtechnologies.

Deliverables: Antenna elegant breadboard models.



Activity Title: Essential Telemetry Support ASICDescription: This activity will specify, design, manufacture and test a mixed analogue/digital

Essential TM Support ASIC capable of performing periodic acquisition of essentialspacecraft parameters such as temperatures, voltages, digital status signals etc.Acquired analogue parameters will be converted to digital values. After acquisitionand conversion the data will be formatted into packets before being output on apacket wire type of interface for connection to an external TM assembler andformatter.In addition to the Essential TM functionality it will be possible to use the ASIC as aUser Interface front end. In this configuration it will be possible for an applicationto access the ASIC to control the data acquisition and to retrieve the acquireddata for further processing. The resulting ASIC shall be made available as astandard component for the space community. In particular the following tasks willbe included: Specification of the ASIC defining all required interfaces andfunctionalities; Design, development and verification of the ASIC design and theassociated test equipments; Manufacturing and validation of the ASIC and theassociated test equipment; Commercialisation of the ASIC.

Deliverables: Essential Telemetry ASIC Specification & Data Sheets/Users Manual ASICPrototypes and associated test equipments.


Activity Title: Radiation Protection for Advanced Equipment DesignDescription: The GSTP-3 activity "Advanced Equipment Design" concerns the development of

advanced concepts for lightweight equipment housings based on compositematerials and offering e.g. high specific stiffness and strength, high thermalconductivity and improved protection capabilities with respect to space radiation orEMI shielding. To meet the requirements the best suited composite materials andmost promising lay-ups are identified. Breadboard models are designed andmanufactured to experimentally verify that the new design concepts can fulfill therequirements for typical electronic boxes.

The objective of the ongoing contract is the development of advanced equipmenthousing concepts with improved performances (mechanical, thermal, radiationand EMI/EMC shielding). The additional work package proposed here aimsparticularly at providing better answers to which multi-layer composite structureshave to be used to provide adequate radiation protection for electroniccomponents. This is to be demonstrated by radiation attenuation simulations andradiation tests.

Within the main contract basic radiation attenuation tests have been performed byHUT/LLS to evaluate the effectiveness of the composite laminate with integratedradiation protection layer. The definition and potential optimization of the structurallayout was supported by radiation attenuation simulations carried out by HIP usingthe CERN/GAENT4 software.

Justification for DN: The execution of the proposed work by HUT/LLS and HIP will ensure thatefficient use is made of the relevant knowledge and experience alreadygathered by these institutions during the previous GSTP-3 activity(contract no. 16725, budget of 950 K€).




Activity Title: Ku/Ka-Band Multifrequency feederDescription: This activity intends to deep in the knowledge on how to combine different

frequencies in the same feeder without degrading the electrical performances ofthe feeder in each individual frequency, and aiming at the same time for mass anddimensions reduction. The objective is to look for an optimum design in theselected bandwidth and to design the polarisers and filters in wide band andnarrow band depending on its position on the feeding chain.

Different configurations will be studied for the feeding network, choosing the onemost promising from the electrical performances point of view combining a simpletopology with a mechanical design which results in reduced mass anddimensions.

The application envisaged for this activity includes EO missions such as ESA’sEGPM (European Global Precipitation Mission EGPM), but alsoTelecommunications (e.g. internet via satellite at Ku-Ka band). Considering EGPMas a first target application, this activity will cover the development andqualification of an EQM feeder in Ka band with five different inputs, two of themwith linear polarization, vertical and horizontal at 18 GHz, the third input beinglinear polarization at 24 GHz and the last two being both polarization at 36 GHz.

Justification for DN: RYMSA has a great experience on provision of antenna devices, analysisand mechanical design, structural implementation, with EM tools availableand workshop capability close to it. Rymsa has tools and capability asregards the radiative performance of feeds with a broadband capability(e.g. CHAMP, ROT-2, Sopera, various filter/matching SW, experience forX-Ka band feeds). Moreover, RYMSA is one of the preferred suppliers ofantenna feeders for ASTRIUM, prime candidate for ESA’s EGPM missionfor which the phase A has been finalised.




Activity Title: Next generation APSDescription: The LCMS and HAS APS sensors have been designed under a previous contract.

Several Star Tracker and Payload developments for ESA are planning to makeuse of these new CMOS image sensor prototypes. Before these new devices canbe used on space missions further development and evaluation work must becompleted. The work yet to be performed consists of consolidation of allassessments and test results and the determination and agreement of anyrequired design modifications and 'bug' fixes; ADC testing over temperature andfrequency; update of 12-bit ADC design; design and definition of FM packaging;design of stand alone ADC packaging; implementation of agreed designmodifications for the HAS; production of a development plan for the LCMS; 16 bitADC upgrade design; production of development plan; manufacture and detailedperformance evaluation, including temperature and radiation testing, of one batchof HAS devices; development of a component qualification plan for the HAS; anddevelopment of flight model screening procedures for HAS.

Deliverables: Test results and SEU effects models as resulting of the characterization testingand modeling of the HAS and STAR1000 devices.

Justification for DN: The innovative carbon fibre tube insert design, that was developed andused for the ROSETTA Lander, is currently subject to a more thoroughand general investigation and qualification under ESTEC/Contract no.16822 (budget of 200 K€ funded by GSTP). The innovative carbon fibretube insert design promises to be generally lighter than standard designs,under equivalent load-bearing capabilities. This activity is a continuationand completion of the already ongoing work.




Activity Title: Optical frequency comb: critical elements pre-developmentDescription: Until recently, there was no reliable optical clockwork mechanism that could count

optical frequencies of hundreds of THz (1 THz = 1012 Hz). MPQ coulddemonstrate that the modes of a mode-locked femtosecond laser can be used asa precise ruler in frequency space as they form a series of frequency spikes,which is called frequency comb and which provides the long missing simple linkbetween optical and microwave frequency. Thus, an optical clockwork can be setup to improve instrument and experiment performance for space missions in allprogramme areas by orders of magnitude.

In this activity, mandatory selected H/W subelements in an optical frequencysynthesizer shall be Breadboarded under the view of the later system applicabilityin space. Thus design and opto-mechanical set up of the most critical H/Wsubelements shall be optimised. Here, laserresonator, mode couple mechanism,positioning elements, amplifier unit and spectral broadening element areconsidered. These elements will be set up in a ruggedized way, tested andcharacterised according to their vibration, temperature and vacuum sensitivity.The activity will be carried out in two phases:

Phase 1: Definition and Pre-Tests. Generation of a requirements documentconsidering the later space application; Preliminary system specifications; Workout of laser specifications; Definition of the laser set-up; Design verification underthe view of typical requirements for a system use in space; Definition of a testprogram; Selection of critical H/W components; Procurement of the hardwarecomponents; Execution of functional tests; Execution of performance tests, BBtesting of laser specifications.

Phase 2: Environmental System Tests. Testing of the components behaviour andcharacterisation of critical elements under space related environmental conditions(especially temperature and vacuum); Optimisation of the selected components.

Deliverables: An optimized and ruggedized design of critical subcomponents shall be generatedand selected BB tests executed.

Justification for DN: Directly after the invention of the optical frequency comb and the foundingof Menlo Systems in 2001, KT together with Menlo Systems set up the firstpreliminary test units targeting towards the later use of the technology inspace. The MPQ spin-off Menlo Systems is single source to buy opticalfrequency synthesizers and has the broadest experience in thetechnology. KT is now deeply involved in the space related aspects for theoptical clockwork.




Activity Title: Investigation on Optical Fiber Harness TechnologyDescription: Optical fiber networks are being considered for digital data communication

systems onboard satellites, as an alternative to the classical electricalcommunication harnesses based on Twisted Shielded Pair (TSP) copper wires.However, the use of optical fibers with its associated opto-electronic componentsin the space environment poses specific problems not encountered in terrestrialnetworks. This activity is aimed at resolving these “space specific” issues. It isanticipated that optical fiber systems onboard spacecraft will be based oncommercial products developed for terrestrial applications, i.e. laser transmitterdiodes, optical fiber cables, photo diodes, optical splitters, optical connectors andother support electronic components. The tasks to be performed to arrive at anoperational space application of such devices include: selection of suitablecommercial or pseudo commercial components; performance testing of thesecomponents in simulated space environments, including high energy radiation,temperature extremes, thermal cycling, vibration, shock, etc; design and testing ofa basic integrated system to demonstrate its performance in terms of data rate,timing precision and timing stability over temperature, Bit Error Rate (BER)measurement with simulated data streams, etc.

Deliverables: Activity report and test results.

Justification for DN: This activity is a follow-on to a previous development which has takenplace as a Rider to the contract 15138 for the "MIRAS Demonstrator PilotProject 3", in which Contraves was entrusted with the development of theoptical harness technology, as resulting from new system level analyses.




Activity Title: Deployment Simulation of Complex Antenna StructuresDescription: Scientific, Earth Observation and Telecommunications missions require the

deployment of antennas, solar arrays, booms and other appendices that need tobe stowed during launch. Typical Project activities, such as Mars Express andLDA (Large Deployable Antenna), require numerical simulation of deploymentkinematics, actuation control and structural dynamics, including shock analysis, inorder to limit the risk in test campaigns and operations during the mission. Thestate-of-the-art algorithms show clear convergence difficulties to capture theshock response.

This activity will be devoted to the prediction and numerical simulation of thedeployment of large structures, including the mechanical shock. It is a highlydemanding objective due to the confluence of diverse disciplines and contradictingrequirements. The need to simultaneously capture widely spread phenomena,such as low-frequency actuation and dynamics, together with high-frequencyresponse, imposes new challenges on the integration algorithms in multi-bodyFEM techniques. In this regard the improvement of an existing tool (Mecano) isproposed (including convergence analysis and implementation of energyconservative algorithms). Since validation with experiments is a mandatory taskfor the production of reliable numerical tools, here the validation will be carried outwith the LDA due to the criticality of its deployment and the availability of testresults including shock. The tasks to be carried out will include the following:- Review of requirements: identification of integration time scales involved in thephysical phenomena- State of the art of conservative time integration schemes- GUI for hierarchical models- Experimental validation- Generation of multi-body FEM models.

Deliverables: Software update; Mathematical models; Breadboards.

Justification for DN: Samtech (BE) is the most suitable company to carry out this activity sincethe initial convergence analyses was developed by this company withinthe Mecano commercial software. Moreover, Samcef Mecano is the onlyEuropean commercial software with these required capabilities.




Activity Title: Carbon Fibre/Aluminium Sandwich Panels Interconnection SystemDescription: The objective of this activity is to develop sandwich panel interconnection

concepts based on the SMART-1 Zip-Edge Connection System compatible withCFRP skins. The panels and the interconnection system shall be made ofcommonly used materials already space qualified. SMART-1 structure (allaluminium panels) implements a novel design which allows easy opening of thepanels during the satellite integration. Along the edges, brackets can be attachedto the panels allowing not only hosting of the structure in any position but also theattachment of hinges. This means that panels can be opened just like aconventional door, improving access to the units during integration. This design isstiff enough to support the opening of two panels at any time, even when thestructure is fully loaded with the attached equipment. Such a design is currentlynot available for CFRP structures. This activity shall consist of two main phases:

-Phase 1. Development of a panel interconnection system with the sameapproach as for the Zip-Edge Connection, i.e. consisting of a continuous link allover the panel edges to maximise the participation of each panel to the overallstiffness of the structure. Design and MAIT of samples. Further development ofthe best interconnection identified to ultra lightweight panels.

- Phase 2. Design and MAIT of a demonstrator structure with several CFRPsandwich panels and a complete connection link of about 1000 mm.

Deliverables: Design concepts and trade-off for interconnection systems applicable to satellitesandwich panels. Development test samples. Design and manufacturing files for ademonstrator structure. Demonstrator structure. Results of the evaluation plan.Identification of advantages of proposed system compared to traditional paneljoining (e.g. cost, mass, schedule trade-off).



Activity Title: Mechanical Cold Gas Regulator DevelopmentDescription: The activity is aimed to get the Cold Gas Propulsion System (CGPS) regulator

requirements survey and report. The purpose is to get the technical requirementsfor a CGPS regulator from potential users, such as Astrium, Alcatel Alenia Space,and others, as well as Nanospace's requirements.In addition, the following tasks will be included in the activity:- Design, Sizing and Analysis of Cold Gas Propulsion System (CGPS)configuration to accommodate results of requirements survey and report.- Preparation of Critical Design Review (CDR) level datapack.- Engineering and design for manufacture. Manufacture, Assembly Integrationand Test (MAIT) for Qualification/ Structural Test Model (QM/STM) model.- Qualification Model (QM) level testing to generic requirements.- Qualification Model (QM) test report and Qualification Test Review Board(QTRB) data pack.

The phase involved is essentially a delta qualification phase, to bring the XenonRegulator configuration, developed for the Alphabus Electric Propulsion Systemprogramme, to the Cold Gas Propulsion System regulator requirements of thePRISMA programme and other compatible Cold Gas Propulsion Systems.

Deliverables: Qualification Test Report

Justification for DN: Marotta Ireland is currently developing a mechanical pressure regulator forthe Alphabus Electric Propulsion System (EPS), under an initial ESAdevelopment contract number 18367/04/NL/PA, and a follow on ARTES 8contract with Alcatel Alenia Space to include the PFM delivery. The workproposed in this activity, the development of a generic CGPS design is afollow-up of the work already initiated in the previous contract.




Activity Title: Metal Matrix Composite Based Flat Heat PipesDescription: Modern communication satellite and the related miniaturization of the components

result in an increasing power density in the used microelectronics. The necessaryheat removal requires advanced packaging solutions to achieve high reliabilityand long lifetime of the electronic devices. AlSiC metal matrix composites offeradvanced properties such as high thermal conductivity (180-200 W/mK), lowcoefficient of thermal expansion (6-8x10-6 K-1) and low density (3 g/cm3), andattract a lot of interest in high performance electronic packaging. Due to thesematerial properties a direct and therefore thermally very efficient bonding of thehigh dissipating chip to such a material is possible.

The activity is aimed to further optimize and improve the performance of flat heatpipes based on AlSiC metal matrix composites. Activities concerning massoptimisation, improved/enhanced wick design, manufacturing reproducibility willbe performed, followed by a complete life-test programme of the improved designunder different load conditions. In parallel to this part, heat pipes will be designed,built and tested with a new metal matrix material (AlC, Aluminium-Graphite), whichwill further allow to reduce the mass of the design.

Deliverables: ´- Procedures and processes to design and build high efficient flat heat pipesbased on metal matrix composite materials- Compatibility/Lifetest data base- Fully tested (performance and lifetime) prototypes of flat heat pipes

Justification for DN: Activity is a direct follow-on of a previous GSTP-2 activity, "Flat Thin HeatPipes" (contract number 13900 with budget 300K€). Electrovac sucessfullyachieved TRL4 with first generation MMC heat pipes. In addition to this,Electrovac is the only supplier/producer of AlSiC and AlC metal matrixcomposites in Europe.

Non-competitive tendering is justified according to Article 6.1.a and c ofthe Contracts Regulations.



Activity Title: MEMS Rate Sensor DevelopmentDescription: Through initial feasibility studies, it has been shown that it is now feasible to

develop a very low mass, power and recurrent cost 3 axis rate measurementsensor for space use based on upgraded terrestrial MEMS technology. Marketstudies have shown that there exists a large demand for such a unit in the worldspace market on all types of missions. Phase 1 of the development is currently inprogress (Contract 18800). Both PDR and CDR for the detector has beensuccessfully completed and these have confirmed the feasibility of meeting therequired performances, the electronics have been studied and show the feasibilityof a radiation hard implementation.

This activity is for Phase 2 and 3 of the development – the design, manufacturingand test of an EQM, the qualification of the detector component and themanufacturing of a PFM to be used for a flight demonstration. The EQM and PFMshall have the following key characteristics: Mass < 600g, Power < 3.5 Watt,Accuracy < 5 deg/hr, recurring target price (ultimate ASIC version) 100 K€. Itshould be noted that these specifications represent a significant improvement overany other unit available worldwide. (e.g. factor 4 to 10 on mass, factor 2 to 6 onpower, factor 1.5 to 4 on cost) unit.

The following tasks are envisaged:1. Continuation of the conceptual unit design and breadboard to full EQM design.2. Finalisation of detector space packaging.3. Manufacture and test of full EQM unit based on FPGA.4. Design update, production and test of PFM.5. Space evaluation testing/qualification of the detector. This evaluation can berequired by Telecom Customers.

It is intended to partly fund this development through the GeoReturnCompensation Scheme up to 1 M€.

Deliverables: EQM MEMS gyro, PFM MEMS gyro.

Justification for DN: The tasks proposed on this activity are a direct continuation of the workbeing done under the contract 18800, "MEMS Rate Sensor Development",funded by TRP and GSTP-3 which provided design and initial breadboardand testing. It is then proposed to continue the development with the sameconsortium, leaded by SEA (UK) and with BAE Systems (UK) and SELES(UK) as subcontractors.




Activity Title: High accuracy spacecraft propellant gauging device using MEMStechnology

Description: Miniaturisation has always been a relevant issue in space technology, sincemass- and volume reduction is in constant demand. With the high accuracyspacecraft propellant gauging system envisaged in the subject work, introductionof MEMS (Micro Electro Mechanical System) technology does not only result inminiaturization, but does in this case also enable a system design with higheraccuracy and increased redundancy. During a previous activity, ”EngineeringModel of a Gauging Device”, it has been identified the need for MEMS technologyto achieve this and the market need for this gauging system.

The goal of the proposed activity is to design, manufacture and experimentallyverify, a miniaturized, MEMS-based engineering model for precision gauging ofpropellant in a spacecraft tank system under micro-g conditions.

The project will have two major phases, the first covering the activities includingthe analysis, design and definition up to the engineering model design review, andthe second phase which is manufacturing and test of the engineering modelsystem. This includes the following major steps:

• To define the design and performance requirements for the subject gaugingsystem based on a market assessment of potential applications and customers. • To analyse and assess the effect of adopting the subject gauging system on atypical application such as a satellite. “Effects” in this context is implications onsystem aspects such as reliability, safety, interface requirement, etc. • Based on the requirement specification and the system analysis to perform thedesign, development and verification work of critical issues at component level. • To define and perform a demonstration engineering model design review. • To manufacture and test a demonstration engineering model system.

Deliverables: Engineering model design data package and engineering model system.

Justification for DN: The success of the subject activity is relying on a number of relatively newmanufacturing technologies, that during the past year has matured atNanoSpace AB (S) to such extent that the first flight of a paralleldevelopment effort (regarding a miniaturized propulsion system) isplanned on the Prisma satellite in 2009. Moreover, the subject activity isbased on a few existing patents held by NanoSpace. Some parallelactivities within this field (pressure sensor) have also matured in a similarway at Presens AS (N) which is planned to be a subcontractor toNanoSpace in this project. It is proposed to procure this activity in DirectNegotiation with NanoSpace AB (S) as prime and Presens AS (N) assubcontractor.

Non-competitive tendering is justified according to Articles 6.1.a and d ofthe Contracts Regulations.



Activity Title: Second Generation APS improvements for flexible low cost and masssensors.

Description: Previous activities have shown that the biggest current limitation of APS (ActivePixel Sensor) comes from the dark current non-uniformity (DSNU). Whereas thisis understood to a functional level, the detailed mechanisms and factorsinfluencing the amount of DSNU seen are not fully understood. If the maininfluencing factors can be fully understood, design and manufacturing processesto reduce the DSNU could be developed. This would enable a significantimprovement in APS performance and have benefits across all of the APS areasof use. The objective of this activity is to investigate the causes and contributors toDSNU and the development and test of methods and processes to reduce theamount of DSNU in APS.

Building on the experience of the LCMS (Low Cost Mass Sensor) development,the contractor shall design, develop, manufacture, test and fully evaluate a secondgeneration APS with significant programmable and flexible on chip pre-processingfunctionality. This shall result in a fully qualified device with a very high level offlexible on chip functionality. It shall enable a large scale reduction in theprocessing and data handling needs of the sensor electronics for a wide range ofAOCS sensors while simultaneously providing significant flexibility and robustnessimprovements. This detector is targeted at miniature next generation APS STR(StarTracker) Optical Head applications with the built in flexibility to be used forsun sensors, planetary navigation sensors and also a number of terrestrialmachine vision applications. Additional functionality will be added to improve thepre-processing of image, increase robustness to SEU effects, add additionalfunctionality and reduce eventual processor load. It is expected that this deviceshall form the basis of the second generation of APS based Star Trackerstargeted to be available in the middle of the next decade.

The following tasks are then envisaged:- Gain detailed understanding of Dark Signal Non Uniformity sources and developand demonstrate mitigation actions.- Design, develop, manufacture and test a second generation flexibly configurableAPS detector with significant on chip image pre-processing functions- To perform a formal evaluation campaign on the resulting APS detector.

Deliverables: 5 Prototype LCMS2 devices; 5 FM LCMS2 devices; a set of LCMS 2 testequipment able to support long term low dose rate radiation testing; a LCMS2demo kit; and final report and technical notes.

Justification for DN: Fillfactory (Cypress BV) has developed the prototype HAS and LCMSsensors under ESA contract number 17235 (budget of 1,500 K€ funded byGSTP) and the Next Generation APS Sensor under ESA contract number19384 (budget of 1,100 K€ funded by GSTP). The HAS and LCMSsensors are key product developments and are already designed as thekey part of a number of future AOCS sensors now in development. It isproposed that Cypress BV continues with the development of this secondgeneration as it is the only knwon company with the relevant expertise.

Non-competitive tendering is justified according to Articles 6.1, c) and a) ofthe Contract Regulations.



Activity Title: Standardisation and building blocks: open source software repositoryDescription: Industry is invited to participate to the decomposition of on-board software

application into building blocks in view of their standardization. Each standardizedblock will be subject to an implementation as a public, open sourceimplementation to be included into reference architecture. The activity addressesthe setup of a development and repository environment for that purpose. Theopen source platform must not be developed from scratch. Instead, an existingone (itself open source) must be instantiated, loaded with the ESA open sourcedevelopment tools (compilers, debuggers, simulators, design tools, etc) andconfigured.

Deliverables: The open source platform derived from existing one and properly configured forspace developments. The process to use the available tools, derived from ECSSstandards


Activity Title: Standardisation and Building Blocks: Maintenance and Evolution ofcomponents

Description: Once frameworks and building blocks have been developed for space industry, inorder to ensure their acceptance and their use by the community, they must bemaintained, under the decision and control of the Standardisation Watch. Theactivity aims at implementing the ECSS-E40B maintenance process on selectedbuilding blocs. This includes: gathering bug reports and improvement requestsfrom users; Interfacing with the standardisation watch in order to get the decisionon the product evolution and versioning; the product maintenance and evolutionitself.

Deliverables: A collection of change requests and bug reports for all the building blocks, theinterface with the standardisation watch, and the new versions of the components.

Modular Systems, including software



Activity Title: Verification and Validation: Schedulability analysis environmentDescription: The activity aims at two objectives: (i) the extension of the capability of the ERC32

schedulability analysis tools to the LEON. The Leon chip contains instructionpipeline and cache. These features have very big impacts performance wise(more than factor 10), but also make much harder to verify the timing behaviour,since the execution history has an implication on the speed of the presentexecution. There are two promising analysis methods that can provide timingevidence: Probabilistic analysis where timing measurements of computer programunits are fitted to statistical models. This kind of analysis is used where it suffice tohave a high probabilistic guarantee that deadlines are meet. The other method isWorst-case timing analysis, where timing of program flow and execution is basedon a model of the hardware. This allows proving that deadlines in the system willalways be meet. These models must enable timing analysis of programs for theLeon. (ii) the consolidation of the global schedulability analysis environment. Fromprevious activities ESA has developed scheduling analysis tools, which cancompute the real-time characterisation of the system based on outputs of thetiming analysis (HRT architecture tool, schedulability analyser, schedulabilitysimulator, WCET tool). These tools need to be packaged as a completeenvironment, distributed and maintained as a whole.

Deliverables: Worst-case execution models of the Leon processor, which will enable timinganalysis to be done on the cache and pipeline. Packaging and testing of newtiming analysis tools integrated with the existing scheduling analysis tools in aconsistent environment. A case study on a flight application.


Activity Title: System-software co-engineering: Frameworks process and toolsDescription: Frameworks are generic architectures generally based on object-oriented

techniques (abstract interface, inheritance, up to Java beans), representing agiven application domain (e.g. banking), supported by instantiation tools (e.g.bean boxes). The use of Frameworks has significantly improved the productivity ofthe software industry out of the space domain, by making reuse of architecture,pieces of code and tests systematic. The goal of the activity is to adapt thetechnology to the space domain. The commercial tools need to be adapted to thespecificity of the space application domain (e.g. it is not graphical, it is real-time).Generic architectures must be completed with the elements needed to fit into aframework tool. The object oriented features usable for space software needs tobe defined: it is the place where the transition between the flexibility of systemlanguages and the accuracy of software design languages will be performed.Finally, the process of using a framework must be described and compared withthe current ECSS processes.

Deliverables: A framework tool set based on commercial tools and their adaptation; thedefinition of the process describing how to make a framework and how toinstantiate a framework; a case study turning a space application into aframework.



Activity Title: Cross development environments: Operating systems - RTEMSDescription: RTEMS is an open source Operating system with associated open source tools

around. The kernel contains many features that are useful for space onboardapplications. Nearly all major primes in Europe has started to use RTEMS andindeed RTEMS is the baseline of projects like Herschel/Planck and the operationsystem selected by Astrium and Alcatel for some of their future platforms. RTEMScomes with a test suite, which tests the interface to the kernel. However there areno unit tests, integration tests or general testing of compliance to the usual ESAcoding, test and quality standards. This activity intends to resolve this bydeveloping, executing and making available to users flight worthy validationtesting. The test harness will be made configurable at the same level as the kernelif possible. A number of well-defined configurations/subsets of the kernel will bedefined and tested. If it turns out that the testing cannot be made fullyconfigurable, testing of these defined subsets will be done instead. Targetcomputers are ERC32 and Leon. There are various tools around RTEMS that areopen-source and loosely integrated or not integrated with the RTEMS kernel andthe gcc development environment. Activities to integrate these and test them canalso be foreseen. Examples are: integration of debugging capabilities ofsimulators into the debugging environment and support for fast target loaders likenetrom.

Deliverables: An industrial structure and a clear process to maintain RTEMS; a configurable testharness; an improved and bug-fixed reference version of RTEMS and surroundingtools; a number of RTEMS subsets, or profile, corresponding to variousscheduling policy, interface drivers, etc.



Activity Title: Cross development environments: Real-time and compiled JAVADescription: A current TRP activity addresses the use of Java for on-board software. Named

AERO, it proposes an adaptation of the Java Virtual Machine (JVM) to on-boardand real-time needs, while allowing running as well legacy software. This activityis a continuation of AERO, and it will be devoted to:- consolidate the results ofAERO and raise the TRL level of the technology towards 6, 7, 8, by getting it closeto flight proven. The real-time functions of the Aero-JVM shall be validated againstgeneral high-level system requirements by implementing a representative Attitudeand Orbit Control System in Java. Furthermore, the Aero-JVM shall be integratedwith a core Data Handling System, thus achieving a complete on-board softwaresystem. A software quality data package shall be produced that clearly documentsthe validation status of the product. This data package shall be compliant with theECSS E40B and Q80B requirements on developing software with the intention tore-use. A port of the Aero-JVM to the RTEMS Operating System shall be made.-Investigate the concept of compiled Java, which aims at combining the benefits ofJava with a more traditional way of producing code, i.e. being compiled and notinterpreted. This will avoid having to validate an interpreter on-board. This will alsoallow it to be harder real-time, faster in execution, and smaller in memory size.

Deliverables: - A real-time Java interpreter, plus development environment and supportingdocumentation that is fit for flight. -A Java compiler and run-time system

Justification for DN: The Aero ("Architecture for Enhanced Reprogrammability and Operability")project is a contract (number 15750) funded with 200 K€ by the TRPprogramme that showed the feasibility of hard real-time Java for the spacedomain. As a result of this contract, an interpreter compliant to theReal-Time Java Specifications was also produced. The proposed workbuilds upon this success.

The outcome will provide the spacecraft community with a validatedJava-environment that supports both interpreted and compiled code andthat can be deployed in various on-board systems, ranging from platformservices like data handling and AOCS to payload service like scientificdata processing. Due to the past experience acquired on this specificsubject, it is recommended to continue the contract with the same pool ofcompanies.

Non-competitive tendering is justified according to Articles 6.1. c) and e) ofthe Contracts Regulations.


Activity Title: Real Time operating System (RTEMS) tasking monitoring toolDescription: RTEMS operating system is selected as the On-Board operating system of

ongoing ESA projects as Herschel/Planck. It is used for the mission criticalon-board software. Therefore, better real time tasking information is required tosupport the testing and validation of the use of the operating system in theon-board software implementations. It is required that an intrusive collector oftasking information shall be provided. The communication shall be via the UARTon the processor and host-based tools shall provide both interactivecommunication, but also display the tasking related information real-time ingraphic displays.

Deliverables: Source code and documentation of the RTEMS monitoring task and the graphicaluser interface communicating with this monitor.



Activity Title: System-Software Co-Engineering: Architectural Language and ToolsDescription: The investigations performed due to the software crisis have demonstrated (and

this was confirmed by the harmonisation exercise), that one weakness in theavionic software engineering is the relationship between the system definition andthe software development, because the software requirements at system level arevery weak, incomplete and inconsistent. A solution is to find a way to have systemand software engineers work together with the same tools at the same time inorder to start the software development on a clean basis. The activity willinvestigate a language allowing system and software engineers to expresstogether the avionic system architecture in terms of hardware, software andcommunication elements and their attributes. The language must allow theexpression of system properties (timeliness, behaviour, dependability), which willbe verified at each step of the avionic implementation. The activity will select alanguage (candidates are AADL, and UML flavours like UML-SE and HRT-UML).The activity will implement, reuse or associate the necessary tools to capture asystem definition, the software requirements and the system and softwareproperties. Then the activity will prepare the bridge with the next engineeringsteps, i.e. the software, hardware and bus design tools. Finally, the activity willdefine the system-software co-engineering process making use of the languageand tools.

Deliverables: The language definition; the language editor, simulator; the filters to the designtools for the next engineering phases; the definition of a system-softwareco-engineering process using these tools; a case study.


Activity Title: System-software co-engineering: Data modelling technologiesDescription: One important element of the set of requirements of a system and software is the

Data Model. It gives a particular view on the application that shows therelationship between data, indicates the flow of information, and ensures theirglobal consistency. The data model is then used all along the implementation, e.g.to generate automatically the data types of the application. The activity aims atdefining the needs in data model engineering for the overall system-softwareco-engineering activity (e.g. data type representation, data implementation andencoding, data value, data classification). This includes the data aspects in thearchitectural language, the data representation in the models, the data generationin the frameworks. The activity does not aim at redefining a new datarepresentation language, but rather to make clever use of the numerous existingone (XML-based, ASN.1, AP233, STEP, etc). The activity will identify the relevantcommercial tools and associate them into the system-software co-engineeringenvironment with proper filters.

Deliverables: Report on data model representation and verification techniques. Toolset for datamodelling environment integrated into the system-software co-engineeringenvironment.


Ref. Number: G607-13OF Budget: 960 K€

Activity Title: Generic and Automated Manufacturing and Operations System (GAMOS)Description: The study builds on the results of the OCIM study carried out under the previous

GSTP programme. It includes enhancement of existing facilities, application ofnew technologies and analysis and proto-typing of new features. The followingsub-activities are envisaged: the development of a Generic Satellite Database, inorder to facilitate migration of data between the various organizations involved indefining instrument, payload, and platform elements, and for the various levels ofspacecraft AIT and operations; the development of an automation test bed forsatellite operations with a view to reduce mission costs; the development of ageneric operations reporting tool (to support all ESA missions) to provide nearimmediate external reporting of sub-system anomalies and automatically generatestatistics to support trend analysis on numbers of anomalies and the down-timesfor the various sub-systems; the development of a generic offline scheduling toolto provide to projects a cost effective solution for mission planning/scheduling forboth spacecraft and ground segments; integrated spacecraft documentationsupport, to provide integrated configuration control for the pre-FOP phases ofspacecraft and operations documentation production; the analysis of COTSproducts impact on MOIS components; and the development of a generic modelto tailor the MOIS procedure editing tools for the On-Board Control Procedures(OBCP) environment.

Deliverables: Software and documentation; final study report.

Justification for DN: The study builds on the results of the OCIM (Operations CentreInformation Management) study carried out under the previous GSTP–3programme (Contract no. 16175, 700 K€ funded by GSTP). It includesenhancement of existing facilities, application of new technologies andanalysis and proto-typing of new features. The Intellectual Property Rightsof the OCIM study software resides with RHEA Systems.

Non-competitive tendering is justified according to Articles 6.1.c and d ofthe Contracts Regulations.


Activity Title: Taxonomy of system FDIR principles and development processDescription: The proposed study aims at identifying a set of generic principles to build a FDIR

(Fault Detection Isolation and Recovery) function. Those principles will definegeneric architectures that take into account mission constraints, types of systemand software architectures, and AOCS behaviour. The following tasks areproposed for this activity: analysis of FDIR architectures for different projects andmissions (ROSETTA, SMART-1, PROBA, etc); definition of generic principles forsystem FDIR; definition of a development process to guide the FDIR designer toselect the most appropriate generic architecture from the project inputs; andmodel design of the generic architectures that can be simulated and used byprojects for designing and verifying their FDIR.

Deliverables: Activity analysis reports.



Activity Title: SpaceNet: SpaceWire and Future Onboard Data-HandlingDescription: SpaceWire (SpW) is a standard of the European Cooperation for Space

Standardisation (ECSS-E50-12A). This standard is now being widely used onmany ESA and NASA missions, and other space agencies (e.g. JAXA) are alsodesigning equipment with SpaceWire interfaces. The SpaceWire standard wasdeveloped by the SpaceWire Working Group with key activities being funded byESA which included the participation of University of Dundee via the TopNetactivity.

The aim of the proposed SpaceNet activity is to provide essential support forfuture onboard data-handling systems by supporting the existing SpaceWirestandard, allowing work to continue on the CCSDS SOIS activities (ConsultativeCommittee for Space Data Systems for Spacecraft Onboard Interface Services),developing a set of network protocols for SpaceWire and producing a standard forSpaceFibre: a higher data-rate version of SpaceWire aimed at SAR, multi-spectraland communication satellites. This shall include the following developments:RMAP (Remote Memory Access Protocol) Protocol in HW; CCSDS SOIS TCONS(Time Critical Onboard Network Services) and OBL (Onboard Bus and LAN) draftstandard; Network Management; SpW Fibre Standard; SpW Support.

Deliverables: VHDL Code: SpaceWire RMAP VHDL, Documentation, Draft Standard, SourceCode.

Justification for DN: The proposed activity is a continuation of an ESA activity (Contract no.17938, 250 K€ funded by GSTP).


The output of the WP 2-3 (SpaceWire Network Management) will be aC++ Code that implements the SpaceWire Network ManagementSoftware. Hence, here the SW clause 42 shall apply, since this SW will beused by the Agency for essential purposes, like space mission validation.



Activity Title: Advanced , Robust Processing Architecture (ARPA)Description: The emphasis within this activity proposal is on the HW development of the core

modules to provide a flight-qualified design of a modular, scalable processing unit(based on LEON2). It will include the design of the processing architecture; coremodules development; EGSE design and development; demonstration andtesting.

Analysis of future European Space Missions identifies a demand for increasedon-board processing capability together with higher levels of integrity. These ideashave been explored within the UNIONICS programme demonstrating thefeasibility of robust, high performance networks. UNIONICS is based on a highlyreliable on-board high speed network based on point to point links and routers.This network provides an homogeneous interface between units (e.g. on-boardComputers, AOCS sensors, Mass memories and Payload instruments). Such anintegrated avionics architecture provides a data system architecture that is moreefficient and flexible than traditional approaches based on redundant processorsand separated command&control and data busses. The approach taken is tointer-connect the processing nodes using a SpW network and Routers. Moreover,this means that it is possible to distribute SW processes to any availableprocessor on the network.

UNIONICS forms therefore an excellent starting point for the development of anAdvanced, Robust Processing Architecture (ARPA). The work proposed in thisactivity addresses the hardware development of core functions required for spaceflight on a range of future missions.

Deliverables: Fully tested HW demonstrator.


Non-competitive tendering is justified according to Article 6.1.c fo theContracts Regulations.



Activity Title: Generic Fault Tolerant Software Architecture using SOIS for DistributedApplications - GenFAS

Description: High Reliability Distributed Data Systems have been identified as a majorrequirement for future space missions. The UNIONICS project has resulted in acomplete benchtop demonstration system of a combined Data Handling/AOCSsystem. Now it is proposed to continue that effort through the present activity.

The primary objective of this activity is to directly answer to the questions comingfrom that UNIONICS activity, and it is the possibility to have a LEON version,FDIR demonstration and SOIS compliance. GenFAS will therefore take thecurrent demonstrator software and move it to a “flight ready” state. To do this it isproposed to port the software from the now obsolete DSP 21020 to the LEONprocessor. GenFAS will incorporate latest advances in standardisation ofon-board communications. In particular, by implementing a full SpacecraftOnboard Interface Services (SOIS) reference architecture. The following maintasks are identified in this activity: port to LEON; mass memory solution; IOdrivers; generic validation; FDIR evolution; and SOIS reference implementation.

Deliverables: Produce a representative application demonstration based on the ExoMars RoverArchitecture.




Activity Title: Deployment demonstration of the CFDP standard in space applicationsDescription: CFDP is a CCSDS standard protocol for file delivery in space applications. It has

been defined in response to the demands of on-board autonomy (the spacecraftdecides when to transfer data with the ground segment) and interoperability(among space agencies, and between space-ground networks). With thepossibility to use relays, it provides a solution for data transfer with spacecraftswithout direct line of sight with the Earth.

This activity aims at the implementation and deployment demonstration of theCFDP protocol. The main objective is to demonstrate a deployment of the CFDPover several network topologies, with communication ends either onboard aspacecraft or on the ground segment. Several file transfer scenarios areenvisaged. With the ground segment and one space segment, reliable orunreliable space-to-ground and ground-to-space file transfers are tested. With anadditional space segment, it becomes possible to demonstrate a space-to-spacetransfer initiated by the ground segment. In this configuration, reliable or unreliablespace-to-ground and ground-to-space transfers via one waypoint may also bedemonstrated.

Deliverables: CFDP flight application S/W

Justification for DN: The work to be carried out in this activity should be considered as thecontinuation of the current development that Spacebel is doing of the flightsoftware and SVF in the contract for PROBA-2 (Contract Number 18000,funded by GSTP).




Activity Title: ISVV process definition for auto-code generated softwareDescription: ESA is currently executing studies of Automatic Code Generation (AGC) under

the TRP funding. The ACG study will look at how auto code can be inserted in thecurrent development process. However, there are still many open questionsrelated to Verification, Validation and Testing. Introducing the auto codingtechnology for mission critical software shall only be done when there is a fullunderstanding of all aspects and impacts of this technology. This includes theformal capturing of requirements, converting into formal models, and it includesthe end-to-end validation process. The objective of this study is to complement theACG study by addressing the Independent Software Verification & Validation ofAuto code generated software.

Independent Software Verification & Validation (ISVV) is today performed onsafety and mission critical on-board software as a mean of risk mitigation and asan activity to improve the overall quality of the software. Introduction of theauto-code generated software require a complete re-thinking of the correspondingISVV process. The objective of this study is to analyse the impact and changes tothe ISVV approach due to the use of auto code generated on-board software. Thestudy will focus on the following areas:

- Independent verification/validation of the models,- Verification/Validation of the auto code generation procedures,- Verification/Validation of the produced code,- Assessment of the development process where some testing activities could bereduced or suppress due to the use of the auto-coding approach.

Deliverables: The output of the study will be the definition of a new ISVV procedure thatcan/shall be used when modeling and code generation techniques are part of thedevelopment process. The study shall focus on the potential impacts of this newapproach and shall identify the major changes to the process. The new ISVVprocess shall be demonstrated by examples. The process shall be assessed forcost effectiveness and shall identify the potential limitations or inherent difficulties.

Justification for DN: The activity address the understanding of AGC tools in order to assessissues related to Independent Software Verification and Validation (ISVV)for Automatic Generated Code. Either the development of auto codingtools and the activities of ISVV constitute niche-specialised markets withpotential of commercial exploitation outside the space market. There is therequirement of ISVV being performed by companies independent of thesoftware developers and it is of ESA interest to assure the availability inequal conditions of the AGC tools to all the industry developing softwarefor ESA projects.

Applying the measure C1 is “resulting in a more efficient allocation offunds due to inherent economies of scale that can be generated” and “tofavour an increased specialisation and competitiveness of equipmentsuppliers” as stated in the document ESA/IPC(2001)29.



Activity Title: Open Image Generation System Phase II (OpenIGS2)Description: ESA has conducted a number of studies to develop 3D graphics technologies.

The latest work ongoing in this area is the OpenIGS study, which focuses onhaving a 3D visualisation tool that is capable of interfacing with the most importantsimulation tools and data sources used within ESA. However, as the resources ofthe OpenIGS study were rather limited, no efforts were done in the area ofhigh-end visual effects and in the development of dedicated spacecraftengineering related graphical features.

The aim of this study is to combine the results of the OpenIGS study with workalready performed in the area of high-end 3D visualisation for astronaut trainingas e.g. used in the ERA MPTE (European Robotic Arm Mission Preparation andTraining Equipment). Furthermore, in this study a set of graphical features shall bedeveloped that can be used to visualise spacecraft engineering data in an intuitiveand efficient way.

The following tasks are envisaged: Add high-end 3D visualisation effects to theOpenIGS application; Add improved engineering visualisation features to theOpenIGS application; Optimise the OpenIGS basic software layer and improve theuser-friendliness; Maintain the OpenIGS application and support its usercommunity.

Deliverables: A core 3D visualisation library and application framework. A set of high-endgraphical effects, supporting man-in-the-loop training systems. A set of spacerelated graphical features that could be used to visualise spacecraft engineeringdata.

Justification for DN: The original OpenIGS software has been developed by ATOS/Origin (NL)under ESA contract (17988), and funded (150K€) by GSTP-3. In addition,as the virtual reality 3D graphics, as used e.g. in the ERA MPTE system,have been improved and maintained by Dutch Space, it is expected toinclude this company as subcontractor. The combined experience of bothcompanies with the already developed software will ensure that theforeseen results can be achieved with no major technological risks.




Activity Title: LEON-II (AT697E) simulator characterisation.Description: The first samples of the space qualified LEON-II chip (AT697E) will be made

available by Atmel during 2005. Until now only different commercial versions ofthe chip and software simulators has been available for the software developers.Experience from previous programmes has shown that software simulators of theSpace qualified processor can have slightly different characteristics to the realhardware and even execution faults. This has lead to unnecessary risk and costswhen using a software simulator tool to develop and test the on-board software.Each simulator might have different representativity/performance trade-offs. It istherefore essential that the formal validation of the simulator will be performed bya characterisation of performance and compatibility against the real processor.

The activity shall formally characterise LEON-II software simulators throughcomparative assessment of the functionality and performance of the simulatoragainst the LEON-II (AT697E) evaluation board. The assessment andcharacterisation will be done by executing a number of test scenarios asinstruction level comparison, bench-marks, operating system performance(RTEMS) and a full space application (PROBA-II on-board software). The testscenarios will be executed on a LEON-II software simulator and on the targetprocessor using a commercially available evaluation board (ATMEL).

Deliverables: Specification, Test procedures, Assessment reports for each of the test scenarios,Non Conformance reports.

Justification for DN: Spacebel is developing the PROBA-II on-board software, which today isthe only available full-scale space application developed for the LEON-IIprocessor. Furthermore, in the frame of the PROBA-II project, Spacebel isdeveloping the Software Validation Facility, which include a softwaresimulator of the LEON-II, which is also a pre-requisite for the execution ofthis task.




Activity Title: Optical waveguides and micro-optical technology in silicon IIDescription: The goal of the proposed activity is to couple light efficiently from compound

semiconductor laser chips into the SOI (Silicon on Insulator) waveguide platform.This work supplements the fiber-waveguide coupling technology alreadysuccessfully developed. The following methods, tools and structures will bedeveloped: 1) Alignment structures on silicon and laser chips, 2) wafer-leveldeposition of anti-reflection coatings on SOI, 3) attachment of lasers on SOI chipswith low optical loss and good electrical contacts, 4) vertical silicon tapers tomatch the silicon waveguides to the optical output of the laser chips, and 5)low-loss bends and mirrors in thin silicon waveguides.

Furthermore, it will be studied whether spot size converters should be laterintegrated on the laser chips. Compared to the vertical tapering on silicon, thisalternative approach could ease the alignment tolerances and improve thecoupling efficiency between the lasers and the silicon waveguides. At the end ofthe work the laser-waveguide integration scheme will be demonstrated with acompact and functional device including at least laser-waveguide andwaveguide-fiber couplings, vertical silicon tapers, and some additionalfunctionality on a silicon chip, such as a switch, a modulator, a filter, or awavelength multiplexer.

Deliverables: Functional demonstrator device (semiconductor laser diode permanently coupledto a silicon-on-insulator waveguide chip)

Justification for DN: VTT is currently executing the contract no. 17703/03/NL/PA, funded(250K€) by GSTP-3, “Optical waveguides and micro-optical technology insilicon”, to be completed by November 2005. In the course of the runningESA contract VTT has developed successfully a generic waveguideplatform in silicon-on-insulator technology realising various devicefunctions integrated on one chip and demonstrating efficient coupling tooptical fibers. VTT will apply the developed technologies to coupleefficiently laser diodes to waveguide chips. In addition, it is expected thatthe laser diodes will be provided by the subcontractor Modulight (FIN).


Other Technologies



Activity Title: SMEAR II. (Radiation effects test protocol for optics)Description: This work continues and expands on work carried out under the fast track contract

entitled "Elaboration of a Standard Methodology for the Assessment of the spaceRadiation impact on the spectral transmission characteristics of optical glasses"(SMEAR). Previous work carried out under a TRP contract ("Radiationcharacteristics of refractive optical components") has clearly demonstrated theusefulness of a so-called "dose-coefficient" approach. This method has beenapplied and further refined in SMEAR, but is not yet fully compliant with anapplicable standard. The concept of this follow-on is to allow the actualcodification of a standardized methodology for the qualification of optical glassesfor use in a space radiation environment.

Deliverables: A specific and verified testing methodology and detailed protocol for the groundbased testing and qualification of optical glasses for use in a space (total ionizingdose TID) radiation environment. This protocol could be eventually included in anappropriate ECSS standard in order to ease its applicability to industry.

Justification for DN: This is a direct continuation and follow-on to a previous contract (number16773, 40 K€ funded by the corporate budget). Critical know-how andexpertise are therefore already in place to carry out the tasks foreseen inthis activity.



Activity Title: High Resolution Optical Metrology System (HROMS)Description: This activity is linked to a series of activities undertaken previously for application

to satellite and structure testing under thermal vacuum conditions in the LSS. Themajor driver at present to achieve a required resolution at the 10 ppm level, orbetter, is the necessity to develop vacuum compatible high resolution imagingsystems with a minimum pixel count of 2k x 2k. This activity aims at either, thedevelopment and production of a prototype imager from commercial off the shelfcomponents, or the custom specification, manufacturing and testing of a device toenable the high resolution imaging requirement to be met.

Deliverables: A complete high resolution imaging metrology system suitable for deployment anduse under thermal vacuum conditions.

Other Technologies (Th. 6)



Activity Title: European mm-wave & sub-mmwave Reliability & Space Evaluation TestCentre

Description: The selected centre will first have to perform an intensive survey of the mmwaveand sub-mmwave technologies, components and products for which evaluationand reliability study would enable access to space application. These productsmay be commercial but also available from open research through a small sizelaboratory or a research centre. Examples of the parts that are expected to beidentified in the survey are: mm-wave schottky diodes, HBV devices and MMICs,180 GHz + mm-wave MMICs processes, PBGs crystals and structures, mm-waveand sub-mmwave membranes, HEBs, etc... The second task will be to defineadequate evaluation and reliability methodologies and procedures applicable tothe device identified during the above survey. Once approved by ESA, thesemethodologies and procedures will be formulated in a document to be used by theEuropean mmwave & sub-mmwave Reliability & Space Evaluation Test Centre asguidelines for the performance of reliability and space evaluation of mmwave andsub-mmwave devices and technologies. The third task to be performed willconsist in a critical review of the test centre existing capacity (in terms ofmanpower, expertise,..) and facility. Using the outcomes of the 2 previous taskshe shall establish its future short and long term needs in terms of expertise,manpower and dedicated equipment.

Deliverables: Survey of the mmwave and sub-mmwave technologies, components and productsand market analysis; mmwave and sub-mmwave devices reliability and spaceevaluation guidelines; verification samples selection and test reports; performancevalidation; final report, brochure, articles, European mm-wave & sub-mmwaveReliability & Space Evaluation Test Centre web page and other promotion tools.



Activity Title: Optical cements and adhesives for space use. (CEMOT II)Description: Complete revision, update and computerization of the original CEMOT study

(1992) on optical cements and adhesives. (cf Contract No. 8719/NL/DG FinalReport Feb. 1992: Cementing and Mounting Technologies for LaserCommunication Optics).The use of cements and adhesives and other bondingtechnologies for space optical systems is still of great importance. Since theCEMOT study 10 years ago many advances and changes in the commercialbonding market have taken place. This work will thoroughly revisit the olddatapackage in order to: 1. Eliminate obsolete information. 2. Include data on newproducts available. 3. Perform space qualification testing on the new products. 4.Completely update the database and. 5. Put it into an electronic format which canbe web accessible on an ESA server for use of the European Space Opticalindustry

Deliverables: Comprehensive data package and electronic database of optical cements andadhesives qualifiable for use in space.

Justification for DN: This activity will make a complete revision, update and computerization ofthe original CEMOT study (1992) on optical cements and adhesives(Contract No. 8719: Cementing and Mounting Technologies for LaserCommunication Optics, 240 K€ funded by ASTP-3). The use of cementsand adhesives and other bonding technologies for space optical systemsis still of great importance. Since the CEMOT study 10 years ago manyadvances and changes in the commercial bonding market have takenplace. Leica was the company who carried out the original CEMOT workunder contract no. 8719. They have the expertise, heritage and motivationto continue.




Activity Title: Optical correlator for push-broom imagersDescription: The very successfully pioneered technology by the University of Dresden shall be

further developed to an in-flight technology maturity level compatible with: a)image de-blurring in a compact 2D camera, b) hyper-spectral imaging from theISS as the platformc) Image motion correction for the RapidEye camera. Thisrequires development to increase the processing rate to ~3200 correlations/sec,an error reduction to ~0.1 pixels while working with images having a signal tonoise ratio close to unity. The activity shall also include the development of asmart focal plane (implementing the correlator) with a linear array combined withtwo CCD (or APS’) as image motion tracking sensors running at a high frame rateof 1600 frames/sec for potential test flight e.g. on the ISS. Although primarilydeveloped and demonstrated for Earth Observation, the applications arefar-reaching, including image-based navigation (for e.g. planetary landers).

Deliverables: - Space-compatible, fully characterized and environmentally tested opticalcorrelator- Space-compatible, fully characterized and environmentally testedsmart focal plane assembly incorporating a VIS linear push-broom imager and twoFIS 2-D motion trackers

Justification for DN: The trend towards smaller satellites and less complex, more integratedsystems also implies reduced primary stability of the platform. Smartsolutions are to be sought to compensate for this by intelligent payloads.One universally applicable example is the optical correllator forpush-broom Earth Observation (or Planetary) missions. A previous ESAcontract, number 17572 (50K€ in GSP, awarded following an OpenCompetitive Tender), with the University of Dresden has very successfullydemonstrated the principle and have resulted in a highly successfuldevelopment of the optical correlator and FPA airborne breadboard. Thisactivity aims at further developing this successfully pioneered technologyin order to reach an in-flight technology maturity level. Due to the specificknow-how developed on the system as well as the competences acquiredby this company, it is then suggested to carry out the proposedcontinuation with the same company.




Activity Title: MAPLE-BIOLIFT 2 - Technique for printing MicrobioarraysDescription: The main objective of this activity is to optimize parameters of previously

developed bio-printing technology and to provide an updated breadboard.

Space biology studies will increasingly need custom-made slides or arrays ofbiological materials such as proteins, RNA or DNA or insect/mice embryos forgene expression studies. A new technique, the MAPLE D/W (Matrix AssistedPulse Laser Evaporation, Direct Writing), with the great potential for fast, flexibleand cost-effective preparation of these samples has been successfully tested in atechnology development phase: it has been possible to bind one protein and oneDNA strip onto a substrate and to prepare a Drosophilae embryo for processing,obtaining good functionality rates for the proteins and good survivability rates forthe Embryo.

The proposed activity consists in characterizing and optimizing the parameters ofthe Maple-Biolift technique, then in developing and testing an integrated,multipurpose BIOLIFT demonstrator protocols to perform protein, DNA or embryopreparation. The activity will include the following:

1. Characterization and optimization of BIOLIFT:

1.1. Analyse the interactions between the laser beam and the biological materialto be deposited for the proteins, nucleic acids and embryos1.2. Derive adaptation parameters, perform and evaluate related technologyadaptations1.3. Selection of Biolift modes (protein, DNA, embryo treatment) and candidatecompounds or samples to be considered for the present activity1.4. Considering outputs of task 1.3, prepare the preliminary design of amulti-purpose system for bio-printing of a wide range of bio-molecules andcondition embryos for gene expression studies.

2. Development of a multi-purpose BIOLIFT:

2.1. Refine specifications of the BIOLIFT multi-purpose system (for bio-printing ofa wide range of bio-molecules and conditioning embryos for gene expressionstudies)2.2. Examine BIOLIFT adaptations that would be required for preparing mouseembryos for gene expression studies2.3. Design and build a demonstrator for the multi-purpose BIOLIFT system2.4. Test the system2.5. Validate the system on selected proteins, nucleic acids and embryos2.6. Assess the use of BIOLIFT for preparing bio-chips and studying interfacesbetween biomaterials and electronics. Propose and pre-test adaptations to bemade to facilitate that use2.7. Provide the preliminary specifications for a BIOLIFT system for use inmicrogravity.

Deliverables: BIOLIFT technology evaluation documentation, BIOLIFT design files, BIOLIFTground demonstrator with validation documentation, preliminary specifications fora zero-g compatible BIOLIFT.

Justification for DN: This activity is the continuation of the work previously done by NTE in theESA contract 15786 (budget of 250 K€ funded by TRP).




Activity Title: Target Projector for Videogrammetry (TPV)Description: This activity is related to the optical calibration of large RF/Sub mm Antennas.

Recent surveys in optical 3-D metrology show that videogrammetry is meetingmost of the metrology requirements for antenna co-ordinate measurement.Breadboards have shown that current space-flight compatible cameras canreasonably achieve the accuracy demands. A credible alternative for thistechnology is the projection of an array of spots. It is the aim of this activity todesign and test a breadboard projector that shall functionally be tested in vacuumwith the previously established videogrammetry breadboard. Angular and spatialstability of spot pattern are the critical factors.

Deliverables: Functioning breadboard of a vacuum compatible target projector system, suitablefor use with the already developed videogrammetry system available at CSL.

Justification for DN: This activity is a continuation of the GSTP-2 work “3D Positioning of alarge set of points”, funded with 300 K€, under contract number 14283. Inorder to continue the initial work done in that activity, it is required tomaintain the contractor company.




Activity Title: Simulation of the Dynamics of Liquids in Partly Filled Tanks withMembrane-type Fuel Management Systems

Description: Planck is a slow spinning satellite with a spin rate of 1rpm. During operation thespin axis has to be frequently redirected. For this purpose Reaction ControlSystem Thrusters (RCS) are fired for short periods of time. Intermittent RCSacceleration can excite parts of the spacecraft that have an oscillatory degree offreedom, e.g. liquids in partly filled tanks.

Planck uses a membrane as fuel management system that covers the surface offuel in tanks. The volume of the already consumed fuel is filled with high-pressureinert gas to prevent gas bubbles in the feeding lines of the RCS engines. Initialstudies at ESTEC have demonstrated that the pulsed operations of the RCSengines have the potential to excite the fuel in tanks. In the initial study, the effectsof the membrane on the resonance frequencies has been neglected; the fuel /inert gas interface was modelled as a free fluid surface. This activity has to berepeated considering the effects of the membrane on the characteristicfrequencies of the fuel.

The objective of this activity is to investigate and predict the effect of the flexiblemembrane on the dynamic properties of fuel in a partly filled tank aseigen-frequencies, eigen-modes and damping characteristics. In particular, itshould be demonstrated that none of the position control manoeuvres is using asequence of RCS thruster firings that would excite oscillation of the fuel in tankswith increasing amplitudes.

The proposed activity will develop and validate all numerical tools that are neededto obtain results on a confidence level that is adequate to the technical importanceof the fluid / structure interaction phenomenon for the success of the overallmission.

Justification for DN: The tasks described in this activity require specialization in advancednumerical modelling and validation which NUMA (IRL) posses and there ispresently no numerical tool available that gives a solution with the requiredaccuracy. NUMA has presented excellent results in the area of advancednumerical modelling, in current and past contracts with ESA. Moreover,this company has also satisfied ESA's requests to validate their numericaltools by comparison with ESA’s numerical and experimental results.




Activity Title: Laser diode technology developments at 779nm and 894nmDescription: The need to improve atomic clocks for Navigation mainly in the longterm periods

(>10000 seconds) has led to the development of laser pumped (LP) atomicclocks. The larger Signal to Noise Ratios of the LP systems can lead to lowerthermal drifts are thus improved clock performance. Nevertheless before we canconsider the implementation of laser for space, certain performance and reliabilityissues need to be solved.

This activity is aimed at the further development and refinement of the RidgeWaveGuide (RWG) semiconductor laser device structure developed for a previousESA activity (see below). The development will progress towards a spacecomponent by focussing on specific growth aspects including material choices,engineering simplifications and finally lifetime prolongation measures. The finaldevice testing should also maintain and improve on the narrow-band spectralperformance attained in the previous ESA activity in the simple package therebyremoving a future major engineering difficulty. This eventual removal could havelarge (positive) cost and development time impacts. The present activity will focuson the 779nm wavelength for Rubidium (cell) and 894nm for Cesium (beam) clockapplications.

Deliverables: Hermetically sealed packaged laser diodes meeting the specification of theSOW/RFQ. The exact number of devices (TBC) at the above specific wavelengthswill be the hardware deliverables of the contract. Additionally there will be lifetimeevaluations on the same batch of components, which shall continue after thedelivery of the packaged devices. It is envisaged that the components produced inthis contract will be subjected to further testing and verification in working atomicclock environments.

Ref. Number: G609-21EL Budget: 100 K€

Activity Title: In orbit demonstration of Digital Sun SensorDescription: A DSS (Digital Sun Sensor) has been developed by TNO in the frame of the

ARTES programme. Now, in orbit demonstration will allow to validate the unit intothe real environment (radiations, sun, etc.). The objective of this activity is then todemonstrate compliance of the unit with space environment (radiations) and proveperformances comparing the attitude data provided by the unit with the highaccuracy pointing data provided by the PROBA 2 star trackers.

This activity consists in (1) performing all necessary tasks to refurbish a prototypeDSS produced in the frame of an ARTES contract into a flight unit and (2)supporting the system activities for the AIT of the DSS on the PROBA 2spacecraft.

Deliverables: DSS flight unit with GSE and associated documentation.

Justification for DN: The proposed activity is a continuation of an ESA activity (Contract no.17238, 530 K€ funded by the ARTES programme).




Activity Title: Advanced Slip-ring SolutionsDescription: The objective of this activity is to identify, select, develop and test a series of

advanced slip-ring technologies compliant to requirements defined for spacecraft.In particular the targeted areas for investigations are: capability for high electricalpower transfer with minimised losses; enhanced electrical and mechanicalcharacteristics; low electrical noise contacts; integrated sensors for positioncontrol; voltage capability in accordance with future satellite buses; and capabilityfor contactless data transfer. Those advanced features shall be incorporated intoan Engineering Model Slip-ring manufactured in accordance with standards forspace applications and tested under space equivalent environment and scenarioto demonstrate its functional performance.

Deliverables: Tested Slip-ring Engineering model. Test reports and documentation.


Activity Title: Distributed Feedback (DFB) Laser diode development at 894nmDescription: The activity is aimed at the development of an extremely narrowband Distributed

Feedback (DFB) semiconductor laser. The use of this type of laser device shallalso capitalise on the athermal properties of the DFB design. The developmentshall progress towards a space-grade component by focussing on specific growthaspects including material choices, solving engineering issues and deal finallywith lifetime estimation and prolongation measures. The final device testingshould also identify space qualification measures [with subsequent plans and timeframe]. The wavelength of prime focus in this activity is 894nm for Caesium(beam) Atomic clock applications. The tuning range required around the listedwavelength will depend on the ability to precisely position the centre wavelength.The activity will include the following tasks: prototype DFB development; reliabilityassessment and improvement; reliability guidelines and pre-space qualification.

Deliverables: Hermetically sealed packaged DFB laser diodes meeting the specifications.Additionally there will be lifetime evaluations on the same batch of components,which shall continue even after the delivery of the packaged devices. It isenvisaged that the components produced in this contract will be subjected tofurther testing and verification in working atomic clock environments.


Activity Title: Compact in-orbit optical image processorDescription: This activity will implement a new optical imaging processing concept (ESA patent

pending) which will allow the on-board real time processing of SAR images and asubsequent image compression. The aim of this activity is to design, manufactureand test an elegant breadboard of an optical processor for real-time SAR dataprocessing. It will include the optical and mechanical design optimization, thedevelopment of dedicated driver electronics capable of operating the processor atvery high resolution and large data throughput. The processor shall be tested withrealistic SAR data in azimuth and range and in real time. The processingperformance shall be assessed with respect to electronically processed images.

Deliverables: Elegant breadboard of a SAR optical processor with dedicated driver electronicsto be operated in real-time, optimized for image performance, tested with realSAR data in real time.



Activity Title: Design and development of extremely narrow band semiconductor DFBlaser technology

Description: The need to improve atomic clocks for Navigation mainly at very long integrationtimes (>>10000 seconds) has led to the development of laser pumped (LP) atomicbeam clocks. Nevertheless before we can consider the implementation of these(as any other) lasers in space, certain performance and reliability issues need tobe solved. These issues will be dealt with in this activity. The specifiedperformance (linewidth and inherent noise) including eventual reliability figures willbe delivered on conclusion of this activity (the space qualification shall follow thissuccessful milestone in a subsequent activity).

The activity targets the technological development for the realization of a new typeof DFB - Distributed FeedBack (and DBR -Distributed Bragg Reflector) gratingsand the fabrication of edge-emitting lasers incorporating these gratings. A majoradvantage of the proposed approach is that the gratings are obtained withoutepitaxial regrowth (on which the conventional approach is based). The activity isbased on very new technological advances that need first to be implemented in afirst phase (if the first phase is successfully concluded a second phase will providethe devices for evaluation). The two phases will include:

Phase 1:- Design, modelling and simulation Deliverables: Dimensional requirements and procedure for evaluation of gratingperformance under variable dimensional restrictions.- Technology Assessment and development Deliverables: Technology sequence for grating fabrication

Phase 2:- Advanced design, modelling and simulation Deliverables: Device model for the edge emitting semiconductor (SC) lasersincorporating the new type of gratings. Procedure for calculating the structuralparameters of the edge-emitting SC lasers incorporating the new type of gratings.- Device development and characterization Deliverables: Edge emitting semiconductor lasers incorporating the new type ofgratings

Deliverables: See above (deliverables for each of the two phases).

Justification for DN: The Research Institute ORC has a unique experience in the new DFBtechnology. In addition to the complete range of equipment they haveavailable and the very good testing and characterisation facilities, thisinstitute also has available the corresponding technical expertise to use itand implement it in new ways. This activity aims at looking at a new formof DFB semiconductor laser where there is no need for overgrowth of thegrating region, as is case with the traditional approach to DFBmanufacture. The ORC proposal is to make a large leap forward inperformance by this new technique. For this, it will be of high interest touse the knowledge they have acquired in the investigation of linear,nonlinear, and near-field optical properties of such structures.




Activity Title: Development of MEMS Accelerometer for Space ApplicationsDescription: This activity aims at producing a specification for a MEMS accelerometer for use

as the accelerometer component of an IMU for s/c applications. It will include thedesign of the accelerometer and showing its feasibility by analysis and test. Thefollowing main tasks are foreseen:

- Consolidate the unit specifications implied by identified space applications,including interface and accommodation requirements, bearing in mind futureintegration with the MEMS gyro.- Develop the design of a European accelerometer to meet these requirements asan alternative to the Honeywell QA3000, which is perceived to be the currentindustry standard.- Analyse and evaluate the design and show feasibility by appropriate test data.- Produce a costed implementation and qualification plan for final development.

Deliverables: Specification; Design report; Analyses; Implementation and Qualification Plan andFinal Report


Ref. Number: G609-28SR Budget: 200 K€

Activity Title: Sloshat FLEVO Post Flight Activities (Phases Fa and Fb)Description: Sloshsat has been launched and operated in February 2005. After the successful

operations of Sloshsat FLEVO, the raw flight data have been delivered. Part of theSloshsat Investigation Programme is the evaluation of the flight data, theidentification of the satellite behaviour and the analysis of the slosh behaviour.

Previously, the Sloshsat FLEVO contract has been concluded with the successfullaunch and operation of the satellite. The last contractual change (CCN-10)provided for a reduced phase Fa. The work consisted of the archiving of the rawflight data and the derived data as obtained during the course of the flightoperations. This doesn’t constitute a full phase Fa. Flight data need to be furtherprocessed to acquire calibrated engineering data, the operations details need tobe analysed and documented, and data need to be processed fur furtherinvestigations. The satellite performance as well as the scientific performanceneeds to be evaluated and presented to ESA.

? Final flight data conversion (phase Fa)? Experiments documentation (phase Fa)? Flight anomaly analysis (phase Fa)? Satellite actuation characterisation (phase Fa)? Satellite inertial properties evaluation (phase Fa)? Satellite performance evaluation (phase Fb)? Scientific performance evaluation (phase Fb)? SMS validation? CFD validation support? Matlab/Simulink toolbox development

Deliverables: This activity leads to the following deliverables: Sensor calibration report; List offlight experiments and events; Reports on a) flight anomalies b) satellite andscientific in-flight performance, c) purpose and execution details on eachexperiment, d) inertial properties in flight configuration; Calculation of actuationforces form telemetry data, and e) Detailed Report

Justification for DN: This activity is the continuation of the work previously done by NLR in theESA contract 10416.




Activity Title: Laser diode device and measurement technology developmentDescription: This activity is intended to support the laser diode (DFB), G609-22MM, and Fairy

Perot Ridge waveguide (FP), G-609-20MM, activities directed at elements of thelasers for use in laser-pumped atomic (microwave) clocks. This support will bebased in the form of the verification of the laser diode specifications that arerequired and that are known to be the most critical in the realisation of theaforementioned clock types.

The tasks in this activity will be defined to help support the ongoing laser diodedevelopment previously mentioned, providing feedback to support the initial laserdiode design process followed by the refinements leading to the final packageddevice that meets the specifications. Specifically, the following tasks can beenvisaged:

- Provide design guidelines at the fundamental level by verifying wavelength,linewidth and tuning characteristics. The noise characteristics may also beinvestigated here as a design variable since this parameter is so important later.- To maintain and improve upon the desired specifications such that thespecification are met in a progressively more robust package- To investigate and predict the device’s long term performance issues that will beof extreme importance to the atomic clock applications.

Deliverables: Measurement test results to support the design and verification steps for theproduction of laser diode devices meeting the specifications for laser pumped (celland beam) type atomic clocks.

Justification for DN: OCN (CH) is the only company with enough accumulated in depthexperience in high precision laser parameter measurement and theimplementation experience in the primary field of application vis-à-visAtomic Clocks, taking into consideration that the required specificationsare quite extreme and not generally required in terrestrial applications.




Activity Title: Compatibility of the PPS5000 plasma Thruster with the new generation ofElectric Propulsion Pointing Mechanism (EPPM)

Description: The Agency is currently developing the next generation of EPPM which will suitthe needs of the European high power electric thrusters as to maximise their flightopportunities. The EPPM shall be compatible with the electric thrusters PPS5000,RIT22/XT, and T6, which are currently under development. Taking intoconsideration that the proper operation of electric thrusters is highly dependent onthe mechanical and thermal behaviour of the EPPM, compatibility needs beensured at an early stage so that identified modifications could be potentiallyretrofitted on both equipments. The ongoing EPPM development is using asreference the T6 thruster, and as the design needs to be made compatible withthe two other models (PPS5000 and RIT22), the main objective of this activity is tostudy the compatibility between the plasma Thruster PPS5000 and the newgeneration EPPM. Thus, it will consist on studying, identifying and reviewingrequirements, performing accommodation, mechanical and thermal coupledanalyses, updating the EPPM and thruster (PPS5000) mathematical models andoperating modes and, deriving requirements of thruster equipments mounted onthe EPPM. Modifications to be implemented at thruster (PPS5000) and EPPMlevels shall be identified, harmonised and mitigated to ensure the compatibilitybetween all the Electric Propulsion equipments. Representative interfaces with thespacecraft shall be considered.

The output of this activity shall be the updated design and adapted operatingmodes of the EPPM and of the thruster (PPS5000), as to ensure full compatibilitybetween the two equipments, which shall be demonstrated by analyses.

Deliverables: Reports / Mathematical Models.

Justification for DN: The activity addresses the electric thruster PPS5000 which is a specificproduct from Snecma. It is necessary then the expertise of this company inorder to successfully carried out the tasks forecast for this activity.




Activity Title: Compatibility of the RIT-22 Grid Ion Engine with the new generation ofElectric Propulsion Pointing Mechanism (EPPM)

Description: The Agency is currently developing the next generation of EPPM which will suitthe needs of the European high power electric thrusters as to maximise their flightopportunities. The EPPM shall be compatible with the electric thrusters PPS5000,RIT22/XT, and T6, which are currently under development. Taking intoconsideration that the proper operation of electric thrusters is highly dependent onthe mechanical and thermal behaviour of the EPPM, compatibility needs beensured at an early stage so that identified modifications could be potentiallyretrofitted on both equipments. The ongoing EPPM development is using asreference the T6 thruster, and as the design needs to be made compatible withthe two other models (PPS5000 and RIT22), the main objective of this activity is tostudy the compatibility between the plasma Thruster RIT-22 and the newgeneration EPPM. Thus, it will consist on studying, identifying and reviewingrequirements, performing accommodation, mechanical and thermal coupledanalyses, updating the EPPM and thruster (RIT-22) mathematical models andoperating modes and, deriving requirements of thruster equipments mounted onthe EPPM. Modifications to be implemented at thruster (RIT-22) and EPPM levelsshall be identified, harmonised and mitigated to ensure the compatibility betweenall the Electric Propulsion equipments. Representative interfaces with thespacecraft shall be considered.

The output of this activity shall be the updated design and adapted operatingmodes of the EPPM and of the thruster (RIT-22), as to ensure full compatibilitybetween the two equipments, which shall be demonstrated by analyses.

Deliverables: Reports / Mathematical Models.

Justification for DN: The activity addresses the electric thruster RIT-22 which is a specificproduct from EADS ST GmbH. It is necessary then the expertise of thiscompany in order to successfully carried out the tasks forecast for thisactivity.



Ref. Number: G609-33EP Budget: 1,000 K€

Activity Title: Development of an integrated resetable latching current limiter with trip offtime

Description: The aim of the activity is the provision of a modern and effective device forenhancing performances in power protection and distribution applications.

Spacecraft make use of Latching Current Limiters (LCLs) to ensure that thespacecraft Bus is not endangered by the failure in short circuit of overload of aBus User. Today LCLs are used on all ESA spacecraft (many of them dependingon non-European basic components). Since each device is made in discrete orhybrid form, the mass and cost of the devices are significant despite the re-use ofdesign from one spacecraft to another. The present activity hence proposes todevelop equivalent LCLs in highly-integrated ASIC (Application-Specific IntegratedCircuit) form in order to generate significant savings in mass and cost, as well asimproved reliability (due to re-use of standard LCLs ASICs in many applications).

The activity will consist in the integration and miniaturisation of a Latching CurrentLimiter (LCL) design into an ASIC solution. Preliminary targets are the reduction ofpower distribution boxes mass and volume by about 50%. The following tasks areforeseen:

1.- Preliminary Design and Approval by the Agency2.- FPGA Design and Development.3.- ASIC qualification in appropriate test equipment.

Deliverables: Pre-qualified integrated latching current limiter (LCL).



Activity Title: Polishing of brazed optical quality SiC mirrorsDescription: SiC mirrors have several advantages over conventional glass ceramic mirrors

such as higher stiffness and good thermal conductivity, which enables a higherdegree of lightweighting. Due to the attractiveness of the achievable masssavings, SiC mirrors become more and more common in optical payloads. Themass savings are particularily important for large size optical payloads, however,there is currently a limitation in size of manufacturable SiC mirrors of opticalquality. This is given by the available facilities for the manufacturing of SiC bulkmaterial and those for the CVD (Chemical Vapor Deposition) coating unavoidablyrequired to achieve an optical quality surface roughness. With a highly accurateand stable joining technique of individual SiC elements this limitation could beovercome.

The aim of this activity is to develop the technology for manufacturing of brazedSiC mirrors of optical quality. For this technology, the CVD coating required byoptical quality SiC mirrors, shall be carried out before the brazing process. Thetechnological challenges to be mastered will, therefore, be the extraordinaryaccuracy demands for the brazing process since the alignment tolerances will onlybe a fraction of the CVD layer thickness. Furthermore, the polishing problemslinked to the brazed joint transition and the difference in the wear function of thesegments need to be managed in order to get a mirror with a good accuracy inshape. The technology shall be demonstrated by manufacturing of a mediumsized brazed mirror which shall be polished to a low residual wavefront error andlow roughness.

The following tasks are envisaged for the manufacturing of a brazed mirror:1. Mirror design2. Blank procurement; grinding; CVD cladding; brazing of mirror segments3. Mirror grinding and polishing4. Mirror coating5. Performance testing

Deliverables: Mirror demonstrator; documentation



Activity Title: Technology Flow Evaluation and Qualification of SAW FiltersDescription: The main objective of this activity is the evaluation of ESCC (European Space

Components Coordination) Technology Flow and the qualification of reliable SAW(Surface Acoustic Wave) filters and to list this flow together with themanufacturers names in the ESCC Qualified Manufacturers List as qualified forpotential use by all space projects.

Technology Flow Qualification is a new concept within ESCC system which putsmore emphasis and responsibility on manufacturer's quality control, especiallyin-process control, compared to the traditional requirements for end-of-line testing.It is deemed very suitable for SAW filters which are always customer specific andcarries a high piece part cost, i.e. almost impossible to qualify as stand alonecomponents for cost reasons. Also, the incorporation of next generation SAWfilters is expected to be more efficient within the Technology Flow approach.

This activity shall be devoted to the qualification of Technology Flow inaccordance with ESCC 25400, split into four phases:- The first phase includes definition of the Technology Flow and its boundariesand preparation of documents. Currently there is no full ESCC specification setavailable for SAW filter technology flow qualification, thus the preparation of draftNo. 2543502, Requirement for the Technology Flow Qualification of SAWDevices, is included in this first phase.- The second phase includes definition of the Quality Management Programmeand Plan.- The third phase will include the actual evaluation testing in accordance withESCC Basic Specification No. 2263502.- The fourth phase will include qualification testing of the Technology Flow.Qualification plan is defined in earlier phases and based on ESCC GenericSpecification No. 3502, and associated implementation of changes todocumentation (Proccess Identification Document - PID, detailed specification,qualification plan).

Deliverables: Technology flow definition, ESCC 2543502 draft, Quality management plan,Evaluation test plan, PID, Evaluation test report, Qualification test plan,Qualification test report, Draft ESCC detail specification



Activity Title: Thermal IR Digital Holography for Non-contact Surface MetrologyDescription: The accurate knowledge of the shape of sub-mm reflector surfaces under

operational conditions (vacuum cryogenic) is an essentially required property forscientific space missions. In addition for commercial and developmentalcommunication satellites working in the Ka band frequencies reflector dimensionalstability is critical once in orbit where they have to face severe environmentalconstraints. To qualify these reflectors, suitable validated measurementtechniques have to be available to ensure the good performance of the item oncein operation. Current precision surface shape metrology techniques are limited toambient conditions and are in general also contact methods It is not then possibleto adapt such machines for operation under the thermal vavuum (and cryogenic)conditions required for space qualification.

This activity aims at developing a working Infra-Red Digital Holography (IRDH)metrology tool to address the accurate metrology of large-area low-areal-densityspecular reflectors under cryo-vacuum test conditions. Previous developedtechniques of high-resolution far infrared classical interferometry are onlyapplicable to mirror (specular surface) testing. A holographic technique has theadvantage of being able to deal with both diffuse and specular surfaces. The coreof the IRDH technique proposed is the use of digital numerical reconstruction ofthe holograms. The IR wavelength proposed is 10.6 micrometers, what will implythat the holographic information can only be recorded in an imaging system andnot on holographic photosensitive material, like in visible light.

The tasks foreseen for this activity are design of the IRDH; prototyping; and teston one or more study cases.

Deliverables: Design reports, manufacturing plans and drawings, test plans and qualificationand tests reports.

Justification for DN: CSl have been involved for several years in the development of precisionoptical measurement technologies for use and application under (thermal)vacuum conditions. They have built up a unique capability and experiencein this field, not available elsewhere in Europe. This activity builds on thisuniquely established expertise and combines it with the on-goingcollaborations with the Microgravity Research Centre (MRC) of Universityof Brussels. MRC offers specific knowledge and capability in the field ofdigital holography. It is in particular considered that the combination ofthese two partners provides a specific opportunity to exploit in a verycost-effective and efficient way their established expertise for furtheringthe European capability in the field of optical metrology of large reflectorsurfaces under vacuum conditions.




Activity Title: Development of an Adjustable Large Range Viscous Rotary DeploymentDamper

Description: The objective of the proposed activity is to develop an Engineering QualificationModel of a Viscous Rotary Damper which is adjustable in damping rate and shallallow deployment angles up to 270°. The fundamental design shall be anevolution of the existing Austrian Aerospace Viscous Damper (AAVD).

Low-cost and mass-efficient deployment systems on spacecraft are depending onhighly reliable, low mass and simple deployment speed regulators. The currentAAVD is capable of 90° rotary angle, and the damping characteristics can bepre-adjusted by using a range of damping fluids with specific, pre-determined,viscosity. Due to the complex fluid dynamics inside the damper analyticalpre-determination of the damping characteristics is however only possible to acertain degree, for precise customer-specific damping characteristics iterations offilling the damper with different fluids may be necessary. The proposed adjustabledamper will up to 270 degrees rotary range will have a much broader applicationpotential and commercial competitiveness.

The first phase of the activity will be the assessment of the limitations of thecurrently available viscous fluid damper AAVD against the market needs. Detailedrequirements, design modifications and steps to achieve the requiredperformances will be identified and derived accordingly. The main technicalaspects that will be considered in order to improve the damper competitivenessare: reliability in terms of function and contamination risk; low mass and envelope;low startup-torque; and low complexity and number of parts.

In a second phase, the EQM will be manufactured and tested in thermal andvacuum conditions to verify and demonstrate the performances of the modifieddamper.

The third phase will include a commercial evaluation to give full visibility onpotential applications and commercial perspectives of the developed hardware.

Deliverables: Engineering Qualification Model of an Adjustable Large Range Viscous RotaryDeployment Damper and Documentation.

Justification for DN: The activity concerns the upgrade of an existing hardware developed andowned by Austrian Aerospace.




Activity Title: Terahertz Camera for Remote Detection of Material Defects and Biologicaland Chemical Substances

Description: The objective of this activity is to develop a THz multi-element camera with largespectral coverage for stand-off detection / identification of buried objects andsubstance identification. The focus of the activity lies in the development of afibre-based broadband distribution network, the development of high-performanceemitters and detectors and the development of the imaging acquisition. This willbe the first demonstation of a multi-element THz camera. It will provide asubstantial advantage for European projects and ESA missions and will establishESA in the forefront of THz technology. The imaging camera will consist ofmulti-element imaging arrays. Standoff measurements of buried objects andsubstances will demonstrate the capabilities of the imaging system. This initialprototype will consist of a small number of transmitter and detector elements (<10)to limit the complexity. It will demonstrate the image acquisition and imageprocessing, as well as THz broadband spectral identification capabilities.

The following tasks will be carried out within this activity:

- Development of alignment-free fibre-coupled freely positionable THz emittersand detectors- Development of 1xN (<10) fibre splitters with sufficient power handling capability- Assessment of fast phase control units- Development of a fibre system for pulsed and CW power distribution to THzantenna arrays- Assessment of imaging system architectures for multi-element compact imagers- Determination of linewidth, stability, repeatability of the system- Efficient image reconstruction algorithms for interferometric arrays

Deliverables: Multi-element THz camera.



Activity Title: Stepper Motor for Space Actuator ApplicationsDescription: ITAR free European Space Actuators have been developed in the last few years

to fulfil the need for deployment mechanisms for various spacecraft appendix, forAntenna pointing, for Electric Propulsion Pointing mechanisms, for Solar ArrayDrive mechanism and other various mechanisms. Most of these actuators areequipped with an high performance stepper motor minimising the torque ripple,which is an important requirement in some cases. For others deployment orpointing mechanism applications involving significant flexible harness, such as theelectric propulsion pointing mechanisms, antenna with RF cables / flexiblewaive-guide, deployable radiator with flexible tubing, ..etc, the actuator shall beable to provide a significant unpowered detent torque in view to avoid theimplementation of complex and costly breaking or detent break system, whileavoiding step loss.

The overall objective of the activity is to develop, manufacture and test a DM (Demonstrator Model) and an EQM (Engineering and Qualification Model) of aframeless stepper motor offering a typical ratio between its Nominal Torque andDetent Torque in a range of 20 to 30 % with I/F compatible with existing EuropeanActuator for space applications.

The first step will be to consolidate the annexed Requirement Specification for theidentified applications such as the EPPM (Electric Propulsion Pointingmechanisms). The proposed motor concepts will be trade-off based onperformance simulations obtained by electromagnetic modelisation. The selectedconcept will be validated by means of designing, manufacture and functional testof a Stepper motor Demonstrator Model prior the Preliminary Design review.Detailed design and analysis will be validated by a Critical Design Review priorthe manufacturing and test of a Stepper Motor EQM offering the I/F andperformance compatible with existing European Actuator at sub-system level.

The targeted FM motor recurrent price should be the half of the existing highperformance stepper motor, resulting in competitiveness improvements.

Deliverables: . Stepper motor DM and EQM. Data package including (definition file, mathematical models and simulations,design justification file, PMP list, Test Report).



Activity Title: Voice Coil Motor Engineering ModelDescription: Voice Coil Motors have been used in several instruments and offers an accurate

positioning capability. Although the Voice Coil Motor is simple, there's nomanufacturer of space qualified Voice Coil Motors in Europe. This activity aims athaving an European source of Space Voice Coil Motor that are intended to beused for a pointing mechanism, like the one's for Meteosat Third Generation(MTG).

The objective of the activity will be to design a Voice Coil Motor with an emphasison Parts, Materials and Processes Validation.

An EM will be designed, built and tested, with the goal to reach at least aminimum set of specifications. A first effort is to establish the Parts, Materials andProcesses (PMP) for the VCM technologies (in relation in particular, with the coilsand the magnetic parts). Although not necessary for this need, coil redundancywill be addressed.

The second effort is to realize an EM allowing an assessment of the feasibility ofthe specific Astrium VCM MTG need. The goal is to achieve the required forcewith the allocated electric power. The required moving mass will results from thedesign. The EM functional performance will be checked. The force at differentcurrents will be measured versus position. A lifetime test will be performed in TVconditions. However, the full table of force per current versus position,temperature, time (ageing) will not be established on the EM.

Deliverables: . VCM EM. Data package including (definition file, design justification file, DML, DPL, DMPL,Test Report).


Ref. Number: G609-40MZ Budget: 450 K€

Activity Title: Flow-Structure Coupling for Hypersonic Flow RegimesDescription: The use of numerical simulation to assist in the design, understanding and

optimization of systems, to shorten production cycles, reduce development costsand enhance reliability, is constantly growing, in particular in demanding fieldssuch as the aerospace industry. In a previous activity, "Flow structure coupling forhypersonic regimes", a tool (OOFELIE) was developed for the resolution ofstrongly coupled multi-physics problems using state-of-the-art computerengineering and object-oriented methodologies. Within that contract, theperformance of different coupling methods has been tested for flow and structuralsolvers with respect to the cost/performance ratio for a number of problems, andbench mark tests have been run to determine the best suitable CFD solver to becoupled with OOFELIE, and the weakly coupled approach has been performed.

The objective of this activity is to further develop the tool to simulate accuratelyand in an integrated fashion the interaction of fluid and structural dynamics forhypersonic flow regimes, based on the previous work. The following tasks areenvisaged:

- Development of transient capabilities based on a second-order accurate timeintegration scheme for the interaction between the inert fluid and the structuraldomains;- Study of the influence of existing turbulence models;- Parallelization using state-of-the-art interprocessor communication tools;- Validation of the new features by comparison with benchmarks performed inprevious phase and by application to time-dependent phenomena.- Application to previously simulated flows demonstrating the advantage of astrongly coupled ananlysis tool with respect to increased efficiency/robustnessover the weak coupling in phase 1.- Preparation of the CFD code for strongly coupled use with OOFELIE.- Adaptation and demonstration of the visualization software tool totime-dependent results.

Deliverables: Report on the activities required to achieve the coupled time dependent flowstructure interaction, including the description of the perfomance of the solver,when applied to a test case chosen in agreement with the Agency.

Justification for DN: This activity is a direct continuation of the phase 1 done under the ESAcontract 18566, "Flow structure coupling for hypersonic regimes", fundedby GSTP-3 with 360K€. After successful completion of this phase 1, it isproposed to continue the development with the same industrial team:Open Engineering (B) as prime and Numeca (B) as subcontractor.

Non-competitive tendering is justified according to Article 6.1.c) of theContracts Regulations.



Activity Title: Multicarrier evaluation and advanced packaging for highly integrated RFSSPA

Description: The main objectives of this activity are the development a copper diamondpackage for improved power dissipation of RF HPA (High Power Amplifiers) andthe Electrical drift assement of HPA under multicarrier conditions.

A running TRP activity has identified a high performance European GaAs RFpower transistor technology which could be used for next generation L/S-bandSSPAs (Solid State Power Amplifiers). However, the thermal management hasproven to be the limiting factor in the development of the L-band power module.Recently new metal-matrix material (Copper Diamond CuD) has become availableon the market and in depth thermal studies of the L-band demonstrator haveshown that a complete CuD package would improve significantly the thermalmanagement at module level (Delta T reduced by 20%). At the same time, inorder to prepare the introduction of the developped power amplifiers to flightapplications, an early assement of electrical drift of performance under worst caseconditions (i.e. multicarrier) shall be demonstrated. Waveforms under multicarrierconditions shall also be assessed as they are intimatly linked to deviceperformance and drive the HPA design in terms of safe operating operation(impact on lifetime).

Hence this proposed activity aims at:- Developping a complete hermetic CuD RF power module package for L/S-bandapplications- Performing the full evaluation of the package in order to assess the flightworthiness of the HPA in an improved thermal environnement- Using the developped package with the formerly developped L-band SSPA- Designing a S-band medium power amplifier as a reliability test vehicle- Performing a reliability assessment under non-modulated and modulated signalto derive safe operating area of the power devices- Assess the stress impact of operation under RF multicarrier signal with respectto unmodulated conditions

This shall be achieved by carrying out the following tasks:

1.- Design of CuD Package2.- Evaluation of the various processes necessary3.- Procurement of material and manufacturing of CuD package4.- Evaluation of package for flight applications5.- Test the formerly developped L-band HPAs when integrated with the CuDpackage6.- Design of a medium power S-band reliability test vehicle7.- Manufacture of test vehicles8.- RF step stress under unmodulated and modulated conditions9.- RF life tests unmodulated and modulated conditions

Deliverables: Copper Diamond packages; 5 RF S-band Power Modules; Documentation

Justification for DN: This is a follow-up of the ESA contract 19127, funded by TRP with 350K€). After succesful completion of that initial development by the AlcatelAlenia Space (FR) it is proposed to continue the work with the samecontractor.




Activity Title: Space System Database Development PlatformDescription: Monitoring and Control (M&C) Databases are key elements of each mission. They

contain data used to operate any element of the overall Space System e.g. asatellite, one of its subsystems, of its payload, the elements of the groundsegment (e.g. EGSE, SCOEs, MCS, Ground Stations). These database systemsare key factors for ensuring the proper exchange of data between all actors of thespace system development and the high quality data for use during operations.Due to the temporal and geographical dimensions of the space systemdevelopment and operations life cycle, developing such database systems is avery complex issue for a mission.The need, to have a database system operational as early as the beginning ofphase C/D (e.g. to support equipment manufacturers development work), is amajor risk for a mission. Often, initiating such development during phase A orphase B implies that the system is not available on time, resulting in many legacytools used to solve equipment/subsystems specific issues needs.Aware of this difficulty, the ECSS has initiated several activities to standardizeissues related to databases, i.e. the E-70-31 standard identifies the data requiredfor monitoring and control space system elements, the ETM-10-23 technicalmemorandum more widely covers all issues related to Engineering databases, theE-10 part 7 standard covers issues related to data sharing and exchange.

In a previous ESA contract, the Space System Database facility was developedaccording to the ECSS concept of Space System Model introduced inECSS-E-70-31. This facility focuses on the suppliers/customers relationships andthe related exchange of products. It implements means to support themanagement of product data that is exchanged between suppliers and customers.The purpose of this activity is to formalise the concept of database developmentframework prototyped in this previous contract, develop the reusable frameworkfacility and apply it to the development of an E-70-31 compliant system databasefor use in AIT.

The following two main phases are envisaged:

Phase 1.- Development of the Space System Database Framework (SSDF).

Phase 2.- Development of the ECSS-E-70-31A Space System Database (SSDB)using the SSDF.

Deliverables: SSDF and SSDB software documentation.

Justification for DN: SSI has developed a Space System Database facility compliant with theECSS concept of Space System Model introduced in ECSS-E-70-31(contract 15670, funded with 500 K€ by GSTP-3) . Within this contract, theconcept of a reusable framework has been prototyped and a databasesystem compliant with the ESTEC SCOS based EGSE reference facilityhas been developed. The tasks proposed in this activity are a directcontinuation of the work already developed in the previous contract by SSIand it is proposed to procure this activity in Direct Negotiation with SSI (I).



Ref. Number: G604-01EP Budget: 1,000 K€

Activity Title: Development of materials for the thin film solar cellsDescription: Thin film materials used for the manufacturing of thin film solar cells are coming

from terrestrial application. Taking into account the fact that they have to be usedin space and the minimum target objective they should reach (15%), this proposedstudy will concentrate on the optimisation of the various materials. The objectivesof this study are the understanding and demonstration of the role of impurity onthe device (thin film cell) performances; the technology development for materialpurification; and the evaluation of the impact of material purification on solar cellcost. The first phase will consist on the pre-development of technology for materialpurification and on the demonstration of the effectiveness of material purificationon state-of-the-art thin film solar. The second phase will be dedicated to thedevelopment and pilot line for material purification and the verification of materialpurification impact on solar cells cost.

Deliverables: Purified materials shall be delivered to solar cell manufacturers for experimentalintroduction and assessment in the thin film cells manufacturing processes;functional devices of thin film cells manufactured with purified materials; technicaldata package including test reports and cell manufacturers assessment; purematerial for manufacturing 300 solar cells; technical data package including costanalysis.


Activity Title: Development of a European Power Supply ControllerDescription: There is a large heritage in needs and problems found in space DC/DC

Converters. Regarding the control aspects of a DC/DC Converter, most of theproblems are usually derived from the fact that the IC controllers used are notinitially conceived for spaceborn products. In general, they are MIL-quality partswith some radiation test data, for low total doses that barely justify their use.Latch-up problems have been found in the past when using some of thesedevices (SEE test data are rarely available). Also, these non-European productsappear and disappear from the catalogue and are exposed to obsolescencewithout notice and control. The objective of this activity should, therefore, be thedevelopment of an Engineering Model of a Standard Pulse-Width-ModulatedIntegrated Circuit. Such a device shall withstand without degradation a total doselevel in the range of 50-60 kRads and shall not be latch-up sensitive in the usualspace radiation environment. Finally, to minimise the European dependence inthis type of products, the development shall be performed within a fully Europeandesign and foundry technology. In the past, the dependence on non-Europeanfoundry has resulted in very high prohibitive costs and also uncontrolledobsolescence of the foundry used.

Deliverables: A fully tested Engineering Model of an Power Supply Integrated Controller and itsdesign data package.

Power generation, storage and distribution efficiency



Activity Title: Single Chip Advanced Data and Power Management System (SCADPMS)Description: In anticipation to the definite need for miniaturized systems in future space

missions, this activity proposes a follow-on project on ADPMS in order to realize asystem-on-chip ADPMS. This system will integrate the main functionalities(processor board, TM/TC, Spacecraft I/F) into one ASIC, resulting in a morecompact and less power consuming system. This small system will allow thebuilding of more compact satellites (micro satellites), the use in interplanetaryexploration programs (e.g. Aurora program), and the application in small butcomplex robotics (e.g. ISS Eurobot). The development, fabrication and validationof the SOC ASIC, should be done according the future ECSS-Q60-02, if availableat the time and taking into account the lessons learned/new methodology/SOCASIC specifications obtained from previous SOC activities.

Deliverables: ADPMS SOC ASIC samples; design specifications, and documentation (as perESA ASIC Design & Manufacturing Standard).

Justification for DN: Verhaert is currently developing the Advanced Data and PowerManagement System, a very powerful and compact on-board computerbased on the radiation-hard single chip LEON processor (100 MIPS),under contract no. 14534, funded with 2800 K€ in GSTP-2 and GSTP-3.This activity is a direct continuation of that contract and thus it is proposedto award it to Verhaert.




Activity Title: Dynamic Modelling of multi-junction GaAs solar arraysDescription: Power dissipation of the solar array regulators and performances with respect to

power bus quality strongly depend on the capacitance of the solar array. Thelarger capacitance of solar arrays with multi-junction solar cells compared to thesilicon cell ones, requires a more precise definition to avoid electronics oversizing.The non-availability of precise models for the prediction of the solar arraycapacitance and the high uncertainty associated to the present capacitancetesting methods, result nowadays in overdesigning the Power ConditioningElectronics. The proposed activity will solve these problems and will help inreducing the mass of the Power Conditioning Electronics. This activity aims todevelop a small signal (AC) and a large signal (time domain) model ofmulti-junction GaAs solar cells that accurately predict their dynamic behaviourwhen connected to a solar array regulator thus enabling its optimization. Theactivity will be focused on shunt, series and maximum power tracker solar arrayregulators. The small signal (AC) and large signal (time domain) models shall beaccurately defined and correlated with test results so that relevant information(capacitance depends on temperature, illumination level, radiation, etc.) isestablished. An optimization of the capacitance testing methods on MJ solar cellsis foreseen under this activity. Three Testing samples (solar cell coupons) shall bemanufactured, each optimized for one type of solar array regulator. Other testsamples may be provided by projects .An extended testing activity shall be carriedout including:- Measurement of capacitance vs. temperature- Measurement ofcapacitance vs. angle of incidence- Measurement of capacitance vs. illuminationspectrum and intensity.

Deliverables: Three Test samples. (Solar Cell Coupons) Process identification documents of themanufactured test samples. Capacitance test procedures including test set-updescription. Technical data package including models definition and applicabilitystudy reports, test reports.


Activity Title: Quality requirements for GaAs solar cellsDescription: The proposed activity aims at experimentally and systematically verifying which

quality requirements (particularly visual inspection defects definition), alreadyestablished for silicon solar cells, are still valid for the current gallium arsenidesolar cells and which new requirements should be introduced. An extensivetesting programme, including thermal cycling and visual inspection at regularintervals, shall be established and performed on GaAs solar cells integrated tostandard rigid supporting structures. Two main types of investigations arerequired: a) manufacturing and testing of samples with well-identified processdefects (such as defective bonding, air bubbles, etc), before and after thermalvacuum cycling and ambient pressure cycling; b) manufacturing and testing ofsamples with cell and/or cover-glass defects (e.g. cracks), under ambientpressure, and checking their electrical performance stability. Both investigationsshall be supported by a large statistically meaningful set of test data.

Deliverables: Eight coupons, or more, submitted to the test sequences; technical data package,including test reports and proposed new requirements specification.



Activity Title: Commercial Off-the -shelf converter developmentDescription: European space users require stand alone DC/DC converters, offering standard

supply rails (12V., 5V, 3.3V, etc) at low cost .The goal of this activity is to minimizethe use of off-the-shelf DC/DC converters (typically American) for which no designdetail, and no design margin is actually available for ensuring the ESA standardsof reliability, stress and worst case usually applied in ESA space programs. Thebenchmarking for competitiveness of cost/prices in the domain of standardmulti-purpose DC/DC converter is the price of so-called space grade or spaceapplication derivations of commercial, aeronautical or military products proposedby some US companies. These products have proven nearly suitable for spaceapplication and offered with an attractive price. However, these commercialproduct have proven very unreliable in the field, for a number of reasons: misuseby lack of knowledge of their exact capability/performance; design not up to thestandard required by space application (components selection and de-rating,stability, failure modes and protections) and difficulty of insertion in a system(compatibility of interfaces, filtering, EMC). While trying to keep the qualities ofcompactness and design to cost of the commercial products, the points mentionedabove will be integrated in the design.

Deliverables: The objective is to get one representative EQM of the COTS converter, fullytested against the applicable interface and environmental requirements, andprovided with a full set of analyses and documentation required for a FM unit. Theanalyses should encompass all the envelope of the converter realisation.


Activity Title: Solar Cell Blocking Diode for High Temperature OperationDescription: Development of a flat blocking diode a so called "Solar cell blocking diode" for

isolating solar cell strings on solar array panels operating in a temperature rangebetween -180 deg. C and +250 deg. C. The electrical contacts of the flat blockingdiodes shall be suitable for the same interconnectors and interconnectiontechniques as used for solar cells (single and multijunction cells). For protectionagainst particle radiation the diodes shall allow for being covered by typical solarcell cover slides. Radiation environment shall envelope BepiColombo, SOLOmissions as well as a typical 15 years GEO mission. The concept of a flat largearea diode allows for a good thermal heat transfer to the underplaying panelsubstrate. The flat solar cell shunt diode has been proven to be successful andwas used in various solar arrays such as for Hubble Space telescope.

Deliverables: 20 flat solar cell blocking diodes successfully tested to qualification level



Activity Title: Study, Development & Verification of a Planar TransformerDescription: Transformers lie at the heart of space DC-DC converters and are often the main

element that is customised from one design to the next. The use of planartransformers has gained momentum in the commercial markets in recent years asa means of reducing the cost of magnetic components within DC-DC converters,since the windings are made by printing or stamping out copper tracks using oneof a number of repeatable and well-know processes. Miniaturisation may also beachieved by using part of the Printed Circuit Board to make the windings. Thehigh costs associated with the winding of more traditional magnetic componentsare also seen in the frame of converters destined for space, where theirmanufacturing is often on the critical path and where the risks associated are high.Nevertheless, the adoption of the planar transformer concept for space has beenslow due to inherent problems associated with inspectability of soldering,adequate separation between connections, and qualification of overallmanufacturing processes, as well as the unavailability of design heritage. Thisobjective of this study is to produce a family of cost- and weight-competitive planartransformers to ESA standards of design and manufacture, suitable for use in low(10W) to medium (50W) power converters. Once design and manufacturingprocesses are established, prototypes of the magnetic components will be builtand tested within a simplified power module. Finally a range of components shallbe qualified for space use.

Deliverables: Range of EQM transformer models


Activity Title: Electrical network for thin film solar arrays (on flexible blanket)Description: A thin-film solar cell generator might allow a significant reduction in the solar

generator and overall system costs especially for large GEO platforms. In additionthin film generators are expected to provide a significant mass and stowed volumesavings compared to classical solar arrays, especially if the thin-filmcells/monolithic modules are grown on thin flexible foils which are mounted onflexible substrates. Integration of the thin film solar cells on the flexible substratesis then a real issue for the use of those cells in space. In particular, the behaviourof the electrical interconnections in between thin film solar cells against thethermal environment is a key point for the use of those cheap components inspace. In addition the cabling and components mounting (diode, resistor) has tobe investigated. The industrialization of the technologies shall be a key parameterfor the choice of one against the other. The activity is dedicated to the design ofthe following technologies: mounting the thin film solar cells on the supportingblanket; interconnection between solar cells (definition of the joint nature,technology and interconnection material) to form strings; interconnectionsbetween strings; wiring and components integration on the flexible blanket. Theabove analysis shall be performed with thin film solar cells and modules. Abreadboard shall be manufactured and tested for thermal and mechanicalconstrains.

Deliverables: Breadboard for technologies demonstration; and technology data packageincluding a statement on the industrialisation of the proposed technologies.



Activity Title: Improved optical modelling of solar cell assembliesDescription: This project aims at improving the performance of solar cell cover glasses and

solar cell coatings. Up to now, anti-reflection coatings have been optimisedseparately for bare cells and cover glasses. This project will perform jointmodelling of cell and cover glass anti-reflection coatings as a single optical unit(including cover glass adhesive) in order to improve the overall spectral responseof the SCA. Ellipsometry measurements will be used as input to the model; thebest designs will be manufactured and tested.

Deliverables: 25 solar cells with optimised coatings and data package / report detailing progressand prospects for implementation / improvement.

Justification for DN: Thales is the only manufacturer in Europe of coverglasses for solar cells.Its experience is then required to successfully accomplish the tasksdefined for this activity.



Activity Title: Radiation studies for Next Generation Solar CellsDescription: Understanding of radiation degradation is fundamental to the development of the

new solar cells. The necessary radiation work will involve the testing and analysis,according to existing methods, in order to understand and predict radiationbehaviour. Additionally, it will require the development of new methods of testingand analysis in order to reduce the requirement for resources associated withprediction of radiation behaviour. In particular, work performed in the presentproposal will pursue these objectives in support of the following activities:development of next generations of multi-junction solar cells; development of nextgeneration silicon solar cells; and thin film solar cell and module development.

Deliverables: Proton and radiation test results on next generation solar cells; and performanceprediction for the tested components using both existing models and new modelsunder development.



Activity Title: Testing Method Definition and Failure Analysis for the Reliability Verificationof the Multi-junction GaAs based Photovoltaic Technology

Description: The development program is devoted to the improvement of the reliability of themulti-junction GaAs photovoltaic technology and to the adjustment of the designparameters and margins, with the aim of extending the power capability of theEuropean Industry and improving the quality and competitiveness of theirproducts. The proposed program will be composed by analysis and experimentalactivities able to define a new set of qualification and acceptance procedure forthe multi-junction photovoltaic assembly. The analysis will be focused to the studyof the failure mechanisms and the verification of cell junction defects together withthe preparation of an extensive "in-orbit" failure database. The evaluation of thein-orbit performance degradation data will be aimed at the updating thedegradation factors in the solar array design. The experimental part will bedevoted to the definition of a new testing method to assure the reliability of thecomplete photovoltaic assembly during the space missions. The main objective isthe verification of the potential instability of the multi-junction GaAs solar cellduring the mission; the test will be based on the forward bias current loadingapplied to Thermal Vacuum and Thermal Cycling Test of the solar cells andmodules. The activity shall also include several non-destructive test methods forthe evaluation of the solar cell and diode hot spot and the solar cell bonding (e.g.:Infrared thermography), and to detect and monitor the defects in the solar cell(e.g.: Electroluminescence test).

Deliverables: The following development samples and documentation will be delivered: 200solar cell assemblies; 16 coupons of solar cell assemblies; Database; TechnologyData Package


Activity Title: Thin Film module pilot line and pre-qualDescription: This study is dedicated to the industrialisation of the manufacturing of thin film

solar cells, in the context of space applications. Two aspects have to be covered,the development of a pilot line and the various manufacturing process to beinvestigated (like roll to roll). The one offering the best compromise in term of costand performance will be developed as a pilot line. Tests have to be implementedlike for usual space qualified solar cell manufacturing and cost aspects shall beevaluated and taken into account at each level. Finally, it will include thepreparation of the generic specification dedicated to the qualification of theproduction of thin film solar cells. This activity shall just be directed to single celland monolithic modules.

Deliverables: 100 solar cells and 50 modules satisfying the space requirements; and technologydata package including cost, yield and performance issues.



Activity Title: Experimental Concentrator Solar Panel for Proba 2 - phase 2Description: Solar arrays with high efficiency solar cells would benefit of concentrators

systems, in terms of cost per watt, by reducing the number of solar cellsnecessary to produce the same power. A new concept of concentrators withon-panel reflectors, developed by CSL (B), would possibly overcome the thermaldrawbacks experienced by the large concentrator systems.The objective of the proposed experiment on PROBA 2 is to demonstrate theconcept of concentrators with on panel reflectors and verify its survivability to thespace environment conditions (mechanical- thermal stress, interface with the solarcells, etc.).The activity will cover the preparation of a flight experiment of a solar cellconcentrator module, to be flown onboard the PROBA 2 satellite. The activity isdivided in 2 phases: the first phase, already included in the GSTP-3 WorkPlan(ref. G00/I71.PROT-016, budget of 200 K€) is dedicated to the technologydefinition and testing on experimental sample. The second phase proposed herewill cover the following additional tasks:- Detailed design, according to the phase 1 results and to the PROBA 2 interfacerequirements.- Manufacturing of the concentrator.- Proto-flight qualification testing.

Deliverables: Flight hardware (15 x 30 cm concentrator module experiment) to be integrated onPROBA 2, and the related documentation (Design report, interface documents,test reports, in-orbit performance prediction).

Justification for DN: The activity is based on the outcome of a call for ideas for PROBA 2experiments issued by ESA in 2002 and open to all European entities (ref.ESA/IPC(2003)4, add. 2), from which the first phase is about to be initiated(GSTP Ref. G00/I71.PROT-016 Solar Array Concentrator, budget of 200Keuro). Moreover, CSL is the only European company having developedthe concentrator technology with on-panel reflectors for spaceapplications.




Activity Title: Improved Manufacturing Technology for Ge SubstratesDescription: Umicore (B) is presently the world leader in the market of Ge substrates for high

efficiency III – V compound solar cells. For 10 years, development andmanufacturing of germanium substrates in Umicore's Olen plant has followed agrowth track, with market share increasing into a position of pronounced marketleadership. This growth path has also been the background to improvement ofproduct quality and cost-effective manufacturing with important support providedby ESA.

Umicore is now approaching a point in the product development curve where anew discontinuous step needs to be taken. Continuous improvement, whichbrought up yields in the current manufacturing environment, is reaching its limitsand market pressure towards cost reduction is increasing. Although marketleader, Umicore still has to be responsive to the requirements of the markettowards substrate price reduction.

The objective of this activity is then to improve the Germanium substratesmanufacturing technology at Umicore, focusing on the less robust areas in theproduction chain, with the aim to meet the more demanding requirements fromsolar cell manufacturers and to reduce the costs. The activity will cover thefollowing:- Yield improvement. Increase of the maximum number of wafers/cm from eachgermanium ingot; Reduction of wafer edge-chipping.- Quality improvement. Including modelling of crystal growth and comparison withexperiments.- Low-cost manufacturing. Implementation of a new process: nano-grinding &touch-polish; Development of alternative chemical etching recipes; Testing ofalternative wafer drying methods.

Deliverables: Technical documentation describing the process improvements; At least 200 Gesubstrates made with improved processes; At least 10 solar cells made byUmicore’s customers on the improved substrates, with appropriate feedback.

Justification for DN: Umicore (B) is the only relevant supplier of Ge Substrates in Europe.Moreover, the activity proposed will serve as a continuation to an ESAcontract (No. 13687, budget of 5,500 K€ funded by GSTP).

Non-competitive tendering is justified according to Article 6.1.a and 6.1.cof the Contracts Regulations.



Activity Title: Hydrogen Gas Storage in Space - Microspheres technology and applicationsDescription: Based on the previous contract, "Hydrogen Gas Storage in Space", the main

focus of using Microspheres as hydrogen storage system is to cover experimentsof basic properties. For introducing Microspheres into the market of hydrogenstorage systems is necessary to consult possible users and to develop withrespect to suitable applications. Further investigations require several basicexperiments. In particular, necessary actions to receive a solid knowledge basewill be: the determination of pore volumes of Microspheres; the acquisition ofselected Microspheres, by separation of pressure resistant fractions of commonborosilicate Microspheres (the remaining "fractions" will represent differentqualities of storage bodies, which can stand 400, 600, 800 and 1000 bar); basicdiffusion tests with above quality fractions; basic diffusion tests with alternative(Fillite) spheres.; and coating of Fillite spheres to reduce hydrogen diffusion atambient conditions. The results of experiments with these coated spheres will becompared to results of common borosilicate microspheres. In addition to theexperimental investigations connections to possible users of Microspheres ashydrogen storage system will be established.

Deliverables: A final report including the results of either the experiments and the applicationsurvey.

Justification for DN: This activity will serve as a follow on of a previous ESA contract (No.16944, 150 K€ funded by Corporate Budget) successfully performed byEnergie Technologie (D).




Activity Title: Multiple Output Low-Voltage DC/DC Converter ModuleDescription: AAE has developed a single output (1.8V or 2.5V or 3.3V, 9A) converter in the

frame of the GSTP-3 activity ‘Very Low Output Voltage DC/DC-Converter’. Basedon this know-how, a new generation of point-of-load power converters for DHS I/Oboards has been developed. According to the existing ASIC technology of the I/Oboards only 5V and ±15V outputs have been implemented. Planar integratedmagnetics is used for replacing the usual wirewound transformer plus the outputinductor. As planar magnetics is relatively new in space applications, a detailedqualification and screening program has been carried out at AAE. However, mostapplications demand for multiple outputs (1.8V, 3.3V, 5V, (-5V), ±15V) with a totalpower of about 10W. This is true both for self-contained equipment like the GPSnavigation receiver selected as target application and for point-of-load convertermodules in a distributed power system of a large system like future data handlingsystems (Distributed power system elements, in particular on-card DC/DCconverters, offer several advantages compared to conventional centralised powersupplies). Hence, a multiple output DC/DC converter with a wide range of outputvoltages from 1.8V to 15V needs new and delicate solutions if good performancewith respect to stability of output voltages, efficiency and cross-regulation isrequired.

The objective of this activity is to develop an Engineering Qualification Model of acompact, efficient and competitive, multiple output low-voltage DC/DC convertermodule for an on-board application. The application in view is the converter for aGPS navigation receiver as used in a typical earth observation mission.

The activity will comprise the design of an easy to use multiple output DC/DCconverter module for on-board applications, the manufacturing of an engineeringqualification model and the respective testing according to typical flight projectqualification requirements. The following design issues will be especially takeninto account: the optimised parts count and selection in order to shrink costs andsize; optimised use of European components; excellent electrical performancewith respect to efficiency, accuracy, cross regulation, dynamic response; highradiation tolerance (SEE); and ITAR free design. It is foreseen to establish apartial breadboard during the initial design phase in order to breadboard thecritical parts, mainly to confirm the cross-regulation performance. After the designconsolidation the detailed EQM design will commence followed by themanufacturing of the EQM model and the associated qualification test program,which includes environmental test such as thermal vacuum, vibration andconducted EMC tests.

Deliverables: An Engineering Qualification Model of a multi-output low-voltage DC/DC convertermodule together with the respective documentation set.

Justification for DN: The proposed activity is a continuation of an ESA activity (Contract no.15893, 350 K€ funded by GSTP-3).




Activity Title: Solar array maximum power point tracking based on boost regulation forhigh power applications

Description: The selection of the Solar Array Regulator topology for the BepiColombo ElectricalPropulsion Module is on going. The use of a Maximum Power Point Tracker hasbeen addressed to be essential for the mission. Due to the required power for thismission (in the range of 10kW), the adaptation of the existing MPPT concepts for28V busses (GOCE, ROSETTA, etc.) to 100V is identified to be an area of risk.The upgrading of Power Conditioning Units from 28V to 50V or 100V has notalways been straight-forward and exempt of development problems. Also, the useof a step-down regulator for Solar Array power conditioning in a 100V bus may notbe a good decision due to the performance limitations of high voltage devices. Astep-up (boost) regulator may be advantageous instead. Furthermore, due to theharsh environment that the Solar Array will be exposed to, the segregation of solararray power may be a very desirable feature (not available, for instance, with theROSETTA approach).

In consequence, this activity will be devoted to conceive, design and manufacturean Engineering Model of a 400W Step-Up Solar Array Regulator Module withMaximum Power Point Tracking (in principle for the BepiColombo mission, butcertainly for other applications as well).

Deliverables: Engineering model of a solar array regulator module.



Activity Title: Analysis of Life-Cycled SAFT Li-Ion CellsDescription: This activity is a continuation of the work already done under the GSTP-3 activity

"Analysis of life-cycled SAFT Li-ion cells". The purpose of this second phase is toimprove the knowledge of the Saft G5 Li-ion cells (VES180) self short circuitedconcept to demonstrate the ability to sustain a LEO or GEO mission withoutbypass device. In addition, the validation of the G4 model (VES140 cells) for theG5 cell technology will also be done.

For G4 cells (VES140) the technique of self shortening was successfullydemonstrated, and as both (G4 and G5) cell designs are based on the sameLi-ion electrochemistry, it is proposed to demonstrate now the feasibility of the cellself short concept for Saft G5 Li-ion cells. and to verify the quality and stability ofthe self short cicuit of VES180 cells under GEO and LEO cycling conditions.


1.- Reversal of G5 cells and comparison with internal resistance of G4 cells2.- Reversal characterisation: influence of state of charge and solstice storage onself-short resistance3.- G5 self short: mechanical, electrical, thermal characterisation4.- Stabilisation, robustness and eventual drift of self-short resistance under LEOand GEO conditions5.- Calendar ageing and real time Galileo cycling test

Deliverables: Final Report

Justification for DN: SAFT (F) has successfully carried out the tasks for contract 18398 (fundedwith 200K€ by GSTP-3) and this activity is considered a direct continuationof those tasks.




Activity Title: Robust Receiver Technology OptimisationDescription: The aim of this activity is to optimise the structure and layout of the GaN High

Electron Mobility Transistor (HEMT) such that simultaneous high output powerand low noise figure can be obtained. This work will allow ESA to assess whetherit is feasible to realise a single chip Transmit Receive front-end using a singleGaN process technology.

Low noise microwave transistors are a vital component for realising highperformance RF receiver front ends in both telecommunications and earthobservation systems. In a previous TRP activity it was demonstrated thatnon-optimised GaN transistor technology had a noise performance comparable tothe GaAs technology, but was significantly more robust to both RF (x20improvement) and radiation damage. Additional studies have also indicated thatthe off-state isolation of a GaN LNA with no limiter is comparable to a GaAs LNAwith its limiter. This could imply some benefits as: Lower overall system noisefigure by removing the limiter function in some applications due to the high voltagewithstand capability of GaN (elimination of the limiter ohmic losses, approx. 1 dB);Dynamic range improvements in LNA and mixer functions can also be envisagedbecause of the improved linearity and power handling; Since GaN technology alsohas comparable advantages for the transmit function, there is the possibility ofrealising a single chip monolithic transmit/receive front-end.

Although in the previous TRP activity, breakdown performance exceeded that ofGaAs, the full theoretical capability was not achieved at that time and changes toimprove overstress performance were needed. In this activity, it is planned toovercome the previous issues by (i) improving carrier confinement in the transistor channel by using Fe doping; (ii) using a thinner upper barrier layer to improve noise figure; (iii) introduction of improved ohmic contacts.It is also envisaged in this activity to study the optimum layout and layerstructures, and to fabricate a new series of robust low noise devices that will bevalidated in a circuit demonstrator.

Deliverables: Technical notes; Device samples; and LNA demonstrator hardware.

Justification for DN: The work proposed in this activity is the continuation of the work carriedout by Qinetiq (UK) during ESA contract 15908 ("Noise Assessment ofGaN Structures", funded with 300K€ by TRP). Given the significantcapability in this area by this contractor and the fact that this activity shouldbe considered a continuation of the work initiated in TRP, it isrecommended to place the contract in direct negotiation with Qinetiq (UK)




Activity Title: Requirement Engineering: Requirements complexity and cost analysisDescription: The requirement phase does not limit itself to English text, but is more and more

supported by models of the requirements. The goal of the activity is to takeadvantage of the existence of the model in order to analyze the complexity andtherefore the cost impact of the requirements. Most models make use of aformalized language, mainly UML, or other with a stronger semantic (which makesthe task easier). The goal of the activity is to make use of this formalization toanalyze the complexity of a model. Each element of the semantic of the languagewill be assessed in terms of complexity, and in terms of its impact on the cost. Forexample, the interrelation of classes in a UML model is one good indicator ofcomplexity. The second goal of the activity is to propose a systematic method toreduce the complexity and/or the cost of a model as representative of a set ofrequirements. It is believed that a very small part of the requirements areresponsible for a large part of the cost. A minor modification of the requirements(as expressed through the models) could trade-off a large part of the cost. Theactivity must propose a method for that purpose.

Deliverables: Selection of the set of modelling languages most used; metrics for the complexityassessment of each language; metrics for the cost assessment of the modeledsystem; guidelines for the reduction of the complexity and the costs.

Technology to reduce the schedule and cost of System Design,AIV, Mission Control and Operations



Activity Title: EGSE architectureDescription: Within the current TRP programme a contract to address test system technology

was awarded to SIEMENS Austria. This activity concerns the development of thetechnology addressed in TRP to a level of usable products. The subjects to beaddressed in this follow-up activity are: -Inclusion in the architecture of the meansto introduce more mobility in AIT through the use of wireless networks supportingportable computers or so called PDAs. The activity will result in implementation ofuser tools and interfaces compatible with hand-held and wearable devices.Definitions of interfaces using XML will be developed and tested. Moreover,software to enable the use of portable computing devices shall be specified anddeveloped to show how such devices can be employed to increase efficiency ofthe AIT team. -To define an Architecture for EGSE where elements are viewed asservice providers and service users in a supporting architecture, the implementingtechnology will be based on web addressing and communication techniques(prototyped in the TRP activity), which provide an ideal vehicle on which to basesuch solutions. An analysis of a typical EGSE system will be evaluated in thecontext of the service based approach and a demonstrator system will bedeveloped.- The EGSE architecture definition will address in particular theinterfacing of elements dedicated to specific subsystems with the system thatmanages the overall testing activity. A standardized means of intercommunicationat the level of an EGSE protocol together with methods and tools to controlaccess and data exchange will remove the need to make project specific solutionsin the future (time consuming and expensive).- Commonality between all phasesof the project life cycle (pre-and post-launch) will be investigated to align theservice based testing approach with the operations concept defined inECSS-E-70-41 in order to ensure a smoother and more efficient transition fromAIT activities to operations activities. A goal here is also to ensure that thearchitectural model is compatible with that of the flight control domain.

Deliverables: -Specification of an Architectural model that supports hand-held devices in aservice oriented web based environment, -Specification of EGSE specificprotocols for communication; -Implementation of AIT MMI on a portable device inweb based environment that demonstrates key technologicalfeatures-Demonstration system (hardware and software)

Justification for DN: This activity is a continuation of contract 14029 "Test System Technology",awarded to Siemens Austria within the current TRP programme. Thisactivity covers the development of the technology addressed in TRP to alevel of usable products.




Activity Title: Low cost platform for system simulation based on EcosimProDescription: The main objective of this proposal is to develop a user friendly and low cost

platform for system simulation based on EcosimPro. The communication betweenEcosimPro and ESATAN (ESA thermal analysis tool) has already been achievedusing the Distributed Calculations protocols and ECLS and propulsion models arealready directly modelled using EcosimPro. As a result, the logical next step is todevelop within the frame of the activity a robust connection between EcosimProand Matlab Simulink because: 1. Simulink is one of the most generic simulationtool, extensively used in the world. 2. AOCS is a rather important subsystemwhich interacts with the TCS and the Propulsion System, and many companiesare developing models using Simulink (GAOCS,...)

Deliverables: New version of EcosimPro with a verified interface with Matlab/Simulink to enableto perform system level simulations with low associated cost.

Justification for DN: EcosimPro is the Agency's standard software package for the analysis andmodelling of environmental control and life support systems. EmpresariosAgrupados have been the prime contractor for the development,distribution and support of the EcosimPro software since the start of theprogramme under ESA Frame Contract 13974 (545 K€ funded by GSTP3and Corporate budget). Their considerable experience and intimateknowledge of the software place them in a unique position to carry out thedevelopment tasks related to EcosimPro. Therefore, due to the pastexperience acquired on this specific tool, it is recommended to continuethe contract with Empresarios Agrupados.




Activity Title: Development of an European Space Propulsion System ToolDescription: The purpose of this activity is to develop and validate, within a common

environment, a software tool to simulate transient multi-disciplinary systems andcycles (e.g. spacecraft systems, propulsion cycles, ground support equipment,ground/qualification tests) to be used by European space industries, researchinstitutes and universities. The present activity will implement the models into ageneral software framework including all functionalities and modularities based onproperly defined user and software requirement documents. Different libraries,addressing several disciplines and/or specific components, need to be developedand validated: 1. Mechanical library: rotational and translational components. 2.Thermal library: 0D, 1D, 2D thermal networks and heat exchangers coupled tofluid flow components. 3. Fluid flow library with advanced algorithms dealing with:a) liquids, cold gases, two-phase flow; b) heat transfer, waterhammer. 4.Combustion and Chemical library: burners, combustion chambers, nozzles. 5.Turbo-machinery library: turbines, compressors, pumps,... 6. Tank library:advanced tank modelling during depletion, filling and operation. Furthermore, thetool should have the capability of representing one or more physical componentsby external simulation tools of different degrees of complexity, from 0D to 3Dmodels (i.e. zooming capability). This coupling and the communication protocolshall be developed for a computational fluid dynamics tool (CFD). All modulesdeveloped will be tested and validated versus analytical and/or experimentalresults.

Deliverables: 1. Mechanical and thermal library for steady and transient simulations. 2.Combustion and chemistry library for steady and transient simulations. 3. Fluidflow library for liquids, gases and two-phase flow for steady and transientsimulations. 4. Heat exchanger, tank and turbomachinery library. 5. Zoomingcapabilities with interface to external CFD-tools. 6. Validation test plan. 7.Documentation and manuals.

Justification for DN: To harmonize the engineering simulation tools within Europe, the samecore of the EcosimPro-tool, already used for other applications (ECLSS),is proposed for this activity. Hence, the activity can profit from previousdevelopments and focus on the key development of prototype models.Moreover, the preparation of libraries requires a deep knowledge of theEcosim-tool. Hence, Iberespacio, as the developer of Ecosimpro, has theexperience of integrating the models into the tool. Work to be carried outby the Subcontractors will include developping the advanced algorithmsand modelling.



Ref. Number: G605-13AC Budget: 300 K€

Activity Title: Concurrent Engineering of Space InstrumentationDescription: Complex space instrumentation that drives the total mission and spacecraft

systems design are becoming frequent in the agency's future programmes. In aprevious activity it was done the development of an instrument conceptual designand modelling capability using an Earth active sounding instrument as a test case.A further study is scheduled for a sub mm instrument using the developed modeland experience gained. In addition the modelling capability for optical instrumentshas been developed but not proven in a study environment. Having demonstratedthe successful extension of the CDF Model and interactive design approach tosuch EO missions, it is proposed to extend the CDF capability as follows:identification and assessment of methods and tools suitable for instrument designat conceptual level and demonstrating their "added-value" in the concurrentengineering environment; derive the key interface parameters that define theinstrument design model and interface with the mission and spacecraft systemmodel; enhancement of the already developed CDF instrument design model withreal time instrument design analysis by developing interface capabilities withmethods and tools currently used off-line to support CDF studies; using the opticaland radiometry model conduct studies to show the application of newtechnologies and systems approaches in conceptual instrument design;demonstration of the enhanced CDF assessment and review analysis capabilityusing environment and technology driven instrument driven mission andspacecraft systems in support of science and EO proposals for future missions;identification and performance of pilot projects based in industry; and investigationof the extension of the methodology throughout the instrument developmentlife-cycle.

Deliverables: Software infrastructure for the implementation of the methods and tools;associated documentation (eg. user manuals, procedures, etc); anddemonstration of the process for a specific project.

Ref. Number: G605-15AC Budget: 100 K€

Activity Title: Concurrent Engineering and "Web Services"Description: The proposed study aims to study the possible added value and effectiveness of

the use of Web Services in the Concurrent Design Facility (CDF), as acomplement to the existing Integrated Design Model (IDM) and the methodology.Furthermore, a working prototype of a "Service" will be developed. Web Servicesis a fairly new name to identify the use of smart communication ways in andbetween businesses and business processes. It is currently mostly used toenhance the efficiency within business cooperation and data sharing. WebServices are self-contained "business" functions that operate over the Internet,they are becoming important to business because they enable systems in differentcompanies to interact with each other, more easily than before. Because Webservices are written according to standards, all parties work from the same basicdesign. Web Services constructed from applications meant for internal use can beeasily exposed for external use without changing code. This means that the CDFIDM model can be easily accessed by external designers (e.g. ESOC, spacecompanies for reviews, etc.). Through Web Services companies can encapsulateexisting business processes, publish them as services, search for and subscribeto other services, and exchange information throughout and beyond theenterprise. Web Services will enable application-to-application interaction.

Deliverables: Documentation; requirements definition of software and hardware; prototypeservice (software product); and test report.



Activity Title: In-flight validation of internal charging toolsDescription: Internal charging tools, such as DICTAT and ESADDC have undergone validation

through laboratory experiments but not yet in space. Users' confidence in suchtools would be increased if an in-flight validation were conducted. An experimentis proposed which would provide end-to-end validation of the tools and allowimprovements to the existing environment models. The experiment would aim atdirect measuring of currents deposited in materials under a wide range ofshielding levels. This would be achieved by an instrument with a succession ofthin plates, one behind the other. The current collected by each plate would bemeasured separately. These measurements would be made over an extendedperiod to measure the internal charging currents and dielectric charging levelsover an extended period, so that dynamic effects arising from changes in the outerradiation belt could be characterized. The experiment would be ideally flown on asatellite in geostationary transfer orbit to give good coverage of the radiation belts.Alternatively, it could be flown in geostationary orbit which would address the orbitof most concern. Data from the current measurements would be compared to theinternal charging currents predicted by internal charging tools and would be usedto validate both the radiation belt environment model, e.g. FLUMIC, and theelectron transport and deposition models used by the codes. In combination withthe current measurements, the measurement of dielectric potential provides thevalidation of the charging aspects of the codes.

Deliverables: Flight experiment to measure internal charging currents and surface potentials;and validation data for the internal charging tools and environment models.


Activity Title: Development of 3-D analysis tools for the Space ENVironment InformationSystem (SPENVIS)

Description: The Space Environment Information System will be extended to include betterengineering interface to a new Single Event Effects analysis tool, along withimprovement of shielding analyses, meteoroid and debris, and spacecraftcharging models. The “small geometry” shielding tool will be enhanced with inputand output in standard geometry formats and export of results to spreadsheetsimplemented. Interfacing with ECSS standards and methods will be implemented.A “stand-alone” version for the individual engineer’s desktop will be furtherdeveloped and promoted.

Deliverables: Updated website containing improved and newly implemented models and tools,along with associated documentation; stand-alone versions of Spenvis andinstallation set.

Justification for DN: BIRA has developed SPENVIS, maintains the system software and runsthe central server system. The activity is a follow-on of a previous GSTPactivity under contract no. 11711 (total budget of 900 K€). The models andtools currently implemented in SPENVIS do not cater for a detailedgeometrical description of the spacecraft hardware and are limited to asimplified one dimensional or omnidirectional analysis. It is proposed toaugment SPENVIS beyond its current function as a first analysis tool byimplementing three-dimensional geometric modelling, which is needed tomodel effects like radiation damage, contamination, charging, andirradiation in more detail.




Activity Title: Microprocessor Simulator with Hardware AcceleratorDescription: The objective of this activity is to develop a commercial product supported by a

company with experience in the field of processor simulation. Instructionsimulators have to meet several goals in order to provide the software developerswith adequate tooling:- logical accuracy, for verification of software code-execution time accuracy, for profiling of software code- near-real time or betterexecution, to facilitate system simulation- user friendliness, to be integrated in thesoftware development tools. In the past, with processors having a computationalpower of 10 to 20 Mips, pure S/W simulation running on powerful workstationwere capable of providing a quasi Real Time simulation of the processor. Withmodern fault tolerant on-board processors providing computational power inexcess of 100 million instructions per second under development by the Agency, itis not longer feasible to simulate in real time a processor in software. A transitionto a mixed hardware and software simulation environment is required. Thechallenging task is still to provide a very high level of accuracy and userfriendliness.

Deliverables: Simulation environment.

Justification for DN: Gaisler Research is one of the most experienced company in the field ofmicroprocessor design for space applications, having developed the lasttwo generations of fault tolerant processors for the European market underESA contracts. The company has a strong internal R&D programme fordeveloping new technologies for both the commercial and the spacemarket, and it is the market leader in the field of software based processorsimulators with their TIM LEON simulator. Its experience is then requiredto successfully accomplish the tasks defined for this activity.



Ref. Number: G605-31EL Budget: 700 K€

Activity Title: Generic Ground Segment for Proba MicrosatellitesDescription: In the frame of PROBA 1, a dedicated automated ground segment has been

developed and installed in the ESA station at Redu. The ground segment is usedboth for spacecraft AIV and for in orbit operations. For the PROBA 2 project, itwas planned to upgrade the ground segment to cope with the new requirementsof the mission and the obsolescence of its components.

The objective of this activity is to extend the scope of the ground segmentdevelopment effort in order to design and build up a multi-mission instead of adedicated ground infrastructure. This infrastructure will be firstly used for PROBA2. It will be designed to be configurable in order to allow the participants to futurePROBA missions to offer turn-key space systems for various applications whichwill include not only the spacecraft but also the associated ground segment. It willcapitalise on the automation features and the lessons learned from PROBA 1integration and almost 3 years of in orbit operations.

The main tasks to be performed are:- To add the environment for operations automation and multi-mission capability tothe available products from ESOC (e.g. SCOS 2000).- To develop the additional elements for the utilization of the ground segment asEGSE (e.g. dedicated interfaces).- To implement the tools for spacecraft data retrieval, distribution and remoteaccess to the ground segment.- To develop, upgrade and procure the elements needed for the ground station forPROBA 2.- To configure and validate the complete ground segment for the PROBA 2mission.

Justification for DN: It is proposed to perform this activity in direct negotiation with VerhaertDesign & Development NV (B) and Spacebel Informatics SA (B) due totheir background and experience on the PROBA 1 mission (Contract no.12700, around 14 Meuro funded by GSTP) in general and therequirements of the PROBA 2 mission in particular (Contract no. 18000,around 14 Meuro funded by GSTP). Moreover, Verhaert is the Primecontractor of the PROBA missions and Spacebel is the on board softwarecontractor on the PROBA missions and has therefore unique knowledge inthe PROBA spacecraft command and control requirements.

Non-competitive tendering is justified according to Article 6.1.a and 6.1.cof the Contracts Regulations.



Activity Title: Kernel for turbine optimisationDescription: A general-purpose optimizer will be developed and aligned to the special needs of

supersonic turbines common in launcher engines such as the Vulcain enginefamily. The first step will be the development. The optimization kernel based onartificial intelligence techniques will be developed along with the communicationprotocol requested for the different existing tools used in the work-chain(pre-processor/solver/post-processor). The optimizer, the work-chain and themethodology need first to be evaluated on typical Vulcain-like turbine bladerequirements (e.g. minimum nozzle length for a certain expansion) and comparedto results obtained with presently used methods (method of characteristics). In asecond step the potential of the methodology can be tested on a limited number ofdesign parameters by focusing on a specific geometrical part e.g. trailing edge forreduced shock losses. The second step will be the demonstration of capabilities.The optimization tool will be tested for multiple design variables describing acomplete turbine blade (e.g. stator) at a typical design point. Also, the genericcharacter of the optimizer into different analytical environments needs to bedemonstrated. The design system capabilities can be extended to a variety ofother turbomachinery blades as well as to multi-point and multi-stageturbomachinery design in a subsequent activity.

Deliverables: General-purpose optimizer tool and design documents.



Activity Title: Advanced Monitoring for a Modern Generic Mission Control System(Extension)

Description: The main objective of this activity is the extension of the ongoing GSTP-3/PECSactivity which shall lead to the selection and demonstration of moderntechnologies and architectures supporting advanced monitoring functions withinground control systems.

An increasing list of ground data systems supporting the mission operationsrequire the usage of reliable and efficient data management functions. The ESOCground data systems are currently undergoing a 're-factoring' process, targeting tothe deployment of a coherent set of applications based on a common set of lowlevel services and software libraries. The risk introduced by this challengingdesign target needs to be mitigated by the execution of demonstration studies,including the currently ongoing GSTP-3/PECS "Advanced Monitoring for a ModernGeneric Mission Control System", for which an extension is proposed.

This GSTP-4 activity proposal covers the GSTP funded part of the proposedextension of the GSTP-3/PECS study "Advanced Monitoring for a Modern GenericMission Control System". The additional GSTP funding is requested in order tocover options 3, 4 and 5 of the existing contract as well as to introduce a newlydefined workpackage (referred to as Option 7 - Data Management Library), furtherdescribed below. The new WP Option 7 shall lead to the development of aquasi-operational S/W library supporting the management of TM/TC andSCOS-2000 packets data. The library shall be designed such to be usablethroughout the ESA Ground Operations Software (EGOS) Ground Data Systemsinfrastructure (including Mission Control Systems, spacecraft models, MCS model,ground equipment models, test-harnesses, etc.). The library shall support allmethods required to process CCSDS TM frames, CCSDS TM packets, EGOS TMpackets, TM parameters, CCSDS TC CLTUs/Frames/Segments/Packets, EGOSTC Packets, TC Parameters, and EGOS Event Packets. The library shall be splitin two parts: a general part (enabling the management of EGOS data units suchas SCOS-2000 packets) and a CCSDS packet specific part (enabling themanagement of CCSDS specific data units).

Examples of general (EGOS) functions to be supported are:

- Encoding/decoding of parameter values into uplink/downlink format, according tothe parameter data types- Calibration/de-calibration of parameter values- Encoding of TM/TC EGOS packets (based on parameter values)- Decoding of TM/TC EGOS packets (parameters extraction).

Examples of CCSDS specific functions to be supported are:

- Encoding/decoding of CCSDS TM/TC packets- Decoding of CCSDS TM Frames (packets extraction, headerextraction/interpretation, CLCW extraction)- Encoding of CCSDS TM Frames- Encoding of CCSDS TC Segment, Frame, CLTU- Decoding of CCSDS CLTUs (extraction of Frames/Segments/Packets).

The defined classes shall provide methods allowing the insertion/extraction of allrelated data, i.e. all EGOS header fields, all CCSDS TM and TC (frame andpacket) header fields, all PUS TM and TC data field header fields, parameterscontained in the packet data field, checksums etc.

The library shall be supported both in C++ and Java. Suitablemechanisms/approaches for ensuring commonality between the two libraries and


minimizing the development/maintenance efforts shall be identified as part of thestudy.

The impacts of adopting the developed library on existing subsystems (e.g. theS2K Packetiser and Telemetry Model) shall be analysed. To carry out these tasksthe activity shall be split among the following phases:

1. Critical analysis of the applicable requirements for the different ground datasystems and definition of the common set of data management functions to besupported by the library

2. Development and validation of a quasi-operational library

3. Analysis of the impact of adopting the developed library in the existing grounddata systems and relevant recommendations.

Deliverables: Technical documentation describing the requirements and design of the DataManagement Library. Source code of the Java and C++ based implementations.

Justification for DN: This activity is the continuation of the work previously done by Siemens inthe ESA contract 18573 (223 K€ funded by GSTP-3 plus 217 K€ by PECSprogramme).



Activity Title: Active Payload AdapterDescription: The final goal of this activity is to achieve active isolation and reduction of the

vibration of satellites and payloads on board Ariane 5 and other launchers.

The feasibility of an active payload adapter for Ariane 5 and other launchers ableto reduce the vibration levels during launch by a factor >4 has been demonstratedby the GSP study "Launcher Payload Dynamic Reduction". This factor ofreduction of the dynamic environment (vibration levels) would imply severalbenefits as the reduction of the structural mass of the payload (a factor around50%), a lower qualification effort and cost, especially in the case of complexscientific instruments, and an increased reliability of the mission. The conceptdeveloped is based on a truss structure with 24 active struts incorporatingpiezo-ceramics. Before starting the development of a full-scale active payloadadapter prototype, an intermediate development step is needed to reduce risksrelated to concept reliability and control robustness, being this the main objectiveof this activity. The following topics shall be addressed:

• Simulation of flexible adapter/payload interfaces, impact of one failed strut, loadover flux verification.• Interaction with GNC system (specifically in what concerns launcher piloting).• Manufacturing and testing of full-scale struts in V-configuration to validatelongitudinal and lateral coupling.• Detail design of overall electrical architecture to guarantee a fail safe design.• Development of a switching type power amplifier.• Electro-mechanical simulation of the V-configuration.

The activity will be split in two phases:

1.- Implementation Phase covering the analysis and design tasks identified above.2.- Manufacturing, Assembly and Test Implementation Phase to validate thedevelopments and simulations identified above.

Deliverables: Reports, breadboard model of power amplifier, 2 full-scale struts.


Ref. Number: G605-41SW Budget: 1,250 K€

Activity Title: Spacecraft Computer Basic Software Development and ValidationDescription: A spacecraft computer provider must in a short time deliver a platform computer

including the basic software. The basic software in general includes all thecomponents which interfaces with the computer hardware like boot-up software,software drivers and operating systems. It also includes test environment and testsoftware to be used by the computer supplier, by the application softwaredeveloper and the platform integrator.

The SAAB-Ericsson Space ERC32 based platform computer, is today astandardised and modular design that can be easily configured to the missionspecific configurations. This development has secured a significantly reduction ofcost and development time of the unit. However, the corresponding modularityand configurability has not yet taken place on the basic software level, whichimplies that this has to be developed for each mission. This often puts the basicsoftware development and qualification on the critical path and also makes theapplication software interface different from one mission to the next. This makesapplication level software re-use difficult.

Deliverables: Source Code, Software Test suite and Documents, according to ECSS-E40B.Basic Software Validation Facility (B-SVF) including simulation models of thecomputer hardware.

Justification for DN: The basic software and computer hardware are normally provided by thesame supplier. The SES S/C computer hardware contains highlyintegrated components as the COCOS and CROME chips. The design ofthe corresponding hardware driver software require intimate knowledge ofthese components, which is only available at SES. This applies equally tothe development of the hardware drivers test suite and test facilities. Thesoftware is highly linked to the corresponding Saab-Ericsson Spacecomputer hardware and shall remain under their IPR.

Additionally the development is based on the experience and re-use ofsoftware from on-going projects. No other contractor has the requiredknowledge and access to the detail hardware design, and even more noother contractor would be able to exploit the accumulated experience ofSES. It is therefore proposed to undertake this activity in DirectNegotiation with Saab-Ericsson Space.




Activity Title: Re-engineering of Data Systems for European Ground Software SystemsDescription: The main objective of this activity is to select 3 main European Data Systems (e.g.

MCS – Monitoring and Control System, FDS – Flight Dynamics System and MPS– Mission Planning System) and adapt them to be compliant with the interfacesdefined in Phase 2 of the European Technology Harmonisation on GroundSoftware Systems, for which the following 3 Phase approach was recommended:

- Phase 1 (funded by TRP) was completed by mid 2005 and its main output wasthe definition of an agreed Reference Architecture for Ground Software Systems.

- Phase 2 (also funded by TRP, currently running and completion planned by early2007) devoted to the establishment of an agreed set of Interfaces between themain Ground Software Data Systems, i.e:

MCS – FDS (Monitoring & Control - Flight Dynamics) FDS – MPS (Flight Dynamics - Mission Planning) MPS – MCS (Mission Planning - Monitoring & Control) Simulation – EGSE (Simulation - Electrical Ground Support Equipment)

- Phase 3 (proposed here under GSTP) will consist of the re-engineering ofexisting European products. It has been realised during Phase 2 that theproposed new interfaces have to be verified by prototyping, as it is the currentbest practice in any standardisation organization (ISO, CCSDS, etc.).

The activities to be carried out under GSTP will consist in the adaptation of 3 mainEuropean Ground Software Data System to be compliant with the proposedinterfaces. The Data Systems are as follows:

Monitoring & Control System Flight Dynamics System Mission Planning System

Each of these Systems should belong to a different entity in order to guaranteethe interoperability of these systems at European level (that today has not beenachieved). The main objective will be to verify the proposed interfaces and to raiseany problem / inconsistency discovered in the Interfaces. Operational scenarioswith an agreed set of normal operations will be used to test all data structures ofeach interface. Such approach will also improve the final re-engineering of theselected products. In detail, the tasks to be performed will include:

1.- Selection of 3 main European Ground Software Data Systems2.- Adaptation of the Flight Dynamics System to be compliant with proposedinterfaces (outcome of Phase 2 above)3.- Adaptation of the Mission Planning System to be compliant with proposedinterfaces (outcome of Phase 2 above)4.- Adaptation of the M&C System to be compliant with proposed interfaces(outcome of Phase 2 above)5.- Integration of the three Data System according to the operational scenarios6.- Execution of a set of agreed operations to verify the validity of the interfaces7.- Analysis of the results and recommendations of I/F modifications

Deliverables: 1. TN with trade-offs for Data System selection, operational scenario for testing,prototype integration activities and main changes to the Data Systems selected; 2.Modified MCS; 3. Modified MPS; 4. Modified FDS; 5. Prototype; 6. Interfaceverification report and set of recommendations; 7. Final Report.



Activity Title: DTL/DML based Mission Control System (MCS) DemonstratorDescription: In the GSTP activity "Advanced Monitoring Extension", as part of the advanced

monitoring for a modern generic Mission Control System (MCS), generic librariescovering the management and transfer of TM/TC data are being developed.These libraries have been designed such to be usable within all ground datasystem applications i.e. without introducing any specific assumption about thenature/purpose of the application nor about its run-time environment. Thisapproach constitutes a significant change of the existing implementations ofground data systems which are all based on targeted specific implementations(with a significant amount of duplications...). The suitability of these libraries foradoption within operational systems needs to be demonstrated. This is thepurpose of the new proposed activity.

The objective of this new activity is to verify the new EGOS (ESA GroundOperations S/W) libraries, namely DTL (Data Transfer Library) and DML (DataManagement Library), within a mission control system. In addition, the telemetryreception and distribution chain of SCOS-2000 will be re-engineered adoptingthese libraries.

The main benefits for ESA of developing this new architecture is that the newserver components, based on the EGOS architecture, will not be depending onthe SCOS-2000 libraries. This allows the usage of the server components not onlywithin a mission control system but also within other components of the groundsegment. In addition, a more flexible concept for cascading data distributors willbe implemented. The specific distribution concept implemented by the centralisedpacket distributor server and the client packet distributor (CPD) will be replaced bya single distributor implementation. It will also include SCOS-2000 clientapplications that can operate with the new EGOS servers.

It is expected that the new architecture developed in this activity will bringincreased flexibility. It allows to use the telemetry chain, both inside ofSCOS-2000 and outside of SCOS-2000 on all locations in the ground segmentwhere the EGOS infrastructure is present. It will in any case increase the flexibilityfor distributing telemetry data in the ground segment. In particular, the followingapplications will be affected/delivered: Telemetry Receiver and Packetiser;Telemetry Live Data Distributor; Telemetry Archive Reader/Writer APIs,compatible to the existing SCOS-2000 applications supporting the management ofarchived data; and Telemetry Packet Client Reception Library.

Finally, the new telemetry chain will be compared against the existing SCOS-2000telemetry chain regarding performance and maintainability. The end-to-end test ofthe telemetry chain will be performed with the automated testing framework "ART"(Automated Regression Testing).

The total budget for this activity (550 K€) is proposed to be covered by GSTP-4(300 K€) and PECS (250 K€, PECS for Czech Republic).

Deliverables: Software package including CVS-Repository with new implementedEGOS-servers and modified SCOS-2000 telemetry clients; Documentation andtechnical notes, including the software requirements specification, the architecturedesign, and the validation and testing reports.


Justification for DN: This activity is a continuation of the work already done under ESA contract18573, "Advanced Monitoring for a Modern Generic Mission ControlSystem" (funded by GSTP-3 and GSTP-4 with 827 K€ and PECS with 489K€). It is recommended to continue the development with the sameindustrial team, Siemens (A) as prime, and ANF-DATA (funded by theCzech PECS Programme).

Non-competitive tendering is justified according to Article 6.1, c) of theContract Regulations.


Theme 7.- PILOT PROJECTS

Ref. Number: G703-01PT Budget: 150 K€

Activity Title: Support to Space Technology Transfer FinlandDescription: This activity aims at continuing the current STTF (Space Technology Transfer

Finland) project, that has been running successfully for several years under theaegis of TEKES. Examples of recent projects implemented under the STTFinclude StarDriver, StarTiger and Avali. The objective now is to actively transferspace technologies to non-space sectors in Finland which would benefit theFinnish economy, spur industrial growth and society in general. The followingspecific tasks are intended to be done in the frame of this activity:

- Ascertain what technologies the Finnish space sector is working on- Ascertain what are the technological requirements of Finnish companies indifferent sectors- Identify space technologies which could be transferred to such Finnish industries- Assist in affecting such transfers

Justification for DN: Turku Science Park Ltd (FIN) is currently the only company with therequired experience to carry out the tasks of this activity as it hasexperience of several years working for the Space Technology TransferFinland project under the aegis of TEKES and the ESA TechnologyTransfer Programme.



Activity Title: Symbiotic Sphere – an Interactive Space Station Communication InterfaceDescription:

Deliverables: High fidelity mock-up; systems breadboard and test results; technologydemonstrator; design documentation (incl. interface requirements document); testand validation plans; progress reports and executive summary; In order to start asubsequent phase C/D and E: Report identifying a realistic flight opportunity andjustification for continuation of the further activities, detailed Exploitation Plan,Phase C/D plan (incl. Strategic review of phase B results); QA and safety plan andcosting.

Justification for DN: This activity is the continuation of the work initiated by the proposedcontractor, Space Synapse Ltd., in the ESA contract 17515 (40 K€ fundedby GSP).


Special Projects



Activity Title: Definition of the VEGA-1 Payload (Step 1)Description: Vega is one of the elements of the European family of launchers that includes also

Ariane and Soyuz from Kourou. This family of launchers will provide Europeanaccess to space for a wide range of missions. The qualification flight of Vega isplanned for end 2007. Vega will be competing in a market so far dominated bylaunchers derived from ballistic missiles and therefore developed, includinginfrastructure, to a large extent by military budgets.

For Vega to succeed it is necessary to demonstrate from the beginning its quality,performance and more gentle environment to payloads. In parallel, it is necessaryto continue improving the technical solutions so as to reduce cost and enhanceperformance by using satellite navigation systems for guidance, navigation andcontrol, and data relay satelliltes for communications with ground.

This is a continuous effort and has a major milestone with the Vega qualificationflight. The following objectives are therefore identified:

1. Demonstration of the environment offered to payloads during launch2. Demonstration of the potential of utilisation of global navigation satellitesystems for launcher GNC3. Utilisation of data relay satellite for communications with the launcher

In addition, the flight can be used as an opportunity for technology demonstrationand education experiments. It is to be noted that objectives 2 and 3 above arealso related to Ariane in the proposed ACEP programme and possibly Soyuz. Theresults of the demonstrations carried out in the Vega-1 flight are therefore of usebeyond the Vega launcher.

To achieve these objectives it is necessary to develop a suitable payload,composed of an appropriate carrier and the required experiments, collect andexploit the data and analyse the results. In the current flight concept the payloadwill be launched to a sun-synchronous orbit of 400 Km altitude and will consist ofa carrier and experiments. The carrier is a copy of the structure of theADM-Aeolus platform with complementary dummy mass to complete the VEGAcapability. The electrical systems are based on the avionics of PROBA-2 to limitthe costs. The experiments will provide the data required to meet the objectives.This type of orbit and payload is very representative of a line of VEGA missions.

It is proposed to do the development in two steps, a first step devoted to theconsolidation of the design and a second step devoted to the actual development,manufacturing, test and integration in the launcher and support to the launch. Thepresent activity is concerned with step 1 and shall be devoted to:

- The consolidation of the concept of the Vega-1 qualification flight, including:- The analysis of the mission objectives and requirements- The consolidation of the mission analysis and establishment of the operationtimeline- The consolidation of the payload concept and its design so as to enable start ofprocurement in step 2- The establishment of the interface requirements documents for the experiments- The establishment of development plans and cost estimates

It is proposed to carry out this activity in four months split in two parts. The firstpart of three months will end with a mid-term recapitulation point at which theexperiment complement will be frozen and the payload and mission conceptoutlined. The second part will be devoted to the detailed definition of the missionand payload and the establishment of the development plan.


Deliverables: Vega-1 Payload requirements document; Vega-1 mission and operations analysisreport; Carrier concept and analysis and definition reports; Experiment InterfaceRequirements Document (EIRD); Development plan; Cost estimates.

Justification for DN: CONTRAVES has designed and built the AEOLUS platform satellitestructure, which is planned to be launched by VEGA. Therefore, it hasbeen decided to use an identical structure on the VEGA maiden flight inorder to obtain a more realistic characterization of the VEGA launchenvironment. As this contract deals with a recurrent build, saving the initialdevelopment cost, it is highly recommended to use the experience gainedby Contraves to produce a duplicate of the AEOLUS main structure. Onthe other hand, Verhaert is developing the ADPMS (advanced data andpower management system) for PROBA-2. As the existing system designfulfills the requirements of VEGA-1, it has been decided to use theexperience of Verhaert to produce a copy of the PROBA-2 data and powerhandling subsystem.


This activity will be coordinated with the Directorate of Launchers. Step 2will follow under joint action of D/TEC and D/LAU.

Ref. Number: G703-05SY Budget: 400 K€

Activity Title: Application domain of the PROBA platformDescription: ESA and Belgian space industry have acquired significant expertise and

development means in the field of micro-satellite systems and their components,in particular within context of the GSTP program (PROBA 1 and PROBA 2). Onthe other side, there are today numerous opportunities to develop commercialmissions using the PROBA platform.

The activity shall identify the constraints related to the customisation of thePROBA 2 platform in the context of potential target missions. It will study variousmission and investigate their feasibilities with the PROBA platform. Alternatives interms of platform system and subsystem design and component selection will beidentified based on the requirements of the new mission and the lessons learned(technical and programmatic) from the on going PROBA 2 project.

The assessment will start with the identification of the SWOT of the PROBA 2platform for possible mission scenarios. The list of adaptations required byspecific missions and the list of critical items will be established and appropriatedevelopment/procurement approach will be defined. Constraints related to theprocurement of subsystem/ components with unique source, limited accessresulting from cost aspects or ITAR rules will also be included in this review. Thestudy will then proceed with the assessment of alternative solutions.

Deliverables: Study Report.

Justification for DN: Verhaert has developed the PROBA platform. A consortiumVerhaert/Spacebel has been created with the objective to commercialisethe PROBA platform.



Ref. Number: G703-06SY Budget: 1,600 K€

Activity Title: Development, qualification, and flight manufacturing of the Cryomagnet SelfProtection (CSP) electronics for the Alpha Magnetic Spectrometer (AMS)

Description: The Alpha Magnetic Spectrometer (AMS-02) is a large particle physics detector tobe installed in the International Space Station. Its purpose is to perform accurate,long duration measurements of energetic primary charged cosmic ray spectra (upto multi-TeV) in order to search in space for dark matter, missing matter andantimatter.

The instrument is composed of several subdetectors, built by an internationalcollaboration with significant European participation (from Italy, UK, Germany,Spain, France, Switzerland, Denmark, Portugal, Netherlands, Finland andRomania). The collaboration also counts with relevant contributions from the USA,China, Taiwan, Russia, Korea, and Mexico. NASA will provide the shuttle flight toinstall AMS-02 in the ISS, with mission management at Johnson Space Center.

The AMS contains the following main components:

• Transition Radiation Detector (TRD)• Time of Flight (TOF) hodoscopes• Superconducting magnet• Silicon tracker• Veto, or ainticoincidence counter (ACC)• Ring Imaging Cerenkov Counter (RICH)• 3-D Sampling Calorimeter (ECAL)

A principal and essential element of the AMS-02 is a massive cryogenicsuperconducting magnet. Its function is to extend the energy range of the AMSmeasurements of particles and nuclei to the multi-TeV region.

The magnet system consists of superconducting coils, a superfluid helium vesseland cryogenic system, all enclosed in a vacuum tank. Outside of the vacuum tankare supporting electronics, located in the Cryomagnet Avionics Box (CAB), valvesand cabling. Operating at a temperature of 1.8 K, the magnet will provide a fluxdensity of 0.86 T at the geometric center of the system of the system.

CIEMAT – National Centre for Energy, Environment and Technological Research- leads the Spanish contribution to the AMS that includes the full responsibility forthe RICH subdetector, already undergoing qualification tests, and for majorelements of the Cryomagnet electronics (by CRISA, under contract with CIEMAT)that shall be placed inside the CAB, and are at different development status asdetailed below:

• For the Cryomagnet Current Source (CCS) - electronics used to charge themagnet - a fully representative Engineering Model of the flight CCS has beensuccessfully tested both at maximum current (460 Amps) with a resistive load, andalso up to 360 Amps with an inductive load provided by a magnet of 0.5 Henriesavailable in the CEDEX facilities in Madrid. This EM will be tested with theAMS-02 cryogenic magnet once its construction is completed in third quarter of2007.

• The Cryomagnet Control and Signal Conditioning (CCSP) is designed, and flightrepresentative EM boards are in various stages of manufacturing and/or testing atboard level

• The Cryomagnet Self Protection (CSP) subsystem – subject of the presentprocurement - is in charge of detecting and protecting the magnet in case of aquench or loss of power or communications. A complete preliminary design existsfor all boards, but is being updated to newly issued requirements originated by the


Magnet.

The CSP subsystem contains two elements that are critical to the safe operationof the magnet in orbit: the Quench Detection function and the Current LeadMonitoring function. This first must monitor voltages in the racetrack coils anddipoles of the magnet to detect the onset of a quench, while the later will detect aquench by monitoring voltages and temperatures in a set of current leads locatedinside the magnet.

The CSP also contains the control electronics for the Run-Down andAfter-Quench sequences, the Quench Heater drivers, and the control electronicsto govern the cool-down thermomechanical pump, valves, and heaters of themagnet.

The CSP shall detect the onset of the magnet Quench and switch on the Quenchheaters within 50 ms of the first detection. The quench detection system shall beactive during steady state operation, current ramp-up and current ramp-down, andis supported by a UPS (Un-interrupted Power Supply) subsystem to power criticalcomponents of the CSP in the event of loss of main supply power.

The CSP subsystem will be physically composed of several electronic boards tobe integrated in the AMS-02 Cryomagnet Avionics Box (CAB). The followingmodules will hence be designed and manufactured (Flight Model) under the scopeof the present activity:

1. Magnet Detector module2. Magnet Detector Converter module3. Current Lead Detector module4. Current Lead Detector Converter module5. CSP Power Drivers module6. CSP TM/TC module

Deliverables: CRISA to deliver to CIEMAT: 1. Electrical design, PCB layout, Mechanical design;2. Design analyses; 3. Magnet Detector EM Board; 4. Magnet Detector ConverterEM Board; 5. Current Lead Detector EM Board; 6. Current Lead Det. ConverterEM Board; 7. CSP Power Drivers EM Board; 8. CSP TM/TC EM Board; 9. MagnetDetector FM Board; 10. Magnet Detector Converter FM Board; 11. Current LeadDetector FM Board; 12. Current Lead Det. Converter FM Board; 13. CSP PowerDrivers FM Board; 14. CSP TM/TC FM Board; 15. Technical Documentation.

Justification for DN: Taking into account CRISA’s long term participation in the AMS-02programme, particularly in the definition, architecture, and design of theelectronics subsystems of the AMS-02 cryogenic magnet, and the need tointegrate the Cryomagnet Self Protection (CSP) subsystem with theCryomagnet Current Source (CCS) already developed by CRISA, and withother subsystems also under development by CRISA into a single physicalequipment (the CAB), it is proposed to carry out the CSP developmentwith this company.

For the implementation of this activity, an agreement has to be signedbetween CDTI, ESA and contractors involved, on the roles andresponsabilities of each of the parties.

Non-competitive tendering is justified according to Article 6.1 a) of theContracts Regulation.

Ref. Number: G703-07ST Budget: 500 K€

Activity Title: National Technology Transfer Initiative (NTTI)Description: The objective of the National Technology Transfer Initiative, (NTTI) is to provide

the opportunity for Member States to tailor specific technology transfer activities


according to local industry and competencies. The Initiative will focus on localgoals whilst maintaining opportunities for international collaboration on technologytransfer activities. It will act as an extension to the existing general technologytransfer service provided by the ESA Technology Transfer Programme Office(TTPO). Since it aims to strengthen technology transfer on a national level theNTTI will be funded through dedicated GSTP contributions made by Memberstates wishing to take part (GSTP contributions will be allocated specifically for theNTTIs, offering more flexibility on the emphasis a Member State wants to give toTechnology Transfer in their region).

The management of the NTTI will be performed jointly by a national entityselected to coordinate activities, ESA TTPO and a steering committee. Thenational entity will be selected under an open competition carried out by ESA andaccording to applicable ESA rules. The steering committee will consist ofrepresentatives from local businesses, industry and research institutions. Thesteering committee’s purpose is to focus activities on market demand and projectsthat are likely to receive interest from sectors of the national business community.

The National Technology Transfer Initiatives will operate in conjunction with theTechnology Transfer Network (TTN) thus enabling full participation in TTNactivities. This maintains access to international cooperation for technologytransfer and knowledge exchange. In this way NTTIs act locally and yet at thesame time contribute to the strengthening of European Industry as a whole.

The basic tasks to be performed under the NTTI are threefold: Technology Push,Market Pull, Transfer Implementation and Promotion:

1. Technology Push• Create a portfolio of space technologies developed in the Member State.• Add this portfolio to the general TTPO technology database. 2. Market Pull•Create a portfolio of technology needs from non-space entities in the MemberState.• Match these needs with entries in the general TTPO database. 3. Transfer Implementation• Select technology transfer activities suitable for funding under the advice of thesteering committee. Utilize the expertise of national entities for specific projectsrelevant to the competences and interests of the country, this could involvecooperation with national science and technology polices where extra funding maybe granted.

4. Promotion• Increase the awareness of space developed technologies in the industrial andacademic environment and promote the space technology pool in the countrytowards non-space sectors at suitable fairs and exhibitions (in particular a one daydedicated event), by press releases in various media, by dedicated brochures andflyers and via a maintained Web site.

Deliverables: • Yearly report of all performed activities.• A yearly one day network event in the country organised in conjunction with theESA TTPO. This event should promote technology transfer in the country andshould give the shareholder and customer groups (such as space and non-spacecompanies, SMEs, universities, incubation centres, venture capital companies,etc.) the opportunity to network.• A portfolio of space technologies which can be included in the general TTPOtechnology database.• A portfolio of technology requests which can be included in the general TTPOtechnology database.• A developed and maintained Web site in local languages as well as English to


promote and give a wider awareness of technology transfer in the country.• A model, mock-up or prototype resulting from a successful transfer should besupplied if practicable with supporting documentation and video footage of thetechnology in operation. Such items will be retained by TTPO for display atexhibitions, fairs and other events. Additional funding may be forthcoming for suchproducts.