EUROPEAN SPACE AGENCY INDUSTRIAL POLICY … · INDUSTRIAL POLICY COMMITTEE GENERAL SUPPORT...

ESA/IPC(2008)89 Att.: Annexes Paris, 15th September 2008 (English only)

EUROPEAN SPACE AGENCY INDUSTRIAL POLICY COMMITTEE

GENERAL SUPPORT TECHNOLOGY PROGRAMME – PHASE 5

PRELIMINARY SELECTION OF ACTIVITIES ELEMENT 1

SUMMARY This document presents an overview of the Preliminary Selection of activities for the Element 1 of GSTP-5. This Preliminary Selection will be the basis for the establishment of the Work Plan for GSTP-5 Element 1. REQUIRED ACTIONS Delegations are invited to take note of the Preliminary Selection of activities proposed.

eCPB-2008-0535

ANNEX I

List of the proposed Activities

ANNEX I: ACTIVITIES GSTP-5 - ELEMENT 1. Preliminary Selection

ESA/IPC(2008)89Annex 1. Page 1

GSTP Id Title Budget (K€)

G511-001MM Vanadium dioxide High-resolution Uncooled Bolometer Array 1,000G511-002EE X/Ka band data transmission antenna qualification model 750G511-003EE Airborne demonstrator for combined CIWSIR/GOMAS 2,000G511-004EE Light weight, very stable rotating reflector antenna 500G511-005ET On-Wafer Measurements to 300 GHz 450G511-006GN Phase centre calibration of GNSS antennas in LEO 250G511-007ET High-power W-band LO source 950G511-008ET Integrated Tile Demonstartor 3,000G511-009EE Low mass Calibration load demonstrator 500G511-010EE Very large space antenna aperture - demonstration model 2,000G511-011EE Multi Frequency high resolution GEO-sounder Demonstrator 2,000

G511-012EE Large aperture, ultra-stable, push-broom antenna withfrequency-multiplexed beams 1,000

G511-013EE Cross Correlator ASIC development 650

G511-014QC Reliability study and space evaluation of European planar Schottkydiode 350

G511-015MM Nd doped GSAG mixed Garnet crystal enhancement for applicationsin Space Waves 500

G511-016MM High power narrowband lasers for laser cooling applications in AtomInterferometry 350

G511-017MM Monolithic filter on detector dye integration technologies 500

G511-018ET EES Ka band High Data Rate Payload Data Transmitter EngineeringModel 1,500

G511-019GI Parallel computing for fast TM processing during short passes 150G511-020ET Membrane circuits for high frequencies 400

G511-021GR Preparation of an advanced standalone error prediction module forSAR interferometry (PEPSI). 200

G511-022GR Automated Service Builder for Semantic Service OrientedArchitectures (ASB) 400

G511-023GR Automatic, Semantic Image Information Mining from Time Series ofVHR images (ASIM) 200

G511-024GR Decision Support and Real Time EO Data Mangement (DREAM) 2,500

G511-025GR The EO Image Librarian: EO image and geoinformation intelligencesearch engine (EOLib) 2,000

G511-026GR European Service Support Environment Enhancements (ESE) 2,000

G511-027GR New Sensors Study for Soil Mapper Application and SSE Integration(NSS) 150

G511-028GF Open-standard Online Observation Service (O3S) 500G511-029GF Ontology Based EO Search (OBEOS) 320G511-030GR Rapid Response Support Server (RARE) 720

THEME 1.- EARTH OBSERVATION




G512-001MM B-BOLD (BOLD continuation) 1,000

THEME 2.- SCIENCES




G513-001MM Micro laser beam scanner 600

G513-002MC Investigation on microcompounds in MELiSSA - PHASE2(BELISSIMA2) 1,500

G513-003MC Water Network Corrosion 250

G513-004MC Preliminary estimation of energy balance of a closed life supportsystem - Application to MEliSSA 250

G513-005MC Process Aeration Device 250G513-006MM Biochemical Analyser Technology (BIOCAT) 350G513-007MM A self standing bioreactor for biological samples 300G513-008MM Respiratory Sensor System - Optimisation and Combination 200G513-009MM MEMS based Gas Chromatograph/Mass Spectrometer 500G513-010MM In-Vivo embolic detector 200G513-011MM Enhanced Autonomous Cultivation System 350G513-012MM Enhanced Virtual Reality Stimulator 600G513-013MM Tactile Training 250G513-014MM Bone and Muscle Modelling 350G513-015MM High-precision Implantable Intra-arterial Drug Delivery Device 600G513-016MM 3D Bioreactor 300

G513-017MM Blood pressure, flow and temperature sensor inserted via a vascularstent 400

G513-018MM Diagnostics for Nucleation Detection 350G513-019MM Nanowire Biosensor 250G513-020MM Compact - 80ºC Freezer 500G513-021MM Rover performance prediction and evaluation tools 500G513-022MM Guided Mole II 300

G513-023EP Development of a Lithium ion cell optimized for low temperatures(-20°C ) 400

G513-024SW Authoring environment for interactive 3D procedures 300G513-025EC One-axis inertial MEMS sensor development 1,900G513-026MC Development of Thermal Insulation for Planetary Landers and Rovers 350

G513-027MC Mechanically Pumped Heat Transport Loop for Planetary Landers andRovers 400

G513-028ET Lander Miniaturised proximity-1 communication package -Engineering Model 1,000

G513-029MM Detector arrays for Imaging Lidar systems 800G513-030SW Autonomous and remote operations reference facility for robotics 600

G513-031ET Orbiter Software Defined Radio Proximity-1 Link Communicationspackage - engineering model 1,000

G513-032ET Lander Compact Dual UHF/X-band Frequency Communicationpackage - Engineering Model 1,000

G513-033MC Additional Unit for Increased Water Loop Closure 500G513-034MC Air Sampler Unit 450G513-035MC Determination of Biomass in Complex Bioprocesses 400

THEME 3.- HUMAN SPACEFLIGHT AND EXPLORATIONPREPARATION



G513-036MC Development of Methane Recovery Assembly 400G513-037MC Feasibilty Study for Manned BIORAT Campaign 150G513-038MC High Performance Pressurized Structure 400G513-039MC Higher Plant Canopy Evaluation 450G513-040MC Inflatable Container for Life Support Waste Water 450G513-041MC MELiSSA Pilot Plant 1,500G513-042MC Plant Stress Detection Unit 550G513-043MC Waste Preparation Unit 600G513-044MC Wet Oxidation Unit 600

G513-045 MELISSA Space Adaption Phase 3: Moon base Life support 300G513-046MC MELISSA Genetic charcaterisation Phase 3 550G513-047MC Axenicity control within MELISSA compartment 2 and IV a 450G513-048MC Recycling of tissues and packaging wastes phase 1 450




G514-001MP E-VEGA Electric Propulsion Service Module technologies preparation. 4,800G514-002ED Safety oriented reference architectures for man tended systems 1,000

G514-003MC Delta-Development of SEPCORE based Heatshield for Earth EntryCapsule of Sample Return Missions 500

G514-004MC Development of Secondary Protections for Hot Structures 250G514-005MP Enhancement of Plasmatron operating capabilities 700G514-006MP Prediction methods for propellant management devices 1,500G514-007MP ESPSS: European Space Propulsion System Simulation 500G514-008MP Kinetic shock tube for radiation data base for planetary exploration 2,000G514-009EC Fault Tolerant Flight Control System Components 600G514-010MC Methodology for analysis/test correlations of an SRM 300G514-011MP Aerodynamics of decelerators : parachutes and ballutes 250

THEME 4.- SPACE TRANSPORTATION AND RE-ENTRYTECHNOLOGIES




G516-01MM Photonic micro-navigator for microsatellites 600G516-02GN GNSS processing strategies for LEO constellations 300G516-03GN Improved radiation modelling for GNSS satellites 400

THEME 6.- NAVIGATION




G517-001MM Voice Coil Motor Qualification Model 150G517-002MM Piezo new sources materials, piezoceramics motor qualification 400G517-003MM Compact Magnetic Bearing for High-Speed Rotor 150G517-004MM Advance material for ball bearings 300G517-005MM Bimorph adaptive large optical mirror demonstrator 1,000G517-005MM Diamond turning of Aluminium alloys for aspheric optics 400G517-006MM Multi wafer hybrid integration: Robotics IMU II 500G517-007MM Testbed For Telemanipulated Satellite Servicing 600G517-008MM Virtual testbed 400G517-009MM Haptic Control 1,500G517-010MM Ground Control Station For Autonomy 600G517-011SW Automatic testing improvement 300G517-012SW Customisation of the ASSERT Framework to industrial environment 200G517-013SW On Board operating system Upgrade for Leon 300G517-014SW Qualification of xLuna operating system 300

G517-015EE Implementation and Demonstration of RF testing approaches forreduced antenna/payload AIT/AIV 750

G517-016EE Implementation and Demonstration of EMI/EMC approaches for fulldevelopment cycle support and reduced AIT/AIV. 500

G517-017EC Reaction Wheel Drive Electronics Improvements 700G517-018EC Low cost, portable sensor GSE 350G517-019SW Industrialisation of the HW-SW Codesign toolset. 500G517-020ED SpW RTC Software Library and Tools 300G517-021ED TOPNET 2nd Generation 500G517-022EP Constant Power charging of Li ion batteries for LEO missions 200G517-023QM ADHESIVE TAPE FOR HIGH POWER LASER INSTRUMENTS 300G517-024QM Joining of composites materials 300G517-025QM Crimping of thermally stable structures with Shape memory rings 200G517-026QM Light weight steel structures 250G517-027QM Development of electroless Silver platting on Ni/Cu coated substrates. 200G517-028QM Processing of Al-Mg-Sc high strength alloys. 400G517-029QM Development and characterisation of Titanium alloy hollow-spheres. 250

G517-030QM Development and characterisation of advanced metal matrixcomposites. 250

G517-031QM Validation testing of Glare 1 to space qualification levels 200G517-032QC Polymer Tantalum capacitor (very low ESR) 400G517-033QC Definition of displacement damage test guidelines for bipolar devices 350

G517-034QC Evaluation of worst case condition for the Single Event Effect test ofpower MOSFET 300

G517-035SW Java on-board software implementation, case study 450G517-036SW Establishment of model reference library 350G517-037SW Adaptation and Demonstration of MBSE for a real project 2,000

THEME 7.- GENERIC TECHNOLOGIES AND TECHNIQUES



G517-038SW System Architecture modelling tool 400G517-039SW System of Systems design environment 750G517-040SW End-to-end performance simulation framework 500

G517-041SY Development and validation of a generic System of SystemsConcurrent Engineering Model 600

G517-042EC European IMU for EDLS, RDV and sample return missions 2,500

G517-043EP Process optimization & pre-qualification activities for multi-junctioncells on thin germanium substrates 400

G517-044EC HAS Active Pixel Sensor detailed annealing behaviour investigation 200G517-045EC Extension of the Mathematical NLP-solver 200

G517-046ED Highly Available COTS based computer, Step2 (Prototyping andvalidation) 800

G517-047ED High Performance COTS based computer step2 (Prototyping andvalidation) 800

G517-048ED High Reliability COTS based computer step2 (Prototyping andvalidation) 800

G517-049QM Upscaling of ultra-stable bonding process of ultra-stable materials 750

G517-050QC Establishment of a commercial GaN epitaxial production facility inEurope 2,000

G517-051QC GREAT - Validation of space compatible GaN foundry process 1,000G517-052QC Improved quality large diameter SiC substrates 2,000

G517-053QCCharacterization and reliability assessment of RF MEMS switchesand switching matrix built on LTCC (Low Temperature CofiredCeramic)

300

G517-054QC Demonstration of the ESCC Assembly & Test House (ATH) CapabilityApproval approach for EEE components. 500

G517-055QC IESD effects on glob-top assemblies 300G517-056SW Verification of operational concepts for human-robot interaction 800

G517-057QC Reliability assessment of a MEMS-based isolation valve forpropulsion systems 250

G517-058QM Nano-hybrid transparent materials 400

G517-059QM RTM processing of novel high temperature high radiation resistantresin 300

G517-060SW Data Modelling using ASN.1 300G517-061SW Dynamic Translation based on-board processor emulator 350

G517-062SW On-Board Computer Simulator architectures and I/F to system testbenches 350

G517-063SW Automatic generation of database applications from a domainontology 750

G517-064TC Virtual Reality for AIV 320G517-065MC Automated layup of Thermoplastic Composites for space applications 500G517-066MC CAD Based Modelling for Space Thermal Analysis 150G517-067EE ESD transients monitor 500G517-068MP Low cost PED propellant tank 600G517-069MC Medium-Power Loop Heat Pipe 200G517-070MC Multistable Composite Structures 250G517-071MC New Concepts for Advanced Structural Sandwich Panels 350G517-072MP Very Low Earth Orbit Satellite (V-LEO) - AERO-THERMODYNAMICS 300



G517-073MP Very Low Earth Orbit Satellite (V-LEO) - Electric PropulsionSubsystem 800

G517-074MP Very Low Earth Orbit Satellite (V-LEO) - Mission Analysis and Design 500G517-075GS Ka-band klystron power amplifier prototype 750G517-076GS Improved Autotrack and search performance for ESTRACK Antennas 300G517-077GS Holography System for Deep Space Antennas 500G517-078GS High Accuracy Reflector Panel 300

G517-079GS Development of an RF test bed for high power testing of groundstation feed systems. 300

G517-080GS Demonstration of simultaneous transmission and reception of data inKa-Band 500

G517-081GI Ground-Station Automation and Off-line operations 300G517-082GI Combinatorial Optimization for Scheduling Applications 400

G517-083GI Integrated development and validation environment for operationsautomation 400

G517-084GI Ubiquitous alert and operations monitoring system 400

G517-085HS Integrated Monitoring & Diagnostic of End-to-End CommunicationLink 350

G517-086GS Deep space receiver for support during superior solar conjunctions 300

ANNEX II

Detailed Descriptions of the Activities

Annex 2. Page 1

ANNEX 2: DESCRIPTIONS ACTIVITIES GSTP-5 - ELEMENT 1. Preliminary Selection

ESA/IPC(2008)89

THEME 1.- EARTH OBSERVATION

Ref. Number: G511-001MM Budget: 1,000 K€Activity Title: Vanadium dioxide High-resolution Uncooled Bolometer ArrayObjectives: Development of a 2-D uncooled detector array of high performances (high spatial

and thermal resolution) breadboard to a higher maturity level (~EQM) targetingthe concrete needs of the selected mission at that time

Description: It had been repeatedly demonstrated that VO2 / VOX as the resistive materialhas superior characteristics to any other presently used thermal sensing elementsuitable for an imaging array (especially w.r.t. 1/f noise). Exploiting the ultimateperformance capability of uncooled imagers will allow several missions to adoptthis technology rather than having to resort to expensive andressources-extensive cryogenic photon detectors. There is no European source ofsuch technology, until the recent close collaboration between XenICs (B) for theROIC and INO (CND), the Canadian manufacturer of VO2 / VOX micro-bolometerdetectors. In view of this consortium, it is of extremely high interest to develop adetector for space, taking advantage of the consortium's business plan to providedevices for airborne and terrestrial markets.

Deliverables: Full-scale breadboard of EQM maturityApplication:Current TRL: 3 Target TRL: 5 Duration: 24 MonthsRef ESTER: T-344, T-325, T-367,

T-396, T-357, T-7886,HarmonizationDossier:

Opt. Instruments -D1-

Ref. Number: G511-002EE Budget: 750 K€Activity Title: X/Ka band data transmission antenna qualification modelObjectives: The objective is to realise a Prequalification of an X/Ka band AntennaDescription: Data volumes to be transmitted for scientific missions are large and rationalisation

of the links is appropriate, with more orbiters around the planet. Earth basedstations have the complete planet inclusive all orbiters potentially in their mainbeam. Consequently a High Gain Antenna is needed and a preparation for that isrecommended. With knowledge in house (Cassini antenna, a 4 m antenna madein Europe for Nasa is 10 years old) and progress in technology an X - Ka bandantenna is proposed for development by ESA. A pre qualification model for anX-Ka band antenna is to be realised in this activity

Deliverables: Prequal Model X-Ka band antennaApplication: Next Interplanetary Satellite ProgramCurrent TRL: 3 Target TRL: 6 Duration: 18 MonthsRef ESTER: Harmonization

Dossier:

Ref. Number: G511-003EE Budget: 2,000 K€Activity Title: Airborne demonstrator for combined CIWSIR/GOMAS



Objectives: The objective of this activity is to implement the combined CIWSIR/GOMASsounder instruments and demonstrate with an airplane campaign the validity ofthe concept.

Description: The present study deals with the implementation and flight of the (sub)mm waveinstrument on-board of an airplane. The follwoing tasks are included:a) consolidation and adoption of instrument requirements for an airplane;b) identification of potential instrument platforms;c) identification of potential partners/cooperation approaches;d) detailed assessment of instrument accommodation and interface requirementson selected platforms;e) instrument update;f) definition of algorithms for instrument performance verifications;g) performance consolidation of the selected design on the selected platform;h) design, development and ground testing of the airborne demonstrator;i) flight campaign.

Deliverables: Airborne demonstratorApplication: Gomas \ CIWSIR, GEO-sounder. Specifically for Numerical weather prediction

and Nowcasting (very short term weather forcasting)Current TRL: 3 Target TRL: 4 Duration: 24 MonthsRef ESTER: T-8206 Harmonization

Dossier:Technologies for (sub) millimeter wavepassive instruments - 2006

Ref. Number: G511-004EE Budget: 500 K€Activity Title: Light weight, very stable rotating reflector antennaObjectives: One of the identified radiometer concepts for Post-EPS missions is the

millimetre-wave cross-track scanner. Because of the demanding horizontalresolutions, especially at low millimetre-wave frequencies, and the 90-deg off-setangle (simple scanning geometry), relatively large reflector antennas are needed(around 1m). A large and heavy reflector together with a 10-years missionrequirement puts a too high stress on the scan mechanism. If we want to reducethe risks of a scan mechanism failure it is clear that light-weight reflectortechnologies are needed, which can provide sufficient stability at nearsubmillimetre-wave frequencies. This objective of this activity is to demonstrate a low mass 1-m class reflectors formillimetre-wave and near submillimetre-wave frequencies.

Description: The application is a cross-track scanner for LEO Earth Observation mission(Post-EPS), using frequencies from 20 to 220 GHz. A trade-off shall be madebetween various reflector technologies, e.g. CFRP and ceramics, and theobjective is to achieve the lowest possible mass while complying with the generalstability and surface accuracy requirements. After the trade-off, the mostpromising technology shall be selected and further detailed design and analysis isneeded to optimise its properties. Finally, by critical breadboarding and testing ofrepresentative RF and thermo-mechanical samples, the technology/design shallbe improved. Manufacturing and testing of a prototype reflector (around 0.5 m)shall be performed.

Deliverables: RF, Thermo-mechanical representative samples, reflector prototypeApplication: Post-EPS. More specifically for the Microwave Sounder that is identified as one of

the three high priority observation missions. It will provide continuity of data.Current TRL: 3 Target TRL: 4 Duration: 15 MonthsRef ESTER: T-8217, T-8224,

T-8227, T-8231HarmonizationDossier:

Technologies for (sub) millimeter wavepassive instruments - 2006

Annex 2. Page 3


ESA/IPC(2008)89

Ref. Number: G511-005ET Budget: 450 K€Activity Title: On-Wafer Measurements to 300 GHzObjectives: Setting up a service for for on-wafer measurements at frequencies up to 300 GHzDescription: On-wafer testing facilitates the development of mm-wave hardware, as the testing

can be done at chip/circuitboard level, without the additional complexity of thewaveguide interfaces. Especially in the development of LNAs and monolithicmixers and multipliers on-wafer testing is indispensable. In previous activitieson-wafer measurement capabilities of MilliLab were developed for 220 GHz. Thisactivity aims to take benefit of the development of test equipment to frequenciesabove 300 GHz, and develop a measurement service that is available Europeancompanies. Setting up an on-wafer test facility, investigation of the calibration,measurement error and DUT (device under test) mounting issues, setting up ameasurement service, definition of accuracies and requirements to the DUT.

Deliverables: Report. Measurement service available to European companiesApplication: measurement infrastructure / ASAPCurrent TRL: 2 Target TRL: 4 Duration: 18 MonthsRef ESTER: T-8200, T-8216,

T-8229, T-8206,HarmonizationDossier:

Passive mm & sub-mm instruments:Activity B29

Ref. Number: G511-006GN Budget: 250 K€Activity Title: Phase centre calibration of GNSS antennas in LEOObjectives: To define and set up an application to calibrate a LEO satellite GNSS antenna in

orbit, by processing of real GNSS data. This will lead to a more realistic andaccurate calibration than can be achieved on ground.

Description: The antenna calibration requires high-accuracy orbit determination of both theGNSS constellation(s) used, and the LEO spacecraft. This activity will defineoptimal algorithms to perform this calibration, and establish the achievableaccuracy of the phase centre calibration in space by implementing a prototypeapplication in existing software. It can be extensively tested on existing GNSSantennas of operational satellites in LEO.

Deliverables: Activity report and a working prototype implementation of the S/W withdocumentation.

Application: Can be applied as soon as available (e.g. Metop-2, GOCE)Current TRL: 3 Target TRL: 7 Duration: 12 MonthsRef ESTER: Harmonization

Dossier:

Ref. Number: G511-007ET Budget: 950 K€Activity Title: High-power W-band LO sourceObjectives: To develop a broad-band W-band LO source with Watt-level output powerDescription: W-band LO source with high output power is needed in several space-borne

instruments, and increasingly also in terrestrial applications. Power level of 100mW was reached in the past GSTP activity using GaAs technology. Todaytechnology selection is wider (e.g. GaN), and much higher power levels (0.5 to 1W) are feasible with European SSPAs. Technology selection for SSPA MMICs.Design, fabrication and testing of two iterations of MMICs the LO source, includingfrequency multipliers and power amplifiers. Integration of the MMICs and othercircuits into a LO module. Final test.



Deliverables: Report, hardware demonstratorsApplication: Post-EPS, Ciwsir, Tandem, Laplace, EVE, FIRI / 2011Current TRL: 2 Target TRL: 4 Duration: 24 MonthsRef ESTER: T-8200, T-8216,


Passive mm & sub-mm instruments:Activity A20

Ref. Number: G511-008ET Budget: 3,000 K€Activity Title: Integrated Tile DemonstartorObjectives: Design, manufacturing and test of integrated front-end tile demonstrator based on

advanced technologies for high coverage Active Array SARDescription: New concepts for SAR allowing high resolution and simultaneously wide swath

will significantly improve performance compared to existing concepts, while highresolution can be traded against radiometric accuracy by multi-looking if desired.Pencil beams in range, formed in the digital domain, improve signal to noise ratioand keep Tx power within reasonable limits. In order to implement those conceptsnew front-end architectures are required separating beam forming functionalityfrom transmit and receive functionality. The beam forming would lead tosignificantly increased wiring density, reasonably manageable only in centralisedsolutions.Depending on the outcome of the study “Advanced SAR Instruments based onDigital Beam Forming” the details of the tile demonstrator will defined. This studywill finish in 2008. Two possible outcomes can be anticipated: Separated transmitand receive functionality (bistatic operation) or a classical (monostatic case)front-end solution with much simplified T/R modules without beam formingfunctionality.Significant advantages in front-end mass due to simplified thermal design andintegrated beamforming solutions are expected in both cases.

The activity shall include:- Overall design of the tile breadboard demonstrator in consisting of- Electrical design: Radiator, Front-end and beam former design.- Thermal design- Mechanical design showing integrated mass saving solutions- Local oscillator and chirp signal generation.- Test in a representative proof-of-concept environment

Future European SAR instruments based on active arrays, e.g.ESA Sentinel 1 follow on significantly benefit from this new architecture.

Deliverables: - Integrated tile demonstrator breadboard- Documentation

Application: By 2014Current TRL: 3 Target TRL: 4 Duration: 24 MonthsRef ESTER: T-353, T-7736, T-7752,

T-8240HarmonizationDossier:

Consistent

Ref. Number: G511-009EE Budget: 500 K€Activity Title: Low mass Calibration load demonstrator

Annex 2. Page 5


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Objectives: Radiometer instruments need hot and cold calibration measurements to achieve ahigh radiometric accuracy. Cold calibration is usually done by looking into coldspace, but for the hot calibration a special load is needed. An absorber type ofload is used as a typical hot calibration target. However, if not only the feeds butalso the reflector has to be included in the hot calibration measurement theabsorber can become quite large (comparable to reflector aperture size).Therefore, it is very important that for future radiometer instruments with relativelylarge reflector sizes (e.g. Post-EPS) the mass of the hot load needs to beminimised in order to be compliant with the instrument mass requirement.The objective is to demonstrate by breadboarding low-mass calibration loads.

Description: This activity is aimed at achieving low mass 0.5 to 1-m class of hot calibrationtargets for future passive remote sensing instruments. Full use shall be made ofactivities already performed. TA critical assessment shall be made of deriveddriving parameters. A detailed design and analysis shall be performed of at leasttwo promising solutions where low mass and small volume is a driver. Finally, aprototype hot calibration load shall be designed, manufactured and tested over thefull range of frequencies in a representative thermal environment.

Application: Post-EPS \ 2011Current TRL: 3 Target TRL: 4 Duration: 15 MonthsRef ESTER: T-8219 Harmonization


Ref. Number: G511-010EE Budget: 2,000 K€Activity Title: Very large space antenna aperture - demonstration modelObjectives: The objective of this activity is the development of a P-Band SAR antenna partial

Engineering Model sufficiently representative to demontrate the mechanicalbehaviour, including deployment, together with the RF performances. The designis expected to be based on the TRP development related to Biomass EarthExplorer candidate.

Description: This activity is concerned with the development of a demonstrator model for anunfurlable/deployable P-band antenna. The Engineering Model shall besufficiently representative with full mechanical, including in stowed and deployedconfiguration, and demonstrate deployment and RF capability. This developmentis necessary within the framework of the Biomass Earth Explorer Missiondevelopment. The implementation of this activity is conditional on the selection ofthe BIOMASS mission.

Deliverables: Antenna partial Engineering Model design , assembly and RF test. DD&T plan forremaining actions up to flight antenna.

Application: BIOMASS \ 2012Current TRL: 2 Target TRL: 4 Duration: 24 MonthsRef ESTER: T-8195 Harmonization

Dossier:"Array Antennas" - 2005

Ref. Number: G511-011EE Budget: 2,000 K€Activity Title: Multi Frequency high resolution GEO-sounder DemonstratorObjectives: Microwave and (sub)millimeter wave atmospheric sounders provide information

on the distribution of radiation emitted by the atmosphere from which verticalprofiles of temperature and humidity through the atmosphere may be obtained.Current generation of sounders are embarked on-board low Earth orbit (LEO)



satellites for providing primarily meteorological data for numerical weatherforecasting, and on the second level global observations for climate monitoring.Across-track scanning of the antenna beam enables to achieve a widemeasurement swath exceeding 2000 km. Sufficient spatial resolutions can beachieved around the nadir with a relatively small antenna size (around 1 mdiameter). However, due to the rapidly increasing incident angle for off-nadirobservations, the spatial resolution is greatly degraded towards the swath edges.The global coverage is achieved by the combination of high ground-projectedspeed of the spacecraft on polar LEO combined with the rotation of the Earth.Continuity of data over tens of years is strongly supported by meteorological andclimate communities. Geostationary observations, unlike those from LEOsatellites, have the key potential advantage to provide continuous coverage of thesame region, which is essential for nowcasting. The basic requirements foratmospheric sounding are high vertical resolution and measurement accuracy. Incontrast to LEO microwave sounders in operation today, the proposed GEOinstrument uses many more channels that range in frequency from 89 GHzthrough to 874 GHz. Observations in microwave (MW) region, going up tosub-millimeter-wave frequencies, are less affected by the presence of clouds thanTIR observations, and are used as complements those observations.The objectives of this activity is to adapt/implement the GEO-sounder instrumentsand demonstrate with an test campaign the multi frequency and high spatialresolution performance of the concept.

Description: Several activities are being or have been planned for demonstration of theGEO-sounder concept. The objective of the present study is to combinemechanical and RF efforts and to demonstrate the multi-freqeuncy and highspatial resolution performance of the (sub)mm wave instrument.a) consolidation and adoption of instrument requirements;b) determining mechanical and RF interfacesc) implementation of multi-frequency receivers and long baselines.d) instrument integration;e) definition of algorithms for instrument performance verifications;f) performance consolidation of the selected design;g) test campaign.

Deliverables: airborne ready GEO sounder demonstratorApplication: Post-EPS, Gomas \ 2011Current TRL: 3 Target TRL: 4 Duration: 24 MonthsRef ESTER: T-8206 Harmonization


Ref. Number: G511-012EE Budget: 1,000 K€

Activity Title: Large aperture, ultra-stable, push-broom antenna withfrequency-multiplexed beams

Objectives: The primary aim of PREMIER is to explore processes controlling the compositionof the mid/upper troposphere and lower stratosphere. The secondary aim is toexplore processes controlling the composition of the lower troposphere/boundarylayer and link to higher layers. To do this, PREMIER will measure IR andmillimetre-wave emitted radiation.The mission objectives will be fulfilled by performing observations with threedistinct measurement techniques. One of them is a push-broom mm/sub-mm(324- 504 GHz) wave limb sounder.The objective of this activity is to ensure that the antenna which is one of the keysubsystems fulfils the stringent requirements.A second objective is to maintain the technological lead that Europe has inreflector antenna technology.

Annex 2. Page 7


ESA/IPC(2008)89

Description: This activity will be targeted to the following main areas:• review requirements and preliminary design• Address critical technological areas identifying potential solutions.• Perform critical breadboard development up to antenna levelThe activity will start with a carefull assessment on the mechanical accuracy andstability requirements.This activity will identify and select the mechanical, thermal and technologicalsolutions and antenna architectures required to achieve the necessary accuracyand stability for reflector antennas. These solutions/architectures will have to bedemonstrated by critical breadboarding .Special emphasis shall be placed on the multi-fequency multiplexing.A development plan to bring this technology to flight level should be provided.Theimplementation of this activity is conditional on the selection of the PREMIERmission.

Deliverables: Antenna EQMApplication: Sentinel 4, 5 premier \ 2011Current TRL: 2 Target TRL: 3 Duration: 24 MonthsRef ESTER: T-8199 Harmonization


Ref. Number: G511-013EE Budget: 650 K€Activity Title: Cross Correlator ASIC developmentObjectives: The objective of the current activity is to demonstrate by breadboarding the ASICS

needed in the GEO-sounder instrument and to enhance the European know-howin this field.

Description: Current generation of Microwave atmospheric sounders are embarked on-boardlow Earth orbit (LEO) satellites for providing primarily meteorological data fornumerical weather forecasting, and on the second level global observations forclimate monitoring. A cross-track scanning of the antenna beam enables toachieve a wide measurement swath exceeding 2000 km. Sufficient spatialresolutions can be achieved around the nadir with a relatively small antenna size(around 1 m diameter). However, due to the rapidly increasing incident angle foroff-nadir observations, the spatial resolution is greatly degraded towards theswath edges. The global coverage is achieved by the combination of highground-projected speed of the spacecraft on polar LEO combined with the rotationof the Earth. Continuity of data over tens of years is strongly supported bymeteorological and climate communities. Geostationary observations, unlike thosefrom LEO satellites, have the key potential advantage to provide continuouscoverage of the same region, which is essential for nowcasting. The basicrequirements for atmospheric sounding are high vertical resolution andmeasurement accuracy. In contrast to LEO microwave sounders in operationtoday, the proposed GEO instrument uses many more channels that range infrequency from 89 GHz through to 874 GHz. Observations in microwave (MW)region, going up to sub-millimeter-wave frequencies, are less affected by thepresence of clouds than TIR observations, and are used as complements to thoseobservations.This activity deals with breadboarding the ASICS needed in the GEO-sounderinstrument.The GeoMS instrument level requirements will be translated to a crosscorrelator detailed requirement specification. The overall cross correlator designwill be developed in parallel as ASIC level design is started to enable a concurrentdesign and optimisation process. Based on the cross correlator design and thepreliminary design results, the design goals for the cross correlator ASIC will bederived. A scaled version of the cross correlator ASIC will be designed, producedand tested. The test results will be analysed and system implications evaluated.



Deliverables: ASIC Design, tested samplesApplication: GOMAS \ 2011Current TRL: 3 Target TRL: 4 Duration: 24 MonthsRef ESTER: T-8206 Harmonization


Ref. Number: G511-014QC Budget: 350 K€Activity Title: Reliability study and space evaluation of European planar Schottky diodeObjectives: Based on previous development and European state of the art Schottky diode, in

Europe, the aim of this activity is to assess and improve the quality and reliabilityof the selected Schottky diode manufacturer for Millimeter and sub millimeterapplication; Mixer and Multiplier This includes: characterisation of process andparameter (DEC, TCV, RIC), determination of product reliability (life time),establish space quality level production capabilities,

Description: Schottky diode technology is considered to be the corner stone of all millimetreand sub millimetre instruments. Indeed, Schottky diode technologies are used formixer and frequency generation. Today, the Europe is fully dependent of USsource (VDI). These products required for European space mission on technologycapability that is not in the current mainstream. As a consequence in order forEurope to maintain acces to high frequency components ESA must support theindustrial Schottky diode processes. his component is essential for detection(mixer) and frequency generation (frequency doubler), and Europe is fullydepending on US Schottky diode to cover our needs. This is a key component forfuture Earth Observation and planetary exploration

Deliverables: Fully characterized schottky, documented production capability, PID, Schottkydemonstrator

Application: By 2010Current TRL: 2 Target TRL: 6 Duration: 36 MonthsRef ESTER: T-283 Harmonization


Ref. Number: G511-015MM Budget: 500 K€

Activity Title: Nd doped GSAG mixed Garnet crystal enhancement for applications inSpace Waves

Objectives: The primary objective for this proposed activity is to define growth conditionsfollowed by a realisation of high optical quality (low intrinsic and birefringent loss)large optically perfect crystal boules. These boules shall have different dopandlevels in dependance of their use vis-a-vis oscillator and amplifier.

Description: These large crystal boules would enable the development of amplifier rods/slabsto be prepared and to enable an achievement of the output energy requirementlisted for Space Waves. Prior work on this crystal development has achieved thedesired H2O wavelength of 942nm in a low energy q-switched oscillator havingthe desired spectral properties and efficiency. The benefit of using an Nd dopantwhere one can use standard 808nm pump diodes, is advantageous for laterqualification. This material while presenting dramatic simplifications at systemlevel and a large increase in efficiency, has some spectroscopic issues that needcareful attention during development vis-a-vis partial ground state population.Additionally damage issues need to be

Deliverables: Large diameter Nd doped GSAG laser boules with a diameter of 6-10 cm andlengths of 20cm with appropriate doping levels

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Application: SpaceWavesCurrent TRL: 2 Target TRL: 4 Duration: 18 MonthsRef ESTER: T-8186, T-8188,


N/A

Ref. Number: G511-016MM Budget: 350 K€

Activity Title: High power narrowband lasers for laser cooling applications in AtomInterferometry

Objectives: The task here is to prepare reliable high power laser cooling sources forapplications in Rb and Cs based Cold atom interferometers.

Description: The realisation of cold atom interferometers in space for Earth Gravity applicationswill require the development of a flight compatible sensor system. The cold atomsensor system comprises atom production, cooling lasers followed by the atomlaunching, splitting and re-combining of the prepared atoms. This first activity willfocus on the laser cooling laser systems, and due to the resonance coolingtransitions in Rb and Cs being located in the same spectral region as lasers usedfor optical preparation of Rb and Cs atomic clocks some commonality ofapproaches can be adopted. The major difference will be the required linewidthand the power.

Deliverables: Compound semiconductor based laser-cooling sources for Rb or Cs based coldatom interferometers

Application: Atom Interferometry for Earth Gravity Post-GRACE type missionsCurrent TRL: 2 Target TRL: 5 Duration: 24 MonthsRef ESTER: T-8194, T-8186,


N/A

Ref. Number: G511-017MM Budget: 500 K€Activity Title: Monolithic filter on detector dye integration technologiesObjectives: Evaluation of potential filter materials and direct-deposition processes directly on

the detector for (one of) the main technologies (Si, InGaAs, MCT), Si being thepriority.A two-phased contract shall be foreseen:1. Establishing feasibility through a comprehensive study2. Proof of concept demonstration only if feasibility of at least one solution isevident

Description: A recurring problem in multi-/hyper-spectral imagers is the (stripe) filteraccommodation where strongly performance-degrading optical cross-talk, fringingas well as mechanical robustness are everlasting issues. This activity shallinvestigate the feasibility of directly processing optical filters onto the detector die.While depositing optimized AR coatings (even as a variable wedge across thearray) can be considered standard procedure, the feasibility of such direct processis far from obvious for a narrow-band optical filter. Apart from opticalperformances (bandwidth, out-of-band rejection), compatibility of the process withthe underlying detector itself must be considered.

Deliverables: Proof of concept demonstrationApplication:Current TRL: 2 Target TRL: 3 Duration: 24 MonthsRef ESTER: T-7886 Harmonization

Dossier:Roadmap Ref. D3



Ref. Number: G511-018ET Budget: 1,500 K€Activity Title: EES Ka band High Data Rate Payload Data Transmitter Engineering ModelObjectives: The development of an engineering model for a high data rate telemetry

transmitter and receiver chain demonstrator in the Ka-band (25.5-27 GHz)Description: The Ka-band (25.5-27 GHz) has been allocated for the high rate payload

telemetry of Earth Exploration Satellites and for the Near Earth Space Researchsatellites. Currently, all Earth Observation Payload Data Transmission’s systemare using the EES X-band frequency allocation and it is expected that within thenext ten years this band will be severely congested. Coming missions also requirevery high data rates that cannot be accommodated in the EES X-band allocation.System studies are ongoing in ESA in preparation for the transition to Ka-bandoperation;The activity shall comprise:The development of a transmitter EM, this unit shall be modular and able tohandle data rates of up to 1 Gbps (at least). Trade-offs on architecture shall beperformed.The investigation of the elements of the receiving chain: LNA, downconverter anddemodulator. The activity requires the development of an engineering model ofthe critical ground station equipment identified.

Deliverables: Transmitter Engineering Model and Critical Ground Station EquipmentApplication: All future EO missions \2012Current TRL: 1 Target TRL: 5 Duration: 16 MonthsRef ESTER: T-8334 Harmonization

Dossier:N/A

Ref. Number: G511-019GI Budget: 150 K€Activity Title: Parallel computing for fast TM processing during short passesObjectives: The Earth Observation Satellites download their stored House Keeping data at a

high rate during very short passes. The Mission Control System is not able tocope with such a rate and this leads to cumbersome storage and re-playingprocesses. The result is that the stored TM is only available for display much afterthe pass. The objective of this study would be to analyse whether SCOS-2000 TMprocessing can be modified to use parallel computing in order to increase asmuch a possible the processing speed, and eventually cope with the massmemory dumps TM in real-time

Description: The study has two phases. In a first phase the problem is analysed and atechnical solution derived for the parallelisation of the tasks related with the TMprocessing (Packetiser, distributor, Behaviour Limit Checker, Saved SyntheticParameter calculation, Storing into the archive). In a second phase, a prototype isdeveloped, covering at least the packetiser and injection into the archive.

Deliverables: Proof-of-concept prototype source code, executable and test dataApplication: Future EO missionsCurrent TRL: 2 Target TRL: 5 Duration: 12 MonthsRef ESTER: Harmonization

Dossier:N/A

Ref. Number: G511-020ET Budget: 400 K€Activity Title: Membrane circuits for high frequencies

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Objectives: To develop integrated Schottky circuits on thin membranesDescription: The roadmap for the development of European Schottky technology is based on

the principle that, if possible, the main development effort, leading to theindustrialisation for the main applications at 300 to 500 GHz frequency range,would be largely funded by EC, and that complementary development actions aretaken by ESA. Technology for the higher frequencies, up to THz, is the mostchallenging and least developed, and pre-development of integrated Schottkystructures for these applications is being carried out in a current TRP activity. Theaim of the present GSTP activity is to continue that development by concentratingon integrated circuits on a membrane, so that Schottky devices also for thehighest frequencies reach sufficient maturity for subsequent industrialisation.

Deliverables: Report, hardware demonstratorsApplication: Post-EPS (MWI), Ciwsir, Tandem, Laplace, EVE, FIRI / 2011Current TRL: 3 Target TRL: 4 Duration: 24 MonthsRef ESTER: T-8200, T-8216,


Technologies for Passive Millimetre &Submillimetre Wave Instruments -



THEME 2.- SCIENCES

Ref. Number: G512-001MM Budget: 1,000 K€Activity Title: B-BOLD (BOLD continuation)Objectives: Develop the Solar-blind technology - whose potential is being proven very

successfully - further to a more mature and full-scale, large area 2D detectorbreadboard. The schedule is presently driven by the need to provide a solidfall-back solution for the presently baselined (but not initiated….) APS detector forSolar Orbiter.

Description: During the still on-going very ambitious and aggressive activity " BOLD",development of epitaxy, test-structures and costly accelerator tests haveestablished the feasibility and potential performance of a) AlN as the optimummaterial and b) two promising diode technologies, yielding world-wide state-of artresults. A technology demonstrator of modest dimensions will be the oucome. Asan immediate follow-on, a full-scale detector breadboard on an optimized ROICshall be developed and evaluated under representative conditions.

Deliverables: Full-scale demonstrator breadboard, representative of a flight model for EUI onSOLO

Application:Current TRL: 3 Target TRL: 4 Duration: 24 MonthsRef ESTER: T-7886 Harmonization

Dossier:Opt. Instruments -D6-

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THEME 3.- HUMAN SPACEFLIGHT AND EXPLORATIONPREPARATION

Ref. Number: G513-001MM Budget: 600 K€Activity Title: Micro laser beam scannerObjectives: A micro laser beam scanner for planetary exploration instruments (3D robotic

vision, lidar, laser pointing for spectroscopy) shall be designed, manufactured andtested under relevant environmental conditions.

Description: Future robotic missions will make use of 3D-vision systems, docking sensors andimaging Lidars, which all require a laser beam scanning mechanisms. Forplanetary exploration, the volume and weight is a critical issue. Today thesemechanisms are heavy or are being avoided altogether for reliability reasons.However, very small devices having low moving masses have the potential to beextremely robust. Making use of MEMS technology, an aggressive miniaturization(low volume and weight, low power consumption) effort shall be undertaken topush robustness and reliability to high level. This technology (including materialsand material analysis methods) is in a reasonably mature stage, so that robusthigh performance solutions can be envisaged already today. The main concern sofar has been the robustness of MEMS devices despite the fact that in theorydevices based on smaller masses (such as MEMS) have an increasedrobustness. Improved structural analysis methods (like adequate x-ray sources)offer today a much higher degree of understanding of the structural breakingphenomena. Emerging highly robust and elastic materials (amorphous metals forinstance) also contribute to a significant MEMS reliability improvement.

Deliverables: 3 Laser Scanners including optical system (laser beam fed by optical fiber),scanning mirror element, driver electronic.

Application:Current TRL: 3 Target TRL: 6 Duration: 24 MonthsRef ESTER: T-8441, T-7860 Harmonization

Dossier:

Ref. Number: G513-002MC Budget: 1,500 K€Activity Title: Investigation on microcompounds in MELiSSA - PHASE2 (BELISSIMA2)Objectives: Objective is to study the behavior and the effects of micro-compounds (trace

elements, hormones, pharmaceutical drugs, plasmids) within the liquid phase ofthe MELiSSA loop, and to define and test associated countermeasures.



Description: Over the past years of the MELiSSA project, priority has been given to the studyof the 6 main chemical elements (C,H,N,O,S,P). Although studies of these mainelements have still to be pursued, the influence and modeling of smallerconcentration elements, of chemical (i.e. Ni, Cu, Na,..) or microbiological nature(i.e. plasmids) has to be taken into account, as well as the toxicology of externalagents (pharmaceutical drugs, hormones). The investigations to be performed aremainly: the identification of limitation and/or toxicity thresholds, the growth kineticsinfluence and modeling, the study and selection and validation ofcountermeasures. As these investigations require numerous toxicity andcontamination tests, potentially lethal for micro-organisms, a micro-MELISSA loop,simplified to the liquid phase and consequently more adapted to theseinvestigations, had to be built. In the frame of BELISSIMA 1, the building phasehas been partially achieved (limited to compartment 1 and 2) and therefore testingcampaigns have been limited to the available hardware. Within the present activity(i.e. BELISSIMA2), the assembly of the mini-MELiSSA loop shall be completedand studies pursued according to the overall objective of BELISSIMA.Also, the strong synergies with terrestrial water treatment research related tobacterial breakthroughs and accumulation of chemicals (drugs, endocrinedisruptors, metabolites etc.) will be studied.

Deliverables: Completed mini-MELiSSA loop with appropriate instrumentation, proventechnologies, comprehensive test data, improved knowledge

Application: 2015/2025 Huma Exploration-Life Support / Preparation for ExplorationCurrent TRL: 3 Target TRL: 5 Duration: 36 MonthsRef ESTER: Harmonization

Dossier:Y

Ref. Number: G513-003MC Budget: 250 K€Activity Title: Water Network CorrosionObjectives: The objective is to study and assess interactions between potable water

containing silver and space vehicle water loop, and provide recommendationconcerning material selection for future manned spacecraft water network.

Description: In the context of manned space mission, consumables for the crew, mainlyoxygen, potable water and food, are required to have a long shelf life. In order tomeet this long shelf life, stringent quality requirement have to be met, and aremnant biocide (i.e. silver for Russian water and iodine for American water) isadded to the potable water, preventing micro-organisms development. Maintainingthe concentration of biocide all along water shelf life is thus of outmostimportance. Experience gained during ATV launch campaign, supported byliterature review, demonstrates interactions between water containing silverbiocide and water containers and tubing occur. This interaction leads to gradualbiocide depletion and drift of water quality. In order to prevent this biocidedepletion, understanding of the interactions/corrosion is needed. This knowledgewill allow providing recommendations concerning material selection for mannedspacecraft potable water loop.

Deliverables: Technical documentations, test plan, test results.Application: 2010 (ATV, ISS, ISS extension, Exploration)Current TRL: 3 Target TRL: 5 Duration: 24 MonthsRef ESTER: Harmonization

Dossier:Y

Ref. Number: G513-004MC Budget: 250 K€

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Activity Title: Preliminary estimation of energy balance of a closed life support system -Application to MEliSSA

Objectives: The relevance of closed life support system is highly depending of their degree ofclosure for an associated energy cost. Within this study it is proposed toinvestigate method to quantify energy cost of closed life support systems, as wellas to perform mathematical simulation.

Description: Almost by definition, closed life support system will include biological processes,use direct Sunlight, and the inputs substrate is highly depending of the recyclingprocesses including crew. Based on the existing design of the current MELiSSAlop, and the associated metabolisms of the selected organism, it is proposed toreview and study methods to quantify the energy cost of a closed life supportsystem.

Deliverables: Technical Reports, including simulation results and generic tools for furthersimulations.

Application: 2015: Tools for futures ECLSS systems study Surface base (i.e. Moon, Marsbases)

Current TRL: Target TRL: Duration: 24 MonthsRef ESTER: Harmonization

Dossier:Y

Ref. Number: G513-005MC Budget: 250 K€Activity Title: Process Aeration DeviceObjectives: The objective is to study, design and develop an efficient aeration device for

processes, which allow significant energy reduction.Description: In the context of closed loop Life Support Systems, one of the most important

steps is the Nitrogen oxidation. Generally, This oxidation is performed by nitrifyingmicro-organisms that require oxygen. Supplying oxygen to the microbialcommunity has been identified as the main operating cost of this nitrificationprocess. In order to further optimize this process, reduction of energy demand isrequired and improvement of the efficiency of the aeration device is necessary.

Deliverables: Technical documentations, test results, aeration device.Application: 2015 (ISS extension, Exploration)Current TRL: 3 Target TRL: 5 Duration: 24 MonthsRef ESTER: Harmonization

Dossier:Y

Ref. Number: G513-006MM Budget: 350 K€Activity Title: Biochemical Analyser Technology (BIOCAT)Objectives: To upgrade the developed technology enabling detection of very low

concentrations of molecules (at Pico molar level or below) and single cellorganisms in aqueous solution (1 cell or bacteria or spore/ ml) and on solidsupport. Define sampling and sample conditioning technologies for the samples tobe analysed with BIOCAT



Description: The existing technology is presently able to detect a known fluorescent moleculedown to picomolar concentrations. The planned activity will extend the range ofmolecules to be detected to a range of autofluorescent biomarkers (keeping thehigh sensitivity). Furthermore it will address sampling and conditioningtechnologies to extend the application within liquid samples and to enable itsapplication range to samples on/in solid surfaces. In the ideal case the technologywill be applicable to solid surfaces without or minimal prior treatment andmechanical contact, thus allowing the fast scanning of large surface areas.

Deliverables: BreadboardApplication: TRL 8 by 2012, Next, MSR, Outer Planet Missions.

For tools and S/W target date should be earliest the date by which the S/W andtools are to become operational.

Current TRL: 3 Target TRL: 5 Duration: 12 MonthsRef ESTER: T-7718, T-7717 Harmonization

Dossier:N/A

Ref. Number: G513-007MM Budget: 300 K€Activity Title: A self standing bioreactor for biological samplesObjectives: To develop a multifunctional biological bioreactor in which cells can be controlled,

observed and maintained.Description: For biological experiments in space, special devices are needed to be able to

culture the samples (cells and tissues) with small or no effort. This activity shalldevelop a new generation of self standing bioreactors which will be able tomaintain the cells over a long period in microgravity, so long term experiments willbe possible. Observation of the samples will be possible, due to an open seethrough frame and the onboard microscope, therefore live imaging will bepossible. The important factors O2, CO2 and the temperature will be controlled onthe bioreactor itself, therefore no special environment, like an incubator is neededand will safe a lot of space. The bioreactors developed so far were only capable incontrolling a few of these parameters, therefore this activity would be aimprovement on existing technology which can help biological research in space.Bioreactors like this could give answers to biological questions about for examplebone research, cytoskeleton activities, tissue development, blood proliferation etc.

Deliverables: A self standing incubation bioreactor in which the samples can be observed andcontrolled via hardware.

Application:Current TRL: 3 Target TRL: 6 Duration: 18 MonthsRef ESTER: Harmonization

Dossier:N/A

Ref. Number: G513-008MM Budget: 200 K€Activity Title: Respiratory Sensor System - Optimisation and CombinationObjectives: Optimise the already-proven technology of thin-film based flow, O2 and CO2

sensors- Reduce the power consumption and optimise the thermal control of the sensors(combine all sensors on same substrate)- Consolidate main-stream solution- Include measurements of relevant complementary parameters required forestablishing respiratory indexes- Integrate H2 measurements- Validation

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Description: Thin-film based technologies to measure respiratory parameters (flow-rate,oxygen concentration, carbon dioxide concentration) using a direct, main streamsensor have been developed and validated under previous ESA activities. Theactivity demonstrated that it is possible to measure above-mentioned parameterswith a device weighting in the range of 1 Kg, which represents a very goodimprovement compared to the other devices working on other principles. Thetechnology is now fully validated for off-line analysis (respiratory flow derivedtowards the measuring system) and for a system where each parameter ismeasured by a separated sensor with own thermal control system. For obtaining afull performance of the system, it is now necessary to optimise the sensorintegration and to consolidate the measurement in the main stream(measurements directly in the air flow). The tasks identified to update the systeminclude: -Improve the thermal regulation (this will likely require a thermal modeling of thesystem)- Combine all the sensors on one substrate (will reduce power consumption andcreate more stable conditions to the thermal regulation law)- Consolidate the main-stream solution (includes performing the requiredanalyses, refine the design of the sensor parts and head to minimise the deadspaces- Define and implement measurements of additional parameters used in theanalysis of the respiratory function (such as heart rate, humidity, ambienttemperature and pressure…)- Integrate the H2 measurements- Integrate those changes in a breadboard and validate the breadboard.

Deliverables: Validated demonstratorApplication: Human space flight and exploration - medical diagnostics technologies. Outcome

of this activity will also be integrated into the product line of Medisoft, which is aBelgian SME manufacturing and commercialising medical devices.

Current TRL: 3 Target TRL: 4 Duration: 16 MonthsRef ESTER: Harmonization

Dossier:N/A

Ref. Number: G513-009MM Budget: 500 K€Activity Title: MEMS based Gas Chromatograph/Mass SpectrometerObjectives: The objective of this activity is to achieve a fully functional breadboard of a

miniaturised Gas Chromatograph and Mass Spectrometer system for in-situchemical analysis in harsh environment based on MEMS technology.

Description: Gas chromatographs in conjunction with a spectral mass analyser for theidentification of organic and inorganic compounds have been flown or are flyingalready on several space missions, e.g. Huygens and Rosetta, and are in theprocess of being built and qualified, as for the Mars Science Lab (NASA) and forExoMars (ExoMars). These instruments are already miniaturised and optimised interms of mass and power consumption to a high extent. MEMS based technologyhowever offers a potential to further reduce resource consumption and cost. Thiswould enable for instance environmental monitoring using a swarm type ofmission. As for applications in human spaceflight, the potential of MEMS baseddevices is the increased mobility.

Deliverables: BreadboardApplication: TRL 8 by 2013, missions NEXT, MSR, Outer Planet MissionsCurrent TRL: 2 Target TRL: 4 Duration: 18 MonthsRef ESTER: T-7717 Harmonization

Dossier:



Ref. Number: G513-010MM Budget: 200 K€Activity Title: In-Vivo embolic detectorObjectives: Continuation of activity - Optimisation of the test bench of the in-vivo embolic

detector - building and validation of a system to measure and characterisebubbles in models of human blood flow.

Description: Development of a technology for non-invasive detection of gas bubbles in blood,based on electrical impedance measurements has been started under theprevious GSTP. The developments made up to now have concentrated in buildinga test-bench and a bubble detection system to characterise the sensors and toperform further calibration of the technology. Results obtained so far show thatthere is a direct link between the amplitude and frequency of the impedance signaland the concentration of bubbles in the fluids under test, however there is a needto refine the relationship between the characteristics of the electrical signalrecorded and the size and concentration of the bubbles detected.The purpose of the activity for the next phase of the activity is hence:i) To update the specifications for the test bench (type, size, concentration ofbubbles, reference measurement systems)ii) To update the test bench with the possibility of generating low numbers ofbubbles of more defined sizes (e.g. using different gas types and porous filters)iii) To run a characterisation of the measuring systemiv) Taking into account above results, to update the breadboard for performingmeasurements of bubble concentrations on animalsv) To evaluate the breadboard by measuring bubble concentrations on animalmodels of the decompression syndrome.

Deliverables: Validated demonstratorApplication: 2012 / Human space flight and exploration - medical diagnostics technologiesCurrent TRL: 2 Target TRL: 4 Duration: 18 MonthsRef ESTER: Harmonization

Dossier:N/A

Ref. Number: G513-011MM Budget: 350 K€Activity Title: Enhanced Autonomous Cultivation SystemObjectives: The objective of the activity is to enhance the capabilities of the existing

(Canadian) flight hardware e-ERISTO to allow cultivation and observation of largercell agglomerates as eg fish eggs.

Description: The successful flight hardware eERISTO has been flown in the shuttle and in thefully automated FOTON mission (Foton M3). Its media storage capabilities andcontrolled delivery made it an appreciated experiment platform for a variety ofbiological experiments like bone cell experiments. The inclusion of the followingfeatures would give a wide range of new experiments the possibility to use a flightproven hardware for their experiments. Presently already an experiment dealingwith the development of fish eggs identified in the D/HME MAP-Programme isvery interested in this hardware. :- the addition of live observation (when a cell culture is in progress) would give thepossibility to visualise and therefore analyse the experiment evolution while it isstill in µgravity. This improves scientific value and information as the analysis orobservation will be immediate and will allow the scientists to react on time to e.g.cope with the development of adverse conditions and hence save the cellcultures. Moreover for specific types of cell cultures (e.g. fish eggs), on-lineobservation would allow the scientists to perform real time analysis of celldevelopment as in the lab.- a variable size of the bioreactor part to accommodate different numbers and

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sizes of cells or organisms as well as a permeable bioreactor wall materialallowing for gas exchange with the environment; this would open up the use of thefacility to new types of cell cultures, e.g. fish eggs.Tasks of this activity will include:- Developing of a new pathway, (inner layer of the eERISTO unit) including thepossibility of permeability and variable volume of the bioreactor and theaccommodation of the visualisation/ monitoring unit- Adjusting and testing interfaces for communication- Developing GSE tools (software) based on existing tools- Testing and validation

Deliverables: New pathway including permeable bioreactors and monitoring unit fitting intoexisting eERISTO unit and Ground Support equipment, documentation

Application:Current TRL: 3 Target TRL: 6 Duration: 18 MonthsRef ESTER: Harmonization

Dossier:N/A

Ref. Number: G513-012MM Budget: 600 K€Activity Title: Enhanced Virtual Reality StimulatorObjectives: Objective of this follow-on activity is the improvement of the existing Virtual Reality

Stimulator (VRS) demonstrator by the update of hardware and software, theintegration of new stimulations (3Dsound) and features e.g. stress and workloadmeasurement and integration of stimulation based learning support foraccelerated learning procedures (feedback loop). The update includes improvedreponse time measurement and use of other electrophysiological signals (EEG,EOG, EMG and ECG) into the feedback loop

Description: The Virtual Reality Stimulator is a multi-purpose experiment platform for cognitiveneurophysiology developed in the scope of the TRP program. It gives theopportunity to explore neuroscience and cognitive aspects in a completecontrolled environment (e.g. 3D mazes) with defined stimulations (like aural,visual, mechanical stimulations). The stimulator gives an experiment editing andexecution platform allowing the user the full editing and execution spectrumneeded for cognitive neuroscience research. It allows for sub-millisecond accuratereaction time measurements and supports the measurement ofelectrophysiological signals such as EEG, EOG, EMG and ECG. n the scope ofthis activity the stimulator will be updated to be more flexible to be able to optimisethe stimulation and environment scenarios for different experiments, this will alsoinclude hardware and software updates to reflect new technology advances. Asmain part the Stimulator will be improved with new features including:- Enhanced reaction time measurement (including voice recognition)- Integration of new stimulations and environments as e.g. exact 3D audiostimulations- Integration of a neurophysically driven training for accelerated learning- Integration of biofeedback loop to allow for e.g. studying response to stress andworkload- Adding and optimising haptic feedback and stimulation (including software handrepresentation), eye tracking and see-through capabilitiesThe present activity can in addition have applications in the medical training field:to train or to maintain skills necessary for medical staff on interplanetary trips orsited on moon/Mars posts.

Deliverables: Technology demonstrator - Validation dataApplication:Current TRL: 3 Target TRL: 5 Duration: 18 Months



Ref ESTER: T-307 HarmonizationDossier:

Ref. Number: G513-013MM Budget: 250 K€Activity Title: Tactile TrainingObjectives: The objective of this activity is to develop a training tool to enhance

countermeasure training in the sense of motivating the astronaut throughcompetition and entertainment and also assessing the performance. At the sametime this system will give the opportunity to train different tactile demanding taskseasily as e.g. tasks to be carried out in the glove-box. Output will be a technologydemonstrator with tailored software.

Description: Countermeasures in space take a high toll in crew time, in addition are theexercises mostly composed of endless repetitions of the same movements. This istrue as well for different training task which are asking for highly specialisedmovements (e.g. assembling of a Biolab experiment inside the glove box). Bothcan be eased with a game-like approach. Scientific studies have proven games asa very good instrument to train special tasks as e.g. laparoscopic tasks used formedical health care - this approach can be extended to tasks under the glove box.In addition such a system can be easily used to divert trainings routine by addingentertainment and feedback into normal countermeasure activities andinstruments and be used to assess the performance while exercising thesecountermeasure devices.Games providing these features are on the low price commercial market andcould be adapted and advanced for the use in space.To achieve the twofold goal of the activity (to have an example training programfor a specialised task and the integration into a countermeasure exercise) theactivity will integrate the following tasks:- Identify possible training tasks- Develop training program for one task based on a game console like approach- Develop set-up for integrating system into an example countermeasure activity- Develop countermeasure (game based) program for diverting exercises andanalysing the performance level- Integrate it in existing countermeasure devices

Deliverables: breadboard including softwareApplication: N/ACurrent TRL: 3 Target TRL: 5 Duration: 12 MonthsRef ESTER: Harmonization

Dossier:N/A

Ref. Number: G513-014MM Budget: 350 K€Activity Title: Bone and Muscle ModellingObjectives: The objective develop of this activity is the development of a new modelling

method to investigate effects on bones and muscles under microgravity throughdetailed modelling of muscle activity and bone loading. The outcome iscustomised software including detailed models for bone and muscle assessmentand countermeasure optimisation.

Description: Bone and muscle degradation is a major concern in human spaceflight. Until nowempiric approaches have been used to develop countermeasures and to assessdegradation. Anybody presents a systematic tool to improve and developcountermeasures and life science instrumentation by providing a physical / visualmodel to analyse or optimise countermeasure hardware or generally tasks (e.g.EVA tasks) in space.

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It has proven its feasibility in an ESA funded activity where a countermeasuredevice was integrated as well as a stress map of the leg is built to assess thestress force in the bone (visible in a Finite Element Model). In this ‘map’ it is visiblewhere stress forces are acting on the tibia bone and how those are different inmicrogravity and 1g conditions.Building upon these results a model for the use in space shall be developedwhere comparisons between space and 1g are easily visible and optimisationalgorithms make it possible to see the best configuration for dedicatedcountermeasure devices or tasks.Therefore the activity will extend the bone FEM model and stress map to the mostimportant bones validate it and analyse the degradation on them.These results will then be used to optimise tasks (including a countermeasureexercise) for optimal muscle and bone loading.Tasks in particular will include:- Optimisation of FEM model for material properties (including density)- Extension of the model to include the most important bones (attached correctlyto the muscle model)- Analysis of countermeasure devices / exercises (e.g. specific EVA task) forassessment of muscle activity and bone stress- Validation of model (comparison of results with experimentally registered bonedemineralisation if possible)- Assessment if and how more dynamic features can be included in the model(e.g. muscle fatigue).

Deliverables: customised modelling software including models and verification of modelApplication: countermeasure development - 2010Current TRL: 3 Target TRL: 5 Duration: 18 MonthsRef ESTER: Harmonization

Dossier:N/A

Ref. Number: G513-015MM Budget: 600 K€Activity Title: High-precision Implantable Intra-arterial Drug Delivery DeviceObjectives: Develop a high-precision drug delivery device, which can be implanted in mice.

The device will be able to be controlled and activated via telemetry, thus suitablefor biological experiments in mice during space missions.

Description: Drug development, preclinical research and biological research rely on animalexperimentation. Only a small proportion of drugs can be given to animals via theirfood, the greater part necessitation either injections or implantable drug deliverypumps. To date the available and widely used implantable drug delivery devicesare driven by osmotic pressure and have major limitations: they give onlycontinuous flow at a given non-controlled rate, offering thus no possibility to giveboluses at specific times or periodic drug delivery, which is required to studyingpharmacokinetics; they are quite inaccurate; and they cannot be programmed orcontrolled once inserted in the animal. There is therefore a great need for aprecise, telemetrically controlled and versatile implantable drug delivery pump.The aim of this activity is to develop a developed a high-precision, telemetricallycontrolled, implantable intra-arterial drug infusion device whereHigh-concentration drugs can be stored within the implant and the dosing is lowso that drug delivery can take place over long periods (weeks to months or years).The device should be small in size to be implanted in small animals (e.g mice),controlled telemetrically, high-precision bolus administration, dosing independentof load (i.e., arterial pressure at distal end of delivery catheter), externallyprogrammable/activated for continuous, periodic or user-defined drugadministration, MRI safe and compatible

Deliverables: breadboard



Application: Urgently needed in the context of animal experiments in space. Flight of MIS onFOTON/BION in 2012


Dossier:N/A

Ref. Number: G513-016MM Budget: 300 K€Activity Title: 3D BioreactorObjectives: Objective is the development of an advanced 3D bioreactor system to maintain

living cardiovascular tissue under controlled physiological conditions forcardiovascular and pharmaceutical research and development.

Description: Research and development on pharmaceutical biotechnology, evaluation ofcardiovascular intervention and therapy, and medical devices and sensors onearth and in space is so far based on output from patient and animal studies. Inaddition and/or as an alternative to animal experiments a significant part of thecardiovascular R&D currently conducted with animals can be carried out usingbioreactors. Although bioreactors provide an environment to keep tissue alive, theefficacy is strongly determined by subjecting the tissue to physiologicallyrepresentative loading. This project aims at developing a sophisticated bioreactorwhich is capable of maintaining living cardiovascular tissue under well-controlledhemodynamic conditions. Existing technology from in-vitro and ex-vivo modelingof the cardiovascular system is used and advanced to develop an ex-vivocirculatory system. Physiology is restored within the system using a nutritiveoxygenated perfusion medium, sophisticated modules for hemodynamic pre- andafterload settings and an integrated flow circulation. Such a setting provideswell-controlled circumstances (uniformity and efficiency), accurate assessment ofthe intervention or treatment applied and can replace a number of animalexperiments. The system offers a test bench for (new) medical devices andsensors, drugs (treatment) and intervention strategies. Moreover, tissueinteraction and responses such as remodeling under microgravity conditions canbe examined with the system. The work within the project includes research,development, validation and evaluation of the circulatory system components, andapplication to vascular tissue and valves. Future applications may include alsocontrolled cell culturing, proliferation, differentiation and tissue engineering amongothers.

Deliverables: A bioreactor demonstrator system which is capable of maintaining living tissue forR&D in the field of (patho)-physiology, pharmaceutics, and medical device andsensor technology.

Application: Needed as a tool for preparation of long term human mission for prediction of longterm effects of microgravity without usin invasive methods on astronauts.

Current TRL: 3 Target TRL: 5 Duration: 24 MonthsRef ESTER: T-8423, T-8422,


N/A

Ref. Number: G513-017MM Budget: 400 K€Activity Title: Blood pressure, flow and temperature sensor inserted via a vascular stentObjectives: Objective is the development of a miniaturised sensor system, on an expandable

stent, to be inserted in small animals, for evaluation of the change ofhemodynamic state in zero gravity conditions based on nanotechnology methods.

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Description: In long duration spaceflight it is necessary to continuously monitor pressure, flowand temperature for the evaluation of the change of hemodynamic state.Individual sensors have been developed already. The challenge is to significantlyreduce the size and weight of the sensors to implant them and access themremotely. Therefore, this activity aims to develop a combined pressure, flow andtemperature sensor on a single, flexible chip, powered and sensed non-invasively,with existing wireless RF-technology, applied to a vascular stent that can beimplanted in small animals. The existing measurement techniques need to beadvanced for the specific application inside a stent. The single sensor must beattached to a stent without breaking and loosening. The proper positioning of thesensor will necessitate a more sophisticated deployment technique than appliedwith a conventional stent. This method of sensing multiple parameters on a singlechip attached on a deploying stent offers the possibility of non-invasive long-termexperiments regarding evaluation of hemodynamic responses to e.g., drugs orexercise under zero-gravity conditions. The activity shall focus on the design,manufacture, integration, calibration and test of the breadboard.

Deliverables: A wireless sensor on a stent, including implantation techniques for invasivemonitoring and evaluation of (changes in) hemodynamic state

Application: 2011 FOTON/BION mission with MISCurrent TRL: 3 Target TRL: 5 Duration: 24 MonthsRef ESTER: T-8422 Harmonization

Dossier:N/A

Ref. Number: G513-018MM Budget: 350 K€Activity Title: Diagnostics for Nucleation DetectionObjectives: Objective is to demonstrate techniques devoted to the detection of the early stage

of crystallisation (nucleation) from solutionDescription: The scientific community currently involved in ESA sponsored microgravity

experiments on solution crystallisation of protein, have expressed interest in thestudy of the mechanisms that lie behind the formation of the very first aggregatesof molecules or nanoparticles. This is an interesting but yet quite poorlyunderstood aspect of crystallisation, due also to the stringent experimentalproblems. That is because the detection of the properties (size, degree ofcristallinity etc) by optical means are not so straightforward. The typical size ofcritical nuclei usually lies below the resolution of imaging techniques. On the otherhand, light scattering techniques that are sensitive up to nanometric length scales,collect light from scattering volumes that are very small (e. g. l) if compared with atypical sample volume of the order of a few ml. The activity shall identify atechnique or a combination of techniques and demonstrate its ability toencompass the detection of nanometric entities over the entire sample volume(typically a few ml). The samples of interest can be proteins, zeolites or colloidalsolutions. The activity shall be finalised by representative measurements on aModel Experiment.

Deliverables: Calibrated operational demonstrator, S/W, test data. Final documentationcontaining representative measurements, the manual for the instrument includingits calibration and s/w description.

Application: PCDF experiments. For techno push technology, earliest best estimated date tohave this techno at TRL5/6.

Current TRL: 3 Target TRL: 5 Duration: 24 MonthsRef ESTER: T-8425 Harmonization

Dossier:N/A



Ref. Number: G513-019MM Budget: 250 K€Activity Title: Nanowire BiosensorObjectives: The objective of this proposal is to fabricate and demonstrate electrochemical

Silicon NanoWire (Si-NW) label-free sensors with enhanced sensitivity for virusand/or DNA diagnostics.

Description: For label-free applications, electrical biosensors are more favorable than othertypes. In this family of sensors, the basic electrical parameters of a Si-NW fieldeffect transistor coated with appropriate probe molecules are modified due to theprobe-target binding chemical reaction. Primarily, the interaction of targetbiomolecules with immobilised probes on the Si-NW induces a chargeconcentration that affects the conductance of the transducer (i.e. the Si-NW FET).Nanoelectronic devices offer a major improvement in terms of sensitivity andlower limit of detection. Furthermore, it has been demonstrated thatnanoelectronic devices can be used to trade-off between biosensor's settling(response) time and the minimum detectable concentration. The demonstrator willcomprise a linear array of sensing elements (each sensing element is a Si NWtransistor) and PDMS microfluid channels that allow controlling the flow of thebiological material above functionalized Si NWs.

Deliverables: demonstrator, breadboard, test resultsApplication: Biology and Physiology research, microbial detection for research and explorationCurrent TRL: 2 Target TRL: 5 Duration: 24 MonthsRef ESTER: T-8420 Harmonization

Dossier:N/A

Ref. Number: G513-020MM Budget: 500 K€Activity Title: Compact - 80ºC FreezerObjectives: The objective is to develop a compact -80 C freezer breadboard suitable for

upload and download of biological samples to and from the ISS in particularcompatible to transport not using the STS (Shuttle).

Description: Since Columbus is attached to the ISS, more biological experiments willperformed in this facility. Biological samples need certain constant temperature tomaintain their viability. So far the freezer in the shuttle for the upload of thesamples can only freeze down to -20 C with accuracy of +10 C in certainconditions. Cells are less viable in these temperatures because certain processesstill continue and cells have the risk to go into apoptosis, regulated cell death.Under these conditions there is a high risk that a lower concentration of cells oreven no living cells arrive in orbit, jeopardizing the quality of the experiment. Thismight result in discrepancies from the ground control measurements or even totalloss of the whole experiment. To compensate for that, scientist need to takecorrective measures by changing their procedures (e.g. in the TRIPLELUXexperiment) which still fosters high uncertainty for cell viability. This activity willdevelop an -80 C freezer breadboard for flexible upload/download of biologicalsamples, to ensure the viability of the cells. This freezer is mainly aimed attransport with SOYUS type carriers and has to be therefore compact and low inpower consumption to be compatible with the constraints.

Deliverables: -80 C freezer breadboard for a save upload of biological samples.Application: as early as possible to support the scientific operation of EMCS, BIOLAB, Kubic

etc presently on board ISS/Columbus.Current TRL: 3 Target TRL: 6 Duration: 18 MonthsRef ESTER: Harmonization

Dossier:N/A

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Ref. Number: G513-021MM Budget: 500 K€Activity Title: Rover performance prediction and evaluation toolsObjectives: Develop a rover performance assessment tool for the purpose of predicting the

overall performance of a rover and correlating rover experimental data withpredictions.Such tool is needed as there is presently no possibility to correlate the predictionof performance of single rover subsystems (e.g. wheel, chassis, piloting andnavigation functions) and the effective measured performance of a rover

Description: The activity shall:1. Identify methodologies for rover performance characterization2. Identify adequate measurement systems/tools for rover performance datagauging3. Design an architecture of a software tool:a. implementing the performance methodologies at1.b. integrating (*) a performance prediction simulatorc. implementing interfaces to the measurement systems/tools at 2.d. implementing functions to correlate predictions with measurements and toupdate the underlying prediction models4. Implement the tool5. Demonstrate the tool on a test case (*) The on-going GSTP activity (3DROV) is developing a simulator that predictsrover performance based on soil interaction,

Deliverables: Documents on methodologies to assess rover system chassis, piloting andnavigation performancesSoftware tool to assess the rover chassis, piloting and navigation performance,Report of test with correlated models

Application: ExoMars/ 2013 (TBC), Mars Sample Return/TRL 5 by 2015Current TRL: 3 Target TRL: 5 Duration: 30 MonthsRef ESTER: T-7719, T-883, T-8431 Harmonization

Dossier:N

Ref. Number: G513-022MM Budget: 300 K€Activity Title: Guided Mole IIObjectives: ESA has pioneered the concept of moles. The most recent development, the

“Guided Mole”, has been designed to burrow itself to the depth of 100 m. Theprototype produced is very promising, however some additional functionalities areneeded to validate the concept.The goal of this activity is to build on the “guided mole” achievements to provideincreased drilling speed and a complete waste management system.

Description: The activity shall:1. Review the outcome of the first “Guided Mole” activity and identifyimprovements to the present design2. Design the improvements and additions3. Implement improvements and additions4. Test and demonstrated the improved Guided Mole

Deliverables: Design and manufacturing files, Test Reports, Final Report, BreadboardApplication: TRL5 2010Current TRL: 4 Target TRL: 5 Duration: 18 MonthsRef ESTER: T-7793, T-8001 Harmonization

Dossier:Automation and Robotics -G1- Q1 2007



Ref. Number: G513-023EP Budget: 400 K€Activity Title: Development of a Lithium ion cell optimized for low temperatures (-20°C )Objectives: The objective of this activity is to develop lithium ion cell optimised for low

temperature performance (i.e. below -20 C) by selecting the electrolyte andelectrodes most suitable for such conditions.

Description: Some space applications would benefit from the improvement of the Li iontechnology at low temperatures, such as exploration missions (rovers). Differentfactors influence low temperature performances of Li ion cell like electrolyteconductivity, cell design, electrodes thickness, separator porosity.As shown in preliminary in-house activities in the ESBTC, present cells do have arather poor low temperature performance, but small modifications to theelectrolyte will result in significant improvement in terms of available energydensity, cycle life and degradation, in benefit to terrestrial applications as well.In a first phase a low temperature Li ion cell will be developed after selection ofthe electrolyte, electrodes materials, processes. The second phase will be the fullcharacterisation of the prepared cells by tests. In a third phase, someenvironmental tests will be performed in order to detect any show-stopper forCOTS cells, and development needed to prepare a space version of the cell willbe elaborated.

Deliverables: Technical Notes, Test Plan, Test Report, Final report, Space cell DevelopmentPlan, Cells

Application: All exploration missions e.g. Mars Sample Return and following explorationmissions


Dossier:Battery roadmap issue 1 revision 3,Activity D1, September 24 2006

Ref. Number: G513-024SW Budget: 300 K€Activity Title: Authoring environment for interactive 3D proceduresObjectives: Design and development of an authoring environment that can build 3D interactive

proceduresDescription: Manual procedure viewers are developed based on a paper legacy. Non-textual

procedure representation has not yet been deployed in the human spaceflightdomain, mainly due to the lack of good authoring tools. Tasks foreseen are- familiarization with space station procedures and on-board computer basedtraining material- familiarization with CAD/CAM outputs and digital human mannequintechnologies- development of an authoring environment for 3D procedures based on theexisting prototype- Demonstration of the product by preparation and evaluation of a sample set of3D procedures

Deliverables: Software environment for human spaceflight procedure authoring- ECSS E40 compliant documentation

Application:Current TRL: Target TRL: Duration: 12 MonthsRef ESTER: Harmonization

Dossier:H3

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Ref. Number: G513-025EC Budget: 1,900 K€Activity Title: One-axis inertial MEMS sensor developmentObjectives: Design, manufacturing and testing of a one-axis inertial MEMS sensor combining

the accelerometer, the gyro and the processing, power and interface functions intotwo co-packaged chips..

Description: The activity aims at designing, manufacturing and testing a miniaturized MEMSsensor that can provide one-axis rates and accelerations for a rover, micro andnano satellite and some EDL applications. This will be achieved by integrating aone-axis MEMS gyro and a one-axis MEMS accelerometer together within thesame chip and incorporating all support and interfacing functions on aco-packaged ASIC. A full EM shall be produced and tested. This activity is afollow on to the feasibility demonstrator activity.

Deliverables: One-axis inertial sensor prototypeApplication: TRL5 by 2012Current TRL: Target TRL: Duration: MonthsRef ESTER: Harmonization

Dossier:

Ref. Number: G513-026MC Budget: 350 K€Activity Title: Development of Thermal Insulation for Planetary Landers and RoversObjectives: The objective is to develop and characterise high efficiency thermal insulations

suitable for Mars/Lunar lander and rover surface missions.Description: Planetary surface missions are mainly driven by power consumption due to the

long diurnal cycles and the harsh environmental conditions. Thermal insulation forplanetary missions (to planets with atmosphere) differ from classical spacecraftMLI due to the potential use of e.g. aerogel, open foam and glass fibre. Theinsulation can be constructed with a combination of materials in order to increaseperformance for both the cruise phase and surface operations. The performanceof the insulation is dependent on the atmospheric composition, temperature,pressure, gravity. The insulating materials will need to be applied directly on thelander/rover external/internal walls, fitted to an electronic box or instrument,wrapped around electrical cables or applied to mechanisms. Such insulationconcepts may be required to withstand multiple installation and removal cycleswithout performance degradation and particle shedding. Furthermore, surfacemissions have stringent planetary protection requirements as well as demandingcontamination control. All these requirements could eliminate existing highefficiency materials due to inherent characteristic (e.g. particle shedding, cracking,brittleness). In order to reach high performance insulation concepts responding toall these requirements, the following steps are proposed:- Issue specifications for the insulation based on Mars/Moon surface missionrequirements.- Review available materials and insulation concepts in view of thesespecifications.- Perform measurements if material properties are missing- Select insulating materials and define concepts/lay-up/packaging in order to fulfilall the mission requirements and to cover all applications (rigid, flexible, etc.) andperform a complete trade-off- Build breadboards and perform characterisation tests- Define roadmap for the adaptation/improvement of existing or for thedevelopment of new materials and concepts, if and where needed.



Deliverables: Material characteristics of basic insulation materialsDefinition of thermal insulation conceptsBreadboard(s) and tests results of such conceptsRoadmaps for adaptation of existing or development of new materials

Application: TRL 8 by 2012Current TRL: Target TRL: 4 Duration: MonthsRef ESTER: Harmonization

Dossier:Not Harmonised yet


Activity Title: Mechanically Pumped Heat Transport Loop for Planetary Landers andRovers

Objectives: The objective is to develop a mechanically pumped heat transport loop in order toprovide a temperature control technology for a planetary lander or rover during thelaunch (in case RHU's or RTG's are used) and the cruise phase. Furthermore,such a mechanically pumped loop can also be used for the planetary surfacephase of the mission to regulate the internal Lander/Rover temperatures.

Description: The thermal control concept of future planetary landers and/or rovers will facevery demanding requirements to provide temperature control starting at launch upto and including the surface operation on the planet. Due to the very limitedavailable power resulting from the long diurnal cycles and the harsh environment,RHU and/or RTG might have to be used and will provide a constant heat loadduring the complete lifetime.Currently two technologies to provide such a temperature control - capillarypumped and mechanically pumped systems - are under consideration for suchapplications.For capillary pumped systems different design options exist in Europe and anadaptation to the use in planetary missions seems possible.Mechanically pumped loops could provide an alternative technology with differentadvantages/disadvantages.As mechanically pumped loops for such potential applications have not yetreached a similar maturity, the following activity is proposed:- Issue specifications for a mechanically pumped loop based on Mars/Moonsurface mission requirements in terms of power consumption, working fluid,operating temperature, material capability, mass, leakage and operational life.- Review available technologies and materials in view of these specifications.- Design a mechanical pump loop system concept- Build a breadboard and perform characterisation tests- Define roadmap to adapt/improve existing or to develop new technologies,where needed.

Deliverables: Specification for MPLMPL concepts and breadboard test resultsRoadmaps for adaptation of existing or development of newcomponents/technologies

Application: TRL 8 by 2013Current TRL: Target TRL: 4 Duration: MonthsRef ESTER: Harmonization

Dossier:Not Harmonised yet

Ref. Number: G513-028ET Budget: 1,000 K€

Activity Title: Lander Miniaturised proximity-1 communication package - EngineeringModel

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Objectives: The objective is to develop an EM of a standardised low weight relaycommunication package for future lander exploration and science missions.

Description: Driven by the robotic exploration program, there is a requirement to provide astandardised, low cost, compact and robust communications package on-board aLander or Probe to communicate with the data relay orbiter. The miniaturisedcommunications package must be able to receive telecommands and transmittelemetry and support basic navigation functionalities. Even more than on aOrbiter, where flexibility to support various landers is a key issue, the landercommunications package design drivers are mass and power consumption andthe necessity to support the CCSDS proximity-1protocol. To achieve minimalmass and power consumption, a 'RF on chip' or ‘system on a chip’ architecture isprobably to be employed. The proposed activity is part of a strategy to developstandardised relay communication package, both for orbiter and lander, that canbe flown on multiple missions of the exploration program. This philosophy of‘service provision’ (as opposed to conventional mission-specific assetprocurement) may be an welcome contribution to the evolving internationalexploration framework.

Deliverables: An Engineering Model (EM) of a miniaturised Prox-1 communication package.This transceiver shall include all the necessary data interfaces, modulator,baseband / analogue filtering, linear transmit output stage etc…based on astringent design specification.

Application: NEXT Mars Orbiter & NEXT Lunar Lander mission TRL 5 by 2012Current TRL: 3 Target TRL: 6 Duration: MonthsRef ESTER: T-7725 Harmonization

Dossier:TT&C transponder and payload datatransmitters

Ref. Number: G513-029MM Budget: 800 K€Activity Title: Detector arrays for Imaging Lidar systemsObjectives: This activity shall focus on the development of advanced detector arrays for

Imaging Lidar sensors.Description: Imaging Lidars (Light detection and ranging), or in other words three-dimensional

imagers, are considered a key enabling technology for the missions envisaged inESA’s Space Exploration Programme. Typically Imaging Lidars rely on scanningmechanisms that are still bulky and often considerably heavy for space missions(like robotic exploration of the solar system). On going ESA activities focus on thedevelopment of Imaging Lidar sensors that shall implement APD (AvalanchePhotodiode Arrays) detector arrays. However the number of pixels of this array(256 pixel detectors) is still small for the required FoV (Field of View) and spatialresolution for the applications in mind. A scanner mechanism is still required(however with relaxed scanning performance when compared with a singledetector system). Large-format APD or SPAD arrays as well as novel CMOSdetector arrays with in-pixel intelligence (such as recently emerging using cwmodulation techniques) - depending on the application (available signal levels) -are the prime candidate technologies for the detector as the critical component inthe next generation of imaging lidars.This activity shall study and develop novel detector arrays to be implemented infuture Imaging Lidar systems.1) Review, analysis and trade-off of novel detectors array technologies forImaging Lidars.2) Perform precursor experiments and delta development activities concerningdetector arrays technologies.3) Design, manufacturer and testing of a detector array for Imaging Lidar sensors.

Deliverables: Novel detector arrays for imaging LIDAR applicationsApplication: TRL5 by 2015



Current TRL: Target TRL: 5 Duration: MonthsRef ESTER: Harmonization

Dossier:Detector Roadmap (OpticalInstruments;, 2006)

Ref. Number: G513-030SW Budget: 600 K€Activity Title: Autonomous and remote operations reference facility for roboticsObjectives: Develop a reference facility for robotics remote operations

This facility shall allow the validation of operational concepts for future roboticmissions and provide the basis for operational simulators to support operationsduring the flight phase for the development of operation plans and their validation,assisted by intelligent planning agents

Description: In order to allow the proper testing of operational concepts and consolidation ofrequirements for robotics teleoperations this facility shall provide the virtualenvironment (simulation and interface) to allow the easy modelling of futurerobotic missions.In order to be able to support the design and operations at an early stage, aneasily configurable and modular framework needs to be established, able tomodel and simulate complex robotic missions. These missions need to expose thesame operational interfaces as the real system and shall allow the link to anoperational front-end for these missions.In order to support the operations, planning assistants, visualisation possibilities,monitoring capabilities need to be basic functions of this reference facility.The development steps will include:• Overall architecture / framework definition• System simulation architecture and reference models (generic models)• Modelling environment to instantiate mission scenarios• Operational front-end with command and control functions• Planning modules• Visualisation options for planning and monitoring purposes (VR)

Deliverables: Reference facility for teleoperationsTest and development environment at ESTEC

Application: Remote robotics mission / 2010-2015Current TRL: Target TRL: Duration: 24 MonthsRef ESTER: T-871 Harmonization

Dossier:


Activity Title: Orbiter Software Defined Radio Proximity-1 Link Communications package -engineering model

Objectives: The objective is to develop an EM of an Orbiter standardised flexible andmultimission data-relay communication package based on CCSDS Proximity-1protocol using software defined radio as the enabling technology.

Description: The current European proximity-link transceivers (as developed in the previousESA missions, for instance Beagle) are limited in flexibility as they are based on alow level of integration between the RF and the digital part. Using the SoftwareDefined Radio technology (similar to that implemented by NASA/JPL for theElectra transceiver) allows a higher level of flexibility with the possibility of unitreconfiguration. Using the software defined approach provides the capability toadd/change functionality by simply changing the software version. This softwareupload (software patch) can be done pre-launch or in orbit, which makes the unitvery flexible and provides the capability to support multiple missions. Thismultimission approach is particularly interesting in case of an Orbiter with

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data-relay capabilities and a long lifetime (such as Mars Express). This way it cansupport different lander missions (European, American and other internationalspace agencies) even the ones it wasn’t intended to serve in the first place.Allowing post-launch reconfigurability of the protocol and signal processingfunctions over the Orbiter lifetime supports protocol updates and provides thepossibility to respond to unanticipated mission scenarios. Secondly, by ensuring astandardised and interoperable data-relay infrastructure allows any lander tomake use of multiple data-relay assets, thereby increasing the science returnwhile at the same time reducing mass and power requirements on the lander. Theultimate goal would be to equip every science Orbiter with a standardised relaypackage, taking away some of the technology burden of small lander missions.This activity is the follow-on of the TRP activity, aiming at developing anengineering model of a reprogrammable Proximity-1 transceiver, based on thesoftware defined radio architecture. The transceiver shall support the Proximity-1protocol in its entirety including support for the full duplex mode of operation. Thetransmit and receive carrier frequencies should be reprogrammable, by use ofsoftware uploads, to any frequency allocated for use by the Proximity-1 standard(i.e. 390 – 450 MHz). The transceiver shall be designed in a modular manner thatallows tailoring of the basic functions for to future missions. Finally, theproximity-link transceiver to be developed shall also support high data-rates andadaptive data-rate. The main application domain is an Orbiter requiring data-relaycapabilities and a long lifetime (such as the ESA Mars Express mission).

Deliverables: An Engineering Model (EM) of a software defined, reprogrammable Prox-1communication package. This transceiver shall include all the necessary datainterfaces, modulator, baseband / analogue filtering, linear transmit output stageetc…based on a stringent design specification.

Application: NEXT Mars Orbiter TRL 5 by 2012Current TRL: 3 Target TRL: 5 Duration: MonthsRef ESTER: T-7725 Harmonization

Dossier:"Harmonisation dossier for TT&Ctransponder and payload data


Activity Title: Lander Compact Dual UHF/X-band Frequency Communication package -Engineering Model

Objectives: The objective is to develop an EM of a standardised compact dual frequency(UHF/X-band) communication package for lander exploration missions.

Description: This activity targets the design and development of a communications package forplanetary probes/landers/rovers able of communicating both with an Orbiter (fordata relay) and directly to the Earth from Planet surface.

In the ExoMars mission, the UHF proximity-link with a data-relay Orbiter will bethe primary link for returning science data. The use of relay links is attractive forreasons of power efficiency and higher possible data-rates compared todirect-to-Earth links. Nevertheless, the ExoMars rover includes also a direct linkto/from the Earth next to this UHF proximity link to the Orbiter. The direct link withEarth will be in the X-band Deep Space frequency allocation and used inemergency situations and for contingency operations, as well as during the entry,descent an landing phase to transmit health status beacon tones. In addition, thedirect to Earth link might be useful also for navigation and RadioScienceExperiment.

Instead of fitting two seperate transponders into the already packed Rover, asingle unit serving both UHF and X-band links would bring important savings inmass and volume without sacrifising functionality or mission safety. In addition,this implementation would open up the possibility to use the proximity link in the



X-band (making use of directive antennas already in place for the direct to Earthlink (see ExoMars baseline)), boosting the data that can be relayed an order ofmagnitude. Nowadays, this architecture is made possible thanks to the advancesin digital signal processing which allows easily processing the UHF Proximity-1protocol and the classical X-band TT&C signals.

The target of this activity is to design and develop a dual UHF/X-band frequencytransceiver serving both the Prox-1 and Deep Space links.

Deliverables: An Engineering Model (EM) of a dual frequency UHF/X-band communicationpackage. This transceiver shall include all the necessary data interfaces,modulator, baseband / analogue filtering, linear transmit output stage etc…basedon a stringent design specification.

Application: NEXT Mars Orbiter & NEXT Lunar Lander mission TRL 5 by 2012Current TRL: 3 Target TRL: 5 Duration: MonthsRef ESTER: T-7725 Harmonization

Dossier: TT&C transponder and payload datatransmitters

Ref. Number: G513-033MC Budget: 500 K€Activity Title: Additional Unit for Increased Water Loop Closure Description: The objective of this activity is to study, develop, manufacture and test a urea

transformation unit for increased water loop closure.The following tasks shall beperformed:- Perform a in-depth characterisation of the core processes- Design and manufacturing of a breadboard unit for experimental verificationsupported by relevant analyses- Performance of comprehensive test programme

Deliverables: Technical documentation, design, test results, urea transformation unit includinginstrumentation and interfaces with membrane based filtration system.

Application: Human exploration - life support / Preparation for Exploration / 2012Current TRL: 2 Target TRL: 4 Duration: 30 MonthsRef ESTER: T-7785 Harmonization

Dossier:N/A

Ref. Number: G513-034MC Budget: 450 K€Activity Title: Air Sampler Unit Description: The objective of this activity is to design, build and test a functional demonstration

breadboard of an air sampler for microbial identification.The following tasks shall be performed:- Design of breadboard unit based on previously selected core technologies,supported by relevant analyses and taking into account the interfaces with themicrobial identification unit- Manufacturing of BB unit- Performance of comprehensive test programme

Deliverables: Functional breadboard and technical reportsApplication: Human exploration - life support / Preparation for Exploration / 2010Current TRL: 3 Target TRL: 5 Duration: 24 Months

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Ref ESTER: T-7781 HarmonizationDossier:

N/A

Ref. Number: G513-035MC Budget: 400 K€Activity Title: Determination of Biomass in Complex Bioprocesses Description: The objective is to validate a method and associated hardware for the monitoring

of biomass for the monitoring of biomass in complex bioprocesses, in theperspective of accurate and robuste control of the bioprocess.Tasks included in the proposed activity cover extensive data collection onbiomass concentration in complex bioprocesses to develop and validate arelevant method of biomass determination. Associated hardware will bedeveloped and validated in relevant environment.

Deliverables: Biomass determination method, design files, developed hardware, validation testsreport,


Dossier:N/A

Ref. Number: G513-036MC Budget: 400 K€Activity Title: Development of Methane Recovery Assembly Description: The objective of this activity is to study, develop, design, manufacture and test a

breadboard of a Methane pyrolysis unit for the ARES system.

Deliverables: Technical documentation, design, breadboard hardware and breadboard testresults


Dossier:N/A

Ref. Number: G513-037MC Budget: 150 K€Activity Title: Feasibilty Study for Manned BIORAT Campaign Description: The objective of this activity is to assess the feasibility and give recommnedations

to test BIORAT technology during a short manned isolation test.�Within this studyit is proposed to investigate the feasibility and establish main recommendation fora one month manned campaign, with total air closure, using BIORAT technolgy asa precursor of MELiSSA loop.

Deliverables: ReportsApplication: Human exploration - life support / Preparation for Exploration / 2015Current TRL: 2 Target TRL: 3 Duration: 12 MonthsRef ESTER: T-7786 Harmonization

Dossier:N/A



Ref. Number: G513-038MC Budget: 400 K€Activity Title: High Performance Pressurized Structure Description:

Improve the structural restraint concept for inflatable pressurized structures�Forthe current high pressure, inflatable structures developments, the structural layeris built using circumferential and meridional restraints, around an internal core.This implies a complex manufacturing and assembly procedure and analyticalverification. In this activity, it is proposed to study an alternative structural layerconcept, which would reduce its mass, manufacturing costs and ease itsnumerical analysis. The activity should encompass a design phase, supported byanalyses and completed by a test of a breadboard. The results of this study wouldmainly be relevant for habitats, airlocks and docking connectors, but could also beused for radiation shielding structures or fluid containers.

Deliverables: design files, test documentation for breadboard test, Development PlanApplication: Human exploration - habitat / all inflatable modules/habitats etcCurrent TRL: 2 Target TRL: 3 Duration: 18 MonthsRef ESTER: T-309 Harmonization

Dossier:N/A

Ref. Number: G513-039MC Budget: 450 K€Activity Title: Higher Plant Canopy Evaluation Description: The objective of this activity is to study, develop and test the main functions of an

evaluation tool fo a ahigher plant canopy.�Technology state-of the art, conceptdefinition, main functions testing will be performed in the course of the study inorder to give recommendation on a preliminary design of procedure and hardwarefor monitoring a whole canopy.

Deliverables: Conceptual design, functional breadboard, tests documentationApplication: Human exploration - life support / By 2015Current TRL: 3 Target TRL: 4 Duration: 30 MonthsRef ESTER: T-7787 Harmonization

Dossier:N/A

Ref. Number: G513-040MC Budget: 450 K€Activity Title: Inflatable Container for Life Support Waste Water Description: The objective of this activity is to study, design, manufacture and test a ground

prototype of an inflatable container for LSS waste water.Taking into account current ESA studies in structure and manned spaceflight (i.e.IHAB), a concept of a generic inflatable wastewater container will be studied.Trade-off addressing the structure, material selection, and design will beperformed. Within this study the characteristics of life support wastewater (pH,temperature, presence of particles, etc.) as well as the space environmentcharacteristics (reduced gravity, mass, deployment,..) will be considered. Aground prototype will be designed, manufactured and tested.

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Deliverables: Technical documentation, test documentation, design files, ground prototypeApplication: Human exploration - life support / Preparation for Exploration / 2015Current TRL: 2 Target TRL: 3 Duration: 24 MonthsRef ESTER: T-7785 Harmonization

Dossier:N/A

Ref. Number: G513-041MC Budget: 1,500 K€Activity Title: MELiSSA Pilot Plant Description: The objective of this activity is to demonstrate and validate regenerative life

support systems on ground.Due to high interaction between all recyling loops (i.e. water, air, food,…) andcurrent technological advancement, there is an inreased requirement to performintegrated tests. This activity will concentrate on the following tasks:- study and development of interface technologies between all MELiSSAcompartments (i.e. separation technologies, technologies for specific extraction ofcontaminants..),- integration of interfaces and test- development and implementation of quality assurance and quality control, in theperspective of a full integration of the MELiSSA loop.

Deliverables: Design reports, proven technologies, technical documentation, test reports,developed hardware, improved knowledge


Dossier:N/A

Ref. Number: G513-042MC Budget: 550 K€Activity Title: Plant Stress Detection Unit Description: The objective of this activity is to study and test the accommodation of a stress

detection unit within the MELiSSA higher plant compartment. Optimisation andtesting of the critical functions of the hardware will be performed in view of furtherintegration in the MELiSSA Higher Plant Compartment. The following tasks shallbe performed:- Trade-off of possible accommodation concepts using previously selectedtechnologies taking into account all interfaces with the existing MELiSSA higerplant compartment- Design of breadboard unit supported by relevant analyses- Manufacturing and integration into higher plant compartment- Performance of comprehensive test programme

Deliverables: Accommodation study, Breadboard, test documentationApplication: Human exploration - life support / By 2015Current TRL: 3 Target TRL: 4 Duration: 30 MonthsRef ESTER: T-7787 Harmonization

Dossier:N/A



Ref. Number: G513-043MC Budget: 600 K€Activity Title: Waste Preparation Unit Description: The objective of this activity is to study, design and manufacture a fully automated

waste preparation unit for further waste degradation.The following tasks shall beperformed:- Trade-off of possible technologies taking into account all interfaces with wastecollection units and waste degradation units (MELiSSA first compartment)- Design of unit supported by relevant analyses- Manufacturing and integration- Performance of comprehensive test programme

Deliverables: Design files; tests documentation; fully automated waste preparation unit,including interfaces with waste collection unit and waste compartment


Dossier:N/A

Ref. Number: G513-044MC Budget: 600 K€Activity Title: Wet Oxidation Unit Description: The objective is to study, design, manufacture and test in a relevant environment

a continuous or semi-continuous pilot prototype of a wet oxidation unit including itsinstrumentation and all interfaces with the waste compartement of MELiSSA.Thefollowing tasks shall be performed:- A sizing/scale-up based on the technology selected during previous activities- A study and design of all interfaces with the waste degradation unit (MELiSSAfirst compartment)- Design of complete unit supported by relevant analyses- Manufacturing and integration- Performance of comprehensive test programme

Deliverables: Technical documentation, design, test results, wet oxidation unit includinginterfaces with the waste compartment and control system.


Dossier:N/A

Ref. Number: G513-045 Budget: 300 K€Activity Title: MELISSA Space Adaption Phase 3: Moon base Life supportObjectives: To define a MELiSSA loop recommended design for a Life Support module of a

manned Moon base.

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Description: A considerable amount of basic research and engineering data has been andcontinues to be generated by the MELISSA partnership. The time is nowappropriate for preliminary sizing of space systems. Based on previous workphases, which leads up to a preliminary concept, it is now proposed to establish arecommended design for a Life support module within a Moon base inspired fromMEliSSA technologies. Main target will be total closure of air and water loop, aswell as 40 % closure of the food loop.ALISSE criteria will be used for trade-offand final evaluation of the recommended design

Deliverables: Reports/ designApplication:Current TRL: 3 Target TRL: 4 Duration: 24 MonthsRef ESTER: T-7762 Harmonization

Dossier:

Ref. Number: G513-046MC Budget: 550 K€Activity Title: MELISSA Genetic charcaterisation Phase 3Objectives: In this phase it is proposed to built on the experience gained within phase 2 and to

focus now on the definition and validation of procedures to monitor/detect stressexpression in MELiSSA compartments II and IVa in order to buildrecommendations for on-line stress detection technology

Description: Containing microbial processes, MELiSSA system can be subject to geneticevolution as a consequence to stress exposure. Consequently, a robust control ofthe overall system requires the detection of any change of the process nature (i.e.genetic evolution).Within this third phase, as a follow-up from the 2nd phase, wepropose to finalise the stress related gene expression study of compartment II andIV a, then to establish and validate procedures associated to a continuous stressdetection monitoring. Requiremenst for an on-lin sensors will be finallyestablished.

Deliverables: Tests Documentation, scientific reports, sensor requirementsApplication:Current TRL: 2 Target TRL: 3 Duration: 30 MonthsRef ESTER: T-7788 Harmonization

Dossier:

Ref. Number: G513-047MC Budget: 450 K€Activity Title: Axenicity control within MELISSA compartment 2 and IV aObjectives: To develop and test sensors for axenicity control of MELiSSA compartment II and

IV aDescription: Within MELGEN 2 activity , methods to monitor the axenicity of compartments II

and IV a have been tested and validated. Requirements for the relevant sensorhave been established. Within this activity it is proposed to finalise trade-off for thetechnological solutions, and to design, construct and test the sensor. Thisdevelopment will include all steps from sample collection up to detection.

Deliverables: Trade-off report, Design files, tests documentation, BreadboardApplication:Current TRL: 2 Target TRL: 3 Duration: 24 MonthsRef ESTER: T-7762 Harmonization

Dossier:



Ref. Number: G513-048MC Budget: 450 K€Activity Title: Recycling of tissues and packaging wastes phase 1Objectives: To evaluate the feasibility of thermophilic transformation of housekeeping and

packaging waste into monomersDescription: In order to maintain cleanliness and hygiene in manned habitats, strict

housekeeping procedures are applied. These procedures imply the use ofbiocide/fungicide impregnated wipes, which composition varies from cellulose topolyester. After use, these wipes have to be discarded and consequently add upto the mission wastes. The same applies to the main part of food packaging. Inorder to reduce wastes mass, as well as launch mass, recycling of these specificwastes shall be envisaged. The feasibility of transformation of these wastes intosimple molecules (i.e. monomers) needs to be assessed and a wipe andpackaging production system (i.e polymerisation) has to be studied, defined andtested. This activity will focus on assessing the feasibility of wipes and packagingdegradation into monomers. The typical composition of these wastes will bedetermined and a prototype treatment system will be defined, assembled andused to assess the feasibility of thermophilic degradation of such waste material.

Deliverables: Technical documentation, prototype thermophilic degradation system design filesand hardware, tests results


Dossier:

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THEME 4.- SPACE TRANSPORTATION AND RE-ENTRYTECHNOLOGIES

Ref. Number: G514-001MP Budget: 4,800 K€Activity Title: E-VEGA Electric Propulsion Service Module technologies preparation.Objectives: The objective of the proposed activity is to achieve technical confidence (i.e.

based on experimental testing) on all new European technologies selected withinthe E-VEGA Electric Propulsion Service Module study (completed under TRP) inorder to achieve system level maturation status compatible with a System LevelPreliminary Design Review.

Description: The E-VEGA Electric Propulsion Service Module has been identified in the frameof a successful TRP study as a new enabling way of increasing the launchercurrent mission envelope (enabling the VEGA launcher to perform GEO,MEO/Galileo Orbits insertion). The E-VEGA concept is not in conflict with existingVEGA evolution scenarios, being capable to be added to the current or evolvedupper stage concepts for VEGA. The E-VEGA Electric Propulsion Service ModuleTRP study has highlighted the need to address a preliminary development of allthe technologies selected for which high level of confidence is required in the earlystage of the programme. The proposed activity shall focus on the technologiesidentified as 'high criticality' with respect to the E-VEGA Electric PropulsionService Module study. The following sub-activities shall be addressed within theproposed activity: 1) High Power Hall Effect Thruster prototyping (development &testing); 2) Power Supply and Control Unit (including high voltage switch)prototyping; 3) Solar Arrays Technology Validation; 4) Electric Propulsion PointingMechanism for High Power HET preliminary design; 5) Other S/S DefinitionActivities. Separate budget shall be allocated to the different sub-activities.1) High Power Hall Effect Thruster prototyping (development & testing) Budget:1500K€. Description: initiating the development of a high power Hall EffectThruster capable of operation at high thrust density, 490mN, with sufficientlifetime, 11000 hours, in the high-voltage regime with specific impulse above2500s in order to satisfy the E-VEGA Electric Propulsion Service Modulerequirements. In this frame, the Contractor shall prepare a preliminary design of a10kW-High Specific Impulse HET using known scaling law to compute the overallthruster performances. Being the high ISP provided by the thruster consideredone of the main driver for the application, the Contractor shall investigate thehighest value reachable within the selected design. The selected thrusteroperational point will be agreed by the Agency through approval. The design ofthe thruster prototype shall include a preliminary magnetic mapping in order tosize correctly the internal and external magnets and shall be completed bymechanical and thermal analyses. Electrical, mechanical, and thermalrequirements of the various thruster's parts shall be defined. During this phase theContractor shall also investigate the feasibility of introducing a magnetic steeringcapability (''Internal Thruster steering capability'') within the thruster design greaterthan +/- 10 deg. Moreover the contractor shall identify the list of materials andprocesses to accommodate demanding operating temperatures and mechanicallevels relevant to the defined class of thruster. The Contractor shall manufacture aprototype that fully incorporates all functional elements of the technology,including cathodes (nominal and redundant). The prototype shall undergo anintensive characterization test campaign in order to define the operationalmargins, to demonstrate compliance to required performances and to characterisethe influence of the increased discharge voltage on the discharge stability, on thethermal behaviour of the thruster and on the ceramic erosion rate. The resultsfrom the test campaign shall be used to validate the preliminary thruster design inpreparation of an Upper Level Model definition (e.g. channel design and ceramicthickness). The test set up shall foreseen the use of the breadboard Power Supplyand Control Unit (see sub-activity 2). The characterisation test shall be performedin accordance to a test plan and a test procedure that shall be submitted to the



Agency for approval.2) Power Supply and Control Unit (including high voltage switch) prototyping.Budget: 800K€. Description: design a breadboard Power Supply and Control Unit(PSCU) to drive the E-VEGA Electric Propulsion Service Module High Power HETand manufacture a prototype including software to be used during EP ThrusterPrototype Characterization Test. The prototype shall be able to verify electricalarchitecture concept, power converter components and thruster control processesin agreement with EPSM requirements. The prototype shall be integrated duringthe EP Thruster characterization test in order to verify the performances whencoupled with the thruster, the Hardware and Software interfaces between thePSCU and the Thruster, XFCS, Thruster Diagnostic System and 1553 bus.???3) Solar Arrays Technology Validation. Budget: 1500K€. Description: design of thecritical technologies of a solar array capable to satisfy the E-VEGA ElectricPropulsion Service Module requirements (BOL power of 13KW, compatibility withstowing volume and dimensions available under existing Vega Fairing, lowrecurring cost (120 $/w), low mass (120 Kg), high efficiency in order to limit the SAtotal surface below 55 m2). In a second phase the Contractor shall design,manufacture and test a demonstrator solar array.4) Electric Propulsion Pointing Mechanism for High Power HET preliminarydesign. Budget: 500K€. Description: perform a preliminary design of an ElectricPropulsion Pointing Mechanism (EPPM) compatible with E-VEGA ElectricPropulsion Service Module High Power Electric Propulsion Thruster design toprepare a back up solution to the ''Internal Thruster steering capability'' selectedduring the E-VEGA Electric Propulsion Service Module study. In this frame theContractor shall prepare a preliminary design of a mechanical thruster pointingmechanism capable to accommodate one or two 10kW HET and to allow steeringcapability greater than +/- 10 deg. The mechanism shall provide structural supportto the main thruster and to the redundant one or to one of the two and shallchange their relative position with respect to the spacecraft according with EPSMrequirements, during every phases of the mission. A trade off between thecapability of accomodating one or two thrusters shall be performed. TheContractor shall consider the environmental constrains as defined by the EPSM.Electrical, mechanical, and thermal requirements of the various parts shall be alsodefined.5) Other S/S Definition Activities. Budget: 500K€. Description: develop theremainig criticality subsystem design and documentation needed to support theE-VEGA Electric Propulsion Service Module System Preliminary Design Review.Subsystem includes: AOCS, XFCS for pressure and flow regulation, TTC, OBDH,Thermal Control and Structures. In this frame the Contractor shall prepare thedesign documentation relevant to each subsystem considered.

Deliverables: 1) Thruster prototype, Preliminary Design Report, budgets and interfaces, list ofprocesses and materials, Characterization Test Plan & Procedure,Characterization Test Reports, DDQ Plan and schedule.2) Power Supply and Control Unit Breadboard, Design Report, Control Software,Coupled test report, budgets and interfaces, DDQ Plan and schedule. 3) Solar Array Technology Demonstrators, Solar Array Technology Test Reports,budgets and interfaces, DDQ Plan and schedule. 4) E-VEGA Electric Propulsion Service Module EPPM Preliminary Design Report,budgets and interfaces, DDQ Plan and schedule. 5) Subsystem Documentation Data-package for S-PDR.For all the sub-activities considered, the candidate programme to reach TRL 8/9 isVEGA Evolution.


Dossier:

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Ref. Number: G514-002ED Budget: 1,000 K€Activity Title: Safety oriented reference architectures for man tended systemsObjectives: Implementation of the core "building blocks" of the safety oriented reference

architecture, in particular of the TM-TC, I/O and buses as defined by the pilotactivity on Safety oriented reference architecture TRP (SD4) and complementedby the Fault Tolerant Computer, step 2, activity that shall make available theprototype of the FT computer to build up a reference avionics test-bench(ironbird).This test bench will allow to perform full scale implementation (hardware andsoftware) and validation of on board processing chain on representative hardware(function and performance) corresponding to selected “use case” mission thatshall be provided by the projects (space transportation, launcher).

Description: To implement the I/O and on board communication/data acquisition/ main systemperipherals support of the reference architecture.To perform the integration of the Fault tolerant computer with the I/O and systemsperipheral (space link interface, mass memory…)To develop a “Development and Test “support system that shall have thecapability of emulating the necessary stimuli as necessary to test/validate theapplication software as well as to exercise the fault tolerance/avoidancecapabilities of the system by injecting faults and record results of automated testsequences.To develop service layer software and test applications software representative offuture mission scenarios (performances, RAMS requirements)

Deliverables: Reference test bench for man tended safety oriented architectureincluding Test and development environment to support fast prototyping/proof ofconcept exercisesTest report and test analysisRecommendations for any delta evolution of equipment under evaluation towardsfinal flight implementationRoadmap towards certification

Application: TRL 6 in 2011.Current TRL: 3 Target TRL: 7 Duration: 24 MonthsRef ESTER: T-959,

T-7747,T7796,T-7800,HarmonizationDossier:

Avionics-Embedded Systems Avionics,S2 2006, A3 and G1


Activity Title: Delta-Development of SEPCORE based Heatshield for Earth Entry Capsuleof Sample Return Missions

Description: The objective is to develop, build (breadboard) and test a heatshield system for

the Earth entry capsule of a sample return mission (e.g. Mars, comets, asteroids)based on the SEPCORE concept. The ablative material developed in a parallelactivity (under TRP) shall be considered. A typical entry environment ischaracterised by peak heat fluxes of 15-20MW/m2 and heat loads up to200MJ/m2.

The work to be performed within this activity includes:o Review of the results from the previous activity and definition of requiredconcept modification for a sample return application.o Verification of representative large scale manufacturing capabilities.o Development and qualifiaction of a suitable mounting technology of the ablativeTPS to the hot structure.o Breadboard design, manufacturing and testing under representative conditions(15-20MW/m2).



Deliverables: Breadboard, documentationApplication: Sample return missions, e.g.MSR or Marco PoloCurrent TRL: 2 Target TRL: 5 Duration: 18 MonthsRef ESTER: T-8282, T-8141 Harmonization

Dossier:NA

Ref. Number: G514-004MC Budget: 250 K€Activity Title: Development of Secondary Protections for Hot Structures Description: The objective is to develop and verify a secondary protection system to be placed

underneath a hot structure (e.g. leading edge) with the aim to mitigate the risk of acatastrophic failure in case of a damaged outer structure (e.g. micrometeorid ordebris impact).

The development shall be based on a ceramic foaming-up system developed in aprevious TRP. In this activity the following tasks shall be performed to raise theTRL: Step 1: Improvement of material manufacturing process; manufacturing ofabout 50 test samples; performance of extensive plasma wind tunnel tests,extensive flame tests and key mechanical tests.Step 2: Evaluation of test results and establishment of a preliminary design database. Analytical estimation of mass budget for a potential vehicle (e.g. IXV) andassessment of residual risk after implementation of the measure.Step 3: Design, manufacturing and test of a demonstrator (larger dimensions,including insulation and ceramic layer).

Deliverables: Material samples, breadboard demonstrator, documentationApplication: Human entry missions, e.g. CSTSCurrent TRL: 2 Target TRL: 5 Duration: 18 MonthsRef ESTER: T-8280 Harmonization

Dossier:NA

Ref. Number: G514-005MP Budget: 700 K€Activity Title: Enhancement of Plasmatron operating capabilities Description: o The contractor shall organize, plan and realize the necessary improvement and

adaptation for the Plasmatron facility concerning the power supply hardware withthe aim to improve steadiness of the flow .o The contractor shall design a dedicated supersonic nozzle for the VKIPlasmatronm to enhance the aerothermodynamics testing capabilities of thefacility. He should ensure the testing procedure in new testing configurationallowing off-stagnation point studies.o The contractor shall harmonize the suitable measurement techniques to supportthe extended studies for new testing configuration. He should pay attention to theassessment of the measurement techniques used for the qualification of the newcapabilities of the Plasmatron facilities. . The contractor shall adapt/develop the CFD tools for supersonic plasma flowscorresponding to the new operating capabilities and testing configuration.o The contractor will also adjust the data-processing tools previously develop foranalysis of experimental data. He should also set-up the methodology for groundtesting duplication of real flight conditions tailored to the improved Plasmatronfacility.

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o The new operating envelope of the Plasmatron facility should be re-definedshowing the enhancement of its testing capabilities. He could also point up thecomplementarities through a standard comparison with current high enthalpyfacilities.o The contractor shall properly address the flight extrapolation methodology inrelation with the new potentialities of the Plasmatron facility and use EXPERT andIXV as examples.

Deliverables: technical notes, experimental adat and analysisApplication: All earth reentry vehicles, planetary probes , future launchers and debris analysis .Current TRL: 4 Target TRL: 6 Duration: 36 MonthsRef ESTER: Harmonization

Dossier:B19/B26

Ref. Number: G514-006MP Budget: 1,500 K€Activity Title: Prediction methods for propellant management devices Description: Objective of this activity is the provision and validation of a software environment

that allows to predict the effects of fluid sloshing in tanks on the space craftdynamics.Fluid sloshing in tanks can be generated by, e.g. attitude control manoeuvers andleads to time depedent forces and moments acting on the satelite until thesloshingis dissipated by friction.. A further consequence is the large uncertainty related tothe fuel position in tanks, endangering uninterupted fuel supply to the engine, ifthe fuel mass is temporarily not covering the engine feeding pipe inlets in the tankdue to large scale sloshing motion.This software shall incorporate engineering models, e.g. for the flow in PMDs ofdifferent types, or the effects of diaphrams or membranes placed on the free fuelsurface, as necessary. It shall also offer the possibility of validating advancedsloshing models against linearized models, e.g. spring mass-damper-systems forthe simulation of the effects of fuel sloshing on the space craft dynamics. Forpractical applications, especially for space craft with a large percentage of fuelmass, e.g. ATV, the system shall provide the possibility to couple the flowsolution to a six-degree-of-freedom model of the space craft dynamics.

Deliverables: Software / manuals / technical reports and numerical data from validationApplication: All future missions and space craft that use PMDs as capillaty devices or

membranesCurrent TRL: 4 Target TRL: 6 Duration: 24 MonthsRef ESTER: Harmonization

Dossier:A14

Ref. Number: G514-007MP Budget: 500 K€Activity Title: ESPSS: European Space Propulsion System SimulationObjectives: A first version of the ESPSS-library is in the make, forming the first basis of an

European tool. On this basis, the tool will be extended with advanced componentmodelling related to tanks, lines with their components (filters, valves, pumps,…),multi-phase and combustion for both steady and unsteady phenomena.



Description: GSTP Detailed model description, implementation and validation based onexperiments for particularComponents of European make such as valves, igniters, thrusters,….

Deliverables: technical notes and experimental and numerical databaseApplication: Propulsion systems/launchersCurrent TRL: 3 Target TRL: 4 Duration: 18 MonthsRef ESTER: Harmonization

Dossier:A7

Ref. Number: G514-008MP Budget: 2,000 K€Activity Title: Kinetic shock tube for radiation data base for planetary explorationObjectives: The objective of the present activity is to investigate high temperature gas

dynamics as they are involved in hypervelocity planetary re-entry. Development ofadvanced physical modelling, as thermo-chemical non-equilibrium and radiation,is a key point for design of probes and vehicles for planetary mission. Howeveronly little database are available to consolidate the models elaborate, and suchactivity demand a complete procedure from the instrumented facility to themodelling implementation in the data processing. Thus such development requireexperimental results based on dedicated set-up like shock tubes suitable forre-entry condition duplication. Moreover if the shock tube facility represent aconvenient tool for the accurate replication of very high speed re-entry conditions(> 10km/s) it should also be able to complement studies carry out in plasmafacilities and classical hypersonic wind tunnels. Attention must be focus as well onadapted optical diagnostics together with appropriate data processing techniquesand efficient numerical tools.All these elements should be integrated for a proper validation process of currentphysical models used to describe high temperature effects on re-entry flows andhelp to built-up efficient tools for vehicle design. Establishement of a Europeanshock tube dedicated to kinetic studies for high temperatures (more than 6000K).

Description: • The contractor shall qualify and assess the experimental set-up for re-entrycondition duplication.• He shall adapt the appropriate measurement techniques for fast measurementsand optical diagnostics with dedicated calibration.• The contractor shall investigate up-to-date thermo-chemical non-equilibriumstudies including collissional-radiative models and integrate activities on radiationmodelling.• The contractor shall develop in parallel numerical tools to data process theexperimental results and set-up validation process for physical modelling studies.• The contractor should propose physical model validation activity based onmeasurements collected on the tools and techniques previously set-up. Thisvalidation should also aims to the cross comparison of shock tube and plasmatronspectroscopic results. A dedicated shock tube shall be developped andinstrumented. Tests will be performed for various gas mixtures, to providespecrally resolved emission and absorption spectra, as a minimum. Moreadvanced techniques shall also be assessed, and if possible demonstrated.Theobtained results will be compared with documented results.

Deliverables: Technical notesApplication:Current TRL: 3 Target TRL: 5 Duration: 36 MonthsRef ESTER: Harmonization

Dossier:

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Ref. Number: G514-009EC Budget: 600 K€Activity Title: Fault Tolerant Flight Control System ComponentsObjectives: To develop and validate the core components of fault tolerant flight control

systems (FTCS): fault detection and identification, active system restructuring,reconfigurable flight controller, reconfigurable flight path planning, on-line systemidentification, and mission adaptation.

To integrate the core components and demonstrate the functionality of eachcomponent of the FTCS architecture for a given reference mission.

Description: Currently ESA and national agencies are evaluating various concepts of reusablelaunch vehicles. One of the critical elements for such future systems isrepresented by the guidance, navigation and control system, which is responsiblefor piloting the vehicle along a reference trajectory. To address the goal ofincreasing vehicle safety and reliability, there is now a significant interest inreconfiguration technologies for flight control systems. The reconfigurationproblem, both at subsystem and system levels, e.g. landing to alternate site incase of abort/contingency cases, is one of the most important and challengingaspects for future reusable space transportation vehicle. Over the last years, anumber of researchers have developed reconfigurable control systems(inner-closed-loop) for a variety of flight vehicles, and promising results wereobtained for systems with sufficient control actuation redundancy. As thisapproach is not sufficient for future reusable launch vehicles, due to their minimalsuite of control actuators, a guidance system (outer-closed-loop) withreconfiguration capabilities is also required to satisfy vehicle and controlconstraints and to achieve a safe abort.

In the light of the above consideration, the aim of the proposed activity is todevelop and validate the core components of fault tolerant flight control systemsable to fly a variety of vehicle types in multiple scenarios, as well as handledispersions, failures and abort requirements in a robust fashion. Special attentionwill be given to the development of advanced control concepts that requireminimum ground effort for retuning and analysis. Specific tasks to be performedinclude:- Analysis and trade-off of fault tolerant flight control system architectures forsafety critical ssytems- Review and evaluation of reconfigurable guidance and control methods- Detailed design of the most promising fault tolerant flight control systemcomponents- Development and validation of the reconfigurable flight control systemcomponents- Adaptation of existing performance simulator for the analysis and robustnessperformance assessment of fault tolerant flight control systems for representativefailure cases

Deliverables: Technical DocumentationSimulation Test DataValidated FTCS core components


Dossier:N/A

Ref. Number: G514-010MC Budget: 300 K€Activity Title: Methodology for analysis/test correlations of an SRM



Objectives: The objective is to develop a methodology based on tests and analysis that allowsa proper modelling of the SRM dynamic vibratory behaviour during flight.

Description: In view of performing accurate dynamic analyses of launchers that use SRMpropulsion, relevant dynamic models of the SRM and the dynamic load cases(ignition and pressure oscillations during the flight) are required. The scope of thisstudy is to develop a methodology based on tests and analysis that enables thedefinition of adequate dynamic SRM models and adequate dynamic load casesfor the SRM flight events. This methodology will be comprised of:• A finite element approach towards the modelling of the SRM structure thatincludes a solid propellant model and an associated damping methodology.• An analytical/numerical methodology related to the modelling of the dynamicload cases (the SRM dynamic model also allows the introduction of specificdynamic excitations).• A test methodology and measurement plan, which will involve specific testrequirements on the dynamic identification of the SRM (thrust profile,accelerations & modeshapes), on the dynamic identification of adjacent structuresof the firing tests facilities etc.• A methodology dedicated to the correlation of the SRM models and the dynamicload cases for the launcher dynamic analysis.Remark: The first 2 bullets are related the modelling of the SRM and dynamic loadcases, whereas the latter 2 bullets are linked to the analysis/test correlation of thefiring tests.

Deliverables: analysis methodology, documentsApplication: Beneficial if results are derived in parallel with the VEGA development. Also

relevant for next solid based launcher, VEGA upgrades etc.Current TRL: 2 Target TRL: 4 Duration: 24 MonthsRef ESTER: T-8115 , T-8122,


Ref. Number: G514-011MP Budget: 250 K€Activity Title: Aerodynamics of decelerators : parachutes and ballutesObjectives: The performance of Down Load Systems (DLS) especially the deployment of

supersonic parachutes have recently shown to be inadequately mastered (lessons learned Genesis). Note that even subsonic deployment is still todaywithout risk ( lessons learned USV) . The expertise on supersonic parachutedeployment resides mainly ( with the exception for Huygens ) in Russia and in theUS.The objective of the present activity is to improve the knowledge of high speeddecelerators (parachutes, ballutes etc...); to prepare experimental windtunelcampaigns in order to set up appropriate data bases useful for parachute designand analysis tool validation ( e.g. PASDA) ; testing of high speed decelerators, inparticular with respect to their deployment and their stability in similated flightconditions. Range of deployments of interest: Mach numbers 2 up to 7.

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Description: .The contractor shall perform the following activities :

• Review state of the art in parachute design and analysis and address thelimitations and short coming of the Agency PASDA tool especially for thesupersonic regime.• Propose experimental strategy taking into account agency needs, selectappropriate wind tunnel models for trans- and supersonic windtunnel testing.• Improve PASDA tool by enhancing engineering routines for supersonic DLSdeployment and perform validation exercise using present new experimental database• Apply updated tool to some agency defined test cases such as e.g. EXPERTand Huygens• Provide synthesis and recommendations to expand PASDA tool to include othertype of decelerators such as ballutes, inflatable systems or other types of dragchutes.

Deliverables: Wind tunnel test data, CFD Solutions, Technical notes,Test Articles, Test Data, updated PASDA

Application: All earth reentry vehicles, planetary probes: the early opening of a decelerator isneeded when the thin atmosphere of a planet (Mars) does not provide asufficiently intense hypersonic braking (e.g when the mass of the vehicleincreases and the diameter of the hypersonic shield is limited by the fairing of alauncher) . It is also necessary even for Earth entry vehicle when additionalstability is required at high Mach number.


Dossier:



THEME 6.- NAVIGATION

Ref. Number: G516-01MM Budget: 600 K€Activity Title: Photonic micro-navigator for microsatellitesObjectives: The objective of this activity is to develop an micronavigator system based on

photonic technologies for use by microsatellitesDescription: The present actvitity shall develop accelerometers based on micro-photonic

technologies that can be integrated in a photonic chip to provide the necessaryfunctionality for an inertial navigator microsatellites

Deliverables: A prototype of a photonic micronavigator at TRL-5Application:Current TRL: 3 Target TRL: 5 Duration: 18 MonthsRef ESTER: Harmonization

Dossier:

Ref. Number: G516-02GN Budget: 300 K€Activity Title: GNSS processing strategies for LEO constellationsObjectives: Improve methods for precise orbit determination of LEO satellites and especially

constellations of such satellites using GNSS receiver dataDescription: Precise orbit determination for low-Earth orbiting satellites can be based

successfully on ground-based measurement systems (SLR, Doris), GNSS dataprocessing or both combined. Other techniques are possible when several LEOsatellites are orbiting in formation or independently of each other. Models andalgorithms have been defined, for example, based on differencing data betweentransmitting satellites, receiving satellites, ground antennas and/or consecutivedata epochs. This activity will start with an overview of existing methods fromliterature, and investigate the feasibility of implementing these concepts in existingoperational or prototype software. Several concepts may be implemented in aprototype manner, and tested using data from existing LEO satellites withon-board GNSS receivers.

Deliverables: Activity report and a prototype implementation of the S/W with documentation.Application: Will be of benefit for the SWARM missionCurrent TRL: 3 Target TRL: 7 Duration: 18 MonthsRef ESTER: Harmonization

Dossier:

Ref. Number: G516-03GN Budget: 400 K€Activity Title: Improved radiation modelling for GNSS satellitesObjectives: To improve further on the radiation pressure modelling in high-precision orbit

determination for navigation satellites.

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Description: Among the forces affecting GNSS satellite motion, and therefore orbitdetermination accuracy, the radiation pressure force is considered the one withthe largest remaining uncertainty. The most performing models used nowadaysare purely empirical, and consist in estimating a number of coefficients of constantor cyclic acceleration components. This has the disadvantage that otherperturbations or error sources are partly absorbed in this. A dedicated activity isproposed to analyse the empirical models in more detail, and in parallel to exploremodels based on detailed geometry / radiation flux interaction.

Deliverables: Activity report and a prototype implementation of an improved radiation pressuremodel with documentation.

Application: Can be applied as soon as available (GPS), and of particular value for GalileoHigh-Accuracy applications.


Dossier:



THEME 7.- GENERIC TECHNOLOGIES AND TECHNIQUES

Ref. Number: G517-001MM Budget: 150 K€Activity Title: Voice Coil Motor Qualification ModelObjectives: The purpose of this activity is to consolidate the development obtained with the

"Voice Coil Motor Engineering Model" activity towards the QM and Flightapplication Model.

Description: Following the "Voice Coil Motor Engineering Model" activity and based on theachieved results, the purpose of this activity is to consolidate this developmenttowards the QM and Flight application Model by means of the Design,Manufacturing, Assembly, Integration and fully Testing, including life test aQualification Model for the identified project(s) and application(s).

Deliverables: Qualification modelApplication: Applications involving voice coil motors, 2010Current TRL: 6 Target TRL: 7 Duration: 12 MonthsRef ESTER: T-7850 Harmonization

Dossier:Electrical Motor Technology, D5

Ref. Number: G517-002MM Budget: 400 K€Activity Title: Piezo new sources materials, piezoceramics motor qualificationObjectives: The purpose of this activity is Designing, Manufacturing, Assembly, Integration

and fully Testing, including life test, of an EQM (Engineering and QualificationModel) based on the new piezo material identified and validated by CNES.

Description: Referring to the CNES presentation during the mapping meeting, this activityconcerning Piezo motor has been proposed in the following context:- In the past decade, CNES and ESA worked together to qualify a piezo sourceand number of flight applications were developed (characteristics so appreciatedfor high precision instruments)- ESA also funded piezo rotating motor study at CEDRAT company (F)- Years of CNES R&D activities at CEDRAT company make piezo actuatorssolutions available for space applications (amplified actuators, lot evaluationprocess…)- Good complementarities with NOLIAC (NW) as European ceramic supplier=> Need to prolong evaluation work performed under CNES funding by an ESCCstandard at ESA level.The purpose of this activity is to Design, Manufacturing, Assembly, Integration andfully Testing, including life test, of an EQM (Engineering and Qualification Model)based on the new material identified and validated by CNES.

Deliverables: Qualification modelApplication: All piezo electrical motors applications, 2009Current TRL: 3 Target TRL: 6 Duration: 12 MonthsRef ESTER: T-7850 Harmonization

Dossier:Electrical Motor Technology, D7

Ref. Number: G517-003MM Budget: 150 K€Activity Title: Compact Magnetic Bearing for High-Speed Rotor

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ESA/IPC(2008)89

Objectives: Development, design, manufacturing and testing of a compact passive/activemagnetic bearing system, which can support a high-speed rotor for potential usein a small reaction wheel. Specific emphasis shall be given on low-cost andlow-complexity solutions.

Description: In the context of a potential speed increase in order to reduce the mass and sizeof future reaction wheels, the life of mechanical bearings (typically ball bearings)becomes very critical. In previous activities, both active and passive magneticbearings have been investigated for high-speed rotor suspension in long-lifeapplications. For cost & complexity reasons, passive magnetic bearings are oftenpreferred, however for very high speed, the low mechanical strength of currentlyavailable permanent magnets restricts the maximum size of the bearing, hencetheir stiffness.A rotor using Magnetically Loaded Composite (MLC), exhibiting high strengthtogether with adequate magnetic properties, is currently being developed by thecompany CCM (NL) under another ESA contract titled “New Material for HighSpeed Rotor”. The new rotor material and design could overcome the current sizerestrictions of passive magnetic bearings. It is therefore required to develop apassive/active magnetic bearing that can be used in combination with theinnovative rotor and a compatible electric motor, for verification of the conceptusing an appropriate hardware prototype.

Deliverables: Magnetic bearing breadboard model (compatible with a high-speed rotordeveloped under another ESA contract), Technical data package,computer-based simulation models and test data files

Application: Magnetic bearing suspension for small reaction wheels and other compactrotating assemblies, e.g. scanners in scientific instruments (need date after 2011)


Dossier:AOCS Sensors & Actuators

Ref. Number: G517-004MM Budget: 300 K€Activity Title: Advance material for ball bearingsObjectives: To qualify the Cronidur 30 as relevant material for space ball bearings

manufacturing.Description: Most of the European space ball bearings are made of 440C that is sensitive to

stress corrosion cracking (table2). The Cronidur 30 has previously been assessedand shown very good performances with respect to stress corrosion cracking butalso with respect to other specific ball bearing critical performances. Furthermore,above 250°C the 440C is loosing its main characteristics, therefore the Cronidur30 is the only solution for high temperature bearings. This material should beofficially validated for space use.

Deliverables: Validation of the Cronidur 30 as standard material for space appliucation.Application: The targeted applications are all mechanisms relying on ball bearings for cryo until

hot temperature. This is the only candidate/solution for Bepi Colombomechanisms.


Dossier:No

Ref. Number: G517-005MM Budget: 1,000 K€Activity Title: Bimorph adaptive large optical mirror demonstrator



Objectives: The objective is to design, manufacture and test a breadboard demonstrator of alarge optical mirror consisting of several (typically 7) mirror segments, which aremade of thin silicon wafers and can be deformed via piezo-actuators attached tothe backside.

Description: Adaptive and active optics make use of small deformable mirrors for the correctionof the wavefront. The first deformable mirrors used in astronomy consisted of acontinuous reflecting layer, deformed by stacked PZT actuators. This conceptpresents an inherent high complexity and thus an insufficient reliability, and leadsto high manufacturing and maintenance costs. On the other hand, the benefitsresulting from the simplicity of the concept of bimorph actuation have beenrecognized since the late 1970's. The principle of bimorph actuation consists ofhaving an active layer on top of a passive substrate. An electrical field appliedacross the active layer and parallel to the direction of polarization induces atransversal localized elongation. Displacement compatibility at the interface to thesubstrate results in an out-of-plane bending deformation.Employing novel techniques as screen printing, it has been possible to use thebimorph principle on large silicon wafers. A single deformable mirror will consist ofa 150mm-diameter Si wafer commercially available with a thickness of about 600to 750 µm covered at the back with a PZT honeycomb actuator array of up to91actuators.Large light-weight (< 10 kg/m2) mirrors will then be formed by assembling anumber of these basic Si wafers side-by-side. In this activity up to seven of thesebasic segments will be combined and the control of the wavefront will bedemonstrated.This activity will include the wafer unit design (size and shape of wafer, wafercutting, number of actuators), electronic design (optimization of connections,selection of amplifiers), metrology design (integrated piston sensor design, largenumber of DOF metrology), mechanical design (light-weighted wafer supportstructure, tip-tilt actuators), control philosophy.

Deliverables: Breadboard of a large optical mirror; test reportsApplication: in 2014Current TRL: 3 Target TRL: 5 Duration: 20 MonthsRef ESTER: T-7855 Harmonization

Dossier:

Ref. Number: G517-005MM Budget: 400 K€Activity Title: Diamond turning of Aluminium alloys for aspheric opticsObjectives: This activity will investigate aluminium alloys and other materials that will allow

obtaining aspherical surfaces with a roughness close to 1-2 nm directly with adiamond turning process and demonstrate the achievable optical quality bymanufacturing and testing of samples of aspheric reflecting optics.

Description: Diamond machining of aluminium optics has progressed dramatically over thepast decade. High quality optics can be made now with very exotic asphericalshapes. With state-of-the-art Single Point Diamond Turning asperical surfaceswith a roughness of a few nanometers can be manufactured. Recent experienceshave shown that the surface roughness can greatly be improved by usingamorphous material obtained by rapid solidification processes. By betterunderstanding the surface properties of the materials it will be possible tomanufacture asperical mirrors with a surface quality better than achievable withthe present manufacturing capabilities. This technology will enable themanufacturing of reflective telescopes with low f-number and it will be possible tobuild very compact telescopes for both panchromatic and multispectral opticalinstruments.

Deliverables: Samples of Aspherical Mirror

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ESA/IPC(2008)89

Application: TRL 6 by 2012. For Science and EOCurrent TRL: 3 Target TRL: 5 Duration: 18 MonthsRef ESTER: T-7861,T-8442 Harmonization

Dossier:NO

Ref. Number: G517-006MM Budget: 500 K€Activity Title: Multi wafer hybrid integration: Robotics IMU IIObjectives: The goal of this activity is to develop an integrated micro localisation platform

based on inertial platform (3-axis solid-state gyro + 3 accelerometer) with a digitalserial bus interface (e.g. CAN). The platform shall be specifically designed for usein navigation for planetary robotics applications where mass is extremely criticaland there is a wide spectrum of mechanical noise. The effort of the activity will beon very tight integration of ESA-developed sensors and interface/processingcircuitry aiming to total mass below 200 gr.

Description: The activity shall continue from the point reached by the TRP activity “Multi waferhybrid integration: Robotics IMU I” to increase the TRL level in order to arrive tolevel 6. Hence design and manufacturing activities will be followed by testing inrelevant environment.

Deliverables: Design and manufacturing files, Test Reports, Final Report, BreadboardApplication:Current TRL: 3 Target TRL: 6 Duration: 18 MonthsRef ESTER: T-1, T-871, T-876,


Automation and Robotics -A4- Q1 2007

Ref. Number: G517-007MM Budget: 600 K€Activity Title: Testbed For Telemanipulated Satellite ServicingObjectives: Future satellite servicing missions need adequate preparation. The proposed

activity aims at the implementation of a testbed, which allows ground testing ofcritical mission phases like the capturing of a client satellite or the stabilization ofthe coupled system via telemanipulation/telepresence technologies.

Description: The activity shall investigate, design, implement and a testbed, which allowsground testing of critical mission phases in the task of capturing a free-flyer.The testbed shall be implemented on the basis of the existing EPOS facility.The activity shall also develop a demonstration showing either capturing of aclient satellite or the stabilization of the coupled system viatelemanipulation/telepresence technologiesThe activity shall as minimum be composed of the following tasks:1. Requirement and test Definition2. Architectural Design3. Implementation4. Test and demonstration

Deliverables: Study and design documentation, reports and video material for demonstration,hardware added to EPOS, software.

Application: No ESA mission foreseen/2010-2020Current TRL: Target TRL: Duration: 18 MonthsRef ESTER: T-1, T-871, T-876,


Automation and Robotics -A7- Q1 2007



Ref. Number: G517-008MM Budget: 400 K€Activity Title: Virtual testbedObjectives: The subject activity will provide means to build rapid prototypes, to visualize

different mission scenarios, to simulate and visualize subsystems and to simulateand test mission time-lines.The virtual testbed will be based on previously developed VR- and simulationtechnology. It will include physics simulation, interfaces to state of the artmodelling and simulation software (e.g. Modelica/20Sim/SCILAB/Matlab) and aninteroperation logic, which supports collaboration between multiple users over theInternet.The testbed could be used to support engineering decisions and concurrentengineering through simulation and visualization of test scenarios. VR-testbedsupport H&W-in- the-loop scenarios, i.e. virtual models can replaced by H/W.The system will enable crew and staff training already at early stages of adevelopment.During a mission it can be deployed as an advanced man machine interfacebased on “Projective Virtual Reality” and serve a powerful tool for the presentationof mission results.

Description: The proposed activity aims to develop and (or) integrate a suite of tool that can beused to support the initial design phase of robotics system. The tool will cover theenvironment and A&R control and dynamic modeling, the kinematic/ path planningspecifications aspects, the activity specification, the simulation of the overallactivities and the performances evaluation.While it is the intention to build on exist tools for contact dynamic (Telemanmodule, Trasys), soil interaction (3DROV, Trasys), 3D realistic modeling (3DRM &VIMANCO, Trasys), activities specifications (DREAMS, FORMID, Trasys) thesetools need to be integrated and extended to cover for instance system dynamic,performances evaluation as well as interface needs for more specialized tools.

The tool shall support interfaces such that modeling inputs/ outputs to others morespecialized tools can be done via existing standard (e.g. STEP, VMRL, XML,…).

Finally, during the activity, the Contractor shall evaluate needs for embeddingsuch a tool in the ESTEC CDF and support the its integration to it.

Deliverables: Study and design documentation, reports and user manual, software.Application:Current TRL: 3 Target TRL: 5 Duration: 18 MonthsRef ESTER: T-1, T-871 Harmonization

Dossier:Automation and Robotics -A9- Q1 2007

Ref. Number: G517-009MM Budget: 1,500 K€Activity Title: Haptic ControlObjectives: The activity aims at developing a haptic interface to allow intuitive and user

friendly use of a remote robot agent. The main objective is to study newalgorithms able to control a remote robot, taking into account transmission delays.

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Description: ESA has developed a concept for teleoperation of anthropomorphic robot agentsby means of arm Exoskeletons. ESA has internally developed its own exoskeletonand also promoted through R&D the development of an industrial one.ESA has manifested the use of exoskeletons as primary way to command theSPERO facility proposed for installation on the Columbus/ ISS. Within SPERO,an exoskeleton will be initially an experiment itself.An Exoskeleton is in principle the most intuitive interface to operate robot arms.However to operate correctly it needs to be complemented by additionalteleoperation devices and operated with suitable control algorithms.The proposed activity aims at integrating the ESA Exoskeleton developments,with other teleoperation devices (such as stereo goggles, head/neck/eye trackers)into a testbed to allow experimentation on haptic telemanipulation in presence ofcommunication restrictions.The testbed will allow preparation of the proposed SPERO experiment.The activity shall as minimum be composed of the following tasks:1. Requirement and experiment Definition2. Architectural Design3. Implementation4. Experiment tests and demonstration

Deliverables: Study and design documentation, user manual, hardware (to complement existingESA hardware) and software.

Application: SPERO facility on Columbus/ 2010Current TRL: 3 Target TRL: 5 Duration: 18 MonthsRef ESTER: T-1, T-871 Harmonization

Dossier:Automation and Robotics -B7- Q1 2007

Ref. Number: G517-010MM Budget: 600 K€Activity Title: Ground Control Station For AutonomyObjectives: The goal of this activity is to build up on previous ESA developments to produce a

ground control station capable to interact with an autonomous controller in orderto prepare and validate the autonomous “behaviour” of the controller and monitorand analyse the execution results.

Description: In the course of several years ESA has developed a number of technologies forproducing control stations for robotics. In particular A-DREAMS is a framework forbuilding control station supporting programming, monitoring and teleoperation ofrobot manipulators, 3DRM a geometric and kinematic simulator, 3DROV a physicsbased rover simulator, MUROCO/FORMID a robot programming specification andverification tool, TAPAS a task planning tool.All these technologies constitute a solid base for the implementation of a controlstation for autonomous robots, the subject of this proposal. Such control stationshall have the ability to:1) program the basic “behaviors” (tasks and underlying actions),2) validate formally the behaviors for safe execution3) compose the behaviors into plans (timelines) compatible with availableresources (e.g. time, energy, bandwidth, mass memory)4) simulate and validate the plans5) upload the plans into a target robot system6) monitor the execution of the plan (on the base of differed telemetry)7) update underlying models on the base of telemetryThe activity shall design, implement and demonstrate in a relevant test theproposed control station. In particular the activity shall as minimum be composedof the following tasks:1. Requirement and test Definition2. Architectural Design3. Detailed design



4. Implementation5. Test and demonstration

Deliverables: Study and design documentation, test reports and user manual, software.Application:Current TRL: 3 Target TRL: 5 Duration: 24 MonthsRef ESTER: T-3, T-801, T-8432, Harmonization

Dossier:Automation and Robotics -C2- Q1 2007

Ref. Number: G517-011SW Budget: 300 K€Activity Title: Automatic testing improvementObjectives: Following the TRP on automatic testing, consolidate and extent the technology to

other modelling languages and with more capabilityDescription: consolidate the tool from Leirios based on the use of UML and OCL with the

Borland tool.- investigate the possibilities with other modelling languages such as Scade,Matlab, or with more usual tools such as Rhapsody- select a set of modeling language and industrialize the tool- refine the process previously defined to take into account the variety oflanguages- perform a representative case study

Deliverables: new version of tools- new version of the process- case study

Application:Current TRL: Target TRL: Duration: 18 MonthsRef ESTER: T7662 Harmonization

Dossier:Board Software -C3-

Ref. Number: G517-012SW Budget: 200 K€Activity Title: Customisation of the ASSERT Framework to industrial environmentObjectives: Customisation of the ASSERT framework to real industrial environment.Description: The ASSERT project has delivered a set of prototypes to support a new

development process ensuring the preservation of properties from early SWsystem specification down to the final implementation.This activity will have to prepare the use of the ASSERT toolset on operationnalprojects by customising the toolset to a specific industrial environment. Such acustomisation will for example include specific modelling tool preselected by theindustry or adaptation to a particular middleware or operating system to replacethe ASSERT generic one.

Deliverables: Development environment; commercialisation plan; case studyApplication: Generic for all missions in phase B / 2011Current TRL: 3 Target TRL: 5 Duration: 18 MonthsRef ESTER: T7743, T7661, T7662,

T7753, T908, T7799HarmonizationDossier:

OBSW RM(B2)

Ref. Number: G517-013SW Budget: 300 K€

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Activity Title: On Board operating system Upgrade for LeonObjectives: To upgrade the existing RTEMS operating system to the Leon 3 and new

generation of micro-processors. Processors. Provide support to European industryin the use and maintenance of such operating system

Description: Porting the On board Operating System to Leon-3 and new generation of spacemicroprocessorsQualification of the OS for selected mission profilesSupporting the application of the operating system in space projects, including thesupport to remove deficienciesThis work is a continuation of past activities:? the RTEMS Validation and Testing Study, performed by Saab Space AB,? the SW Safety and Dependability Evaluations, performed by Critical Softwareand? Support and the Maintenance CENTRE to RTEMS operating system, developedby EDISOFT.

Deliverables: maintained operating system for LEON 3 and for NGMPApplication:Current TRL: Target TRL: Duration: 18 MonthsRef ESTER: T7671, T7665 Harmonization

Dossier:Onboard Software - J1-

Ref. Number: G517-014SW Budget: 300 K€Activity Title: Qualification of xLuna operating systemObjectives: A Linux-like operating system allows for easy development and execution of

non-critical onboartd applications alongside with critical ones. This facilitates forinstance the development of software by scientists and principal investigators tocontrol their onboard experiments.The objective of this activity is to qualify the pre-existing product called xLuna.

Description: Today the product is ready but is not enough mature for be embarked on asatellite computer.Critical Software is porting ExoMars rover application on xLuna for ademonstrator. In the meantime particular attention is dedicated to increase theperformances and to reach source coverage with basic tests.The purpose of this GSTP is to qualify this product to fill the gap and be compliantwith the new ECSS E 40 and Q 80, now in version C, for SW used in spacemissions

The work to be carried out under this GSTP is structured as follows:1. consolidate the existing design documents2. generate a test plan compatible with ECSS-E-40 and ECSS-Q-80 for criticalSW.3. implement the test suite4. execute the tests and provide the reports.

The work will be performed on new LEON 3 microprocessor also to verifyperformance in comparison of old LEON 2

Deliverables: Qualification test suite (SW + Documentation).Final version of xLuna (source code and executable).

Application:Current TRL: Target TRL: Duration: 24 MonthsRef ESTER: T7665 Harmonization

Dossier:Onboard Software -J1-



Ref. Number: G517-015EE Budget: 750 K€

Activity Title: Implementation and Demonstration of RF testing approaches for reducedantenna/payload AIT/AIV

Objectives: To implement testing methodologies for antenna/payload end-to-end RF testing atsatellite level

Description: The increasing complexity and stringent performances required in RF instrumentsand payloads demands more and more that RF functional verification beperformed on the integrated satellite under the most realistic operationalconditions. As a consequence and in order to minimize the cost and duration oftest campaigns it is necessary to develop advanced RF test methodologies.Extending testing to end-to-end performance requires a significant departure fromtraditional techniques, mostly based on CW tests (Continuous Wave tests, i.e.using non-modulated single frequency input signals) under (simulated) worst-caseconditions, in favor of methods that expose antennas, instrument or payload torealistic operational conditions, in terms of signals, power levels, etc.Following the results of previous studies it is necessary to extend existing testfacilities to cover the new needs have to be explored, taking into account thedifferent type of performance figure required for system-level assessment. At thesame time to keep the overall testing time within acceptable limits, it is needed todevelop performance interpolation procedures using existing accurate EMmodelling capabilities to achieve complete functional characterization from areduced number of measurements. Starting form the result of the precursor TRPactivity, advanced instrumentation and test beds shall be studied andimplemented in a reference facility. The testing methodologies shall then berefined and consolidated, fixing the criteria to establish the "performance samplingand interpolation rules" to be used in common cases and defining the proceduresfor the use of the relevant antenna modeling tools as interpolators. Finally the newmethodologies will be demonstrated on selected realistic configurations.

Deliverables: Validated methodology implementation and reference facility, including modellingtools

Application: Advanced AIT methods 2012Current TRL: 3 Target TRL: 6 Duration: 18 MonthsRef ESTER: T-7557 Harmonization

Dossier:

Ref. Number: G517-016EE Budget: 500 K€

Activity Title: Implementation and Demonstration of EMI/EMC approaches for fulldevelopment cycle support and reduced AIT/AIV.

Objectives: To implement new methodologies to perform EMC testing at satellite level

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Description: The complexity and stringent performances of most satellites demand reliable andcomplete EMI/EMC assessment during the full development cycle, in particularbefore final integration and verification at system level.Also worst-case testing at unit level does not always provide the right answer andthere is need for verification under the most realistic operational conditions.New testing methods as well as advanced modelling tools to support full-life cycleEMI/EMC assessment are necessary to cover these needs with the objective ofminimizing the cost and duration of test campaigns at satellite level while ensuringdesign optimization.The activity shall consolidate the results obtained in the TRP precursor activityand result in the implementation of new methodologies for EMC testing underrealistic conditions enabling the application of best practices across the fulldevelopment cycle. The development will start with the definition of generic EMCmodels suitable for the purpose, then advanced instrumentation and test beds willbe studied and implemented in a reference facility, also including validatedsimulation tools with adequate features. The resulting methodology will finally bedemonstrated on selected realistic configurations.

Deliverables: Validated methodology implementation and reference facility, including modellingtools

Application: Advanced AIT Methods/2012Current TRL: 3 Target TRL: 6 Duration: 18 MonthsRef ESTER: T-7557 Harmonization

Dossier:

Ref. Number: G517-017EC Budget: 700 K€Activity Title: Reaction Wheel Drive Electronics ImprovementsObjectives: Provide a mass and cost reduction with simultaneous improvement of

performance of the existing reaction wheels in 15 to 40Nms range.Description: Reaction wheel drive electronics are still relatively massive and frequently based

on old designs. There is room to improve these with the introduction of full digitalcontrol, digital interfaces which can significantly reduce parts count, improvereliability, performance (i.e. the addition of a wheel speed loop) and mass (viare-packaging).

Deliverables: - updated and tested WDEApplication: Q2 2011Current TRL: 3 Target TRL: 6 Duration: 18 MonthsRef ESTER: T-7816 Harmonization

Dossier:N

Ref. Number: G517-018EC Budget: 350 K€Activity Title: Low cost, portable sensor GSEObjectives: Design and production of a new set of STR GSE that is low cost and easily

portable for the purposes of AOCS open/closed loop testing.



Description: STR GSE is typically expensive and unweildy. Within this activity, a STR suppliershall develop, in co-operation with Primes, a specification for a new STR GSE(EGSE and OGSE) and shall develop a compact, low cost and user friendly set ofGSE to meet these requirements. This new GSE shall be manufactured andtested and then offered with future STRs. This contract shall aim to match therecent advances in sensor developments with similarly significant advances in theEGSE and OGSE for those sensors. Miniature APS based units shall be targeted.The goal is to develop a fully functional EGSE / OGSE that is easily portable, hasvery low recurring cost and can be used both in stand alone mode and to facilitateclosed loop, robustness and sign testing of the units.

Deliverables: - Full set of STR GSEApplication: Q1 2010Current TRL: 3 Target TRL: 6 Duration: 12 MonthsRef ESTER: T-7816 Harmonization

Dossier:N

Ref. Number: G517-019SW Budget: 500 K€Activity Title: Industrialisation of the HW-SW Codesign toolset.Objectives: Industrialisation of the HW-SW Codesign toolset developed in the context of the

TRP activityDescription: As a result of the TRP activity on HW-SW codesign, a prototype of a new toolset

integrated in the ASSERT environment has been produced. This toolsetcomplements the ASSERT process to handle the HW-SW partitioning,co-simulation and co-generation. This activity will have to improve the maturity ofthis toolset up to the level of a tool usable on an operational project. The maturitylevel will have to be confirmed with a full implementation of a significant casestudy.

Deliverables: The ASSERT Development environment completed with a mature support toHW-SW co-design.- A complete set of guidelines and user guides to use the new environment- A case study entirely developed with the new toolset,- Lessons learned from the experience and proposals for extensions orrecommendations for use on operational projects,- A commercialisation plan and spin-off opportunities

Application:Current TRL: Target TRL: Duration: 24 MonthsRef ESTER: T7743, T7661, T7662,

T7753, T908, T7799HarmonizationDossier:

Onboard Software

Ref. Number: G517-020ED Budget: 300 K€Activity Title: SpW RTC Software Library and ToolsObjectives: Development on a set of software libraries and software development tools for the

SpaceWire Remote Terminal Controller (SpW RTC)

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Description: ESA has developed a system on chip called SpaceWire Remote TerminalController (SpW-RTC). The SpW-RTC device includes an embedded Leon2 FTmicroprocessor with FPU, two SpaceWire links, two CAN bus interfaces,ADC/DAC interfaces for analogue acquisition/conversion, standard interfaces andresources (UARTs, timers, general purpose input output). This device has a quitewide range of potential uses in the field of spacecraft instrument control andpayload data processing. In order to further facilitate the application of this ASIC inflight programs a set of software libraries and tools needs to be developed beyondthe tools that are existing today.

Deliverables: A validated set of software libraries and software development tools for theSpaceWire Remote Terminal

Application:Current TRL: Target TRL: Duration: 18 MonthsRef ESTER: T-8159 Harmonization

Dossier:On-board Payload Data Processing, S22006, A9.1

Ref. Number: G517-021ED Budget: 500 K€Activity Title: TOPNET 2nd GenerationObjectives: Development of SW and HW for the implementation of the Second Generation of

the successful TOPNET concept.Description: The TOPNET Pilot Implementation Activity proved the usefulness of the TOPNET

concept. Many improvements were suggested by ESA and/or industry during theprevious activity. Objective of this proposal is first of all to implement all the newfeatures, in order to make the tools more close to an industrial product. A furtherobjective is to extend the TOPNET concept, having in mind the SOIS architecture,to introduce further Data Link Layers besides SpaceWire.

Deliverables: IP Tunnel SW, IP Tunnel HW (SpaceWire and other Data Link Layers)Application:Current TRL: Target TRL: Duration: 18 MonthsRef ESTER: Harmonization

Dossier:On-board Payload Data Processing, S22006, B6

Ref. Number: G517-022EP Budget: 200 K€Activity Title: Constant Power charging of Li ion batteries for LEO missionsObjectives: The objective of this activity is to evaluate the impacts of constant power charging

on the cycle life of Li ion batteries for LEO applicationsDescription: In LEO applications, high power is available when getting out of eclipse. This

available power could be used to charge the battery at constant power, implying tocharge the battery with a higher current at the beginning of the charge. But theusual charge profile of Li ion batteries is constant current-constant voltage. So theimpacts of constant power charging on the cycle life of the Li ion battery have tobe evaluated by testing and modeling to show if the Li ion battery can meet LEOmission requirements with such charging conditions.In a first phase, the charge profiles will be defined for different LEO missionsbased on the outputs of the previous ESA activity "Study of new power systemsarchitecture for LEO missions" and the test plan will be described. In a secondphase, a life test will be initiated with constant power charge and in parallel areference test with usual charge profile (constant current-constant voltage) will bestarted. In a third phase, the test results will be compared and by modeling theinfluence of the charge process will also be assessed.



Deliverables: Technical Notes, Test plan, Test reports, Final reportApplication: LEO missions (Earth observation)Current TRL: 5 Target TRL: 6 Duration: 24 MonthsRef ESTER: Harmonization

Dossier:

Ref. Number: G517-023QM Budget: 300 K€Activity Title: ADHESIVE TAPE FOR HIGH POWER LASER INSTRUMENTSObjectives: To validate an adhesive tape which is compatible with the laser induced

contamination requirements for high power laser instruments operating in vacuumDescription: High power laser instruments operating in vacuum place stringent requirements

on the use of adhesive materials in close vicinity to the optical components. Theinteraction of the laser beam with the outgassing products from the material cancause deposition of organic layers on the optic, and resulting performancedegradation, even if the material conforms to standard outgassing requirementsfor space use. Adhesive tapes often need to be applied during AIT activities, forexample to install sensors during environmental testing, or to prevent parts of theelectrical harness from crossing the optical path. The risk is enhanced if the tapeis added at a late stage of integration, and it is not possible to implementadditional contamination control measures on the hardware e.g. bake-out.Moreover, if the tape can be pre-conditioned, it is difficult to store and supply tapeusing standard methods e.g. on a roll. To limit the risk of laser inducedcontamination, an appropriate adhesive tape selection needs to be made,processing/conditioning parameters need to be investigated and a storage /supply method for the conditioned tape needs to be implemented.

Deliverables: Material survey according to current knowledge of laser induced contaminationeffects Investigation of risk reducing processing parameters (e.g. bake-out,conditioning), Laser induced contamination testing, Mechanical testing (adhesivestrength). Development of storage and supply methods

Application: TRL6 by 2010/11 (for Earthcare)Current TRL: 4 Target TRL: 6 Duration: 24 MonthsRef ESTER: T-8393 Harmonization

Dossier:

Ref. Number: G517-024QM Budget: 300 K€Activity Title: Joining of composites materialsObjectives: The aim of the proposed activity is to review and characterise different joining

techniques for composite materials such that size constraints of e.g. autoclavesare circumvented. Examples of possibly successful routes are welding ofthermoplastic composite materials or electron beam welding of thermosets. Theintegrity of the joined materials shall be assessed by sample testing.

Description: Composite materials are attractive for launchers due to their excellent stiffness toweight ratio. One drawback though is that most composite materials aremanufactured in autoclaves which naturally limits the size achievable of theresulting launcher component.

Deliverables: Part 1: Assessment of materials joining techniques Part 2: Characterisation of joining efficacy by sample testing and feedback toprocessing conditions Part 3: Synthesis of work performed

Application: TRL 6 (?) by 2013

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Dossier:

Ref. Number: G517-025QM Budget: 200 K€Activity Title: Crimping of thermally stable structures with Shape memory ringsObjectives: To use shape memory alloy rings to produce crimp joints between Invar and

silicon carbide.Description: Invar and silicon carbide have a matched CTE making them compatible for

cryogenic applications. The joints between the materials are complicatedbecause the CTE of fastener systems are not compatible which means thatcomplicated joints must be designed to allow for the mismatch. Crimping the Invarwould make this joint much easier to fabricate. A shape memory alloy ring wouldallow the joint to be made and unmade by the application of heat.

Deliverables: Breadboard for cryogenic testingApplication: All cryogenic misiosn using large thermally stable structures eg SPICA / 2010Current TRL: 1 Target TRL: 5 Duration: 24 MonthsRef ESTER: T-7895 Harmonization

Dossier:

Ref. Number: G517-026QM Budget: 250 K€Activity Title: Light weight steel structuresObjectives: Production of steel structures with lower weight than existing designsDescription: Aluminium structures are usually made up of individually components machined

from larger billets. The size of the original billets means that the heat treatment isnot optimal throughout the structure. Steel allows structures to be deep drawn andhydro-formed which can produce structures with very thin walls where onlystiffness is required and thicker walls at joints. These technologies have been verywell demonstrated in the packaging industry for drinks cans and by the sportsindustries for high performance bicycles. The specific stiffness of steels is slightlybetter than aluminium and titanium and there is a significantly wider variety ofalloys available. An appropriate alloy should be selected and used to produce athin walled breadboard using deep drawing and hydro-forming technologies.

Deliverables: Breadboard available for vibration testingApplication:Current TRL: 2 Target TRL: 6 Duration: 24 MonthsRef ESTER: T-8389 Harmonization

Dossier:

Ref. Number: G517-027QM Budget: 200 K€Activity Title: Development of electroless Silver platting on Ni/Cu coated substrates.Objectives: To develop a stable electroless silver deposition process on a defined and well

mastered under-layer. To address the compatibility of this deposited silver with thebase materials used in non-structural applications



Description: Develop stable electroless silver coating bath and establish a processing windowfor obtaining thick deposits of several micrometers on top of electroless Ni and/orCu. To test the coating behaviour when it is deposited on classical substrate suchas aluminium.

Deliverables: Process window, test samples, test reports, test data.Application: All missions for e.g. waveguides and antennae.Current TRL: 3 Target TRL: 6 Duration: 18 MonthsRef ESTER: T-8389 Harmonization

Dossier:

Ref. Number: G517-028QM Budget: 400 K€Activity Title: Processing of Al-Mg-Sc high strength alloys.Objectives: To evaluate the possibility of using new high strength aluminium alloys in space

application and address the benefit of advance processing techniques applied tothis new alloy.

Description: Phase 1: Characterisation of alloys based on the Al-Mg-Sc system with respect tospace applications and assessment of welded joints. Phase 2: application ofadvanced processing of the Al-Mg-Sc alloys; single-point-incremental-forming andmulti-points forming techniques.Rationale: Machining out from a bulk block of metal leads to distortion of thehardware during the machining. Having processes allowing making complex partswithout spring-back effects and other distortion would be of benefit and allow morefreedom in making small series production. Therefore process limits for the newprocesses applied to advanced alloys has to be established

Deliverables: Test samples, test reports, material data and breadboard, process limits for thenew processes applied to advanced alloy.

Application: All satellites.Current TRL: 2 Target TRL: 5 Duration: 24 MonthsRef ESTER: T-8389 Harmonization

Dossier:

Ref. Number: G517-029QM Budget: 250 K€Activity Title: Development and characterisation of Titanium alloy hollow-spheres.Objectives: To transfer the technology of pure Ti hollow-spheres to stronger alloy Ti6Al4V. To

characterise the mechanical behaviour and the physical properties of thedeveloped hollow-spheres. To assess the manufacturing limits of thesehollow-spheres (e.g. bonding, scaling-up, coating, machining).

Description: The pure Ti hollow-sphere manufacturing process has been developed in previousESA activities. One conclusion has been that the obtained material is the bestenergy shock absorption existing. Another conclusion has been that tremendousimprovement (200%) could be achieved by using Ti alloy instead of pure Ti.Beside, such material could be used is many applications.

Deliverables: Test samples, test reports, test data and processing window.Application: mars sample return, Marco-polo, hard-landing missionsCurrent TRL: 1 Target TRL: 4 Duration: 24 MonthsRef ESTER: T-8389 Harmonization

Dossier:

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Ref. Number: G517-030QM Budget: 250 K€Activity Title: Development and characterisation of advanced metal matrix composites.Objectives: To develop advanced metal matrix composite that comply with the general space

requirements. To assess the manufacturing limits of the selected materials. (e.g.bonding, scaling-up, coating, machining).

Description: Selection of advanced metal matrix composite systems. Development and ofthese composite systems, assessment of the processing possibilities –mechanical, physical and corrosion resistance characterisation of the developedmaterials.Rationale: Structural metals (Ti, Steel, Al) are roughly all equivalents in terms ofspecific stiffness. Metal matrix allows a further increase of the stiffness metalbased materials with increase in performance of several tens%.

Deliverables: Test samples, test reports, test data and processing window.Application: All projects.Current TRL: 3 Target TRL: 4 Duration: 18 MonthsRef ESTER: T-8389 Harmonization

Dossier:

Ref. Number: G517-031QM Budget: 200 K€Activity Title: Validation testing of Glare 1 to space qualification levelsObjectives: The objective is to demonstrate the mechanical and physical properties of Glare 1

coupons under thermal cycling and constant high and low temperatures. Alsohumidity testing and outgassing tests are part of the programme.

Description: Six different types of Glare are produced. Glare 1 consists of AA7475-T761 withglass fibre reinforced FM906 epoxy (High strength Glare), and the AA2024-T3with glass fibre reinforced FM94 epoxy (Glare 2 to Glare 6).The most used Glare type with the AA2024-T73 with the FM94 epoxy system iscured at 120C and has as a consequence a maximum temperature usage with iswell below the standard space qualification temperatures.The Glare 1 epoxy system cures at 180C and shows promises for the requiredtest temperatures. The data on Glare 1 in for space required temperature domainis very limited.

Deliverables: Test data to show the capability of Glare 1 at temperatures between -150 and+150 C


Dossier:

Ref. Number: G517-032QC Budget: 400 K€Activity Title: Polymer Tantalum capacitor (very low ESR)



Objectives: This program of work is planned in order to develop a very low ESR and highvoltage (50V) tantalum capacitor in Europe for space application.The polymer solid tantalum capacitors use a new technology replacing the MnO2material for the cathode by a doped polymer with a higher electric conductance inorder to reduce the equivalent series resistor and then enhance the electricalcharacteristics versus frequency. In the future this new technology could replacethe type II ceramic capacitors used for power output filtering for example in theoutput filtering stage of the DC-DC converters, and especially when themulti-anode configuration is used.

Description: This Technology is actually only use for commercial terrestrial application (andtherefore reliability data is limited) and limited to low rated voltage (16V max). Itshould be more surge robust and not subject to the ignition failure mode by theuse of polymer in place of MnO2 for the cathode.This activity can be shared in 3 parts:1/ an evaluation of the current capability of the selected manufacturer should beperformed. It will show the potential weakness of the product and will determinethe main improvement path for obtaining high voltage reliable capacitors suitablefor space application2/ Based on the previous results this part of the activity will consist of the selectionof technological developments that will allow increasing the rated voltage of thecapacitor. Samples will then be manufactured with the new technology/process.3/ a new evaluation of the obtained final components will be performed to assessthe improvement and confirm the new rated voltage.

Deliverables: evaluation of the current polymer tantalum capacitor, high voltage polymercapacitor samples


Dossier:Y

Ref. Number: G517-033QC Budget: 350 K€Activity Title: Definition of displacement damage test guidelines for bipolar devicesObjectives: To date there is no ESA test guideline/procedure for displacement damage. An

overall programme has been initiated to generate an ESCC displacement damagetest guideline to fill this gap. As part of this programme funding has been securedto establish displacement damage test guidelines for 2D imaging devices anddetectors and an activity is ongoing to establish displacement damage testguideline for optocouplers. The objective of this activity is to produce adisplacement damage test guidelines for bipolar based devices for inclusion in thegeneral ESCC displacement damage test guideline

Description: Based on the large database and experience available at TAS in the frame of theGlobalstar project, displacement damage test and design guidelines for bipolardevices shall be established. Additional irradiation test campaigns may by initiatedto cover the following issues:- lot to lot variation- effect of annealing- effect of bias- sensitivity to displacement damage of BiCMOS devicesIn addition Proton testing and combined neutron + TID tests shall be performed onselected candidates to establish the best way to get a realistic worst case value ofcombined TID and displacement damage degradation following ground basedtesting

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Deliverables: WP1: Management. WP2: Study report WP3: Irradiation Test plan. WP4:Irradiation Test Report WP5: Data analysis report, test guideline and designguideline documents

Application: The database and guidelines need date is mid-2010Current TRL: 4 Target TRL: 6 Duration: 18 MonthsRef ESTER: Harmonization

Dossier:

Ref. Number: G517-034QC Budget: 300 K€

Activity Title: Evaluation of worst case condition for the Single Event Effect test of powerMOSFET

Objectives: SEE tests employing highly penetrating heavy-ion of radiation hardened powerMOSFET have shown increased destructive SEE sensitivity with increasing heavyion range.These results have cast doubt on manufacturer test data currently in use by theEuropean space industry (major ESA projects have been affected by this issue).However, minimum ion range requirements have not been clearly established.Therefore, there is a risk to unnecessarily over-specify test requirements. Theobjective of this study is to define realistic minimum ion range requirements andinject the results in an updated ESCC25100 "SEE Test Method and Guidelines".The objective of this activity is to define a realistic (compared to actual spaceenvironment) worst case test condition for the Single event Effects (SEE) test ofpower MOSFETs

Description: Several hardened and non hardened power MOSFETs covering the voltage rangefrom 100 to 500V will be selected and procured. Parts will be tested at differenttest facilities with different ion species and ion range (penetration depth). Basedon test results, minimum ion range will be established for each voltage range(100V, 200V, 400V, and 500V). The resulting data is subsequently analysed andformatted suitable for inclusion in the ESCC25100.

Deliverables: Final report including data analysis, establishment of minimum ion rangerequirements and a suitable chapter on the subject for inclusion in ESCC25100

Application: mid-2010Current TRL: 4 Target TRL: 6 Duration: 18 MonthsRef ESTER: Harmonization

Dossier:

Ref. Number: G517-035SW Budget: 450 K€Activity Title: Java on-board software implementation, case studyObjectives: Assess the efficiency and suitability of using JAVA as the next generation

on-board real-time software programming language by implementing arepresentative test case.



Description: In previous ESA contracts Real-Time JAVA VM’s have been developed for theERC32/LEON microprocessors. In order to demonstrate the suitability andmaturity of the RT-JAVA technology for space application a representativeon-board software application shall be implemented. As testcase shall aspacecraft central software data management function be selected. It shall includethe most commonly used PUS services compatible to the ECSS-E-41A. It shallreplace the current data management software of the Eagle-Eye virtual spacecraftimplemented in the D/TEC Avionics LAB on the ATB-SVF. It shall further beintegrated with the autocoded AOCS software such that it together forms a newimplementation of the Eagle Eye Virtual Spacecraft on-board software.

The implementation shall be assessed on production productivity overall suitabilityas the future real time programming language for spacecraft applications.

The Avionics end-to-end Testbench is a D/TEC Avionics System facility providinga simulator implementation of a fictitious low earth orbit satellite ‘Eagle Eye’, whichincludes the platform on-board software for Data Management and AOCS and theavionics and environment simulation models. The E2E-AST lab facility is meantfor technology validation and demonstration.

Deliverables: full Java Data Management System on-board software, integrated with the AOCSsoftware and integrated on the D/TEC Avionics system laboratory (AvionicsEnd-ro-end Testbench).- Design documentation of the JAVA software and its integration on the ATB-SVF- Product technology assessment reports.


Dossier: Onboard Software -D2-

Ref. Number: G517-036SW Budget: 350 K€Activity Title: Establishment of model reference libraryObjectives: Develop a database and initial population of space system simulation modelsDescription: Based on the portability standard and a reference architecture the structure of a

library shall be defined and implemented to host reference simulation models forthe use and exchange between all stakeholders in the space domain.The structure of the database shall be based on the reference architecturedeveloped under other ESA activites. A concept needs to be defined andimplemented which allows the central management and maintenance of thelibrary, ensuring proper access control and compliance with the correspondingstandards (such as the simulation model portability standard).An initial population of this library shall be developed, and support for "open"models as well as models with IPR issues has to be demonstrated.

Deliverables: Model library with reference modelsApplication:Current TRL: Target TRL: Duration: 18 MonthsRef ESTER: T-7834 Harmonization

Dossier:System Modelling and Simulation Tools-B4-

Ref. Number: G517-037SW Budget: 2,000 K€Activity Title: Adaptation and Demonstration of MBSE for a real project

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Objectives: Quantify benefits of MBSE-based methods for space projects by performingphase B activities as shadow engineering in parallel with a selected mission

Description: Based on the results of previous, ongoing and planned activities to define amodel-based systems engineering (MBSE) based approach for space systemsand to develop the necessary support tools and interface standards, its benefitsneed to be quantified through the application in a real project.In order to have the most realistic quantification of the benefits of the methodsused, it is necessary to apply the methods and tools in a real project. To allow abenchmarking exercise it will be necessary to perform shadow engineering inparallel to a selected project, with a (partially) separate engineering team andaccess to the same data and requirements. This covers mainly the activitiesperformed in phase B.To minimize any impact on a project schedule and programmatics, this activityneeds to be run independently from a programmatic point of view. However,agreements need to be made on technical level to guarantee the transparency ofdata and processes between the two engineering teams.Programmes to be considered as potential cases include missions in the IAP(Integrated Applications Programme), Sentinel 4 and 5 (precursor), exploration,Cosmic vision of the Space Situation Awareness (SSA) initiative.All relevant system databases, models and simulations shall be developed tosupport the design process and allow the full design verification of the selectedmission.

Deliverables: Verified system design for the selected mission, comparable with the baselinephase B process


Dossier:

Ref. Number: G517-038SW Budget: 400 K€Activity Title: System Architecture modelling toolObjectives: Develop a system architecture modelling environment on the VSD model and

processDescription: The ongoing activity on Virtual Spacecraft Design prototypes tools to support the

model-base systems engineering process (MBSE). These tools provide theinterface on system level to define, analyse and modify the architecture of spacesystems, interfacing to engineering disciplines through mechanisms using acentral engineering database.Based on the tools and interfaces demonstrated, there is the need to reinforce theinterface layer towards the system and project engineers of a project. These toolsshall allow a system engineer to directly access the relevant functionality of theenvironment supporting the MBSE development process. This tool shall be basedon graphical representations and views meaningful to the system engineer andnot rely on SW-centric notions (such as UML, SysML), but translate the MBSEinternal representation into system engineering concepts consistent with theunderlying metamodels and concepts. The tool shall hide the complexity of theoverall system design reflected in the database and synthesise the design to alevel adequate for architectural analysis and system engineering integration andcontrol tasks.A specific emphasis shall be put in support to process definition and monitoringwithin this tool suite. The resulting tool will be integrated in the overall engineeringenvironment for the MBSE.

Deliverables: Modelling toolsConsolidated Interface definitions




Dossier:

Ref. Number: G517-039SW Budget: 750 K€Activity Title: System of Systems design environmentObjectives: Consolidate and tailor a System of System (SoS) Design environment for an

Agency projectDescription: Ongoing activities prepare the methods and tools required for the analysis and

design of System of Systems with space components. A prerequisite of theoperational use of these methods in the context of future SoS programmes of theAgency (e.g. the IAP programme, GMES / GEOSS follow-on…) is the provision ofa stable environment and a repository of all known and relevant assets of such aSystem of systems.On the basis of developed prototypes it will be required on one hand to strengthenthe framework, and on the other hand to produce relevant models for the system.The levels to be addressed include technical, programmatic and strategic,focusing on the interface with external partners (on all these levels). An expertteam needs to be set up to support the design and analysis phases for theprogramme managers and to maintain the repository, reflecting the inherentchanges of interfaces and external assets in these programmes.

Deliverables: Consolidated (operational) SoS analysis and design environmentReference repository of relevant assets


Dossier:

Ref. Number: G517-040SW Budget: 500 K€Activity Title: End-to-end performance simulation frameworkObjectives: Develop a generic framework and integrate representative simulation models for

mission performance analysesDescription: To justify and verify the correctness of the design of space systems it has become

common practice to go beyond so-called system simulators, addressing thetechnical performance of the system, to mission performance simulations,addressing the end users of a mission rather than the engineering /implementation level. They also provide the necessary synthetic mission productfor the timely development of higher level products and / or additional services.These tools have often been ad hoc developments, integrating existing scientificand engineering performance models. To be able to capitalize on pastdevelopments and to ensure that future modelling efforts are reusable acrossmissions it is necessary to define a suitable architecture and interfaces for a largeclass of future Agency missions. It has to be analysed to what extent differentinstrumentation can be combined in a common architecture, considering theinherently different logic of active vs. passive space instrumentation, andinstruments for which the performance is mainly driven by the available (static)environment (data-driven simulations), and those requiring the dynamics of thesystem.After the definition of this architecture and its scope, a corresponding SWframework will be implemented and an initial population with relevant existingmodels will be done. A clear ICD will be produced as requirements document for

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future model developments

Deliverables: Framework for end-to-end performance simulationsReference models for space instrumentationICD for future model developments


Dossier:

Ref. Number: G517-041SY Budget: 600 K€

Activity Title: Development and validation of a generic System of Systems ConcurrentEngineering Model

Objectives: Development of a tool for the definition and validation of a new System ofSystems (SoS) architecture based on existing and planned mission models foruse in the CDF-like environment. The tool will be based on the outputs of the GSPactivity “Modelling and simulation for system of systems” which will define theprototype software reference models.

Description: Analyse and implement the recommendations derived from the GSP activity onSystem of System and related CDF test cases- Establish the tool specifications enabling a generic approach and use of thesoftwwre- Evolve and develop the SoS custom models (output of the GSP activityModelling and simulation for system of systems) into a stable generic modelincluding dynamic validation capabilities for performances, operational andreconfiguration aspects- Demonstrate the generic SoS software tool for application in a concurrentengineering environment CDF-like using test case(s).

Deliverables: Modelling tool + associated documentationsApplication:Current TRL: Target TRL: Duration: 12 MonthsRef ESTER: T-7557 Harmonization

Dossier:

Ref. Number: G517-042EC Budget: 2,500 K€Activity Title: European IMU for EDLS, RDV and sample return missionsObjectives: Development and breadboard testing of a three-axis European IMU for EDL, RDV

and sample return missions, to get non dependence and remove associated risks(ITAR restrictions, obsolescence risks, lack of visibility on quality andperformance)



Description: A TRP system study was initiated to derive the accelerometers needs for an IMU,to investigate the gyro and accelerometer market in view of the IMU and topropose a preliminary concept for the IMU. The study covers a wide scope ofmission needs, including EDL and RDV needs. Following this system study, theactivity aims at 1) developing, manufacturing and testing an accelerometer(MEMS is a candidate technology), 2) developing and tuning the 3-axis IMUalgorithms from accelerometers and gyro measurements, 3) developing,manufacturing and testing a 3-axis IMU breadboard, integrating the MEMSaccelerometer with the gyro (already developed MEMS gyro or HRG). The needfor dedicated hybridization in the IMU (e.g. with altimeter measurements andplanet atmosphere model for the EDL phase) is proposed to be investigated in aparallel Hybrid Navigator studies and will be used as complementary inputs forthis activity.

Deliverables: MEMS accelerometer prototype, IMU algorithms, IMU breadboardApplication: TRL5 by 2011Current TRL: Target TRL: Duration: MonthsRef ESTER: Harmonization

Dossier:Yes

Ref. Number: G517-043EP Budget: 400 K€

Activity Title: Process optimization & pre-qualification activities for multi-junction cells onthin germanium substrates

Objectives: The objective is to adapt solar cell manufacturing processes to the use of thinner(nominally 80micron) germanium wafer substrates. Note that this technology isneeded for the next generation of 30% cell.

Description: Thin (80-100µm) Ge substrates have been developed by Umicore in the frame ofESA contracts (eg. ‘Improved Manu. Technology for Ge Substrates’). In order tobenefit from this improvement, solar cell manufacturers have to optimize theirproduction processes to produce triple junction solar cells using these lowerweight Ge substrates with the same yield and performance as currently achievedfor cells on thicker (140 µm) germanium substrates.

Activities will involve process trials using a statistically significant number ofwafers (of the order of several hundred) in order to demonstrate that satisfactoryyields can be envisaged.

Deliverables: 200 solar cells produced from Ge substrates with reduced thickness (approx. 80microns)

Application: Telecom, terrestrial market/a.s.a.p.Current TRL: 3 Target TRL: 5 Duration: 12 MonthsRef ESTER: T-7937 Harmonization

Dossier:Harmonisation Roadmap for SolarGenerators

Ref. Number: G517-044EC Budget: 200 K€Activity Title: HAS Active Pixel Sensor detailed annealing behaviour investigationObjectives: To determine via test all key factors affecting the annealing behaviour of this APS.

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Description: The evaluation programme has shown the high temperature annealing behaviourof these devices in biased and un-biased conditions. However, there is a stronginterest from users to know the annealing behaviours, for both biased andnon-biased detectors, at lower temperatures. This activity shall take a number ofdetectors and subject them to both TID and proton irradiation. The annealingbehaviour under different conditions (biased, unbiased) and at varioustemperatures (10, 40, 70, 125 deg C) shall be examined and the effects vs annealtime shall be monitored.

Deliverables: - Final ReportApplication: Q4 2009Current TRL: 7 Target TRL: 8 Duration: 9 MonthsRef ESTER: T-7815 Harmonization

Dossier:N

Ref. Number: G517-045EC Budget: 200 K€Activity Title: Extension of the Mathematical NLP-solverObjectives: The objectives of this activity are to adapt the ESA's Universal Non-Linear

Programming Solver (NLP) for optimization problems in other domains thantrajectory optimization. In a previous ESA activity, it is being developed aNon-Linear Programming (NLP) mathematical solver based on SequentialQuadratic Programming (SQP). The intended primary use was at the time of thisactivity for trajectory optimization. This activity will realized the adaptation of thissolver to areas different than trajectory optimization, like for example: spacecraftstructures optimization, optimization of launcher stages, optimization of fabricationof ASIC component, etc.

Description: The activity concerned will establish a preliminary design, development andcoding of the adaptation of the European Non-Linear Programming (NLP)mathematical solver based on Sequential Quadratic Programming (SQP)algorithms to be used by ESA optimization problems in the areas of antennaedesign, potential field modeling, electronic components design and fabrication,structures optimization, testing facilities optimization, optimization ofaerodynamics shapes, etc. The activity will be segmented in phases being phase1 the search in the ESA's market place possible options of collaboration withIndustry and European Universities and academia in this field.

Deliverables: Software algorithms and the corresponding API (application Program Interface) forthe upgraded solver. A set of technical notes describing the solver aplicability toESA''s optimization problems in all areas of interest. An interface (document andsoftware) with client software that require optimization engines.


Dossier:NA

Ref. Number: G517-046ED Budget: 800 K€Activity Title: Highly Available COTS based computer, Step2 (Prototyping and validation)Objectives: The objective of the activity is to manufacture and test in representative

environment the prototype of a COTS based highly available computer.



Description: The activity is a direct continuation of a GSTP 4 activity "Highly available COTSbased computer step 1" that had been covering the trade-off and specifications upto PDR level. This new activity shall consist in performing the detailed design andmanufacturing of the COTS based computer prototype (EQM) as specified in thestep 1 and including the testing (environment/radiation) to validate theeffectiveness of the fault avoidance/tolerance capabilities of the design with aspecial emphasis on the system resilience to transient effects (SEU, SET,MEU).

Deliverables: Prototype (EQM) including the relevant test and development support system, testapplication software and models, test and validation data with the identification ofany potential improvements to be implemented on the final product.

Application: TRL 6 in 2011Current TRL: 3 Target TRL: 6 Duration: 18 MonthsRef ESTER: T-7747, T-7796,


Avionics/Embedded System Datasystems and computer (COTS enabled

Ref. Number: G517-047ED Budget: 800 K€Activity Title: High Performance COTS based computer step2 (Prototyping and validation)Objectives: The objective of the activity is to manufacture and test in representative

environment the prototype of a COTS based high performance computerDescription: The activity is a direct continuation of a GSTP 4 activity "Highly Performance

COTS based computer step 1" that had been covering the trade-off andspecifications up to PDR level. The emphasis is put on the capability of the COTSto provide a high processing load and in this case substantially above the currentcapabilities of standard rad-tolerant microprocessor although tolerating limitedinterruption of service for the purpose of fault recovery and as such targetingapplications where the high processing capability is privileged onto other aspectssuch a availability or reliability (see harmonization 2003 and 2006 dossier for theintroduction to the category of systems based on RAMS considerations).This new activity shall consist in performing the detailed design and manufacturingof the COTS based computer prototype (EQM) as specified in the step 1 andincluding the testing (environment/radiation) to validate the effectiveness of thefault avoidance/tolerance capabilities of the design with a special emphasis on thesystem resilience to transient effects (SEU, SET,MEU).





Ref. Number: G517-048ED Budget: 800 K€Activity Title: High Reliability COTS based computer step2 (Prototyping and validation)Objectives: The objective of the activity is to manufacture and test in representative

environment the prototype of a COTS based high reliability computer.

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Description: The activity is a direct continuation of a GSTP 4 activity "High Reliability COTSbased computer step 1" that had been covering the trade-off and specifications upto PDR level. This new activity shall consist in performing the detailed design andmanufacturing of the COTS based computer prototype (EQM) as specified in thestep 1 and including the testing (environment/radiation) to validate theeffectiveness of the design.





Ref. Number: G517-049QM Budget: 750 K€Activity Title: Upscaling of ultra-stable bonding process of ultra-stable materialsObjectives: To demonstrate the viability of the output of TRP activity ( Joining technology to

bond Carbon to Carbon) dealing with bonding of ultra-stable materials.Description: The adhesive material and the bonding process developed within TRP will be

applied on a breadboard having roughly dimensions of a square meter, i.e.compatible with the requirements of future missions. The obtained breadboard willbe tested according to a test programme derived from the qualification programmeof the ultra-stable instrument support panels used in GOCE but taking therequirements of future missions into account.

Deliverables: Test samples, test reports, test data and a breadboard of about 1 m2 that will beused for performing tests.

Application: Eddington baseplate or equivalent exo-planet mission - Next generation missionsof GMES - High temperature missions as solar probe instruments( Bepi Colomboor Solar Orbiter) - Interferometry base structures carrying several telescopes -Darwin.


Dossier:

Ref. Number: G517-050QC Budget: 2,000 K€Activity Title: Establishment of a commercial GaN epitaxial production facility in EuropeObjectives: ESA is currently benchmarking under the capabilities of European GaN epitaxial

suppliers. The majority of potential European suppliers are still at the researchinstitute level or are volume suppliers with track record in other material systemsand have not established their production facilities in Europe. A program of work isrequired to assist in the funding of technology transfer from the R&D level towardsa true commercial production facility. Discussions are already ongoing with anumber of suppliers and options for joint funding schemes are being investigated.ESA seed funding is needed to stimulate this transfer.



Description: Similar to SiC substrate supply, an activity on this topic is absolutely essential tobuild an ITAR free European industrial capability. The availability of the GaNepitaxial starting material is a key building block that ultimately determines deviceperformance and reliability. This and the related item on SiC will provide themissing links to establish a fully European ITAR free supply chain from substratesto materials growth through to device processing. The epitaxy approach wouldalso investigate inclusion of CVD grown diamond layers close to the active devicechannel for more effective heat removal. If successful this approach couldrevolutionise the power performance achievable which is currently thermallylimited.

Deliverables: Epitaxial wafers, Establishment of a non-dependant European production supplychain for GaN epitaxy

Application: Generic applicability to all missions. Future EO programs (e.g. Sentinels,COREH20), and future Telecommunication satellites and Science missions (e.g.Solar Orbiter)

Current TRL: 2 Target TRL: 5 Duration: 24 MonthsRef ESTER: T-152 (04) Harmonization

Dossier:CTB Microwave component

Ref. Number: G517-051QC Budget: 1,000 K€Activity Title: GREAT - Validation of space compatible GaN foundry processObjectives: Within GREAT (TRP and GSTP) it was originally planned to undertake an activity

to validate the performance of the GaN foundry process developed in Europe,through design and demonstration of relevant component functions and tostabilise/enhance the design rules issued by the European foundry. However, thispart of the program has had to be suspended since the full financial envelope wasnot made available by the German and Belgium delegations. A follow-on Phase 3program of work is needed to independently validate the stability of the processesdeveloped and to assess their performance for space use. If successful thisactivity shall also provide and include a preliminary space evaluation of thefoundry processes developed for future listing in the EPPL. Unless this activity isundertaken it will not be possible to fully assess the suitability of the processesdeveloped on GREAT for space application.

Description: Foundry access will be given to independent teams outside of the GREATconsortium to evaluate the design rules, process stability and performanceachievable. Demonstration designs will be fabricated, as per the original SOW inGREAT and tested to ensure suitability for use in space.

Deliverables: Hardware (prototypes, test samples), experimental test results, reliability data,fully documented foundry design guide and libraries, preliminary spaceevaluation/qualification test plan, preliminary de-rating guidelines.

Application: Generic applicability to all missions. Future EO programs (e.g. COREH20), andfuture Telecommunication satellites and Science missions (e.g. Solar Orbiter)



Ref. Number: G517-052QC Budget: 2,000 K€Activity Title: Improved quality large diameter SiC substrates

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Objectives: This activity is planned in order to improve the quality and size of SiC substratesfabricated in Europe. High quality SiC semi-insulating substrates are required toallow fabrication of GaN components and SiC diodes for RF payloads, highvoltage dc-dc converter sub-systems and for developing electronic componentsthat are capable of operating in harsh environments (temperature, radiation etc ..).Activity on this topic is absolutely essential to build an ITAR free Europeanindustrial production capability. High substrate quality is important as it stronglyaffects device reliability. Moving to larger wafer size, 10cm diameter and above,is essential to achieve commercially competitive prices for SiC and GaN basedcomponents. A high reliability basic process technology for GaN components isbeing performed under other ESA activity. However, the substrate material for thisdevelopment is procured from a single US supplier for which the risk of becomingITAR product is now almost a reality. In order to achieve the ultimate objective ofan independent European supply chain it is mandatory to develop a spacequalified source of SiC substrates in Europe. This is also relevant for other SiCtechnology applications and can have further stimulating effects.

Description: The primary focus shall be to minimise wafer bow, reduce micropipe density andeliminate impurities that are known to adversely affect reliability. Targeted outputsfrom this work shall be judged through (i) successful use of European SiCsubstrates on GREAT and (ii) Establishment of a production supply chain inEurope.

Deliverables: SiC substrates with 10cm (or greater) diameter for processing in GREAT(TRP/GSTP), establishment of a European production supply chain

Application: Generic applicability to all missions. Future EO programs (e.g. COREH20), andfuture Telecommunication satellites and Science missions (e.g. Solar Orbiter)




Activity Title: Characterization and reliability assessment of RF MEMS switches andswitching matrix built on LTCC (Low Temperature Cofired Ceramic)

Objectives: The objective of this activity is to perform the functional characterisation and thereliability assessment of RF MEMS switch matrix built on LTCC.

Description: A 2x2 RF MEMS switch matrix built on LTCC from is candidate for a flightdemonstration on Alphasat.Taking into account this context, in the frame of the proposed activity, thefollowing work will be performed on this device:• The functional characterization (RF, switching speed, actuation voltage…).• Definition of a Space evaluation test plan relevant to telecom satellite application(lifetime, drift and ageing, vibration and shock, temperature, radiation,EMC/ESD…).• Fabrication of samples and performance of the evaluation testing.• Upon acceptance of the evaluation test plan and depending on the evaluationtest results, ESA will consider listing the technology in the EPPL-Part-II (EuropeanPreferred Part List).

Deliverables: Sample devices, Technical notes, final report and final presentationApplication: Alphasat technology demonstration payload in 2011. Targeted applications:

compact reconfigurable receivers in telecom payloads and MEMS-based TDL(Tapped Delay Line) for SAR (Synthetic Aperture Radars).

Current TRL: 3 Target TRL: 5 Duration: 18 MonthsRef ESTER: T-275, T-7828, T-7752,


CTB MNT




Activity Title: Demonstration of the ESCC Assembly & Test House (ATH) CapabilityApproval approach for EEE components.

Objectives: This ESCC project aims to secure a long term increment in Europe’s capacity toprovide the space industry with a significantly extended range and variety ofavailable EEE components. The intention is to introduce a systemic qualificationmethodology through the definition of a European ATH. The latter is usuallydefined as a small or medium size company proposing a back-end packaging ortest service for wafers/dice manufactured by another entity.The need stems from the strength of European semiconductor know how on theone hand and the disjointed capacity dedicated to space high reliabilitycomponents production on the other. The outcome will be matched competencesthat will be better prepared to meet the demands of future space projects.The ESCC defines one quality level, therefore components provided throughATHs will meet all the ESCC requirements and demonstrate an equivalent qualityto current ESCC qualified products together with long term availability atcompetitive costs. It is not intended to duplicate existing ESCC products and thisapproach could address, among others:- Markets not already covered or outside the scope of possible ESCCqualifications (e.g. manufacturers not interested by a Hirel, low volume production)- Technology gaps strategic to European needs such as fast analogue/digitalconverters and next generation microprocessors- Diminishing or obsolete references only available under wafer/die form- Semiconductor foundries proposing only wafer runs or intending to outsourceback-end activities.- RF components (e.g. the 2 GaAs foundries listed in the EPPL do not havepackaging capabilities)

Description: Tasks to be completed will include:- Develop requirements and criteria for the assessment and evaluation ofestablished standard semiconductor technologies for long term reliability includingspecific constraints for space applications (e.g. radiation),- Validate wafers/dice acceptance requirements and criteria for procurement,- Validate and finalise the ESCC documentation establishing the space quality andtechnical requirements for ATH activities,- ESCC evaluation of a selected component or family of components.

Deliverables: Validated new and/or updated ESCC specifications for the management of futureATH activities and ESCC Qualification of ATH products. Completed ESCC evaluation of a component/component family manufactured byan ATH and the related semiconductor technology.

Application: Most space missions.Current TRL: Target TRL: 5 Duration: 24 MonthsRef ESTER: T8448, T7885 Harmonization

Dossier:Y

Ref. Number: G517-055QC Budget: 300 K€Activity Title: IESD effects on glob-top assembliesObjectives: The objective is to define an analysis and experimental program in order to

quantify the Internal Electrostatic Discharge effects (IESD) susceptibility of aGlob-top assembly.

Description: Dielectrics having a resistivity above 1012 Ohm?cm under radiation can have atendency to build-up electrostatic charges due to their intrinsic low leakage rate.This charge accumulation could cause discharge when the local electric field

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exceeds the dielectric strength of the material or, between dissimilar surfaces, acritical potential. The discharge amplitude and duration is function of the chargedeposited. This problem falls in the domain of the so called Internal ElectrostaticDischarge (IESD) effects. It is also to be considered that the resistivity has atendency to increase with aging in orbit. So the potential threat increases duringthe spacecraft mission. In the case of Glob-top assemblies we have dielectricresin layer directly on the bare dies and wire bonds, which due to the integrationscale are becoming more and more ESD sensitive to lower voltage levels. Thecontractor shall:• Define a test plan to simulate the aging in orbit of the glob-top resin• Measure resin resistivity and dielectric breakdown after accelerated ageing andvacuum bake of the resin.• Make an analysis for GEO orbits to determine the worst case electron fluxarriving at the Glop-top assembly. In addition other orbits regime can beconsidered like MEO, PEO and planetary missions to Jupiter, Saturn and Mars(?).• Prepare resin samples (including aging and vacuum baking) and theexperimental set-up to detect the discharge events and measure pulse amplitudeand duration under electron beam.• Make electron beam tests on the resin with beam energy at: 100KeV, 500KeV,1Mev, 2MeV and 3MeV. Electron beam fluxes shall be in the range from 0.1 to1.0 pA/cm2. Flux vs. energy shall be derived by the above worst case electronflux analysis.• Implement margins on the collected experimental data to design a worst casescenario electron beam test on actual glob-top assembly (i.e. worst environment,least shielding). The testing shall foresee the DUT under maximum operativerating conditions.• If anomalous functioning is observed perform detailed investigation, andsimulation if deemed necessary, to confirm the cause was an IESD event.• Identify all the prevention (if not possible mitigation) techniques to avoid (or tolower to an acceptable level) the IESD risk.

Deliverables: Detailed Test Report and recommendationsApplication: 2009-2010Current TRL: 3 Target TRL: 5 Duration: 12 MonthsRef ESTER: T-5000 Harmonization

Dossier:CTB Hybrid WG

Ref. Number: G517-056SW Budget: 800 K€Activity Title: Verification of operational concepts for human-robot interactionObjectives: Define operational concepts and knowledge interchange requirements in a

heterogeneous environment, requiring close interaction between humans androbots in a self-contained collaborative team. These concepts need to be testedand consolidated in a simulated environment.

Description: In some of the scenarios for future lunar/planetary exploration purely roboticmissions are followed by crewed missions. These missions will rely on the roboticinfrastructure which has been built up, but will require different interactionsbetween this infrastructure and the human, since the agents need to collaboratemore closely together. In a teleoperating context the robots are executing orders /achieving goals in an autonomous way, they will have to interact with the humanon a more collaborative level in order to form a team and achieve the commongoals. The role for robots will shift from an exploration more towards a fieldsupport and service function.

Traditional autonomy concepts need to be enhanced to allow knowledge sharingon semantic level between the agents. Similar challenges are known from e.g. themining industry, the off-shore sector and nuclear industries (operations in complex



& hostile environments).After an initial survey of operational concepts from other domains with similaroperational constraints as space (such as mining, underwater exploration, nuclearinstallations), an analysis will performed of applicability of these concepts to thedomain of human spaceflight. This analysis needs to be based on an operationalscenario of a future mission, incorporating robotic and human agents in acollaborative environment on a lunar/planetary surface.Based on the results, an operational concept will be defined, based on theknowledge exchange and task-sharing between the (human and non-human)members of the team. An increased situational awareness needs to be achieved.The necessary interfaces and interaction modi need to be defined, taking intoaccount the limited resources available for space missions. Goal oriented planningsupport concepts as well as monitoring functions need to be integrated. Theoperational concept must also include support for reactive planning.In order to evaluate and consolidate the operational concepts, a simulationenvironment needs to be defined to support the execution of a scenario. Using ademonstration with (ideally) some robotic equipment in the loop the benefits andlimitations of collaborative approach shall be quantified and drivers for operationaldevelopments shall be identified.

Deliverables: • Definition of Operational concept for human-robotic interaction• Specification of the interface (knowledge, human-machine interface) betweenhuman and robots in a collaborative environment• Architectural design for demonstration testbed• Detailed design of testbed• Prototype of testbed• Evaluation report• Detailed design for operational layer for robots


Dossier:


Activity Title: Reliability assessment of a MEMS-based isolation valve for propulsionsystems

Objectives: During this activity, the contractor will perform the reliability assessment of aMEMS isolation valve for satellite propulsion systems. The device shalldemonstrate zero-leakage, resistance to Space environment and a high reliabilityon the long term.

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Description: A small and light-weight MEMS isolation valve for satellite propulsion systems hasbeen developed by Nanospace AB (Sweden) during the ESA activity 18829/05.To enable the use of this component in Space application with an increasedconfidence, reliability testing is proposed in this activity.Task 1:• PA/QA documentation of the device (Description, PID, existing test data, etc).• Market study, including Space and terrestrial applications.• Identification of potential end-users/partners and flight opportunities.Task 2:• Preparation of a test plan according to the requirements of a relevant missionprofil or else according to generic Space requirements (i.e. telecom mission).• Manufacturing of engineering modelsTask 3:• Performance of the reliability testing on engineering models• Analysis of the testing results to deduce potential weaknesses and limitations,and necessary design or processing improvements.The contractor will also deliver sample devices to ESA for the performance of aconstruction analysis in ESTEC laboratory.

Deliverables: Technical notes for each taskHardware samples

Application:Current TRL: 3 Target TRL: 5 Duration: 18 MonthsRef ESTER: T-867, T-857 Harmonization

Dossier:CTB MNT

Ref. Number: G517-058QM Budget: 400 K€Activity Title: Nano-hybrid transparent materialsObjectives: This study aims to find a replacement for silverised FEP, a well-known and widely

used flexible second surface mirror based on the transparent property of FEP.The reason for that replacement is that space retrieved hardware from the HubbleSpace Telescope (HST) showed that this material badly degraded and has beenseverely attacked after being seven years in orbit.

Description: The combination of organic and inorganic materials leads to a class of so-callednano-hybrid materials. Such hybrid materials offer properties that cannot be foundin the individual material alone because a wide variety of functional groups can beadded that enable to tailor individual material properties. Therefore, the aim of thisstudy shall be the development of a highly transparent material in combinationwith a high radiation resistance (Proton, electron, UV, VUV, X-ray etc.) and goodhandling flexibility.

Deliverables: Part 1: Review of radiation resistant moieties and experimental manufacturing ofhybrid materials for screening investigation application Part 2: Screening Investigation on radiation resistance and down selection ofhybrid material composites Part 3: Materials testing in relevant space environment leading to a pre-qualifiedstatus Part 4: Market study and proposal for industrial scale up of production

Application: TRL 6 in 2013Current TRL: 2 Target TRL: 4 Duration: 24 MonthsRef ESTER: T-8390 Harmonization

Dossier:



Ref. Number: G517-059QM Budget: 300 K€Activity Title: RTM processing of novel high temperature high radiation resistant resinObjectives: The aim of the activity is to assess and optimise the processing of a newly

developed resin by RTM processing. This resin is deemed to have extremelyattractive properties in terms of temperature performance as well as radiationresistance. Challenges are the high temperature required for processing and theexact process window optimisation.

Description: The Materials Physics and Chemistry Section is currently assessing a set a ultrahigh resistant materials based on novel Polyimides. One of the resins underinvestigation is RTM processible which implies that complex shapes could bemanufactured. The material has a high spin off potential for other hightemperature industries.

Deliverables: Investigation and optimisation of processing window for RTM processingCharacterisation of thermal endurance and thermo-mechanical properties onmaterials test samplesSynthesis report

Application: TRL 6 by 2012Current TRL: 2 Target TRL: 4 Duration: 18 MonthsRef ESTER: T-8393 Harmonization

Dossier:

Ref. Number: G517-060SW Budget: 300 K€Activity Title: Data Modelling using ASN.1Objectives: Based on the previous GSTP (System Software Co-Engineering: Data Modelling

Technologies), the goals are to (i) consolidate and extend data modellingtechnologies and tools to an industrial level and (ii) make building blocks out of thedata models in a consistent way that is compliant with both the PUS standard andSystem Databases formats.

Description: The activity will consist in making an industrial tool-chain out of the ASN.1technology that was prototyped and validated earlier by ESA and Prime spaceindustry, and to apply it on a realistic case study. Training material will also berequired so that any space company will be able to make use of the resultingtools. The ASN.1 Environment will be free of charge and will ensure Europeanindependence on data modelling key technology. The tool-chain will consist of (i)a space pre-qualified ASN.1 compiler with compact binary encoders (based atleast on PER, ECN and/or PER EI standards), (ii) an automatic ICD generator, (3)automatic code generators for functional modelling languages to automaticallymake use of Data models and (4) an adaptive programming layer to help userswork with complex data models.

Deliverables: Industrially-useable Data Modelling Toolchain- Use case: Data Models of the PUS standard- Training material

Application:Current TRL: 4 Target TRL: 6 Duration: 18 MonthsRef ESTER: T7662 Harmonization

Dossier:Onboard Software

Ref. Number: G517-061SW Budget: 350 K€Activity Title: Dynamic Translation based on-board processor emulator

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Objectives: The software emulation of the new generation of microprocessors used for Spaceapplication does at best reach 30% of real-time when it is based on instructionemulation. New and promising dynamic translation technology opens the scopefor achieving a factor 10 in performance.Precursor studies have demonstrated the feasibility of using this technology alsofor emulating real-time applications, where the focus is on an accurate I/Operformance model and on the need of being able to integrate the emulator intoan overall system simulator

The objective of this activity is to build and characterise a dynamic translationbased emulator for the LEON micro-processor that supports an I/O representativeemulation model.

Description: Design and develop a generic LEON emulator using the dynamic translationtechnology. Focus the emulation model to be real-time representative at theI/O-level. Assess the performance of this architecture.Assess the system representiveness and impact of this approach on theverification functions and its suitability to support the software and systemverification and validation.Demonstrate the capability in context by prototyping a representative test caseusing the Avionics LAB ATB-SVF.

The ATB-SVF is a D/TEC Avionics LAB facility providing a simulatorimplementation of a fictitious low earth orbit satellite, including platform on-boardsoftware for Data Management and AOCS and the avionics and environmentsimulation models. The ATB-SVF facility is meant for technology validation anddemonstration.

Deliverables: The deliverables are- The beta version of the LEON dynamic translation emulator- The emulator integrated with the ATB-SVF- Performance characterisation based on test case executing on the ATB-SVF.- Assessment of its suitability for use within Software and Validation Facilities andpotentially Operations simulators.

Application:Current TRL: Target TRL: Duration: 12 MonthsRef ESTER: T-7665, T-303 Harmonization

Dossier:System Modelling and Simulation Tools-C4-

Ref. Number: G517-062SW Budget: 350 K€Activity Title: On-Board Computer Simulator architectures and I/F to system test benchesObjectives: Modern On-Board Computers (OBC) contains in addition to the processor a high

number intelligent peripherals in the form of ASIC’s, FPGA’s or integrated as aSystem-on-chip solution. In order to create a representative simulation model ofthe OBC it is necessary to integrate accurate functional models of theseperipherals together with the processor emulator. These peripheral functionalcomponents may be proprietary provided by the hardware supplier or may bedeveloped specifically within the simulator context.

The OBC emulation / simulation models need to reflect this evolution and enablethe correct representation towards the rest of the avionics system.

The concept is undergoing technical feasibility assessment in the frame of theLeon-SVF contract. The output of this contract shall be taken into account for theconsolidation of the architectural and interface specification foreseen in thisactivity.



The objective of this activity is• to consolidate the OBC simulator architecture, taking into account the ability tointegrate functional simulation components provided potentially by third parties ina performance effective way;• to consolidate the standardised interface to the functional simulationcomponents;• to implement a representative prototype of the architecture, and characterise theperformance of the interface to a system test bench.

Description: Develop the architecture for a complete OBC simulator, comprising the processorand all its closely integrated interface functions. The activity shall take intoaccount the Functional Component Plug-in Protocol (FCPP) which has beendefined in the Leon-SVF contract.Revise/consolidate relevant lower level model interfaces that allow performanceefficient integration of models and take into account that building blocks may bedelivered from the third party vendors.Define the relevant interface to the system test bed, compliant to the standard forsimulation model portability (ECSS E40-07). Prototype the architecture andcharacterise the performance of the OBC / system test-bed interface using theD/TEC Avionics LAB on the ATB-SVF.Assess the limitations of architecture for SW and system verification andvalidation.

The ATB-SVF is a D/TEC Avionics LAB facility providing a simulatorimplementation of a fictitious low earth orbit satellite ‘Eagle Eye’, which includesthe platform on-board software for Data Management and AOCS and the avionicsand environment simulation models. The ATB-SVF lab facility is meant fortechnology validation and demonstration.

Deliverables: • The definition of the reference architecture for OBC simulator, including thedefinition of the functional component interface protocol (FCPP)• Interface definitions and characterisation OBC simulator within the systemtestbed.• the simulator prototype integrated on the D/TEC Avionics LAB ATB-SVF• Assessment of usability and perormance for Software and system verification &validation

Application:Current TRL: Target TRL: Duration: 12 MonthsRef ESTER: T-7665, T-303 Harmonization

Dossier:System Modelling and Simulation Tools,-C1,C2-

Ref. Number: G517-063SW Budget: 750 K€Activity Title: Automatic generation of database applications from a domain ontologyObjectives: This objective of this activity is to substantially improve the quality, availability and

efficiency of monitoring and control databases for use in AIT through theapplication of state-of-the-art database engineering methods and tools.It will demonstrate how, from a formally defined Ontology (the means to model adomain of knowledge) of Monitoring and Control Data how database softwareapplications can be automatically produced”. Output will be a means to definevalidated data models and DB applications that fulfil AIT needs for any missionacross the development life cycle, according to current and emerging standards(ECSS, CCSDS, OMG).

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Description: ORM (Object Role Modelling) is a formal methodology and related tools that havebeen successfully used by the Agency for formally specifying conceptual schemaof information systems related to AIT. In previous ESA activities, the ORMmethodology and a related tool is being extended to allow expressing ontologiesrelated to the Space System domain according to ECSS standards.From a given ontology, the automatic generation of data models to be instantiatedwithin a data base management system, the automatic generation of softwareapplication compliant to these models, including MMI, export/import facilities havebeen demonstrated. The consolidation and development of the ontology tool andthe generator of database application software will be further developed andconsolidated by validating them using mission data.

Deliverables: A database development platform based on the ontology toolAn information system derived using the development platform and validatedagainst real mission data.

Application: All mission starting phase B from 2012Current TRL: Target TRL: Duration: 18 MonthsRef ESTER: T-7292 Harmonization

Dossier:N/A

Ref. Number: G517-064TC Budget: 320 K€Activity Title: Virtual Reality for AIVObjectives: Improve the use of Virtual Reality in the Assembly, Integration and Verification

phase reducing cost and risk of Phase C/DDescription: During 2004-2007 a TRP activity called "VRAIV Virtual Reality for AIV" has been

performed. In this activity, it has been developed a software tool which is opensource and dedicated to the Virtualization of AIV procedures. The documentationhas been delivered to the ESTEC library and is available to European Industry.This tool is now at prototype level and has been used for some pilot projects(EXPERT re-entry test bed Payloads AIV, Large Space Simulator upgrades ofservomotors).With this activity it is foreseen to add functionalities to the existing VRAIV tool,among them: improve the automatic AIV procedure generation, allow for thecomplete virtual generation of the AIV documentation of a project starting from adatabase linked to the S/C Model database, improve the virtualization of AIVprocedure and the process of generation, modification, execution and reporting ofAIV procedures, improve the link with existing CAD tools.The aim is to reach a full operation and validated tool which can be linked to theVirtual Spacecraft Design (VSD) framework as a tool dedicated to the AIV phase.

Deliverables: Design and validation of VRAIV toolApplication:Current TRL: 3 Target TRL: 9 Duration: 16 MonthsRef ESTER: Harmonization

Dossier:

Ref. Number: G517-065MC Budget: 500 K€Activity Title: Automated layup of Thermoplastic Composites for space applications



Description: Rapid, cost effective manufacturing out-of autoclave for large CFRP structures.Manufacturing of thermoplastic composites using automated tape laying machine,with integrated heating for melting and consolidation of the composite directlyduring the layup, has a great potential to reduce manufacturing costs, scheduleand risk. Thermoplastic resins is a promising alternative both with respect toperformance as well as for practical reasons such as longer shelf life of rawmaterials, less environmental impacts compared to conventional resin systemsetc. By using automated layup featuring integrated heating and consolidationduring layup, there is no need for autoclaves to consolidate the material and meltthe resin. The significantly increased shelf and workshop life of the materialcontributes to reduce the risks during manufacturing. The proposed study is todevelop and manufacture and test a demonstrator corresponding to a major spacestructure using this technique. The technology is existing but is not yetimplemented into space structures.

Deliverables: documentation, demonstrator structureApplication: launcher and spacecraft structuresCurrent TRL: 3 Target TRL: 5 Duration: 24 MonthsRef ESTER: T-7556 Harmonization

Dossier:N/A

Ref. Number: G517-066MC Budget: 150 K€Activity Title: CAD Based Modelling for Space Thermal Analysis Description: The graphical modelling environments that exist today for space thermal analysis

have grown from small applications designed to visualise geometry used forcalculation of radiative exchange factors and heat fluxes. As these niche toolshave matured the developers have tried to improve the modelling environment,and to provide all the modelling functionality desired by users, whilst alsodeveloping the core functionality of their tools; namely the radiative kernel.Considering the limited resources of the developers, and the limited number ofusers of the tools, this has proved to be a difficult task and, as such, the currenttools are often cumbersome to use and lack the interactivity and functionality ofdedicated modelling environments, such as:

o Computer Aided Design (CAD) modelling environments e.g. CATIA, AutodeskInventoro Computer Aided Engineering (CAE) modelling environments e.g. SAMCEFField, MSC Patran

The basic premise of this proposal is that developers of niche software, such assoftware for space thermal analysis, can concentrate on developing and improvingthe core of their tools, specifically the radiative and thermal solvers, and providemodelling capabilities in the form of plug-in applications for dedicated CAD/CAEmodelling environments.

This type of approach has several clear advantages:

o Only the core solvers of the tool, and the interface with the modellingenvironment, need to be developed and maintainedo The solvers can be independent from the modelling environment and can beembedded in different modelling tools by developing different interfaceso All of the functionality of the CAD/CAE modeller is available to the thermalengineer e.g. parametric and adaptive design, solid modelling, meshing

The objective of the proposed activity is to develop a prototype plug-in application

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for a commercial CAD/CAE modelling tool. The plug-in shall permit the user tocarry out all aspects of the thermal analysis process from within the CAD/CAEmodelling environment. The actual solution of the thermal and radiative problemsshall be carried out by existing thermal solvers and the transfer of data betweenthe modelling environment and the solvers shall be completely seamless andinvisible to the user. The post-processing and visualisation of results should alsobe possible from within the modelling environment.

A second key theme and objective of the proposed activity is the use ofcomponent based modelling and smart components. Smart components are 3DCAD parts that are available for the thermal engineer to drag-and-drop into theirmodel. These smart components not only describe the geometrical and massproperties of the physical object, but also have a pre-defined thermal behaviour.Thus the user can drag-and-drop smart components from a library or palette andquickly build a fully parameterised thermal model. The use of such smartcomponents has clear benefits in terms of reducing modelling errors, increasingproductivity and allowing the engineer to focus on the design rather than themodelling aspects.

In order to limit the scope of the activity, a pre-defined usage scenario isenvisaged which focuses on subsystem and instrument design.

Deliverables: (a) Prototype space thermal analysis S/W plug-in for a CAD/CAE tool(b) Demonstration library of smart components for space thermal analysis

Application: All space missionsCurrent TRL: 3 Target TRL: 6 Duration: 12 MonthsRef ESTER: T-7882 Harmonization

Dossier: Thermal and Space EnvironmentAnalysis Software

Ref. Number: G517-067EE Budget: 500 K€Activity Title: ESD transients monitor Description: A monitor will be developed to measure the amplitude and characteristic

time-scales of electrostatic discharge (ESD) transients directly in spacecraftelectrical systems. The operation will be verified by realistic irradiationexperiments looking at both surface and internal charging. The result will be themonitor equipment itself and the characterization of realistic ESD transients to beused in defining requirements for ESD testing of future systems. The output of theactivity will be a protoflight model of the monitor that could be further developed tobecome a standard device to measure ESD transients in operational satellites.

Deliverables: Protoflight model of ESD transient monitor. Results of laboratory experimentsusing ESD transients monitor developed.

Application: All GEO and MEO missions, also Jupiter/Saturn missionsCurrent TRL: 1 Target TRL: 6 Duration: 24 MonthsRef ESTER: T-18 Harmonization

Dossier:Technology area not harmonised

Ref. Number: G517-068MP Budget: 600 K€Activity Title: Low cost PED propellant tank



Description: The SPF of Titanium alloys is a well proven technology for aeronauticalstructures, and can guarantee a final lightweight product with a low costmanufacturing technology. The PED technology applied to bi-propellant systems,will enable flexible fulfilment of spacecraft and launcher upper stage missionsimplying complex manoeuvres and attitude control tasks that are in general notallowed or affected by operational constraints using the currently availabletechnology in Europe; surface tension Propellant Management Device (PMD). Inaddition the PED technology is earmarked to provide appreciable cost advantagesover the mentioned currently available PMD solution. The objective of thisprogram is to increase the TRL of the described technologies to a maturity leveladequate to demonstrate the PED tank concept suitability with a prototypedemonstration in a relevant environment. Task1: definition of tank functional andenvironmental target requirements. Task2: preliminary design of at least twoalternative tank concepts compatible with bladder or diaphragm PED solution.Task3: development of a manufacturing process for diaphragm/bladder. Task4:manufacturing of a suitable batch of diaphragm/bladders and development testingin a mock up tank model. Task5: manufacturing of tank shells by SPF (superplastic forming). Task6: development of tank system manufacturing process: partswelding and integration. Task7: manufactured prototype acceptance includingrepresentative functional and environmental testing. Task8: preparation of tankmanufacturing file

Deliverables: Documentation relevant to the identified tasks.Application: LV upper stage bi-propellant storable propulsion systems, Small-medium

Bi-propellant spacecraft, Space exploration missions, Orbit transfer vehicles.Current TRL: 3 Target TRL: 5 Duration: 18 MonthsRef ESTER: Harmonization

Dossier:Yes

Ref. Number: G517-069MC Budget: 200 K€Activity Title: Medium-Power Loop Heat Pipe Description: The objective is to design, manufacture and test a medium power, medium size

Loop Heat Pipe at development level.

The activity shall consist in either scaling up the existing mini LHP or thescaling-down of the high power and large size LHP, resulting in a medium size,medium power LHP for an operating range of 30 to 200 W for e.g. instrumentthermal control. Such a medium size LHP shall then be designed, manufacturedand extensively tested.

Deliverables: Development model(s) of medium-power LHP; complete set of technicaldocuments incl. design, test and test evaluation documents

Application: EO, Science, Exploration, TelecomCurrent TRL: 3 Target TRL: 5 Duration: 18 MonthsRef ESTER: T-7874 Harmonization

Dossier:Consistent with Heat Pipe & Two-PhaseHarmonisation 2003

Ref. Number: G517-070MC Budget: 250 K€Activity Title: Multistable Composite Structures

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Description: The objectis of this study is to explore the possibility of using asymmetriccomposite laminates in spacraft applications. Typical applications of compositematerials in spacecraft are all based on a design having quasi-isotropic propertieskeeping the mass as low as possible. This typically results in symmetrical layupsof CFRP laminates having zero curvature. Asymmetrical laminates with non-zerocurvature and showing multistable behaviour might have interesting applicationsin deployable structures, thermal control systems (deflecting or focusing IRradiation), latches, safety mechanisms, valves, etc. The advantage of theselaminates is that there is only the need to spend energy to transition from onestate to the other. �Initial feasibility studies for use of multistable structures inspace applications. Phase 1: Identification of space application and respectiverequirements, review of state of the art of multistable composites. Development ofaccurate models to predict the multistable shapes, optimization, propose actuationsolution, manufacturing and test on sample level, demonstrator proposal (2-3different concepts/applications). If the sample tests are promising, a Phase 2should be initiated. Phase 2: Design, analysis and manufacturing of thedemonstrators. The envisaged demonstrator structure will be representative of theapplications. The demonstrator tests will include basic performance tests, as wellas functional tests, also under different thermal, moisture environments. Phase 2will be concluded by the evaluation of test results and an update of possible spaceapplications.

Deliverables: 1. Materials samples, 2. Breadboard, 3. DemonstratorApplication: all spacecraft missionsCurrent TRL: 2 Target TRL: 3 Duration: 18 MonthsRef ESTER: T-543


N/A

Ref. Number: G517-071MC Budget: 350 K€Activity Title: New Concepts for Advanced Structural Sandwich Panels Description: New materials, mechanical configurations and processes developed within other

domains of engineering, allow for advanced concepts not yet implemented inspace applications. Foam cores enable either thermal isolation or in the oppositecase an improved thermal/electrical conductivity, depending on the parameters.Chiral core types of honeycomb cores would offer the possibility to manufacturelarge-curvature plates with negligible effect of the core, while offering othercapabilities, such as shape controllability. The consideration of transmissionlosses and dielectric constants within the materials and configurations ismandatory, e.g., in the transmission mode of antenna designs. In general, theimplementation of these and other new materials and structural concepts shallresult in a beneficial optimisation of sandwich structures for several applications.�The objectives of this activity are: 1. Study new materials and configurations forhoneycomb cores for different applications (ultrastable sandwich structures,antenna reflector sandwich structure, composite material thermal radiators, solararray substrates and RF transparent sandwiches), 2. Manufacture and testbreadboards for the applications, 3. Development of insert applications (e.g. useof composite inserts developed in Europe, 4. Verification procedures, 5.Demonstrator testing.

Deliverables: Study on new concepts, Samples and breadboards, Mathematical models,Demonstrator testing.

Application: All spacecraft missionsCurrent TRL: 2 Target TRL: 4 Duration: 18 Months



Ref ESTER: T-534, T-7750 HarmonizationDossier:

Consistent (Composites Harmonisation)

Ref. Number: G517-072MP Budget: 300 K€Activity Title: Very Low Earth Orbit Satellite (V-LEO) - AERO-THERMODYNAMICS Description: The activity "Low Flying Platform - Mission Analysis and Design" aims at

developing a new concept of satellite platforms able to fly at very low altitudes.

One objective is to gain confidence in the aerothermodynamic environment,identify the criticalities for the thermo-mechanical subsystem and identify possiblesolutions, evaluate the impact of new development on the phase C/D planningand cost.

The contractor shall perform:

o simulation of orbital dynamics inside the atmosphereo evaluation of thermal loadso identification of preliminary thermal control solutionso identification of possible improvement to the platform shape/attitude in order tooptimize thermalo identification of health-monitoring sensors necessary for the specific application

Deliverables: Final Report, ModelsApplication: Very Low-Earth Orbiting MissionsCurrent TRL: Target TRL: Duration: 12 MonthsRef ESTER: Harmonization

Dossier:N/A

Ref. Number: G517-073MP Budget: 800 K€Activity Title: Very Low Earth Orbit Satellite (V-LEO) - Electric Propulsion Subsystem Description: The activity "Low Flying Platform - Mission Analysis and Design" aims at

developing a new concept of satellite platforms able to fly at very low altitudes.

ESA founded studies have already identified Electric Propulsion (EP) as enabletechnology for future Earth Observation Missions due to its high fuel massefficiency and its high accuracy thrust capability. Those studies (Ref: C.N.18271/04/NL/CP) have highlighted the potential payload advantages of usingElectric Propulsion Systems compared with Chemical Propulsion Systems, gainedby reducing altitude and/or to increase the mission lifetime, in terms of:o Improvement of mission performanceso Mass savingo Cost (use of cheaper launchers)

Within this progect the optimal EP system shall be identified with reference topotential LEO mission requirements and accomodation on the reference satelliteplatform.

Within the project the contractor shall design and manufacture an EM thruster forthe related mission scenario, to be hosted onboard an existing satellite platform(e.g. MITA, future french multiporpose platform).

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Mechanical, magnetic (if applicable) and thermal analysis shall be included. List ofprocess to be used shall be included.

The thruster shall undergo a functional test campaign followed by endurance testto verify capability to satisfy the envisaged requirements.

Deliverables: Thruster Design Report, Thruster design data file(s), Thruster test data file(s),Test report, DDQ Plan and schedule, Engineering Model

Application: Very Low-Earth Orbiting MissionsCurrent TRL: 3 Target TRL: 5 Duration: 18 MonthsRef ESTER: Harmonization

Dossier:EP harmonisation: activity I2

Ref. Number: G517-074MP Budget: 500 K€Activity Title: Very Low Earth Orbit Satellite (V-LEO) - Mission Analysis and Design Description: The proposed activity covers the system level mission feasibility study and the

preliminary design of the platform able to fly at very low altitudes (i.e. from 250Kmto 400Km) and compensating all the effects induced by such environment, suchas the atmospheric drag. The study will identify different mission scenarios thatcan drive the specification of the platform, focusing in particular on EO missionsthat can mostly benefit of the very low orbit, such as LIDAR and opticalinstruments.A dedicated and customized software tool for V-LEO missions analysis will bedeveloped in order to effectively support trade-off phases for specific missionrequirements and for optimization of the main platform configuration and sizingparameters.In fact, different key aspects will have to be considered due to the specificenvironment of V-LEO, both for the compensation the atmosphere affects (e.g.drag, dynamics, impacts on movable appendices, thermal aspects, etc.) and alsofor the most effective exploitation of the features that the peculiar orbit will present(e.g. revisit time, ground station aspects related to high velocity, etc.).The SW tool will allow to size the on board resources in order to determine thebest V-LEO orbit, as a function of the mission requirements, the mission life, theinstrument complexity, the power requirements, the consumables, etc.Such trade-off will identify the modifications to be introduced in a standard LEOplatform (e.g. MITA) in order to define the most suitable concept for the V-LEOplatform, the relevant Design and Development Plan that will lead to theelaboration of the roadmap for the consolidation of the platform design.Among other aspects already mentioned above, a key technology for theproposed V-LEO concept will be the propulsion technology necessary formaintaining the orbit by compensating the atmospheric drag. Consequently, thepropulsion related aspects will be focused in specific, in order to identify the besttechnology that can provide low thrust and high specific impulse with optimizationof on board resources (e.g. electric propulsion).

Deliverables: Phase A feasibility study. V-LEO mission analysis toolApplication: Very Low-Earth Orbiting MissionsCurrent TRL: Target TRL: Duration: 12 MonthsRef ESTER: Harmonization

Dossier:N/A

Ref. Number: G517-075GS Budget: 750 K€



Activity Title: Ka-band klystron power amplifier prototypeObjectives: 1) Analyze and determine the way to implement the Ka-band uplink with special

focus on the phase stability and Allan deviation (ADEV) performance.2) Develop a Ka-band transmitter compatible with the movable feed requirementsof the Ka Aberration subsystem starting from the Ka Band KPA (Klystron PowerAmplifier) developed by ASI (that does not consider the movable feed)

Description: The contractor shall perform a trade off between the different architectures toimplement the Ka-band KPA (Klystron Power Amplifier) compatible with amovable feed for compensating the Ka-band aberration. Architectures rangingfrom fixed Ka up-converter plus KPA and flexible waveguide, to the feed tomoveable KPA plus up-converter connected with rigid waveguide to the feed (plusintermediate and others envisaged by the contractor) shall be analysed and theirperformances evaluated in terms of power handling, reliability, phase stability,Allan deviation, etc.breadboard developed for ASI, in order to meet the specific requirements of ESA(specially concerning phase stability and feed movement). A prototyperepresentative of a production unit shall be manufactured and tested with the finalobjective (if the rest of elements are available) of mounting the prototype in ESACebreros station to validate on site the overall performances of the Ka transmitsubsystem.The activities to be executed are:* Trade off between the different architectures to implement the Ka-band KPA.Special focus on performances on power handling, reliability, phase stability, Allandeviation shall be considered. * Design, manufacturing and test of a KPA prototype representative of anoperational production unit (HW plus design documentation, test results and userdocumentation)

Deliverables: KPA prototype, Design and test documentationApplication: Bepi-Colombo radio science experiment: TRL 8 by 2013, Future Cosmic Vision

missions with Ka-band uplinkCurrent TRL: 3 Target TRL: 6 Duration: 18 MonthsRef ESTER: T-1264 Harmonization

Dossier:N/A

Ref. Number: G517-076GS Budget: 300 K€Activity Title: Improved Autotrack and search performance for ESTRACK AntennasObjectives: Enhancement of the search approach leading to reduced search times at

X/Ka-band in the Deep Space environment. Development, implementation andvalidation of additional features and functionalities for ESTRACK Antenna ControlUnits. Improvement of the Autotrack performance for LEO spacecrafts atX/Ka-band.

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Description: The Antenna Control Units (ACU) in the 15m and 35m stations of ESA ESTRACKnetwork are key components ensuring the required pointing and trackingperformances. Starting from the current status of development it is proposed todevelop the ACU further in order to implement additional functionalities andfeatures with the aim to: - improve the autotrack performance. The current autotrack controller concept isnot suitable for LEO spacecraft operated at Ka-band due to the large positionerrors in case of high accelerations (high elevation passes). Pre-studies haveindicated a very promising way to improve the tracking accuracy for such casesleading also to a benefit at S/X-band.- improved search leading to shorter search time, which are in particular importantfor X/Ka-band and in the Deep Space environment, where the antenna beam issmaller.- allow auto-tuning of the controller parameters- improve the tracking performances by e.g. employing accelerometers at reflectorand subreflector level (already installed in ESA Deep Space antennas), asadditional feedback information in the tracking control loops in order to achieve abetter wind gust disturbance rejection

Deliverables: ACU with additional features and functionality integrated and tested in anESTRACK station

Application: ESTRACK stations/when availableCurrent TRL: 5 Target TRL: 6 Duration: 18 MonthsRef ESTER: T-1108 Harmonization

Dossier:N/A

Ref. Number: G517-077GS Budget: 500 K€Activity Title: Holography System for Deep Space AntennasObjectives: Extension, implementation and validation of holography system developed for

VIL-4 Ka-band antenna for ESTRACK Deep Space AntennasDescription: A holography system, which measures the reflector accuracy of the VIL-4

Ka-band antenna, has been developed already. The holography measurementsare based on the simultaneous reception of the downlink signal of a geostationaryspacecraft with the antenna under test (AUT, here deep space antenna) and thereference antenna. From the measurement results (amplitude delta and phasedelta between both antennas), the surface accuracy of the antenna reflectors(AUT) can be derived.

The available system should now be extended for its usage at the ESTRACKdeep space antennas. In particular the measurement approach has to be refinedand the signal acquisition unit has to be adapted to the downlink equipment usedwithin the deep space antennas. The reference antenna delivered in the frame ofthe VIL-4 holography development will be used also for the deep space antennameasurements.

The deep space antennas are equipped with movable sub-reflectors. Theextended holography system will be able to optimize the sub-reflector position withrespect to maximum G/T.

As the CEB DSA is already mechanically prepared to host a holography system,the validation shall take place at CEB.

Deliverables: Holography measurement system including hardware and software required carryout reflector surface accuracy measurements.

Application: ESTRACK deep space stations/when availableCurrent TRL: 5 Target TRL: 6 Duration: 18 Months



Ref ESTER: T-1109, T-1108 HarmonizationDossier:

N/A

Ref. Number: G517-078GS Budget: 300 K€Activity Title: High Accuracy Reflector PanelObjectives: Development of a new reflector panel design for DSA3 with improved

performances compared to DSA1 and DSA2Description: ESA plans to establish a third Deep Space Antenna similar in design to the

already existing antennas in New Norcia and Cebreros. With the experiencegained from the New Norcia antenna, the accuracy requirements for the reflectorpanels were tightened for the Cebreros antenna in order to achieve the overalldesired performances in the Ka-Band. Due to schedule constraints, the approachchosen at that time was to keep design changes to the minimum compared to theNew Norcia panels. The only modification in the design was the addition ofinsulation of the panel backside in order to limit the thermal gradient across thepanel thus limiting its deformation due to thermal loads. Although this approach isworking satisfactorily for Cebreros, the following aspects could become critical forthe next DSA. - Reflector surface accuracy marginally fulfilled for Cebreros, for more severethermal environments this could no longer be the case.- Due to the additional weight of the insulation, the improvements achieved in thethermal behavior were partially compensated by a higher gravitational deformationin Cebreros- Long-term stability of the insulating material, cost in case of refurbishment- The chosen approach is only reducing one contributor in the overall surfaceaccuracy budget, with a different approach like change of panel materials, changeof panel manufacturing technologies or change of the panel design morecontributors could eventually be reduced.- Furthermore it is expected that with newer manufacturing technologies nowavailable, highly stable panels can be produced at reasonable cost.

It is thus proposed to develop a new reflector panel design aiming to improve theperformance of the next DSA reflector panels with the following scope of work:Review and Consolidation of Draft specification already elaboratedTechnology Survey and Panel Design Trade-offDetailed Design of a DSA 3 Representative Reflector PanelManufacturing of PrototypePrototype Validation

Deliverables: Prototype reflector panelApplication: ESTRACK stations/when availableCurrent TRL: 5 Target TRL: 6 Duration: 12 MonthsRef ESTER: T-1109, T-1108 Harmonization

Dossier:N/A


Activity Title: Development of an RF test bed for high power testing of ground station feedsystems.

Objectives: Develop and validate an RF test bed for high power testing of ground station feedsystems.

Description: Feed systems composed by dichroic mirrors and radiating horns operating up to100 KW will be required in the next future for Deep Space Missions application. It

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is presently not feasible testing the feed systems in anechoic chambers(absorbing panels are not able to handle very high power). Currently the testing isperformed by radiating directly into the sky. In Europe is not possible to performdirect radiation tests due to frequency and power restrictions thus very often sucha tests have to be performed outside Europe at very high costs.It is thus proposed to develop an RF test bed for high power testing of groundstation feed systems with the aim to develop a compact structure that can beused/integrated into any European anechoic chamber. With such a test bed all theRF high power transmitted by the feed system will be focused into water cooleddummy load. Additional measured will be adopted to reduce the thermal noise intothe receive chain.

In order to achieve this overall objective the following activities are envisaged:Requirements analysisDesign of RF test bedManufacturing of hardware Assembly, integration and validation of test bed in X-Band (Deep Space Missionband)

Deliverables: RF test bed for high power tests in X-Band usable in an anechoic chamberApplication: As soon as available, since some of the X-band RF components is already

available for testingCurrent TRL: 3 Target TRL: 6 Duration: 18 MonthsRef ESTER: T-1109 Harmonization

Dossier:N/A


Activity Title: Demonstration of simultaneous transmission and reception of data inKa-Band

Objectives: Integrate beam waveguide mechanisms and RF elements developed under TRPinto one of our Deep Space Stations and validate them in an operationalenvironment.

Description: Future Deep Space Missions are expected to simultaneously transmit and receivein Ka-Band.At these frequencies antenna gains are higher than for the currently used S- orX-Band thus the beam widths are very narrow, in the order of 20-30mdeg. Thesesmall beam widths in combination with the long distances involved in Deep SpaceMissions require to have a variable squint between the receive and transmitbeam.

This beam squint is necessary due to the relative movement of S/C and groundstation while the RF waves are propagating between both, similar to a huntertargeting ahead when trying to hit a moving object.

In the frame of preceding TRP study two prototype mechanisms have beendeveloped and tested at breadboard level that allow to move BWG elements andthus to realize the beam squint necessary for a simultaneous transmission andreception in Ka-Band. Parallel to that also Ka-Band RF elements (dichroic mirrors,feed) have been developed and tested component level.

The GSTP activity now proposed aims to integrate the developed these RFelements and prototype mechanisms into one of ESA ESTRACK Deep SpaceAntennas (Cebreros) and to demonstrate the overall concept and validate allelements in an operational environment.

In order to achieve this overall objective the following activities are envisaged:



- Software upgrade/modification of the controller of the prototype mechanisms tocommunicate with the Antenna Front End Controller- Corresponding adaptation of the Antenna Front End Controller software- Physical integration and alignment of the RF elements, the prototypemechanisms and the related controller in the DSA- Commissioning and testing of the new system, demonstration of the concept.

The on-site activities will have to be performed without interfering with operationalpasses.

Deliverables: Ka-Band beam waveguide elements (feed, dichroic) mounted on beam waveguidemechanisms and integrated into one of ESA´s Deep Space Antennas (Cebreros)

Application: Future deep space missions using Ka-Band transmission and reception like e.g.Bepi 2013


Dossier:N/A

Ref. Number: G517-081GI Budget: 300 K€Activity Title: Ground-Station Automation and Off-line operationsObjectives: The main objective of this study is to identify a scenario for automated

Ground-Station. Based on the scenario, the study shall focus on the requiredfunctionality that would support automation and allow the provision of TC and TMoff-line services.

Description: This study aims at analyzing possible scenarios for automated operations suchthat the control-centre would not need to be permanently connected. Typically,this kind of operation is needed for missions having short Passes over theStations (e.g. Earth Observation): automation would allow optimal provision ofservices. The following capability should be considered:- automatic configuration of the Ground-Station and capability;- off-line telecommanding allowing the control centre to download in advance thestack of Telecommands required for one or more passes, and subsequenttransmission of time-tagged Telecommands to the Spacecraft, with guarantee ofdelivery- capability to automatically receive, store and prepare off-line transmission ofTelemetry to the control centre;- capability to automatically acquire the signal and track the spacecraft.. capability to automatically execute mission configuration and spacecraftacquisition tasks to cope with short passes (typically, Earth Observationspacecraft).The study shall as well look into automatic recovery in case of problem: loss ofsignal, retransmission of Telecommands.Finally the study shall identify the information required for post-pass analysis andcorrection of possible misbehavior.The Study shall produce a prototype implementing an initial set of functions.

Tasks to be performed:1.- Identification of the various possible scenarios and possible operationalapproach; this includes the definition of the Protocols (within the SLE services) foroff-line TC services and for operations reporting.2.- Identification of the existing functions that would be affected;3 - Analysis of the recovery capability that would be required.4.- Prototype implementation, with the objective of demonstrating operationalimpacts.

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Deliverables: 1.- Technical notes and other supporting documents reporting about the technicaloutputs of the study, in particular including recommendations for an approach tothe layout of such a concurrent collaborative environment.2.- S/W prototype of infrastructure supporting the feasibility of the approach.

Application: Targeted missions shall be low earth orbiting mission characterized by (very) shortpasses over the Stations (presently this is the case for GOCE). This is atechnology push Study. Best estimated date is 2010.


Dossier:Not Harmonised

Ref. Number: G517-082GI Budget: 400 K€Activity Title: Combinatorial Optimization for Scheduling ApplicationsObjectives: Applicability of combinatorial optimization approach for scheduling purposes and

in particular for the efficient allocation of ground station passes.The combinatorial optimization approach is not only linked to the allocation ofground station passes, it could also be applied in other domains, as example forpayload operations where scientific opportunities or usage of channels wouldhave to be allocated in an optimal way. Expected benefits:- best use of ESA ground station assets and resources for the benefit of the ESAand non-ESA user community,- increase in efficiency for mandatory planning processes within ESA missionoperations,- better and faster service and access for ESA mission operations customers.

Description: Satellite operations require ground stations, from which the communications(Telemetry, Telecommand and Tracking) with the spacecraft can be conducted.The identification of the ground station passes to be selected is still primarily amanual process, which seems to be the case as well for several other SpaceAgencies.It is obvious that this manual process of selecting station passes becomes easierwhen more ground stations are available or when spacecraft dedicated groundstations are used. However, maintaining a larger network of ground stations has acost implication. The optimal and automated allocation of ground station passeswould require less ground antennas and furthermore less scheduling effort.

It is proposed that a combinatorial optimization approach for the efficientallocation of ground station passes is applied. It is proposed to study various methods in the area of combinatorial optimizationincluding aspect as:- relaxation based mixed-integer approach providing lower and upper optimalitybounds,- fast branch-and-bound and branch-and-cut algorithms,- advanced enumerative schemes,- constraint programming techniques,- acceleration by polyhedral and general cutting plane techniques.

For the selected method there should be mathematically founded guarantee that afeasible solution will be found under the assumption that one exists. In case thereis no feasible solution then approximate solutions will have to be computedaccording to user specified priorities.

The selected method should be able to cope with additional requirements such as:- treatment of larger number of satellites and ground stations,- fast check if requests by additional customers can be satisfied,- efficient short term and long term prediction capabilities,



- effective re-optimization for real-time changes e.g. of user requirements oravailability of resources.

Deliverables: Study report and a prototype software for the selected methodApplication: Optimization of ESTRACK ground stations scheduling. 3rdQ 2010Current TRL: 1 Target TRL: 6 Duration: 15 MonthsRef ESTER: Harmonization

Dossier:

Ref. Number: G517-083GI Budget: 400 K€

Activity Title: Integrated development and validation environment for operationsautomation

Objectives: The objective of this activity is to enable the efficient production of formalisedprocedures supporting the spacecraft operations automation. The added value ofthe pre-operational implementation that will be delivered is in the capability todefine and completely validate automation procedures within one singleenvironment.

Description: Now that generic tools supporting the deployment of operations automation areavailable, the main effort to actually automate the spacecraft operations will be inthe definition and validation of the automation procedures. The objective of thisactivity is therefore to provide the users with a pre-operational implementation of acomfortable environment which supports the definition and just-in-time validationof the automation procedures. The intention here is to bridge the gap betweenprocedures definition and procedures validation in the run-time executionenvironment. It is envisaged to capitalise on the existing generic products used byall missions at ESOC to define procedures (MOIS), to execute them automatically(MATIS), to interface with the automated system (SMF) and to simulate thebehaviours of Ground Data Systems (SIMSAT and GSTVi).

Deliverables: S/W demonstrator supporting the capability to efficiently set-up a test-bed forautomation procedures and the actual execution of automation validationactivities.

Application: These elements can be very generic as automation procedures and theautomation interface to ground infrastructure are defined according to standards.The intention is to integrate an operationally qualified version into the ESOCAutomation Infrastructure and to make it available to future missions as from year2011.

Current TRL: 4 Target TRL: 6 Duration: MonthsRef ESTER: T-7842, T-120 Harmonization

Dossier:

Ref. Number: G517-084GI Budget: 400 K€Activity Title: Ubiquitous alert and operations monitoring systemObjectives: Previous studies have provided an analysis of technologies compatible with

mobile phones to implement a 'remote operators alert system'. While the analysishas proved the feasibility of the approach, a formal validation of the differenttechnologies involved has yet to be done in the various operational environments,covering both spacecraft and ground station operations. In addition, it is requiredto extend the monitoring capabilities of remote operators by enabling them toaccess the most relevant operational data in order to properly handle the receivedalerts.

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Description: The increase of the space segment autonomy and the need to reduce the runningcosts of spacecraft operations have recently lead to the adoption of operationsconcepts that do not rely on the continuous presence of operators in the controlrooms. Similarly, on the side of ground stations control, an increasing level ofautomation is being implemented, thus enabling the relaxation of the continuousmonitoring approach adopted so far. However, a full deployment of 'lights-out'operations of space systems can only be achieved by a) having a monitoringsystem that can trigger an alarm in case of problems, b) having a system tocontact on call engineers in case of anomalies and c) enable the alerted operatorto properly assess the status of the controlled system and thus react to thereceived alert (e.g. accept, forward, disregard).The monitoring of the controlled system status (spacecraft or ground station) andassociated alarms generation is already part of the relevant control system (theSpacecraft Control System or the Station Computer). However, the functionality tonotify alerts to on-call personnel and to enable their remote access to theoperational data is still missing.A previous GSTP study successfully demonstrated the feasibility of a number oftechnologies to implement these tasks. The deployment and roll-out of such asystem, however, cannot be done unless a thorough validation in the relevantoperational environments is performed. This study will perform such validation. Inaddition to this, the capability to collect and visualise a minimum set of essentialdata on personal (ultra-light) devices that can communicate via standard mobilenetworks will be implemented and demonstrated. This will require the definition ofhighly portable and optimized data visualization and presentation techniqueswhich enable the remote operator to acquire an appropriate amount of detailsusing devices of very limited size. The security implications of such an applicationwill also be carefully assessed.

Deliverables: The study will deliver a pre-operational demonstrator of a remote alert and statusmonitoring application, enabling access to essential operational data via ultra-lightpersonal devices (of the size of a mobile phone).Such prototype will be based on deliverables of the previous study but will extendit to cover:• Capability to notify alerts received from any critical ground data system related tospacecraft and ground segment control• Capability to visualize remotely the operational status of the controlled system onultra-light devices• Capability to

The study will also cover the system installation and deployment such to test thedeliverables in the relevant operational environment. This includes ESOC’snetworks reserved to operations, ESOC office network, the public GSM networkand probably the Internet. The validation campaign will be based on a real mission(GOCE).

Application: GOCE will be the first mission to apply the concept. Several validation tests shallbe done in parallel with GOCE routine operations (end of 2009).

Current TRL: 3 Target TRL: 6 Duration: 12 MonthsRef ESTER: T-96, T-8412, T-8413 Harmonization

Dossier:

Ref. Number: G517-085HS Budget: 350 K€Activity Title: Integrated Monitoring & Diagnostic of End-to-End Communication LinkObjectives: The objective of this project is to implement a pre-operational prototype

application that monitors in near real-time the complete communication link inorder to detect anomalies and interruption of services in the various elements andto support the identification of the root cause.



Description: The end-to-end communication link consists of many different elements that aremanaged and operated separately. Starting at the spacecraft, going over theground-stations to the ground communication network, the NIS, to the controlcentre and finally to the operator's console and to the archives, the complete chainis managed by different control units and responsibility is split. No end-to-endsituation awareness is available in one single monitor and in case of degradationor disruption of service the root cause analysis is not straight forward.Relevant data will be automatically collected in near real-time from availableinterfaces and/or repositories. The data will then be analyzed using appropriatetechnologies such as machine learning and other artificial intelligence techniques.The data will be processed and compiled in order to present to the user a globalview of the status of the end-to-end communication link through a graphical userinterface.

This activity is a continuation of the TRP study CESADS, which addressed theend-to-end communication link in the case of ENVISAT with an early prototypesystem.

The proposed study consists of two phases:- Phase 1: System design and prototype implementation using prepared data setsoffline- Phase 2: Application of the prototype system in the real environment usingavailable data sources at infrastructure level in near real-time

Deliverables: Software prototypeApplication: Applicable to all missionsCurrent TRL: Target TRL: Duration: 21 MonthsRef ESTER: T-95 Harmonization

Dossier:N/A

Ref. Number: G517-086GS Budget: 300 K€Activity Title: Deep space receiver for support during superior solar conjunctionsObjectives: To develop and test a receiver which is optimum in a channel where Rician

fluctuations are dominant, which is the typical scenario applicable to deep spacemissions during superior solar conjunctions.

Description: Deep space missions incur periodically in superior solar conjunctions, i.e. phasesduring which the telecommunication link between Earth and Spacecraft transitsthrough the solar plasma. This is causing impairments to the quality of the link, interms of amplitude and phase fluctuations, spectral broadening and other effects,in turn causing loss of telemetry on ground reception side. The impact issignificant in terms of science data return, which is interrupted for periods of timeranging between days and weeks, depending upon the level of solar activity. Thedeep space receivers of the ground stations are generally optimized for receptionof signals through Gaussian channels, i.e. channels where the unique perturbationis given by additive Gaussian noise, with generally assumed flat power spectrum.However the Gaussian model is not adequate for describing thetelecommunication channel during a superior solar conjunction: in such phase aRician model describes more effectively the amplitude and phase scintillationeffects which are observed, and which are due to the transition of thecommunication signals through inhomogeneous plasma medium.The objective of the proposed work is to study receivers which are optimum in aRician channel, and which can be used during a superior solar conjunction toimprove as much as theoretically achievable the quality of the telemetry reception.Work in this direction has been made in mobile telecommunications; however, thistechnology has to be introduced in deep space communications, especially for theESA deep space network.

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The input to the activity is a large set of data, representing the downlink signaltransmitted by an ESA Deep Space Spacecraft (Venus Express) and received atESA deep space ground stations during a superior solar conjunction. The signal isrecorded in open loop by using a wide bandwidth, covering the whole telemetryspectrum.As part of the study, a software receiver is designed, developed, and tested overthe recorded data. The selection and procurement of the COTS hardware platformwhere this software will run efficiently is also part of this development.The receiver is designed taking in to account the characteristics of thetelecommunications channel, and its performances are compared with theperformance of the available “standard” deep space receiver, suitable for aGaussian channel and acting on the same data.The output from the study consists of the prototype receiver, of demonstratedsuperior performances in respect to the standard deep space receiver, as well asall associated documentation. The prototype has a sufficient level of operabilityallowing its use during a subsequent solar conjunction of a deep space mission,for validation of its superior performance during an operational support.

Deliverables: Prototype software receiver, including the hardware platform. All associateddocumentation (survey of literature, design, architectural definition, testing)

Application: The proposed development is required for all ESA deep space missions, for useduring superior solar conjunctions. It is of particular use for BepiColombo, due tothe low separation angle from the Sun experienced during the whole in-orbitphase.


Dossier:N/A

EUROPEAN SPACE AGENCY INDUSTRIAL POLICY … · INDUSTRIAL POLICY COMMITTEE GENERAL SUPPORT...

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