GSTP-6 Element 1 Compendium of Potential Generic ... - emits - ESA

ESA UNCLASSIFIED – For Official UseestecEuropean Space Researchand Technology CentreKeplerlaan 12201 AZ NoordwijkThe NetherlandsT +31 (0)71 565 6565F +31 (0)71 565 6040www.esa.intGSTP-6 Element 1Compendium of Potential GenericTechnology Activities (SD7)Activities intended to be initiated in 2013Prepared by N. PeinadoReference TEC-SGT/2013-007/NPIssue 1Revision 1Date of Issue 26-02-2013StatusDocument TypeDistribution

ESA UNCLASSIFIED – For Official UseTitleIssue 1 Revision 1Author Date 26-02-2013Approved byDateReason for change Issue Revision DateIssue 1 Revision 1Reason for change Date Pages Paragraph(s)Page 2/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseTable of contents:1 INTRODUCTION ................................................................................................................................ 42 LIST OF ACTIVITIES ......................................................................................................................... 73 DESCRIPTION OF ACTIVITIES ........................................................................................................ 153.1 CORE ................................................................................................................................................................................ 153.1.1 TD 1- On-board Data Systems ....................................................................................................................................... 153.1.2 TD 2- Space System Software ........................................................................................................................................ 183.1.3 TD 3- Spacecraft Electrical Power ................................................................................................................................ 223.1.4 TD 4- Spacecraft Environment & Effects ...................................................................................................................... 253.1.5 TD 5- Space System Control .......................................................................................................................................... 313.1.6 TD 6- RF Payload and Systems ..................................................................................................................................... 373.1.7 TD 7- Electromagnetic Technologies and Techniques ................................................................................................. 393.1.8 TD 8- System Design & Verification ............................................................................................................................. 423.1.9 TD 9- Mission Operations and Ground Data Systems ................................................................................................ 483.1.10 TD 10- Flight Dynamics and GNSS ............................................................................................................................... 563.1.11 TD 11- Space Debris ....................................................................................................................................................... 583.1.12 TD 12- Ground Station System & Networking............................................................................................................. 603.1.13 TD 13- Automation, Telepresence & Robotics .............................................................................................................. 623.1.14 TD 14- Life & Physical Sciences .................................................................................................................................... 633.1.15 TD 15- Mechanisms & Tribology ...................................................................................................................................663.1.16 TD 16- Optics ................................................................................................................................................................. 703.1.17 TD 17- Optoelectronics .................................................................................................................................................. 783.1.18 TD 19- Propulsion ......................................................................................................................................................... 843.1.19 TD 20- Structures & Pyrotechnics ............................................................................................................................... 863.1.20 TD 22- Thermal ............................................................................................................................................................. 933.1.21 TD 22- Environmental Control Life Support (ECLS) and In-Situ Resource Utilisation (ISRU) ...............................963.1.22 TD 23- EEE Components and quality ........................................................................................................................... 973.1.23 TD 24- Materials and Processes .................................................................................................................................. 1103.2 SAVOIR .......................................................................................................................................................................... 119Page 3/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Use1 INTRODUCTIONDuring the Council meeting at Ministerial level held in November 2012, the sixth Period ofthe GSTP (ESA/C(2012)199) was presented and extensively subscribed by the GSTPParticipating States with the following framework:GSTP-6 Element 1 – Support Technology Activities for Projects and IndustryGSTP-6 Element 2 – CompetitivenessGSTP-6 Element 3 – Technology Flight OpportunitiesGSTP-6 Element 4 – Precise Formation Flying DemonstrationFollowing the approval of this new GSTP Period, this document provides the first list ofcandidate activities to the Initial work Plan of the GSTP-6 Element 1, in line with theprocess and timeline described in the information note to September IPCESA/IPC(2012)98 – Preparing the work plans for the GSTP-6 Element 1.As indicated in this referenced document, Technology development activities in ESA areorganised in 9 service domains (SD) and 25 technology domains (TD). This first preselectioncorresponds to activities belonging to the Generic Domain, SD7, devoted totransversal technologies common to several other SD, and to exploitation of technology (r)-evolution.According to the ESA-wide technology E2E process described in ESA/IPC(2008)61 rev 1,the activities which are part of this compendium have been pre-selected following anintensive internal exercise started in October 2012 and which included programmaticscreening, technical evaluation and consistency checking with technology strategy andTHAG Roadmaps.In addition to the core activities which are dedicated to the development of technologies,building blocks and components for future space, three special areas have been identifiedwhose activities are shown in these documents in separate sections:CLEAN SPACE: This is an ESA cross-cutting initiative with the aim to contribute tothe reduction of the environmental impact of space programmes, taking intoaccount the overall life-cycle and the management of residual waste and pollutionresulting from space activities. The list and descriptions of candidate activities forthis special area is provided in a separate document.SAVOIR: Space Avionics Open Interface aRchitecture. This is an initiative tofederate the space avionics community and to work together in order to improve theway that the European Space community builds avionics subsystems.SPACE & ENERGY: This special area addresses open innovation, spin-in /out andjoint R&T as currently initiated under GSTP 5 with the overall goal of achieving amore sustainable, less-carbon intensive European energy sector.Page 4/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseThis compendium is divided in two separate documents according to the intendedinitiating dates of the activities:GSTP-6 Element 1 Compendium of Potential Generic TechnologyActivities (SD7) - Activities intended to be initiated in 2013. Includes a listand detailed description of 77 activities. (Present document)GSTP-6 Element 1 Compendium of Potential Generic TechnologyActivities (SD7) - Activities intended to be initiated in 2014–Includes a listand detailed description of 63 activities.This compendium is issued to Delegations of GSTP-6 Participating States and theirindustries for comments. Such comments will be considered in establishing the initial workplan for this GSTP 6 Element 1.The objective is to have a good indication of the developments GSTP Participating Statesmay consider to support in order to present the GSTP-6 Element 1 Initial Work Plan with aconsolidated set of activities to the IPC in May 2013 and the corresponding ProcurementPlan to the IPC in June 2013 for approval.Page 5/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

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ESA UNCLASSIFIED – For Official Use2 LIST OF ACTIVITIESTD 1- On-board Data SystemsGSTP-6ReferenceTitleBudget(K€)G617-003ED Reconfigurable Payload Processor 1,000G617-005ED Transducer interface ASIC 1,000G617-008EDDemonstration and validation of an inter-processor link for futureOBCs300Total 2,300TD 2- Space System SoftwareGSTP-6ReferenceTitleBudget(K€)G617-009SW OBCP BB Product Specification Validation 700G617-011SW RTEMS qualification extensions 500Total 1,200TD 3- Spacecraft Electrical PowerGSTP-6ReferenceTitleBudget(K€)G617-015EPImplementation of new Power Systems architectures for LEOmissions - Solar Array Regulator based on Buck-Boost Regulator600G617-017EP Lithium-ion VES16 cell Balancing System 400G617-020EP Improved Ge wafer technology for multi-junction solar cells III 1,000Total 2,000TD 4- Spacecraft Environment & EffectsGSTP-6ReferenceTitleBudget(K€)G617-022EEHighly Miniaturised Radiation Monitor Phase C-D and single-chip(LETmeter) version.1,500G617-024EE ESD monitor 500G617-026EEStudy of radiation energy effects on electronic components withhigh energy heavy ion beams.500G617-027EE Geant4 kernel speed-up for high-efficiency simulations in space 500Total 3,000Page 7/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseTD 5- Space System ControlGSTP-6ReferenceTitleBudget(K€)G617-028EC High accuracy image stabilization system prototyping 1,000G617-030EC GNC Analysis, Design and Verification Framework using MATLAB300onlyG617-035EC Generic AOCS/GNC techniques and design framework for Failure700Detection Isolation and RecoveryG617-036EC Pointing Error Engineering Software Framework 400Total 2,400TD 6- RF Payload and SystemsGSTP-6ReferenceTitleBudget(K€)G617-037ET Advanced manufacturing and integration techniques for TT&C800transponders/transceiversG617-040ET Miniaturized Timing Sources 1,000Total 1,800TD 7- Electromagnetic Technologies and TechniquesGSTP-6ReferenceTitleBudget(K€)G617-047EE Millimeter wave Validation Standard (mm-VAST)antenna 350G617-051EE Accurate RF material characterisation using scattering300measurements from Quasi-Optical benchG617-052EE Medium-to-high gain X-band antenna with customisable patternand polarisation600Total 1,250TD 8- System Design & VerificationGSTP-6ReferenceTitleBudget(K€)G617-054SW Precise and Flexible Wiki-Based Requirements Engineering 700G617-055SW Adaptation and Demonstration of MBSE for a real project (Pilot) 2,000G617-056SW A Generic Mapping Toolbox for Space CAE Data 400Total 3,100Page 8/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseTD 9- Mission Operations and Ground Data SystemsGSTP-6ReferenceTitleBudget(K€)G617-061GI Integration of ESA Ground Data Systems into Cloud Based200Platforms (PaaS and SaaS solutions)G617-062GI Security as a Service for Ground Data Systems 300G617-064GI Harmonisation of Numerical Software Validation Facility (NSVF)200and Operational Simulator modelsG617-065GI Scalable ground systems for high rate and high volume mission500operational dataG617-066GI Automated rule-based cross-validation of operational data 400Total 1,600TD 10- Flight Dynamics and GNSSGSTP-6ReferenceG617-067GFTitleExtension of the DO-IT trajectory design software forinterplanetary trajectories based on low-thrust propulsioncombined with flybysBudget(K€)200Total 200TD 11- Space DebrisGSTP-6ReferenceG617-073GRTitleBi-static beampark experiments and novel mechanical scanningand stare and chase conceptsBudget(K€)300Total 300TD 12- Ground Station System & NetworkingGSTP-6ReferenceTitleBudget(K€)G617-074GS Eye-Safe Ground Beacon System 400G617-075GS Experimental 20-40 GHz band InP MMIC based cryogenic LNAsprototyping500Total 900Page 9/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseTD 13- Automation, Telepresence & RoboticsGSTP-6ReferenceG617-076MMTitleDevelopment of technology tools for training and operations of theMETERON Mission Preparation and Training CentreBudget(K€)770Total 770TD 14- Life & Physical SciencesGSTP-6ReferenceTitleBudget(K€)G617-077MM In Situ Plasma Cleaning of Space Optics 600G617-078MM Self Validating High Temperature Sensors 700G617-079MM Optimisation and validation of ultra cleaning methods applied tospacecraft materials500Total 1,800TD 15- Mechanisms & TribologyGSTP-6ReferenceTitleBudget(K€)G617-080MS Improvement of Solar Array Deployment Mechanisms1,250technologies.G617-081MS Improvement of high accuracy angular optical sensors. 800G617-082MS Advanced simulation tools for deployment, dynamics predictions300and on-ground verificationG617-083MS In-orbit manufacturing of very long booms. 200Total 2,550TD 16- OpticsGSTP-6ReferenceTitleBudget(K€)G617-085MM Digital Micro-Mirror Array (DMA) for space optical instruments 1,000G617-086MM Calomel-Based TIR Hyperspectral Imager 950G617-087MM High Speed Deterministic Polishing of Strongly Aspherical Mirrors 800G617-088MM WFE test of large aspheric optics 500G617-089MM Effect of radiation on light-weighted mirror substrates (in750particular Zerodur)G617-090MM Particle contamination: scattering models and measurement device 500Total 4,500Page 10/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseTD 17- OptoelectronicsGSTP-6ReferenceTitleBudget(K€)G617-092MM Multi-Gigabit Optical Fiber Communications 600G617-094MM Enhancement of electrostatic accelerometers for Earth and800planetary sciences and fundamental physics: flight data analysis,model and design refinements, breadboarding and testingG617-095MM Development of low-noise laser-diode drive source for ultrastable450coherent CW laser sources applicationsG617-096MM Low cost, low power, medium performance resonant-micro-optical800Gyrosope (RMOG)based on resonant ring lasersG617-097MM High performance optical filters based on Si fine grid supportedultra thin SiN foils220Total 2,870TD 19- PropulsionGSTP-6ReferenceTitleBudget(K€)G617-099MP CUSP ION ENGINE 1,000G617-100MP Improvement of the lifetime of Electric Propulsion Thrusters usingdifferent propellant by reducing sputtering effects on materials300Total 1,300TD 20- Structures & PyrotechnicsGSTP-6ReferenceTitleBudget(K€)G617-101MS Verification of Composite Laminates under Cryogenic Thermo-300Mechanical LoadingG617-104MS Development of modular multifunctional structure panel prototype 450G617-106MS Demonstration of Thermoplastic Composites 500G617-107MS MATS: Multilayer Adaptive Thin Shell Reflectors for Future Space600TelescopesG617-108MS Improved design and verification of cryocoolers subjected to veryhigh number of fatigue load cycles ('gigacycles')500Total 2,350Page 11/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseTD 21- ThermalGSTP-6ReferenceTitleBudget(K€)G617-110MT Low Profile, Low Thermal Conductivity and Highly Stable Stand-300OffsG617-111MT Enhancement of Loop Heat Pipe (LHP) Modelling Tool 150G617-112MT Bi-Metallic Junctions for Loop Heat Pipes and Heat Pipes 300Total 750TD 22- Environmental Control Life Support (ECLS) and In-Situ Resource Utilisation(ISRU)GSTP-6ReferenceG617-115MMTitleStudy of countermeasures against microbial contamination ofspacescraft and payloadsBudget(K€)350Total 350TD 23- EEE Components and qualityGSTP-6ReferenceTitleBudget(K€)G617-116QT Prototyping and characterization of 600V SiC MOSFET 700G617-118QT Evaluation of high density optical links for high speed300transmission.G617-119QT Radiation testing of non-volatile memories for space applications 300G617-122QT Miniature Solderless Interposer Type Connector 500G617-123QT Improved thermal management capability of power2,000semiconductorsG617-124QT Development of Standard Interface Components 800Total 4,600Page 12/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseTD 24- Materials and ProcessesGSTP-6ReferenceTitleBudget(K€)G617-125QT Friction Stir Welded Low Cost Titanium Propellant Tank 1,500G617-127QT Evaluation of the potential of the Thin Ply Technology for space700applicationsG617-128QT Evaluation of low temperature processing capabilities of novel thin500and flexible ceramic coatingsG617-130QT Evaluation of lighter and more efficient radiation protection for500electronic and sensitive parts.G617-131QT Filament winding TISIC 2,500G617-132QT Electron Beam Welding for Safety Critical Space Applications 500Total 6,200Specific area: SAVOIRGSTP-6ReferenceTitleBudget(K€)G61V-001EC AES/SAVOIR New models for the AOCS Unit Simulation Models400Library (AOCS UnitSim)G61V-005ED AES/SAVOIR Electronic Data sheet definition 800Total 1,200Page 13/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

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ESA UNCLASSIFIED – For Official Use3 DESCRIPTION OF ACTIVITIES3.1 CORE3.1.1 TD 1- On-board Data SystemsCore /Specific AreasCORETechnologyDomain1 On-board Data SystemsRef. Number:G617-003EDBudget(k€):1000Title:Reconfigurable Payload ProcessorObjectives:Description:Development of a reconfigurable payload processor building block prototypeReconfigurable Processing Modules have a good perspective and a number ofapplications in the future. Based on reconfigurable FPGA or similar technology,they offer the possibility to reuse a once developed hardware platform for a widerange of applications. The silicon fabric of the latest generations of reconfigurableFPGAs offer vast amounts of logic resources that carter for high performancecomputing as well as hardware optimisation of processing algorithms. This isachieved by implementing a new hardware design adapted to the new processingrequirements, simply by loading a new configuration to the FPGA. This can notonly be done at design time on the ground but also during the whole missionlifetime. This offers for example the opportunity to reuse the same module fordifferent functions in subsequent mission phases by reconfiguration.ESA has initiated two parallel activities to study these concepts where focus isdirected towards ensuring high reliability and safety for the mission. The DRPMstudies encompassed also aspects related to the on-board data handling SW,performance benchmarking of typical on-board data processing tasks as well asstudying FPGA development tools that insert radiation mitigation techniques in anautomated fashion.In this proposed activity will develop a generic building block based on thistechnology that can be applied in a wide range of future missions. The FPGA can bea COTS one, but in the future can be the next generation FPGA (developed jointlyin TRP and FP7).Deliverables:PrototypeCurrent TRL: 3 Target TRL: 5Duration(months)24Applicable THAG Roadmap: On-Board Payload Data Processing (2011)Page 15/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain1 On-board Data SystemsRef. Number:G617-005EDBudget(k€):1000Title:Transducer interface ASICObjectives:Description:A generic mixed analog-digital sensor ASIC implemented in a low-count pinpackagewith CAN/SPI InterfaceA generic mixed analog-digital sensor ASIC shall be developed as ideal complementto discrete control lines integration into transducer buses and to increasemodularity of RTU designs. A simple low pin count ASIC, with (at least) an analogfront-end 12-bit 50ksps ADC, a mux and circuitry for sensor conditioning shall bedesigned, manufactured and validated. To be used as remote node to be digitallycontrolled by a RTU/RIU or by the OBC through a SPI or CAN interface. Theavailability of this component will allow to decentralize the collection of sensorssignals reducing the harness complexity on a Spacecraft.TASK Requirements definition and analysis, Feasibility and Architectural Study,Detailed Design, Implementation and Validation. An adequate set of devices will bemanufactured in order to perform a validation test campaignDeliverables:PrototypeCurrent TRL: 3 Target TRL: 5Duration(months)24Applicable THAG Roadmap: Data Systems and On-Board Computers (2011)Page 16/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain1 On-board Data SystemsRef. Number:G617-008EDBudget(k€):300Title:Objectives:Description:Demonstration and validation of an inter-processor link for futureOBCsThe architecture of new OBCs for High Performance platforms requires the use ofa interprocessor link as fast and reliable interface between the main Processor andother complex ICs as Co-Processor or Enhanced Memory Controller and/orbetween Main and Redundant Processors of a OBC.The use of the low speed serial communication channels (e.g. RS422/485)orparallel bus (PCI bus) is not sufficient in term of sustained performances andspecific features as reliability. Fast and highly reliable link is necessary for futuregeneration core processor. A study and validation of a new bus is the main objectiveof this activity. Spin-in from the commercial/embedded world (TRL 3) will beconsidered, in particular High Speed Serial Link as RapidIO, HyperTransport,PCIexpress but also proprietary ones (e.g. Intel QuickPath) will be considered.After a trade off a candidate will be selected and a demonstrator representing aflight scenario will be built and validated in a relevant environment.Deliverables:Other: Study Report & qualificationCurrent TRL: 3 Target TRL: 5Duration(months)18Applicable THAG Roadmap: Data Systems and On-Board Computers (2011)Page 17/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Use3.1.2 TD 2- Space System SoftwareCore /Specific AreasCORETechnologyDomain2 Space System SoftwareRef. Number:G617-009SWBudget(k€):700Title:OBCP BB Product Specification ValidationObjectives:The On-Board Control Procedure (OBCP) concept is a powerful way to controlspacecraft or to implement on-board functions. OBCPs are flight controlprocedures that can be resident on-board or that can be uploaded to the spacecraftas required by the ground. They serve for controlling processes, which may beactive for an extended period of time and which may involve the execution of asequence of commands. OBCPs represent, along with the Mission Timeline (MTL),the most important capability that provides a high degree of autonomy to thespacecraft. However, although the MTL allows for autonomous TC execution, itscapability is too limited as it does not allow immediate reaction to unexpectedbehaviour.An ECSS standard on OBCPs has been published (ECSS-E-ST-70-01C). Thestandard defines the concept of an OBCP system, identifying the on-boardfunctionality for OBCP execution and the ground functionality for OBCPpreparation and subsequent control. It also defines the development lifecycle forOBCPs and identifies the relationships of this lifecycle with the overall spacesystem, and in particular with the other elements of the spacecraft flight software(FSW).The piece of software to execute on-board procedures, called an OBCP engine orinterpreter, has been identified as a potential building block in the FSW referencearchitecture. Today, a number of proprietary implementations of this buildingblock exist, having been used in various ESA missions over a number of years andhaving successfully demonstrated its validity and usability. However their interfacehas not been standardised and they are in general not compliant to the new OBCPstandard. Hence, a software architecture study in the frame of the GSTP Element 2is needed to identify requirements for compatibility with open interfacearchitectures and in line with the new standard.Various projects have produced their own OBCP engines, however there has beenminimal effort to standardise the engine or its interface to the flight software(FSW). The engines all use different languages with different capabilities and allowfor various degrees of accessibility to FSW. Several technologies have beenconsidered as a basis for the OBCP engine, in particular Java, scripting languages,EGSE languages such as PLUTO (Procedure Language for Users in Test andOperations) and various ad-hoc languages.The activity shall be implemented in coordination with SAVOIR and its mainobjectives are as follows:1) Consolidate requirements and interface specifications defined in the precursorPage 18/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseGSTP 5.2 activity and execute the first level of SAVOIR review to establish aSAVOIR OBCP product specification. The consolidated product specification shallfurther be submitted to the second level of SAVOIR review invloving the wholeSAVOIR community.2) As a validation activity of the SAVOIR product specification, Design, developand test a full-fledge implementation of the OBCP Building Block, compliant withthe now consolidated requirements and interfaces defined in the previous GSTPactivity, and compliant to the ECSS-E-ST-70-01 standard, taking into account i) thereview of the standard performed in the precursor activity and also ii) the review ofexisting implementations. The development should be compliant to the ECSS-E-ST-40C standard. The idea is to validate the product specifciation, with theobjective that the product could be integrated to Flight Software of a particularmission and subjected to integration validation3) Take into account reusability of i) ground-based tools, ii) OBCP building blockand iii) OBCP scripts. This depends on the selection of source language, targetlanguage and overall OBCP development concept. One of the key motivatins of theSAVOIR-FAIRE Reference Architecture is reuse, but these options for OBCP reusedemonstrate that there are several levels on which reuse could be done.4) Take into account an option that the building block's architecture could dependon the use of logical partitioning as used in the Integrated Modular Architecture(IMA for Space).Description:This activity is a follow-up of the "Requirements and Interface Definition forFuture OBCP Building Block " activity, GSTP ref : G522-001SW.The precursor GSTP activity, kicked off in early 2011 is composed of three phases:1) In Phase 1, it makes an assessment of the ECSS-E-ST-70-01C OBCP standardamnd also assessment of existing OBCP BB implementations in various ESAmissions. The assessment takes into account compliance to the standard, maturity,qualification effort, use for various mission purposes (such as autonomousoperations, FDIR, software maintenance), functionality and capabilities. Plannedand actual use of OBCPs for on-board applications (OBAPs) and operations(OBOPs) is considered, as well as use of specific OBCP capabilities, especially thelanguage capabilities by the existing OBCPs. This includes an assessment of theinfluence the mission type (e.g. Earth Observation, Telecoms, Science, etc.) has onthe definition and implementation of the OBCP engine.2) In Phase 2 the assessment made in Phase 1 is used in order to determinerequirements for the future implementation of the OBCP engine as a building blockfitting into the SAVOIR-FAIRE architecture.The interface of the OBCP Building Block is also defined: Both the OBCP BuildingBlock provided and required interface, as well as the services accessible to OBAPsand OBOPs, and the global function service accessible to all OBCPs. Top-levelarchitecture of the OBCP engine in the context of the FSW is proposed.An important part of the new activity is to propose a vision for the future use ofOBCPs, i.e. a consideration of possible innovation in FSW development and therole the OBCP concept can play. For the vision of the future OBCP use, theContractor shall consider the overall context, supporting technology and processesPage 19/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Useneeded, for instance temporal and spatial partitioning, new compilation or codeexecution techniques, incremental validation, multi-core processors, etc.3) In Phase 3 of the precursor activity a prototype of the OBCP buidling block isbuilt, based on the source and target languages designed, and focused on showingthe validity of the requirements and interfaces as well as to demonstrate support ofcritical elements of OBCP: execution of OBOPs and OBAPs, their resource control,safety, access to FSW services, fault containment and the ability to execute a newlyuploaded OBCP. In addition, the new prototype should be able to demonstrate thevision of the future use of OBCPs as presented in Phase 2, focusing on advancedand innovative features.Deliverables:SoftwareCurrent TRL: 4 Target TRL: 6Applicable THAG Roadmap: On-Board Software (2010)Duration(months)18Page 20/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain2 Space System SoftwareRef. Number:G617-011SWBudget(k€):500Title:RTEMS qualification extensionsObjectives:Description:A particular version of the RTEMS on-board operating system (4.8) has been prequalified.In order to control the costs and to focus on user missions, somerestrictions have been introduced in the scope of the validation, namely a reducedset of services and a limited number of hardware processor targets.In order to extent the user community of RTEMS 4.8, it is useful to consider moreprocessors (IP Cores) and potentially other services offered by more recent versionof RTEMS (4.10, 4.11)The activity includes:1) identification of future users needs collected from past experience, includingprocessor targets (monocores, multicores, partitioning kernels) and functionalitiesensuring consistency with the SAVOIR-FAIRE architecture.2) development of the needed adds-on to the pre-qualification data package.3) some tools have been developed around RTEMS. These tools ease the use ofRTEMS and support the promotion of RTEMS. However, the limited budget of theprevious activities did not permit to develop all the features that are wished by SWdevelopers to ease the development, the test, the integration and the validation.This includes accurate tasks and events viewer/browser with new features likefiltering, application profiling, CPU and memory budgets measurements, statisticson RTEMS objects, etc. This requires the development of specific libraries forRTEMS and the development of tools on workstation (on the use of COTS/OpenSource SW)Deliverables:SoftwareCurrent TRL: 5 Target TRL: 6Applicable THAG Roadmap: On-Board Software (2010)Duration(months)18Page 21/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Use3.1.3 TD 3- Spacecraft Electrical PowerCore /Specific AreasCORETechnologyDomain3 Spacecraft Electrical PowerRef. Number:G617-015EPBudget(k€):600Title:Objectives:Description:Implementation of new Power Systems architectures for LEO missions- Solar Array Regulator based on Buck-Boost RegulatorTo arrive to the qualification of the Solar Array Regulator (SAR) module based onBuck-Boost Regulator (B2R) developed as breadboard in a previous TRP program.According to a trade off performed at system level in TRP 22727, the Solar ArrayRegulator (SAR) module based on Buck-Boost Regulator (B2R)resulted as the mostsuitable one to cover most of LEO satellites solar array conversion.The winning B2R topology won the trade off due to its efficiency and extremeflexibility of use: the B2R can be configured as a truly recurrent converter able toaccommodate different solar array and battery voltages without any modification,and always offering very good efficiencies.The present activity consists in the development and the qualification of the B2R,according to the following tasks:1. design consolidation after prototype development and testing performed in theprevious TRP study;2. detailed electrical analyses of the final B2R design;3. manufacturing of the engineered module to be subject to qualification;4. testing and qualification of the B2R module.Deliverables:Other: Qualified B2R moduleCurrent TRL: 4 Target TRL: 6Duration(months)18Applicable THAG Roadmap: Power Management and Distribution (2008)Page 22/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain3 Spacecraft Electrical PowerRef. Number:G617-017EPBudget(k€):400Title:Lithium-ion VES16 Cell Balancing SystemObjectives:Description:To qualify the Lithium-ion VES16 cell Li ion balancing system.The VES16 is a small capacity cell, based on the well proven electrochemistry of thelarge cell (VES140 and VES180). This cell requires balancing during LEO or GEOmissions and it is proposed to include an active balancing at cell level.A GSTP activity is on-going on a VES16 module qualification tests and focuses onthe VES16 cells qualification but does not include the balancing qualification.However, the balancing of the cells is a major issue and requires more study andtests for full qualification.The proposed activity will focus on the qualification of this cell balancing system socalled: SBS, Smart Balancing System. The activity will include qualification ofcomponents, identification of all failure modes, and also testing activities.A full qualification data package of the VES16 balancing system will be delivered atthe end of the activity.Deliverables:Full qualification data pack and qualification modCurrent TRL: 4 Target TRL: 6Duration(months)18Applicable THAG Roadmap: Electrochemical Energy Storage (2010)Page 23/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain3 Spacecraft Electrical PowerRef. Number:G617-020EPBudget(k€):1000Title:Objectives:Description:Improved Ge wafer technology for multi-junction solar cells IIIThe main objective of this activity is to improve the quality of the Germaniumwafer that is a prerequisite for reaching highest efficiencies in next generation solarcell structures.Major improvement areas identified are "wafer strength" and "surface perfection".Wafer strength is mainly required to avoid breakage (of wafers and/or solar cells)and thus increase yield and decrease cost. The surface of the Germanium wafer isthe most important parameter for the success of the subsequent epitaxial process atthe solar cell manufacturer. As the quality of the epitaxy keeps on increasing, it isultimately the substrate that will limit the performance of the solar cell. In order toanticipate this evolution, substrates need to be produced that only show a minimalamount of light scattering defects. The defects shall be characterised by the socalled"Candela tool" which is a new type of surface inspection tool capable ofinspecting ungrown substrates and to bin the defects according to their type in pits,particles, scratches, haze, stain,etc. Minimisation of defects will be done revisingand improving all process steps from the initial crystal pulling step up to the finalclean etching step.The wafer strength will be improved mainly by lowering the intrinsic stress andimplement a rounded edge. Intrinsic stress manifests itself as bow, warp, wavinessand total thickness variation and optimising processes shall improve these figures.The developments needed for rounding the edge are mainly due to the thinnerwafers required by customers. Today, thin wafers do not have rounded edgesmainly because of incompatibilities of current process steps.Deliverables:Engineering ModelCurrent TRL: 4 Target TRL: 5Duration(months)36Applicable THAG Roadmap: Solar Generators & Solar Cells (2009)Page 24/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Use3.1.4 TD 4- Spacecraft Environment & EffectsCore /Specific AreasCORETechnologyDomain4 Spacecraft Environment & EffectsRef. Number:G617-022EEBudget(k€):1500Title:Objectives:Description:Highly Miniaturised Radiation Monitor Phase C-D and single-chip(LETmeter) version.Based on the design of the previous TRP activity, the objective is to develop andqualify a Flight Model of the Highly Miniaturised Radiation Monitor, in 2 versions:the monitor configuration with up to 4 ASIC sensors arranged in a stack and thesingle chip version.The Highly Miniaturised Radiation Monitor design established in the previous TRPactivity (4200022766) is based on mixed ASIC sensors arranged in a stackconfiguration enclosed in a tiny mechanical case. The Phase A-B prototype weightsonly ~52 g and is able to measure accurately radiation doses and energy spectra ofelectrons and protons in a wide range of space environments. The HMRM can alsobe made as small as a typical electronic component if only one packaged ASIC isused. In that case HMRM will be limited to measure only doses/LET but it willweight only ~ 0.8 g and consume < 200 mW, thus it will be very easy toaccommodate on any type of spacecraft.This design will be further iterated and consolidated in order to reach the level ofmaturity required to proceed to the manufacturing of a flight model.Major critical elements that require careful development are the ASIC sensors andthe back-end chip. The Phase A-B prototype includes a COTS FPGA that needs tobe replace with a flight-grade component (either a FPGA or an ASIC).The work will be completed with a full flight qualification programme on bothversion of HMRM.Deliverables:Other: Flight ModelsCurrent TRL: 5 Target TRL: 8Duration(months)30Applicable THAG Roadmap:Radiation Environments & Monitoring, Effects Tools &Testing (2009)Page 25/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain4 Spacecraft Environment & EffectsRef. Number:G617-024EEBudget(k€):500Title:ESD monitorObjectives:Description:To develop and test a prototype monitor of electrostatic discharge transients onspacecraft and to produce a flight model design.The evidence for a link between environment-induced electrical charging inspacecraft and upsets and damage to electrical circuits is strong but circumstantial.It is assumed that charging leads to electrostatic discharge (ESD) and this causeselectrical transients in circuits. However, these transients have never been directlymonitored on European spacecraft. The detection of electrical transients in wiresand radiated interference resulting from ESDs would have benefits in anomalydiagnosis, improvement of modelling and in defining ESD testing requirements. Inlaboratories, commercial pulse-height analysers and multichannel analysers arecommonly used to perform this task and pulse-height analysers on single chipshave been developed. A prototype spacecraft monitor which will identify andcharacterise electrical transients and ESD radiated waveforms will be developed inthis activityDeliverables:PrototypeCurrent TRL: 3 Target TRL: 5Duration(months)12Applicable THAG Roadmap:N/APage 26/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain4 Spacecraft Environment & EffectsRef. Number:G617-026EEBudget(k€):500Title:Objectives:Study of radiation energy effects on electronic components with highenergy heavy ion beams.The objective of this activity is to continue the work performed under the previousTRP activity "Investigation and analysis of very high energy accelerators forradiation simulation" (contract 21985/08/NL/AT) and to perform SEE tests onelectronic components (to be selected in coordination with TEC-QEC) at the highenergy heavy ion accelerator facility GSI in order to investigate energy and ionspecie effects. The use of the GSI facility is necessary in order to test EEEcomponents in a realistic radiation environment with particles energies/species asclose as possible to what is observed in space. Morover,the ion energy must be high enough such that the ion can penetrate deep enoughinto the active region of the semiconductor with suf;cient LET to capture allmechanisms that can lead to SEU or SEL. Failure to do so can lead to erroneousresults. Note that if the mechanisms for SEU or SEL are not captured, evensigni;cant overtests will not ensure part functionality in space. For some deviceswith moderate to high SEU or SEL thresholds, high energy ions can also causenuclear interactions creating secondary particles that can trigger SEU or SEL forincident ions with LETs below the apparent LET threshold; whereas, lower energyions may not trigger SEU or SEL. Because of these effects, for any given LET, theworst-case ion energy is the highest ion energy.The ranges of ions obtainable from most of the european radiation facilities are notsuf;cient for ensuring that all failure mechanisms are captured. This is especiallytrue for advanced IC technologies which can have very thick overlayers of oxidesand metals. Another reason for testing at GSI is thatmodern complex IC have plastic packages are very difficult to handle and notpossible to put on sockets. This makes design of SEE test PCBs very complex andmakes almost impossible to design for test in vacuum (necessary to increase ionrange). Furthermore delidding or thinning of plastic package may easily damagecomplex ICs, further adding to test results uncertainities (some packages are pressmolded, not encased). Availability of a reliable source with energies capable ofpassing thick passive layers can result on overall test setup savings.Description:In this activity further testing with high energy ion beams will allow to assessenergy and particle species effects occurring in radiation assurance testingperformed at different facilities. The experimental activities will include testing indifferent conditions (ion energies/LET, ion species etc.) the ESA SEU monitor,SRAM/SDRAMs and power MOSFETs. A Monte-Carlo simulation (based onGeant4) will be performed in order to validate the measured SEE rates and tosupport the eleboration of a new radiation hardness assurance methodology andstrategy.Deliverables:Other: Study report, SoftwarePage 27/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCurrent TRL: 3 Target TRL: 4Duration(months)24Applicable THAG Roadmap:Radiation Environments & Monitoring, Effects Tools &Testing (2009)Page 28/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain4 Spacecraft Environment & EffectsRef. Number:G617-027EEBudget(k€):500Title:Objectives:Description:Geant4 kernel speed-up for high-efficiency simulations in space- Study of existing Geant4 radiation transport software kernel and architecturefrom computational efficiency point of view- Development and application of computational approaches for an order-ofmagnitudeimprovement in the simulation efficiency for space industry andacademia applications, while maintaining the physics performance- Prototype architecture and software development- Coordination with and feedback to the Geant4 Collaboration for inclusion in thepublic Geant4 releasesGeant4 and the various software tools and applications based on it have to datebeen used in support of more than 40 space missions or experiments world-wide.One of the key parameters for the utilisation of physics-based analysis softwaresuch as Geant4 is its computational speed. Over the years, in addition to developinga broad range of space-specific Geant4 models and tools, ESA has thereforedeveloped rapid solutions deriving from the base software. These efforts haveresulted in substantial improvements as seen by the user. However they havemostly been built upon Geant4, less so touching the actual kernel of the software.At the same time, the kernel computational speed has become increasingly criticalfor High Energy Physics (HEP) sponsors of the software, notably at CERN, wherethe LHC and its experiments require computational resources worth several tens ofmillions of Euros per year. Increasing emphasis is being placed in solutions such asmulti-threading, biasing techniques, GRID applications, and various prototypingefforts such as porting of the software to Graphical Processing Units orrearrangements of the Geant4 base architecture.Thus far, these proposed kernel speed-up solutions and other prototypedevelopments almost exclusively stem from and are funded by the HEP domain,and as such do not directly take into account the requirements of the spacecommunity. Some of the activities, while aiming for computational speedimprovement, carry with them the risk of added complexity in the form of forcedlinks to large additional HEP software which may make them prohibitive for manyspace users.In this context, it is vital that ESA establishes its own efforts for substantial Geant4kernel speed improvements with the space community in mind. The presentactivity will analyse in detail and implement various methods to address this,including:- Extensive code profiling for a range of typical space user cases- Investigation and development of semi-automated biasing techniques for space- Improved handling at kernel level of the various Geant4 hadronic physics models(primarily those that bear most relevance to space applications, including heavy ionPage 29/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Usetransport models and radioactive decay)- Hybrid methods between analytical and Monte Carlo solutions- Further improvements in Inverse Monte Carlo method convergence and speed- New developments in low-energy computational efficiency for SEE a cellular-levelradiation analyses- Prototyping of alternative base architecture designs- Analysis of alternative processor (Graphical Processing Unit or other) options- Considerations on substantial code simplifications- Cloud computing- Other prototypesThese developments will be carried out in coordination with the already ongoingefforts within the Geant4 Collaboration, will comply with the Collaboration nearandmedium term strategy, and in addition to their utilisation in existing Agencymodels and tools will be fed back as possible inclusions in the Geant4 releases.Deliverables:SoftwareCurrent TRL: 6 Target TRL: 6Duration(months)20Applicable THAG Roadmap:Radiation Environments & Monitoring, Effects Tools &Testing (2009)Page 30/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Use3.1.5 TD 5- Space System ControlCore /Specific AreasCORETechnologyDomain5 Space System ControlRef. Number:G617-028ECBudget(k€):1000Title:Objectives:High accuracy image stabilization system prototypingThis activity will provide the analytical proof-of-concept and breadboard validationin laboratory environment for a high-precision/high-pointing stability imagestabilization system located inside the instrument.The motivation comes from the increased needs of better performances by EarthObservation and Science missions and from the availability of refined controltechniques and technologies for sensing and actuation. The target improvement ofpointing performance is between one and two orders of magnitude, if compared toa conventional platform and instrument design.Description:Conventional pointing concepts rely on a centralised pointing at platform level anda very quiet thermo mechanical environment for the instrument. It is proposed toinvestigate decentralised pointing concept for Earth Observation and Sciencemissions, as a generalisation of the precursor Pointing Acquisition and TrackingSystems developed for laser communication terminals (Silex on Artemis and Spot4, EDRS). The proposed system will be based on the following not exclusiveconcepts for image stabilization:- line-of-sight stabilization: the line-of-sight jitter with respect to the focal plane isnulled at optical system level (e.g. mirror);- focal plane stabilization: the line-of-sight jitter with respect to the focal plane isnulled at focal plane level (either mechanically or electronically).The architecture of the stabilization system will be addressed considering either:- a fully stand-alone solution, i.e. needed sensors, actuators and EU are inside theinstrument/stabilization system;-or an integration with AOCS for possible performance improvement,equipment/information sharing, control design approach.The main tasks of this activity shall cover:- a survey of candidate Earth Observation and Science missions which could takeadvantage of the image stabilization system (e.g. EUCLID, ECHO, MTG, Premier,etc.), considering criteria like operating wavelength range, image resolution/qualityand associated pointing requirements and other instrument design/system aspects.- the preliminary definition of candidate concepts for the considered missionsincluding the following tasks:o High-level review of the instrument designo Definition of requirements (pointing performance, mass/volume constraints,etc.)o System architecture and control design, considering also reliability aspectso Development of a numerical simulator for control algorithm design,sensor/actuator requirement specification, performance assessment, validation.o Preliminary breadboard specification- Detailed breadboard design and development considering available technologiesPage 31/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Use(h/w, s/w, additional operating procedures, etc.)and testing in laboratoryenvironment- Recommendations and preliminary development plan for future activities.Deliverables:BreadboardCurrent TRL: 2 Target TRL: 4Duration(months)30Applicable THAG Roadmap:N/APage 32/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain5 Space System ControlRef. Number:G617-030ECBudget(k€):300Title:Objectives:GNC Analysis, Design and Verification Framework using MATLAB onlyThe objective of this activity shall be to design, develop and test a softwareframework for Guidance, Navigation, and Control systems using MATLAB only anda Model-Based Approach. This framework is aiming to integrate the GNC systemdesign, verification and validation cycle from requirements definition and designup to Hardware in the Loop testing, making use of the modern MATLABautomation functionalities. The goal of this study is to produce a softwareframework able to cover the GNC life cycle for space mission phases from A to F,including post-flight performance analysis, verification and establishment oflessons learnt.The scope of this activity will be going up to Processor In the Loop (onlyrepresentative CPU processor in the loop), leaving the more complex Hardware Inthe Loop (including OBC engineering model and GNC hardware units) as theultimate target.Description:The modern version of MATLAB allows not only for the design of a GNCsubsystem, but also its auto coding, the automatic generation of documentation,the automatic generation of test plans and test reports, linking with keys designrequirements and the automatic verification of the GNC algorithms. In this line,MATLAB is regarded as a key tool for GNC engineers favouring a significantreduction in production time of the GNC subsystem and its quick verification in aprocessor in the loop facility.A comprehensive development of the GNC subsystem shall aim to enhance thesubsystem design and validation as an integral part of the on-board softwareautomatic code generation. This will be achieved with the definition of the Modelunit tests, structural coverage and functional coverage for Model-Based Software.In addition this will allow reusability of the Model test cases in the softwareverification facilities and in the GNC test benches and reducing not only the lagbetween algorithms design and software coding, but also pursuing an overallreduction of the validation and verification effort.In the design validation phase where a large set of simulations are run (e.g.MonteCarlo simulations and Worst-Cases analyses) a down selection of a set ofreference cases is performed in order to verify the GNC performance in thedifferent stages of the Processor-in-the-loop (PIL) verification. Therefore, theframework shall help to identify these reference cases. The framework tool set shallpermit auto coding into a PIL system that shall be provided by ESA (e.g. RASTA).This activity can benefit of ESA internally developed library: SPACELAB.The interaction between the design validation and the functional verification istherefore formalised within this framework. The tailoring will allow to integratethree major elements:1) The formal verification of documents including compliance to ECSS Standards,Requirement Baseline Specification, Models Design Documentation, VerificationPage 33/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseControl Documents, Test Plan and Test Report.2) The GNC algorithms prototype and plant model.3) The verification environment: Software in the loop, Processor in the Loop.The outcome of this study shall produce a framework and procedures for spacemission that allow to: interface all above mentioned elements; identify a formal process for the model based code to be checked and ensurefor GNC Requirements Baseline traceability, ECSS standards compliancy (inparticular the E40 and E-60 standard series) and auto-coding constraints; automation of documenting models architecture and models detailed design; d.define and manage the specification and verification documents such as:Model Unit test and Integration test specification, cases and reports enhance and speed up the V&V phase, in particular with the validationspecification, cases and reports; automatic documentation, test plan generation, test report generation andVerification Control Document (VCD); provide a range of analyses tools: fault tree, test coverage, cross checking ofsimulation w.r.t Processor-in-the-loop (PIL) environments; the tuneability of the tools and its portability to different mission scenariosshall be fully addressed and documented; The product assurance aspects of models validation will also have to beassessed, such as model metrication and the "quality model" of the model.The activity shall consist of the following phases:1) Review of existing modern MATLAB capabilities and tool requirement'sspecifications in the development of: GNC, Failure Detection Isolation & Revocery(FDIR), Mission Vehicle Manager (MVM), Software Autocoding, FPGA or ASICautomating the Hardware Description Language (HDL) programming, RASTAboard.2) Design, development, and integration of the framework. This phase shallcomprise the selection and definition of the best user's interface and the design anddevelopment of the components required and their tight integration.3) Preparation of a demonstration. A mock-up or prototype of an example coveringthe life cycle of a real ESA mission like GNC system shall be used to beincorporated in the final presentation of the study. The contractor shall propose theGNC system to be used for the demonstration, provided they are compatible withthe overall concept and authorised by ESA.4) Test and validation of the tool.5) Delivery of the tool with the corresponding documentation and presentation atESA.Full technical documentation shall be delivered, covering software specifications,architecture, testing, verification, and validation.Deliverables:SoftwareCurrent TRL: 3 Target TRL: 5Duration(months)15Applicable THAG Roadmap:N/APage 34/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain5 Space System ControlRef. Number:G617-035ECBudget(k€):700Title:Objectives:Description:Generic AOCS/GNC techniques and design framework for FailureDetection Isolation and RecoveryThe objective of this activity is to propose generic solutions for the AOCS/GNCfunctional chain to recurring issues currently met with Failure Detection Isolationand Recovery (FDIR), both in the technical design versus requirements area and inthe early verification area.The standard 'Satellite AOCS requirements' (ECSS-E-ST-60-30C, to be issued in2013) will not impose a strict upfront architectural design with a full segregation ofA branch and B branch. Innovative control solutions need to be proposed, with theproper balance between mission availability and satellite survivability while alsoreducing the current complexity of FDIR implementation.Projects also suffer from a late dynamic verification of the FDIR mechanisms oftenpostponed to the overall avionics verification, when all HW and SW elements areavailable. A design framework will thus be proposed allowing already in Phase A/Ban early prototyping and dynamic verification of FDIR AOCS/GNC mechanisms.This will complement the current TRP activity 'FDIR Development and V&VProcess' which tackles discrete failure observables.This activity will contribute to mitigate the current lack of systematic approach andthe lack of engineering transparency and guidance of the FDIR engineeringprocess, with also the aim to decrease overall complexity. It will contribute fromthe AOCS/GNC perspective to the preparation of an ESA FDIR design anddevelopment handbook, in coordination with Software and Data Handling efforts.The activity will include the following tasks:- critical analysis of customer's requirements evolution between fully segregatedHW constraints for Safe Mode(traditional ESA approach)and authorised reusepending justifications;- critical analysis of current AOCS/GNC FDIR complexity and proposals forsimplification with equivalent coverage, including model-based approach orintelligent sensors;- survey of ECSS documents relevant for AOCS/GNC FDIR bottom-up synthesis(failure analysis) and top-down synthesis (feared events analysis) and guideline forAOCS/GNC engineers from QA/PA techniques;- development of a design framework allowing a rapid prototyping and earlydynamic verification of FDIR from the AOCS/GNC perspective in Phase A/B, to betested on already developed AOCS FDIR systems (either Telecom or EarthObservation or Science missions);- recommendations for next generation intelligent sensors enabling more efficientFDIR and Health Monitoring Systems;- conclusions and control inputs for an ESA FDIR handbook.Deliverables: Other: Study report, software.DurationCurrent TRL: 3 Target TRL: 4(months)Applicable THAG Roadmap: Avionics Embedded Systems (2010)24Page 35/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain5 Space System ControlRef. Number:G617-036ECBudget(k€):400Title:Pointing Error Engineering Software FrameworkObjectives:Description:The main objective of this activity is to develop, enhance and maintain a softwareframework supporting Satellite Pointing Error Engineering for all ESA missions, inline with the ECSS Control Performance Standard ECSS E-60-10C which does notauthorise the traditional simplified summation rules.The resulting software framework shall be considered as an operational softwarefor ESA, with the objective to distribute it to the European space community.The activity will develop a first version of the software framework based on theexperience got through a successful prototyping exercise in 2012 called PEET(Pointing Error Engineering Tool). The prototype implements the step-by-stepprocess elaborated in the ESA Pointing Error Engineering Handbook published in2011 as ESA applicable document ESSB-HB-E-003. An accompanying SWframework is necessary to process complex calculations for high accuracypointing,to support frequency domain techniques introduced in the handbook,toprovide traceability and a common platform for exchange of information betweenthe various entities.The main objective of the activity is to extend and streamline the existing PEETprototype to get an operational version for wide applicability to ESA projects. Inparticular, the following tasks are foreseen:- Review of lessons learnt from the prototype and feedback from users- Update of the software framework requirements- Review and streamlining of the core computational routines of the PEETprototype to optimise SW execution- Extension of modules to support high precisions missions (e.g. Euclid, MTG,EDRS,etc)- Based on the existing sensitivity analysis feature, implementation of a specificfunctionality for pointing requirement allocation (apportionment)- Extension of the reporting functionality according to suggestions by future usersin ESA and industry-Extension of the PEET website with repository, bug tracker, online manual,tutorial and forumDeliverables:SoftwareCurrent TRL: 3 Target TRL: 4Duration(months)12Applicable THAG Roadmap:N/APage 36/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Use3.1.6 TD 6- RF Payload and SystemsCore /Specific AreasCORETechnologyDomain6 RF Payload and SystemsRef. Number:G617-037ETBudget(k€):800Title:Objectives:Advanced manufacturing and integration techniques for TT&Ctransponders/transceiversThe objective is to study, identify and validate the enabling technologies for futureTT&C transponders/transceivers, with a main goal to enhance manufacturing andintegration of key transponder components towards a System-on-Chip conceptwhich can be used as a core building block in future TT&C transponders andtransceivers.Description:The use of the VLSI technologies (through high density, low power consumptiondigital ASICs) together with RF miniaturisation techniques (Analogue ASIC,MMIC,System on a chip etc.) are being used in many devices in order to developlighter and smaller transponders. Particular examples of these are:- The TT&C subsystem for the future deep space missions, such as Bepi-Colombo- Lander and orbiter proximity link transponders/transceivers.- Earth Observation S-band TRSPs- Telecommunication command receivers, transmitters and beaconsThe higher integration at circuit level results in a decrease in the number ofrequired components. This simplifies the integration process and reduces theassociated tuning activities. This has significant benefits, both in terms of designrobustness and cost reduction.Higher integration can also be used to include more functions inside thetransponder in order to increase its flexibility whilst reducing the unit mass. Thisactivity will provide a critical assessment of the technologies on how to reduce themass and power consumption of future transponders/tranceivers for use onspacecraft/landers and will manufacture and test a generic system on a chip for usein multiple transponder units for different space applications. This will require thedesign, development and validation/verification of a highly integrated buildingblock for use in multiple TT&C TRSP units and will be tested as part of anintegrated breadboard.Deliverables:BreadboardCurrent TRL: 3 Target TRL: 5Duration(months)24Applicable THAG Roadmap: TT&C Transponders and Payload Data Transmitters (2012)Page 37/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain6 RF Payload and SystemsRef. Number:G617-040ETBudget(k€):1000Title:Miniaturized Timing SourcesObjectives:Description:The objective of this activity is the design, development, test and validation of atiming source based on micromachined atomic clock technology as required forhigh-end navigation and secured-telecom receivers, as well as high resolutionsensors and instruments.A number of studies have demonstrated the many advantages of miniature batterypoweredtiming sources: integrated in a portable user terminal, such sources allowfor ultra-fast acquisition (e.g. for secured telecom with long spreading codes) andlong coherent integration (e.g. for GNSS operation in interference or indoorenvironment). Similarly, it has been shown that such sources would significantlyimprove the sensitivity of some on-board EO instruments (e.g. radiometers, radiooccultation;).After major achievements in the US over the last years resulting in the availabilityof a commercial unit, a number of studies and investigations have flourished inEurope for the development of miniature and low power consumption atomicclocks. Despite many efforts, most of today concepts rely on miniature glass-blownvapour cells that do not fully exploit the micromachining technologies. Recentprogress in Si-based micromachining techniques open new possibilities to furtherreduce the size and integration capabilities of the vapour-cells, thereby allowing forthe realisation of fully integrated Micromachined Timing Sources.ADDITIONNAL INFO AS REQUESTED:The proposed activity shall include the following tasks:1) litterature/patent review and specification consolidation2) design definition3) manufacture, assembly, test and validation4) design assessment and recommendationsCurrent TRL is 3 (cf. e.g. http://www.mac-tfc.eu/).The proposed development shall target both ground and space applications.Deliverables:BreadboardCurrent TRL: 3 Target TRL: 4Duration(months)24Applicable THAG Roadmap: Frequency & Time Generation - Space (2005)Page 38/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Use3.1.7 TD 7- Electromagnetic Technologies and TechniquesCore /Specific AreasCORETechnologyDomain7 Electromagnetic Technologies and TechniquesRef. Number:G617-047EEBudget(k€):350Title:Objectives:Description:Millimeter wave Validation Standard (mm-VAST)antennaDefinition, manufacturing and testing of a mechanically and thermally stablemulti-frequency reflector VAlidation STandard antenna for range qualification atmm-wave frequencies (Ku, Ka and Q/V-bands)Inter-comparison and validation of antenna measurement ranges either withreadily available antennas or with dedicated VAST antennas has been carried outfor at least three decades. These activities allow finding and help correcting largeand small problems in the measurement procedures, thus leading to animprovement of the measurement accuracy and facilitating better understanding ofthe measurement techniques.The early experience gained demonstrated that readily available antennas can beuseful, but do only partially meet the requirements of a validation campaign. Thus,it is definitely preferred to have available dedicated test or VAST antennasspecifically designed for validation campaigns of antenna measurement ranges.Such VAST antennas are used as a standard for validation of test ranges but as wellsoftware in support to qualification activities for ESA and other programmes.Standards have already been developed by ESA for C and X band and newstandards are required for application at higher frequency up to 50 GHz. A multifrequencyantenna covering Ku, Ka and Q/V-band shall be made available.This activity will:Review of the requirements for a multi-frequency VAST antenna and comparisonof different reflector configurationsInvestigation of already existing technologySelection of the optimum configurationDesign and simulation of the antenna and all its components to enable a wellcharacterised,mechanically and thermally stable multi-frequency reflectorVAlidation STandard antenna for range qualification at mm-wave frequenciesManufacturing of the VAST antennaTesting of the VAST antenna at a high performance rangeDeliverables:PrototypeCurrent TRL: 3 Target TRL: 5Duration(months)12Applicable THAG Roadmap:N/APage 39/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain7 Electromagnetic Technologies and TechniquesRef. Number:G617-051EEBudget(k€):300Title:Objectives:Description:Accurate RF material characterisation using scattering measurementsfrom Quasi-Optical benchThe objective of this activity is to increase the accuracy of RF materialcharacterisation by taking into account the scattering properties, which occur bothin transmission and reflection, for rough or inhomogeneous/anisotropic materials.This will allow improving antenna analyses accuracy, using available modellingtools, by accounting for all possible effects extracted from these measurements.Many different materials and composite materials are used in the field of antennas.Examples are dielectrics, frequency/polarisation selective surfaces, sandwichstructures, Carbon Fiber Reinforced Plastics, ceramics, metal plates that can beseen in application ranging from low frequencies up to sub-mm waves. An accurateRF characterization of these materials is of vital importance for all future spacemissions.A common way of describing these materials is in terms of (single) reflection,transmission and absorption. This is sufficient in case of homogeneous materialswith perfectly flat interfaces. However, when the material is rough and/orinhomogeneous some of the incoming radiation will be scattered away in multipledirections. The magnitude and direction of this scattering is a function of thewavelength, refractive index of the material and the size of the inhomogeneity andwill occur in both reflection and transmission. Therefore, in order to accuratelyderive the RF parameters (reflectivity, transmittivity, refractive index, ohmiclosses, etc.) of the material, the way the reflectivity measurements is performed andprocessed shall be reconsidered. If this is not the case, then scattering will give riseto errors in the values of the reflection (R), transmission (T) and absorption.Several Quasi-Optical benches have been developed in Europe, including at ESTEC,for RF material characterization. The outcome of this study shall be applicable toany QO bench in Europe and close the loop between simulations andmeasurements.This activity will identify and implement the design adaptations of the RFcharacterisation test bench(es) and develop the required processing and dataacquisition enabling the accurate RF characterisation. The measurement data shallbe compatible with the state of the art electromagnetic simulators where thepossibility of including the angular reflection and transmission properties of thematerials is included. This will enable to accurately design the antenna andimprove their performance predictions. The validation shal be perform on samplescovering a large frequency range and type of structures.Deliverables:Other: Study report, HW development, modelling toolCurrent TRL: 3 Target TRL: 4Duration(months)12Applicable THAG Roadmap:N/APage 40/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain7 Electromagnetic Technologies and TechniquesRef. Number:G617-052EEBudget(k€):600Title:Medium-to-high gain X-band antenna with customisable pattern andpolarisationObjectives:To implement and validate a medium-to-high gain antenna with pattern andpolaristation flexibility at X-band.Description:Having a generic antenna structure suitable to generate different patterns withsingle linear or single/dual circular polarisation is of major interest. The idea is touse a same basic design or a small range of designs with different aperturediametre which radiation characteristics are adapted to specific missions need byexploiting the conjugate-matched metasurface concept which has been successfullydemonstrated in the recent past under TRP. Both shaped beam (isoflux andsectorial isoflux) as well as spot beam configurations where shown to be feasiblewith a simple disk-shaped antenna fed from its centre, featuring extremely lowthickness (~2cm) and simple "printed circuit" manufacturing. Earth Observation,Science and Robotic Space Exploration missions are the natural targets for thisconcept that promises to overcome the limitations of current technology eitherrequiring redesign or acceptance of available performance. Antenna reuse acrossmissions typically results in costly compromises on link performance reducing datatransmission capabilities, while a COTS antenna which can be easily customised tofit the needs of each mission will provide the best possible performance at theminimum cost. The objective of the activity is to design, develop and test up toEQM level the new antenna concept with two baseline set of requirements anisoflux beam for data-downlink from LEO and a spot-beam for deep spaceapplications.Deliverables:Engineering ModelCurrent TRL: 3 Target TRL: 5Duration(months)18Applicable THAG Roadmap:N/APage 41/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Use3.1.8 TD 8- System Design & VerificationCore /Specific AreasCORETechnologyDomain8 System Design & VerificationRef. Number:G617-054SWBudget(k€):700Title:Objectives:Description:Precise and Flexible Wiki-Based Requirements EngineeringTo develop a wiki-based method and tool for requirements engineering of spacesystems up to the System Requirements Review (SRR) that is efficient, precise andflexible as well as very user-friendly.For any space mission or system the set of requirements specifications are the mostimportant description of the problem to be solved and form the basis of anycontractual arrangements between the customer and the supplier(s).It is generally recognised that the quality, completeness, consistency and precisionof the requirements specifications are of paramount importance for the successfulexecution of a space project, from all perspectives: technical, cost, schedule,logistics and risk. Omissions or mistakes in the requirements specifications oftenseverely impact later project phases, in terms of cost increase and/or schedule loss,and sometimes also technical performance. Therefore it is wise to invest in a solidrequirements engineering capability.However up to now, requirements engineering is mostly done quite informally inoffice documents (MS Word, Excel), the DOORS COTS tool or ad hoc simpledatabases. In DOORS requirements can be stored in a well-structured way andthere are some ways to import a Word or Excel requirements specification. StillDOORS is considered more a Requirements Management tool for formalrequirements configuration control. Its main application and strength is to be usedafter the requirements baseline has reached a more or less frozen state, whichtypically happens at SRR. DOORS is much less useful and effective as a tool forauthoring, derivation, refinement, allocation and validation of requirements in theearly life cycle phases (Phase 0, A, first half of Phase B up to SRR) with a multidisciplinaryteam. During these phases the requirements are subject to a lot ofchanges and part of the (technical) negotiation between customer and (main)supplier. In the early phases the requirements engineering method and tool musthave the following characteristics:- flexible but precise, with readily accessible revision history;- easy-to-use by engineers from all disciplines in a multi-user / multi-disciplinaryenvironment, i.e. it should not require so-called "DOORS specialists" and a longlearning curve;- support for requirements specification templates and "boilerplate texts";- support for integrated glossary / glossaries of terms;- support for re-use of previous requirements specifications;- support for semantically precise formulation of requirements that can bequantified in terms of mathematical expressions -- e.g. mass_of_service_module

ESA UNCLASSIFIED – For Official Usesystem modelling tools like DOORS and SysML modellers;The TRP study "Next Generation Requirements Engineering" conducted in 2011-2012 has explored and demonstrated a very promising and attractive new way ofauthoring and developing requirements specifications. It uses a semantic-wikienvironment to author, express, browse and report the requirements, with(limited) support for mathematical expressions involving semantic properties inorder to formulate quantifiable requirements that were to become machineinterpretable and suitable for early validation with system design models. It hasstrong hyper-linked navigation features. It also demonstrated basic capabilities toexchange (import/export) requirements between the wiki environment andDOORS, as well as a bi-directional gateway between the wiki environment and aSysML modelling tool (Papyrus).In addition the TRP study hinted at the possibility to use some automated naturallanguage processing features in order to further enhance to quality of therequirement formulations.The current activity shall realise a semantic-wiki-based method and tool forrequirements engineering in the first life cycle phases from Phase 0 to the first halfof Phase B up to SRR. The method and tool shall take the results of the TRP study"Next Generation Requirements Engineering" into account. The semantic wiki shalluse and build on top of W3C Semantic Web technology, comprising at leastRDF/OWL and SPARQL. The selected semantic wiki technology shall be opensource, and compatible with distribution under an ESA Community Open SourceLicence.Furthermore it shall provide means to connect to MBSE tools for design definitionand early validation. For concurrent engineering an interface compliant with ECSS-E-TM-10-25 shall be implemented.It shall also have an import and export interface for requirements datasets thatimplements the OMG ReqIF standard and is validated with DOORS.The work shall be performed in compliance with the established ECSS standardsfor software development E-ST-40C and Q-ST-80C tailored for "CriticalityCategory D" software.It is proposed to perform this work in two phases:- Phase 1. Initial design and implementation including validation alongside twoselected ESA space projects: one Phase 0 feasibility study and conceptual designusing concurrent engineering, and one Phase A industrial study.- Phase 2. Full elaboration into a robust and operation tool for use in spaceprojects.The distribution of funding between the two phases is estimated at 400 and 300k&curren; respectively.Detailed list of deliverables:(1) Documentation: Software Development Plan (including V&V Plan), SoftwareSystem Specification (user and interface requirements specification), SoftwareRequirements Specification, Software Product Assurance Plan, Software DesignDocument, Software Configuration File, Software Release Document, SoftwareUser Manual, Getting Started Guide with worked examples, Software VerificationReport, Software Reuse File, Software Product Assurance Report, Final Report(2) Software deliverables: source code, installable software product, build scripts,test scripts, test data.Page 43/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseDeliverables:Other: See detailed list in DescriptionCurrent TRL: 3 Target TRL: 6Duration(months)21Applicable THAG Roadmap:N/APage 44/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain8 System Design & VerificationRef. Number:G617-055SWBudget(k€):2000Title:Objectives:Description:Adaptation and Demonstration of MBSE for a real project (Pilot)Demonstrate and quantify benefits of MBSE-based methods for space projects byperforming phase B activities as shadow engineering in parallel with a selectedmissionBased on the results of previous, ongoing and planned activities to define a modelbasedsystems engineering (MBSE) based approach for space systems and todevelop the necessary support tools and interface standards, its benefits need to bequantified 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 should be in the appropriate phaseof the life-cycle (beginning or just before phase B).Deliverables:Other: Verified system design and benchmarking resultsCurrent TRL: 5 Target TRL: 7Duration(months)24Applicable THAG Roadmap:N/APage 45/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain8 System Design & VerificationRef. Number:G617-056SWBudget(k€):400Title:A Generic Mapping Toolbox for Space CAE DataObjectives:Description:- Development of a software library for the mapping of CAE data across domains,with a focus on thermal, structural and fluidic analysis- Selection and / or development of graphical tool to support the mapping of thedataThe mapping of computation analysis data between tools is always a majorchallenge when running multidisciplinary analysis. Examples are (not exhaustive):- Thermo-Elastic: Mapping of temperatures from thermal analysis tools tostructural codes- Aero-Thermal Heating: Mapping of CFD data (e.g. heat fluxes) to a thermalmodels for temperature predictions in the structure- Opto-thermal mechanicalThese data exchanges usually involve a transfer of the data between differentmeshes, often with different levels of refinement and abstraction. Moreover, theunderlying numerical methods typically differ between disciplines with FiniteElement, Finite Volume/Difference and Lumped Parameter modelling typicallyused for structural, CFD and thermal analysis respectively.Past projects have sought to develop ad-hoc point to point data transfer tools. Onesuch example is the SINAS tool developed for the mapping of thermal data tostructural FE codes. This tool provides a quality mapping for temperate data,however, it is in need of work to bring it up to date and to remove some historicalS/W dependencies.The proposed activity would involve the development of a toolbox for the genericmapping of CAE data. It should support all of the major analysis methods namely,FEM, FV, and LPM. As far as possible the toolbox should be independent of actualtool formats (e.g. ESATAN or NASTRAN) but rather use a neutral meshrepresentation and, where possible, open standards such as STEP-TAS. Theinterface to specific tools or solvers can then be handled via dedicated plugins.To carry out the mapping some sort of graphical environment is essential tosupport the engineer. For example SINAS uses MSC Patran as a graphicalenvironment and geometrical engine. Unfortunately this specific dependence hasactually restricted the use of SINAS due to the reluctance of some industrial entitiesto use MSC Patran on the grounds of cost/availability/training etc. Learning thelessons from this, the proposed activity would also seek to identify a suitablegeneric graphical environment that could be used. Essential properties of such agraphical environment (in addition to being functionality adequate) are low costand openness for customisation.Page 46/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseDeliverables:SoftwareCurrent TRL: 2 Target TRL: 5Duration(months)18Applicable THAG Roadmap:N/APage 47/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Use3.1.9 TD 9- Mission Operations and Ground Data SystemsCore /Specific AreasCORETechnologyDomain9 Mission Operations and Ground Data SystemsRef. Number:G617-061GIBudget(k€):200Title:Objectives:Integration of ESA Ground Data Systems into Cloud Based Platforms(PaaS and SaaS solutions)Evaluate on the concrete case of SIMULUS the benefits and the challenges ofestablishing a Platform as a Service (PaaS) cloud-provisioning Model for ESA spacemission critical systems.Evaluate on the concrete case of the SIMULUS generic models as well as FARC,PARC and DARC the benefits and challenges of Software as a Service cloudprovisioning model for ESA space mission critical systems.Evaluate based on the above two use cases how Cloud Computing could addresssome of the main challenges of modern Ground Data Systems, including* IPR ownership of solutions developed by industry for ESA* IPR and licensing handling of ESA operational software and its provisioning tothe industry* Avoidance of revalidation of generic cross mission infrastructure in the context ofeach mission data system (by using PaaS and SaaS)* Management of ever growing baselines (HW/OS/COTS/Application)Description:HSO-GDA have performed in a systematic analysis of the ***cloudability***; ofGround data Systems with a focus on identifying the most suitable CloudComputing model for main ESOC ground data systems applications. The analysishas considered on one side the different Cloud Computing models- Infrastructure as a Service (RnT.IaaS)- Platform as a Service (RnT.PaaS)- Software as a Service (RnT.SaaS)And at the other side different cloud deployment models:- Private Cloud- Public Cloud- Hybrid Cloud- Community CloudAs a result of this study the following concrete candidates have been identified foreach service provisioning and deployment model :1. SIMSAT as RnT.PaaS deployed on a private cloud (for operations) and on apublic/hybrid cloud for development2. SIMULUS Generic Models as RnT.SaaS deployed on a private cloud (foroperations) and on a public/hybrid cloud for development3. FARC, PARC and DARC as RnT.SaaS deployed on a private cloud (foroperations) and on a public/hybrid cloud for developmentWe are proposing to take the next step and implement a concrete demonstrator foreach of the three identified CC application domains in in the context of a new studyand analyse the impact of a cloud based environment on the development,deployment , validation and operation of related ground data systems.Page 48/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseDeliverables include:1. Technical note: Architectural and deployment design for each scenario2. Software Development Lifecycle documents (ECSS-E-ST-40C TT4 for R&Dtype)3. Proof of Concept Demonstrator for each Scenario (SoftwareImplementation and deployment)Deliverables:BreadboardCurrent TRL: 4 Target TRL: 5Applicable THAG Roadmap: Ground Systems Software (2008)Duration(months)12Page 49/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain9 Mission Operations and Ground Data SystemsRef. Number:G617-062GIBudget(k€):300Title:Security as a Service for Ground Data SystemsObjectives:To demonstrate that standard security controls can be implemented as Security asa Service (SaaS) for mission data systsems. This implies in particular: Simplification of provision of Security Controls in software solutionswithout compromising on the security goals. Harmonisation of implementation of Security Controls in softwaresolutions (ease of maintenance and operation). Ensuring correct and adequate implementation of Security Control in allsoftware solutions (QoS).Description:Security and Data Policy are two important architectural concerns for all grounddata systems. Awareness of these concerns is increasing within the Agency asprogrammes such as SSA, Galileo, and GMES evolve and security requirements aremore often put forward by the Agency's international partners. It has becomeevident in the recent past that security controls are becoming more and morenecessary in the context of mission data systems in particular when these systemsare part of the central processing chain that supports the business processes of amission or programme. The Security Directives Implementation Project (SDIP) hasidentified the need for a number of mandatory and standard security controls thatrequire implementation in numerous mission data systems such as authentication,access control, identity management, and encryption.While the awareness and the need for security controls in mission data systems isgrowing, at the same time the necessary security expertise is not present at allengineering levels when it comes to implement mission data systems. Moreover, inorder to address the security aspects adequately, the security concerns must beincorporated appropriately in all steps of software development lifecycle(requirements engineering, design, implementation, validation, deployment,operation, retirement).In general security is often perceived as a cumbersome, complicated, and resourceintensive subject.Any reduction of the complexity of the subject and simplification of the securityaspects, while not compromising on the security objectives, is therefore muchwelcomed by all stakeholders.A promising approach towards simplified embracement of security concerns insoftware solutions is provision of Security as a Service.To give a simple and understandable analogy, one can compare this concept to theservices of a firewall, which provides certain network security controls as a Servicein a quite transparent manner to the software developers.Similarly other security and data policy concerns at application level such asConfidentiality, Integrity and Authenticity can also be provided as a Service in aneasy-to-use and more transparent way to all software projects.The concept of Security as a Service is gaining more importance in the ITcommunity and is becoming more feasible as Service Oriented Architectures (SOA)and Cloud Computing paradigm take a prominent role in the IT landscapes.Page 50/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseRepeated and redundant implementation of the same security controls in differentprojects increase the amount of resources, maintenance and risk of erroneousimplementation. The consolidation of security capabilities, like authentication,authorization, encryption and digital signatures, in form of re-usable and selfcontainedservices, increase the interoperability and maintainability of the softwaresolutions.The most important objective here is however simplification of the security subject.If this objective is achieved, security stops to be a complicated topic and turns to bea common, central and standardized piece of the solution.Deliverables include: Technical Note: Analysis and identification of the candidate securitycontrols to be provided as a Service Proof of Concept Demonstrator (Software) Deployment Architecture Design for a Service Oriented Architecture (TN)Deliverables:PrototypeCurrent TRL: 4 Target TRL: 6Applicable THAG Roadmap: Ground Systems Software (2008)Duration(months)12Page 51/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain9 Mission Operations and Ground Data SystemsRef. Number:G617-064GIBudget(k€):200Title:Objectives:Harmonisation of Numerical Software Validation Facility (NSVF) andOperational Simulator models1) Interview and collect the opinion of all the European S/C prime contractors onthis topic.2) Consolidate a business approach for viable and sustainable reuse of modelsbetween SVF facilities and operational simulators including clarification of theroles of SMEs in this process. The feasibility and the potential benefit of re-usingSVF models as part of the production of the specific Reference Test Facility of EGS-CC (EGS-Common Core) based systems shall also be investigated.3) Establish a set of key requirements on the SVF models that the S/C primecontractors must adhere to in order to make the business case viable including bothtechnical, legal, license, risk and financial aspects. It should be studied if these keyrequirements can form a common requirement basis between SVFs andOperational Simulators.4) Investigate the potential gain for different level of reuse:- At infrastructure level (i.e. reuse of Simsat/UMF for SVF)- Reuse at simulation level (i.e. reuse of complete S/C models)- Reuse of subsystem/individual models (ie. reuse of models for individualspacecraft units)5) Demonstrate the above established concepts with a case study of taking SVFmodels and reusing them in Simsat based Operational Simulators.6) Evaluate the various Reference Architectures existing in Europe relevant for thistopic and recommend solutions that would lead to further technical harmonizationwithin Europe and that would improve the overall efficiency in the developmentand use of SVF and Operational Simulators.Description:Simulation model reuse between SVF facilities and Operational Simulators hasbeen talked about for a long time, but has never matured in practise within the ESAcontext. During the last years several changes has occurred that now makes this theright time to tackle this topic for real: The SVFs has moved to a pure numerical emulation of the OBSW, hence isnow much more similar to the Operational Simulators than in the past. The SMP-2 standard is now well known within European industry provinga sound technical foundation for model transfer. The missions are under an ever increasing pressure to cut cost. The spacecraft electronic systems are getting more and more complicated,making redevelopment a more and more complicated task.Larger and larger parts of the spacecraft software are put under IPRrestrictions making an independent development of operational simulatorsharder.Secondly, recently in the scope of Seosat, an initiative from Astrium France andGDT in Spain that has prove that this approach can be both economical feasibleand technical viable, however it is required to study the approach in a generic waytaking on board the input also from all the other S/C prime contractors in EuropePage 52/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Useto ensure that a consistent solution is found that reduces the overall cost of all ESAoperations in a sustainable way.Deliverables:BreadboardCurrent TRL: 3 Target TRL: 6Applicable THAG Roadmap: Ground Systems Software (2008)Duration(months)18Page 53/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain9 Mission Operations and Ground Data SystemsRef. Number:G617-065GIBudget(k€):500Title:Objectives:Description:Scalable ground systems for high rate and high volume missionoperational dataEnd-to-end analysis and demonstration of state-of-the-art technologies andapproaches for managing ultra-high data rates as well as massive volumes of datagenerated by operational processes (e.g. spacecraft telemetry data, space systemsengineering state, recording of user actions, etc.).The management of the data generated by mission operations support systems isfacing the problem of managing continuously increasing data rates and volumes.The transfer rates of Telemetry data are expected to achieve levels (in the order of 1Gbps) which are by far beyond the capabilities of the existing implementations andmay imply radical rethinking of the ground systems architectures and design.Further, current and future missions expect that modern systems are able to recorddata in a format which is suitable for later replay. The downlinked data areexpected to be stored in the Ground Stations in a format which is suitable forforwarding and recovery of all received data. The state of space systems (e.g. thespacecraft) is expected to be stored in the Control Centre in processed form such toavoid the need of reprocessing when retrieving and distributing state data and alsoto remove the dependency on specific system configurations and tailoring. Afurther example is the recording of user actions, which can eventually be replayedfor the purpose of re-executing the same operations (e.g. for automated testing) orfor troubleshooting anomalies detected during operations execution. The amountof data to be stored/managed is proportional to the duration of missions, thus theneed of adopting technologies which are not only able to deal with massiveamounts of data but offer also scalability features supporting the management ofincreasing volumes of data (e.g. RnT.NoSQL technologies)Deliverables include:- Technical note reporting the analysis of system level impact of high data rates andvolumes onto the ground infrastructure- Technical note documenting the high-level design covering the full chain of datasystems involved in the forwarding, reception, processing and storage of high ratetelemetry data- Technical note on future data storage analysis and scalability techniques- Proof of concept (code + documentation)Deliverables:PrototypeCurrent TRL: 3 Target TRL: 6Applicable THAG Roadmap: Ground Systems Software (2008)Duration(months)18Page 54/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain9 Mission Operations and Ground Data SystemsRef. Number:G617-066GIBudget(k€):400Title:Objectives:Description:Automated rule-based cross-validation of operational dataThis study aims at supporting the rule-based validation of data definitions (M&Cdatabase) against operational data (in the pre-launch phase) and vice-versa thevalidation of operational data against the data definitions (in the post-launchphase). It represents the natural continuation of the TRP study OPSVAL.Deliverables include:- demonstrator suitable to be used in an operational environment- Code and documentation of a consolidated suite of tools supporting the datacross-validation- Document reporting the analysis of the use needs and possible support options inthe area of pre-launch and post-launch validation of missions' data- Support to deployment of the validation tools to a running mission and a missionin the preparation phaseA significant share of the mission operators man-power is devoted in pre-launch aswell as in the post-launch phases to data validation activities. In the pre-launchphase mission operations artefacts are defined in a way which is compatible withthe space systems implementation and the mission operations deign. In the postlaunchphase the mission data are evaluated in order to monitor the state of thespace systems, in particular of the spacecraft and ground stations equipment. Thisstudy aims at designing support tools which enable the automated repetitiion ofdata validation activities. It is based on the principle that the definition of data andthe actual values are expected to be coherent, thus cross-validation of datadefiniions against a valid set of mission states and viceversa the validation ofmission states against a valid set of data definitions is possible. The relevant rulescan generally be generated automatically but may also need to be augmented by theoperators relying on their expertise and knowledge of the mission rules.Deliverables:SoftwareCurrent TRL: 4 Target TRL: 6Applicable THAG Roadmap: Ground Systems Software (2008)Duration(months)14Page 55/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Use3.1.10 TD 10- Flight Dynamics and GNSSCore /Specific AreasCORETechnologyDomain10 Flight Dynamics and GNSSRef. Number:G617-067GFBudget(k€):200Title:Objectives:Description:Extension of the DO-IT trajectory design software for interplanetarytrajectories based on low-thrust propulsion combined with flybysThis activity shall extend the functionality of the DO-IT trajectory design softwaresuch that low-thrust trajectories and flybys can be addressed as integral part of thetrajectory design problem.The design of low-thrust interplanetary missions requires a good understanding ofballistic mission design and a versatile software for low-thrust trajectories. DO-ITis a prototype software tool that can be used to design interplanetary trajectorieslike the ones for Rosetta or MarcoPolo. Due to the modular approach, the differentphases of a mission can be assembled together in forms of building blocks. Thesoftware contains an optimiser that allows to further improve any possible missioncandidate. The software was tested and validated with numerous chemicalpropulsion missions, both historically flown and also theoretical ones.However, the prototype modules for low-thrust missions are only applicable in veryspecialised cases. To make the tool useful for low-thrust trajectory design newmodules need to be developed. The thrust-coast structures between flybys"learned" from BepiColombo and MarcoPolo-R shall be translated into simplebuilding blocks where the user only defines the departure body, the arrival bodyand the transfer time (or equivalently the number of heliocentric revolutions). Onelevel above, a module needs to be developed that evaluates the most promisingpermutations of the flyby bodies. A branch and bound utility which either runsautonomously or is guided by the user shall be programmed to avoid thecalculation of non-physical solutions and excessive CPU-times.There is a timely need for such a software tool in order to support the upcominginterplanetary missions. For instance, the development of the ion-engines forBepiColombo is coming close to a flight-readiness level and therefore it can beexpected that the efficiency of ion-engines in terms of fuel consumption will beconsidered for many Cosmic Vision studies. In this context a commercialisation ofthe DO-IT software has a good potential to be successful in specific areas of missionanalysis and flight dynamics in governmental agencies and industry.Specific tasks to be performed:1) Development of building blocks for low-thrust trajectories. The most commonthrust profiles useful for interplanetary transfers shall be programmed (e.g. coastthrust-coast-thrust-coastbetween launch and Earth flyby).2) Development of Algorithm to scan the sequence of the flyby bodies. Thealgorithm has to be tested and validated for interplanetary missions as well as formissions like Juice in a planetary system with moons.3) Development of a branch and bound module. An efficient algorithm needs to bePage 56/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Usedevelopment, that selects the most promising solutions and discards options thathave too high delta-V requirements.Deliverables:SoftwareCurrent TRL: 3 Target TRL: 6Duration(months)18Applicable THAG Roadmap:N/APage 57/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Use3.1.11 TD 11- Space DebrisCore /Specific AreasCORETechnologyDomain11 Space DebrisRef. Number:G617-073GRBudget(k€):300Title:Objectives:Bi-static beampark experiments and novel mechanical scanning andstare and chase conceptsThe current population of space debris objects in Low Earth Orbit is highlydynamic. Space debris models describe the estimated object population in space,but they require measurements to calibrate the model and to detect new debrisgenerating events and sources. Radar instruments are best suited to providemeasurement data for objects of a few cm in size in LEO altitudes. In so-calledbeampark experiments (24h campaign with a fixed viewing direction) the debrisenvironment can be reasonably sampled with some 500 detections. However, thesedetections are not able to provide orbital parameters.The objective of the activity is to generate the radar measurement data required toallow for improved space debris models for the benefit of all missions in Earthboundorbits. The idea is to develop and apply novel observation concepts thatallow to generate a better estimation of the orbital parameters.Description:The TIRA (Tracking and Imaging RAdar) of Fraunhofer FHR, has the requiredpower and wavelength combination and the requried observation mode andprocessing software to conduct 24h beampark experiments. This radar shall beused to provide a statistical sampling over the space debris environment over 24hand translate it into detection lists for a classical bistatic mode jointly with theEFFE(Effelsberg Radiotelescope) in order to allow for detections of objects down to1cm size in 800km altitudeIn addition the feasibility of mechanically scanning a given azimuth/elevation fieldwith TIRA alone in a periodicity that allows each object to be detected at least threetimes during a passage shall be analysed. Should an observation and scanningmode be possible that fulfills these constraint, algorithms for the correlation ofdetections during one passage to a single objects shall be developed. Thesealgorithms shall be tested with simulated data. The campaign shall then beconducted for a reasonable measurement time, long enough to cover at least twoconsecutive passages of LEO objects. Correlation and subsequent orbitdetermination shall be performed.Alternatively, (if the required performance is not achievable with scanning), thefeasibility of a stare and chase approach shall be studied (i.e. the angular rates of aspontanous detection are determined on the spot followed by immediate tracking).This mode shall be as well experimentally verified.Deliverables include:- Study ReportPage 58/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Use- In-track correlation algorithms- detection listsDeliverables:Other: Study reports and softwareCurrent TRL: 3 Target TRL: 5Duration(months)12Applicable THAG Roadmap:N/APage 59/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Use3.1.12 TD 12- Ground Station System & NetworkingCore /Specific AreasCORETechnologyDomain12 Ground Station System & NetworkingRef. Number:G617-074GSBudget(k€):400Title:Eye-Safe Ground Beacon SystemObjectives:Description:The objective is the development of a scalable high-power laser beacon system asan acquisition and pointing aid as well as high data rate uplinks for opticalcommunications addressing all critical aspects, including regulatory eye-safetyconsiderations.Optical communications technology offers the potential of a dramatic increase indata-rates, specifically in down-link of science data, thereby allowing for asubstantial increase in science return per cost element.One major challenge of an operational optical terminal is a high-power laserbeacon system as acquisition and pointing aid (usable also for actual data uplink).Such a beacon is a necessary feature of a reliable optical link (Tesats LCT, whilebeing described as beacon-less simply utilizes the communications beam itself as abeacon, rather then employing a separate beam;). Several aspects of what mightseem a simple concept is in reality fairly complex.Critical areas to address are:- efficient generation of a high-power laser output- transmission of several incoherent sub-beams (e.g. from separate sub-aperturesof the receiving telescope) to mitigate atmospheric scintillation / fading at thesatellite terminal- proper co-pointing and beam-waist management to maximize received power atthe satellite terminal- consideration of regulatory eye-safety issues (size of sub-aperture, technical andoperational safety measures)- a modular, scalable design (e.g. multiplication of sub-apertures) allowing toimplement the proper power output as required by each particular missionThe activity will produce an engineering model:a) A scalable laser beacon system at 1550nm consisting of at least four sub-beamsvalidated in a ground-based (e.g. inter-island btw. La Palma and Tenerife)experiment.b) Any necessary safety system to ascertain regulatory eye-safety compliance (fulldetailed design; implementation to the degree allowed by the available budget.Deliverables:Engineering ModelCurrent TRL: 4 Target TRL: 6Duration(months)24Applicable THAG Roadmap: Optical Communication for Space (2012)Page 60/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain12 Ground Station System & NetworkingRef. Number:G617-075GSBudget(k€):500Title:Objectives:Experimental 20-40 GHz band InP MMIC based cryogenic LNAsprototypingThe main objective of this activity is to industrialise a wide band 20- 40GHz InPMMIC based LNA for multipurpose application (EO, Science, Exploration, etc...)Future near Earth mission such as Euclid will use 26 GHz band and future deepspace missions (potentially Juice) 32 GHz (Science) to transmit high datarate. Verystringent noise performance requirement will impose the use of very highperformance cryogenic low noise amplifier. The advantage of MMIC technology iscost reduction for a large scale production and performance repeatability. Thefuture ground stations architecture will use arrays of antenna and will benefit fromthis performance improvement and cost reduction. The purpose of the activity isthe design of large band MMIC cryo LNA, the production of a test wafer (few 10 s ofMMIC) and validation of the industriability over a set of few 10's of complete LNA.Description:Two parallel TRP activities have been completed in 2012 for the development of Kaband InP cryogenic amplifiers. These two TRP activity were awarded to CentroAstronomico de Yebes (Spain, prime contractor) with ETH (Switzerland) assubcontractor and to Chalmers University (Sweden). The purpose of the proposedGSTP is the continuation of the TRP activity for the validation of the K/Ka bandamplifier in operational environement and for the preparation of the productdemonstration. MMIC technology is intrinsically wideband and the design willcover the frequency band of many applications from earth exploration, science andexploration mission and radioastronomy as well.Deliverables:PrototypeCurrent TRL: 3 Target TRL: 5Duration(months)18Applicable THAG Roadmap:N/APage 61/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Use3.1.13 TD 13- Automation, Telepresence & RoboticsCore /Specific AreasCORETechnologyDomain13 Automation, Telepresence & RoboticsRef. Number:G617-076MMBudget(k€):770Title:Development of technology tools for training and operations of theMETERON Mission Preparation and Training CentreObjectives:Description:Software development for performance analysis of robotic missions involvingshared autonomy, teleoperation and autonomous robotic action sequencing.Experiment training tools for robotic activity training and real-time operationsprocesses will be developed in this activity. Software for simulation of a the onboardsegment functionality, failure injection, recovery strategy analysis, andperformance evaluation of ground and in-orbit operators. Including developmentof ISS Mockup Hardware, Operations Software, Training Software, Comm's andoperational software and development of experiment software and scenarios for theMETERON in-orbit experiment on ISS.Deliverables:SoftwareCurrent TRL: 6 Target TRL: 7Applicable THAG Roadmap: Automation & Robotics (2012)Duration(months)12Page 62/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Use3.1.14 TD 14- Life & Physical SciencesCore /Specific AreasCORETechnologyDomain14 Life & Physical SciencesRef. Number:G617-077MMBudget(k€):600Title:In Situ Plasma Cleaning of Space OpticsObjectives:The objective of this study is to design, build test and characterise a compact in situplasma cleaning device for space optics.Description:Cleanliness of optical surface is of utmost importance for e.g. earth/planetaryobservation or astronomy missions. Even thin layers of organic and small amountsof particulate contamination can jeopardise the performance or introduce artefactsin imagers or spectrometers. Another well known problem is the challenge of laserinduced damage caused by organic contaminants on optical surfaces ( e.g. inspaceborn LIDAR lasers). Contamination can build up as well during operations ofa spacecraft due to unwanted but eventually unavoidable out gassing products. It isproposed to introduce an active cleaning method. This method consists of ashielded microwave induced remote low temperature plasma to remove layers oforganic contaminants and even organic particulates within the area of interest.Currently this technique is applied and tested on E-UV lithography machines andreticles, achieving a significant reduction of organic contamination and particleload.Deliverables:BreadboardCurrent TRL: 3 Target TRL: 4Duration(months)24Applicable THAG Roadmap:N/APage 63/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain14 Life & Physical SciencesRef. Number:G617-078MMBudget(k€):700Title:Self Validating High Temperature SensorsObjectives:Description:Improving the accuracy of contact temperature measurements above 1300K up to2600K and validation of a system prototype in relevant environment.Contact temperature measurements above 1300K are challenging with respect tolifetime and drift of the sensors. High Temperature Fixed Points (HTFP) cells fromcarbon-metal eutectics (which will be the new reference for ITS-90) in combinationwith W-Re (Type C) thermocouples provide a solution to check the health of thesensors and to compensate for signal drift by using the melting and freezing of theeutectic.A current finalized activity (TRP T714-067MM) proved the feasibility of multipoint calibration cells. Further activities are needed to improve the design(stability, size) and gain confidence in life test campaigns also in combination withother strategies e.g. electrical noise thermometry (ENT).Space applications are in the field of reentry or tests thereof e.g. in shieldingmaterial tests in plasma wind channels. Propulsion tests, sensors for harshenvironments and materials characterization are potential applications. Terrestrialapplication include the monitoring and control of all high temperature processes (e.g. solar, nuclear or metallurgy) and in turbines. For this reason this proposal isalso of the 'Power and Energy' roadmap.Deliverables:PrototypeCurrent TRL: 4 Target TRL: 7Applicable THAG Roadmap: Aerothermodynamic Tools (2012)Duration(months)30Page 64/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain14 Life & Physical SciencesRef. Number:G617-079MMBudget(k€):500Title:Objectives:Description:Optimisation and validation of ultra cleaning methods applied tospacecraft materialsThe objective of this proposal is to optimise and validate ultra cleaning methodsand their compatibility with spacecraft materials of concern, to give designrecommendations for spacecraft materials and surface specifications in order tocomply i)with mission specific performance and cleanliness requirements and ii)with the compatibility of the spacecraft materials.Precision and ultra cleaning of surfaces is required on spacecraft surfaces andsystems requiring high levels of cleanliness. Particulate, molecular and biologicalcontamination of solid surfaces may jeopardise the scientific and technologicalobjectives of a mission, be it for optical surfaces in astronomy and earthobservation missions ( e.g. telescopes, laser optics prone to laser induced damageetc.), be it for analytical instruments and spacecraft surfaces for explorationmissions requiring the absence of contaminants to avoid false positive or falsenegative measurements. A preliminary TRP study has been successfully concludedon a first systematic investigation on cleaning efficacies of one cleaning process(CO2 snow jet) for molecular, particulate and biological contamination, by directand indirect measurement methods. This revealed interesting and promisingresults which flowed directly into project activities ( ExoMars) on industry side,however it was limited to one process. Depending on the application, severalprocesses may need to be considered (supercritical fluid cleaning, multi solventcleaning, plasma cleaning...) the analytical approach needs to be refined (methodsand protocols) and the range of materials widened to comply with customer needs.The results of this study will support the ECSS standard under preparation for ultracleaning methods (ECSS-Q-70-54C).Deliverables:Other: Procedures, Process validation, ECSS standardCurrent TRL: 3 Target TRL: 6Duration(months)20Applicable THAG Roadmap:N/APage 65/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Use3.1.15 TD 15- Mechanisms & TribologyCore /Specific AreasCORETechnologyDomain15 Mechanisms & TribologyRef. Number:G617-080MSBudget(k€):1250Title:Objectives:Description:Improvement of Solar Array Deployment Mechanisms technologies.To develop and consolidate new SADMs technologies to improve their design androbustness. This includes development and evaluation of European new electricaltransfer contact materials, ball bearing cages and motors operating at hightemperature.Description: This activity aims at two main objectives:-Following the outcome of the on- going ITI activity Miniaturized Solar Array DriveMechanism (SADM) for Nanosatellites, the need of developing and consolidate newSADMs technologies for small platform has been identified, namely in terms ofmass and volume optimisation and complexity reduction (as per THD for SADMs,activity B06).-For high power and/or long lifetime SADMs, as well as for any mission whichforesees high temperature environment, a Europe dependence on US productexists, especially with respect to electrical transfer contact material, ball bearingcages material and electric motors technologies. The second objective of this GSTPactivity shall be then focused on the development and evaluation of fully Europeannew electrical transfer contact material (as per THD for SADMs, activity B09),cages material (as per THD for SADMs, activity D02), and on electric motorstechnologies, both customised and/or adapted from industrial product (as per THDfor Electric motors, activities A04 and A06), capable to sustain high environmentaltemperatures.Deliverables:BreadboardCurrent TRL: 4 Target TRL: 5Duration(months)24Applicable THAG Roadmap: Solar Array Drive Mechanisms (2008)Page 66/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain15 Mechanisms & TribologyRef. Number:G617-081MSBudget(k€):800Title:Objectives:Description:Improvement of high accuracy angular optical sensors.To develop and consolidate new technologies allowing the improvement in highresolution optical sensors in terms of performance and reliability.As a lesson learnt, in order to provide support for the medium term applicationsthere is the need of identification with due advance of means to reach a stepforward for optical encoders and to implement the necessary preliminary steps topave the reach of the qualification maturity level. This need involves, for opticalhigh precision angular sensors, both the performance, such as the angularresolution, accuracy of measurement, speed, and also reliability aspects, such astemperature range and radiation tolerance. High-rel ASICS with ESA and CNESfunding are implemented. Encoders on laser terminals are implemented and arestarting to entre the market for other applications as well. New technologies andpotentials are already identified in the last periods, such as improved tolerance toradiations provided by optical diodes, high accuracy encoder technology, etc. Theactivity is intended to identify the technologies availability and perform thedevelopment activities needed to breadboard a new generation of encoders withenhanced long term reliability and measurement performance. A breadboardincluding the required technology shall be built and tested against performance.Deliverables:BreadboardCurrent TRL: 4 Target TRL: 6Applicable THAG Roadmap: Position Sensors (2009)Duration(months)18Page 67/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain15 Mechanisms & TribologyRef. Number:G617-082MSBudget(k€):300Title:Objectives:Advanced simulation tools for deployment, dynamics predictions andon-ground verification- Improve the solution convergence robustness of complex dynamic deployment bytranslating mechanical discontinuities (such as latching, brakes,...) with pseudocontinuouselements;- Improve and validate the structural damping mathematical models for dynamicdeployment including test correlation;- Implement energy measurements in order to assess validity of numericalsolution;- Enhance sensitivity Monte-carlo-like analysis tool to be able to introducedisturbance on elastic properties (such as mode shapes, frequencies,...).Description:In the frame of past research activity focused on reviewing numerical timeintegration schemes for solving complex deployable space system such as LargeDeployable Reflector and P-band FLATS antenna, two main limitations wereclearly identified. The first limitation is on the modelling of discontinuities (suchlatches, brakes,...). The current representation of these elements is not optimizedwith severe consequences on solution convergence and robustness. The second oneis on the selection of the proper structural damping mathematical representation.It is essential to identify the most suitable representation among the several modelsare current available in literature.Furthermore in large solar array deployment the need to independently assess thevalidity of numerical solution by mean of monitor the energy characteristics of thewhole system (kinetic energy, potential energy, total angular momentum, ...) isvital.Moreover there is a clear need to perform to investigate the effects of uncertaintieson elastic components of the system without the need of re-condensate the FiniteElement Model.Above identified improvement are crucial also for the dynamic simulation andverification activities for long deployable mast and more in general ultra stabledeployable structures, which are essential to enable future science and Earthobservation missions.Deliverables:Study ReportCurrent TRL: 3 Target TRL: 5Duration(months)18Applicable THAG Roadmap: Deployable Booms & Inflatable Structures (2010)Page 68/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain15 Mechanisms & TribologyRef. Number:G617-083MSBudget(k€):200Title:In-orbit manufacturing of very long booms.Objectives:Description:To develope a technology allowing the in-orbit realisation of very long, slendercomposite booms for large aperture applications.Description: Techniques to in-orbit manufacture very long booms (from 20m up toapproximately 50m and more) have been addressed in the past by looking at inorbitbonding of thin-walled composite booms. Composite technology also allowsthe direct manufacturing of a long, continuous, constant cross section beam bymeans of a pultrusion process, permitting the achievement of lengths, up to 200m,with potential superior accuracy / stability performances. The present activity aimsat a feasibility study of the pultrusion process application to in-orbit manufacturingof very long booms, realisation and testing of a pultrusion machine to be operatedin vacuum, to realise a portion of composite beam to be mechanicallycharacterised.Deliverables:BreadboardCurrent TRL: 2 Target TRL: 4Duration(months)24Applicable THAG Roadmap: Deployable Booms & Inflatable Structures (2010)TD 15- Mechanisms & TribologyPage 69/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Use3.1.16 TD 16- OpticsCore /Specific AreasCORETechnologyDomain16 OpticsRef. Number:G617-085MMBudget(k€):1000Title:Objectives:Digital Micro-Mirror Array (DMA) for space optical instrumentsThe objective of this activity is to develop in Europe the technology for DigitalMicro-mirror Arrays, which are considered mission-enabling key components inoptical spectrometers in Earth Observation (next generation of Sentinel 5,CarbonSat or Flex type of missions), Planetary Exploration (next generationMarsExpress type of missions) and Astronomy (multiobject spectroscopy likeNIRSpec).In a first technology development step a linear array of digitally (on/off) actuatedmicro-mirrors shall be designed, manufactured and tested to be used as aprogrammable slit for push broom spectrometers. Placed in the slit of aspectrometer, such a device will significantly improve the system performance byadding new functionalities such as scene/object selection, detection noise reductionand scene equalisation. Placed after a dispersive element (grating) this device canbe used as a programmable spectrometer, in which enhanced sensitivity to specificmolecules/spectra can be programmed. A particular focus of this activity lies onmeeting the challenging requirements with respect to mechanical robustness,stability and reliability. The test programme will therefore include environmentaltesting w.r.t. temperature loads, shock, vibration and acoustic loads.Description:DMAs as today available in Europe do either not fulfil the functional requirementsor are mechanically not robust enough to survive space environmental conditions.A US commercial product could in principle be used in space (however only atroom temperature), but its design is not optimised for space applications.Placed in the slit of a spectrometer, such a DMA significantly improves systemperformances by adding following new functionalities:- Scene/Object selection: Blocking the bright scenes (clouds, sun-glint) at thespectrometer slit and transmitting only the useful part of the scene decreasessignificantly the stray-light and at the same time increases the number ofexploitable image pixels. It also allows scientific observation of scenes very close toor inbetween clouds which is not feasible today.- Detection noise reduction: By closing the slit during the detector's read-out timethe detector is not illuminated and therefore has no read-out smear. Thiseliminates a detection noise contributor.- Scene equalisation: High contrast scenes with deep absorption lines which have tobe spectrally resolved pose a challenge in terms of dynamic range of the detectorand stray-light. By equalizing the scene brightness, the contrast of the scene can beeliminated and the signal dynamic range can therefore be reduced by orders ofmagnitude (factor ten to hundred) which improves detection and stray-lightperformances.Placed after a dispersive element (grating) this device can be used as aPage 70/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Useprogrammable spectrometer in which enhanced sensitivity to specificmoelcules/spectra can be programmed. For the programmed spectra a SNRincrease can therefore be achieved.The proposed activity covers the development of the technological processesneeded for the manufacturing of one- as well as two-dimensional Digital Micro-Mirror Arrays. Whereas in this activity only one-dimensional arrays will beproduced and tested, the manufacturing and testing of two-dimensional arrays willbe addressed in a dedicated follow-on activity.Deliverables:Other: 1-Dimensional Array EMCurrent TRL: 3 Target TRL: 5Duration(months)24Applicable THAG Roadmap:N/APage 71/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain16 OpticsRef. Number:G617-086MMBudget(k€):950Title:Calomel-Based TIR Hyperspectral ImagerObjectives:1) To design a Hyperspectral Imager operating in the Thermal Infrared (TIR)spectral range based on Acousto-Optic Tunable Filters (AOTF) using Calomelcrystals,2) To breadboard and test critical technologies, in particular the Calomel AOTFassembly.Description:The successful development of the Calomel AOTF done in 2012 under GSTPcontract has put the basis for the development of Hyperspectral Instrumentsworking in the Thermal Infrared. The novelty of this technology requires to gothrough an application study to better understand the potential of this newtechnology and its possible applications, and to breadboard the novel and criticaloptical elements.The activity will comprise:- Instrument architectural design & performance analysis,- Application analysis of the instrument for Earth Observation remote sensing /Planetary Survey / Scientific Instruments,- Preliminary instrument design & identification of critical technologies,- Breadboarding and testing of critical technologies.The work will be performed in two phases, with the breadboarding performed aftercompletion of Phase 1.Deliverables:BreadboardCurrent TRL: 3 Target TRL: 5Duration(months)15Applicable THAG Roadmap:N/APage 72/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain16 OpticsRef. Number:G617-087MMBudget(k€):800Title:Objectives:Description:High Speed Deterministic Polishing of Strongly Aspherical MirrorsTo develop technologies for improving surface roughness and shape accuracies oflarge (300mm) and strongly aspherical aluminium mirrors applying cost-effectivepolishing processes. The objective is to demonstrate the technology bymanufacturing and testing a breadboard of a strongly aspherical mirror withdiameter up to 300mm, shape accuracy better than 30nm (rms), and surfaceroughness lower than 2nm (rms).Single Point Diamond Turning has proven to be a very cost-effective method toproduce strongly aspherical mirrors. A limitation of this technology is theachievable surface roughness limited to 4 nm (rms) and the poor shape accuracyfor mirrors with diameter larger than 250mm.Aspherical mirrors of large diameter can be manufactured in other substrates likeZerodur and SiC using conventional polshing methods, however strong asphericycan only be achieved at the expenses of a long proceses time and high cost.Deterministic polishing, now available thanks to recent developments inmanufacturing tools, has not yet been proven on lightweight aluminium opticalmirror. This technology, if successful, will provide the process for developingstrongly aspherical and lightweight aluminium mirrors with diameters up to300mm. These mirrors are instrumental to reduce mass, envelop and cost ofoptical systems, both for Earth Observation instruments and for compact highperformanceoptical instruments for planetary probes and scientific payloads.Furthermore, the capability to manufacture low roughness strongly asphericalmirrors opens the possibility to innovative optical design of both panchromaticcameras and spectrally resolved instruments.Deliverables:Other: breadboard + detailed "process description"Current TRL: 4 Target TRL: 6Duration(months)12Applicable THAG Roadmap:Technologies for Optical Passive Instruments (Stable &Lightweight Structures, Mirrors) (2008)Page 73/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain16 OpticsRef. Number:G617-088MMBudget(k€):500Title:WFE test of large aspheric opticsObjectives:- To review concepts for the accurate measurement of the Wavefront Error (WFE)of large aspheric optics;- To study, design and manufacture an accurate test setup for the reproducibleWFE measurement of large aspherical optical elements.Description:Deliverables:Two clear trends can be identified for all future optical space missions:1) Image quality requirements will become more challenging2) Instruments (and in particular telescopes) will make a widespread use of big-sizeaspherical and free-form optical components.Such tight image quality requirements will be flown down to very low wavefronterror (WFE) requirements for each single optical element. This will require veryaccurate measurements of the aspheric profile. As a rule of thumb the errorinduced by the setup in a WFE test should be at least 3 times smaller than the WFEof the surface under test. Setup accuracies better than 4-5 nm rms will become acommon requirement for the next generation of optical instruments.A commonly used WFE measurement of an aspherical surface is currently based ona null interferometric test with a Computer Generated Hologram (CGH). Themanufacturing quality of these holograms is usually a key driver for the accuracy ofthe WFE measurement. In particular the substrate homogeneity and pattern errorsaffect directly the accuracy of the test. High quality CGHs are often procuredoutside Europe raising potential dependence issues.Another disadvantage of CGH is linked to the fact that for each specific asphericprofile a specific hologram is required. A small change in the design requires theprocurement of a completely different CGH for the test. Universal scanningmeasurement machines have been developed as potential alternatives to null tests,but currently these machines cannot guarantee the same level of accuracy. Despitethis technological limitation, the improvement of test setups being an alternative toCGH should be pursued.A first objective of this activity is a critical review of all potential test concepts forthe WFE of aspherical components. The second objective is the definition and theimplementation of a very accurate test setup. This setup can be based onholograms, null lenses or alternative concepts.Deliverables of this activity are:- TN with review of test concepts and study of an accurate test setup.- Test setup.PrototypeCurrent TRL: 3 Target TRL: 6Duration(months)12Applicable THAG Roadmap:Technologies for Optical Passive Instruments (Stable &Lightweight Structures, Mirrors) (2008)Page 74/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain16 OpticsRef. Number:G617-089MMBudget(k€):750Title:Objectives:Description:Effect of radiation on light-weighted mirror substrates (in particularZerodur)To review radiation induced damage effects on common substrates used for lightweightedmirrors and to measure and analyse the radiation induced wavefronterror on light-weighted mirror substrates (in particular Zerodur)All materials exposed to radiation coming from the space environment are to someextent subject to compaction or expansion due to damages occurring at atomic ormolecular level.Zerodur , one of the most commonly used materials for mirror substrates (inEurope), can be affected by compaction due to radiation effects. Usually thiscompaction introduces a modification of the mirror profile resulting in a WFEcontribution and corresponding degradation of the image quality during operation.The analysis of this effect during the design phase of optical instruments is difficultand can therefore be affected by mistakes and wrong assumptions. Since Zerodurmirrors are widely used for telescopes in Earth observation and Science, the entiresubject requires a critical review because of the inherent uncertainties in themodelling. The selection of such substrates is always a very critical program choice.The last experimental test programme on this subject in Europe was done in 1979.Deliverables of this activity are:- Technical note with a critical review of the radiation effects and updatedanalytical/numerical model of radiation induced compaction for a range of typicaldose levels.- Light-weighted Zerodur mirror measured before and after radiation testsDeliverables:BreadboardCurrent TRL: 4 Target TRL: 5Duration(months)18Applicable THAG Roadmap:Technologies for Optical Passive Instruments (Stable &Lightweight Structures, Mirrors) (2008)Page 75/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain16 OpticsRef. Number:G617-090MMBudget(k€):500Title:Objectives:Particle contamination: scattering models and measurement device1) Critical review of the straylight models currently in use for the evaluation ofscattering effects induced by particle contamination,2) Tailoring of the straylight models to the actual status of clean rooms in Europe,3) Input to possible review of ECSS standards,4) Development of a breadboard of a portable (contactless) device which wouldallow to measure particulate contamination on optical surfaces in-situ.Description:A correct straylight analysis is of the utmost importance for the success of allmissions flying optical instruments. With the improvements of surface polishingtechniques, the scattering due to surface roughness is becoming comparable orsometimes even negligible with respect to the scattering due to particlecontamination. This explains why the assessment of straylight induced by particlecontamination is becoming more and more important.The methodology for the analysis is addressed in the European ECSS standard andin the MIL STD 1246C.However, this methodology needs to be reviewed for several reasons:1. It has been published in literature that the particle distribution slope indicated inthe standard is not in agreement with fallout measurements done in US cleanrooms. As consequence the application of the standard is sometimes leading tounrealistic and too demanding cleanliness requirements at instrument andsubsystem levels.2. The particle distribution slope is known to be different from the standarddepending if a cleaning procedure is applied or not. This aspect is usually notconsidered in the analysis.3. The justification of the model is based on the Mie-scattering theory of sphericalparticles made of silica. This is clearly a simplification not corresponding to reality.Another critical subject is the measurement of the actual contamination level ondelicate optical surfaces. The current way to measure contamination in theinstruments is to use dedicated samples located close to the optical elements. Thesamples are extracted from the instrument at a certain step during the instrumentintegration process and analysed. The advantage of a portable device would be thepossibility to measure contamination directly on the optical surfaces and to obtainthe information about the distribution of the contamination over the surface(contamination map). It may also allow to avoid using contamination samples incertain cases, thus simplifying instrument design and integration.The device for measuring contamination could, for example, include a photocamerawith a microscope objective integrating a lighting system and image processingsoftware.Deliverables of this activity are:1. TN with review of particle contamination BRDF models, from theory to actualapplication to clean room environment and AIV/AIT procedures. TN shouldPage 76/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Useinclude scattering measurements of contaminated samples. Samples are adeliverable to ESA.2. TN describing the operation principle and the design of the portablecontamination measurement device.3. Breadboard of the portable contamination measurement device.Deliverables:Other: Breadboard and Design Report of contamination measCurrent TRL: 3 Target TRL: 4Duration(months)18Applicable THAG Roadmap:N/APage 77/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Use3.1.17 TD 17- OptoelectronicsCore /Specific AreasCORETechnologyDomain17 OptoelectronicsRef. Number:G617-092MMBudget(k€):600Title:Multi-Gigabit Optical Fiber CommunicationsObjectives:Description:Fiber optic communication combines a number of unique properties such as beingdielectric and EMI free, lightweight, mechanically flexible, and protocol agnostic(can convey any type of signal) at any data rate. Indicatively the WFI instrument ofthe ATHENA (ex IXO) space science mission has baselined fiber optics for suchlinks. It is also worth noticing that SMOS, the first satellite payload worldwide tocritically depend on the use of tens of fiber optic links, decided to use thistechnology for its EMI properties and mechanical flexibility as the payload requiredto deploy 3 branches of a radiometer.To meet these future needs the objective of the activity is to develop an EM of bidirectionaloptical transceiver module capable of multi-gigabit digital opticalcommunication. Such a component would provide a complete intra-satellite digitaloptical communication solution covering data rates from Mbps to 10 Gbps,bringing all the advantages of optical communications together with harnessreduction by applying a bi-directional approach.Qualification is not expected.Building on the positive experience of both the SpaceFibre Transceiverdevelopment activities and the Small GEO optical TM/TC developments, thisactivity will develop an bidirectional optical module providing opticalcommunication covering Mbps-10 Gbps communication bandwidth. Over the past6 years the Agency has invested in advancing the associated technologies to a TRL4, however there continues to be a need to address three main issues related to thepackaging in order to continue to increase the TRL of this technology:1) Hermetic sealing. This comes with an open issue to address whether thehermetic sealing is required for reliability of optoelectronic components (VCSELsand PIN diodes).2) Mbps 10Gbps operation, including a reliable board mounting approach suitablefor the 10Gbps operation.3) Bi-directional operation, to maximise the harness reduction of the technology,and improve the network reliability by reducing the number of connectors.Addressing the above three issues an EM will be designed and tested in a relevantenvironment in order to reach a TRL5.Deliverables:Engineering ModelCurrent TRL: 4 Target TRL: 5Duration(months)24Applicable THAG Roadmap: On-Board Payload Data Processing (2011)Page 78/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain17 OptoelectronicsRef. Number:G617-094MMBudget(k€):800Title:Objectives:Enhancement of electrostatic accelerometers for Earth and planetarysciences and fundamental physics: flight data analysis, model anddesign refinements, breadboarding and testingUltra-sensitive electrostatic accelerometers using capacitive sensing have beendeveloped at ONERA (FR) under various ESA and CNES activities for over twodecades (cf. e.g. Development of Ultra-Sensitive Spaceborne Accelerometers, inPreparing for the Future ESAs Technology Programme Quarterly, Vol. 4 No. 2,June 1994). They have flown in a number of missions (multiple STS flights,CHAMP, GRACE and GOCE missions) or are about to fly in new ones (e.g.MICROSCOPE). Culmination of this research and development is theaccelerometer of the gravity gradiometry mission GOCE, currently in its extendedoperations period.All flight results have confirmed the outstanding performance of the design andimplementation of the accelerometers in this family of sensors (collectively referredto here as the gradio accelerometer, as per original naming). The gradioaccelerometer has however not yet reached its limit of performance and furtherimprovements will be of major importance to many future missions in the domainsof Earth sciences, planetary sciences, fundamental physics, drag-free spacesystems, and more. The goal of the present activity is to further develop the gradioaccelerometer aiming at improved performance with respect to the units currentlyflying on GOCE satellite.Description:The characterization of the noise of the accelerometer in the low-frequencydomain, and the detection and characterization of systematic errors are particularlyimportant in view of future missions. The flight data from GOCE offers a uniqueopportunity to verify the performance of gradio accelerometers in space, both atsingle accelerometer level and in gradiometer configuration, in conjunction withGPS and other sensors. Therefore the flight data will be exploited for specificanalyses, additional to what performed so far within that mission (driven bygradiometer data validation rather than accelerometer perfomance improvement),devoted to the finest characterization of the performance. Such analyses areexpected to lead to substantial revisions of the assumptions used to generate errorallocations in former models and to predict performance more reliably, potentiallyavoiding pessimistic assumptions and excessive margins. Combining the availableknowledge (including detailed models) in the accelerometer technology and theanalysis of the GOCE flight data is a pre-requisite to design, integrate and test abreadboard model of a modified, improved version of the accelerometer, which willconstitute the bulk of the present activity. Opportunity for improvements of the keyelectrical elements (capacitive detection, drive voltage amplifiers, analogue-todigitalconverters..) and of the thermo-mechanical set up will be analysed in detailand validated with end-to-end and ad-hoc models.This work will allow reaching TRL 5 compared to the current TRL for suchPage 79/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Useenhanced accelerometer, which due to the combination of flown elements and ofnew elements only preliminarily analysed at present - cannot be assumed to exceed3. All future missions employing sensitive accelerometers will benefit from theperformance characterization available from the thorough analysis of the GOCEaccelerometer science and engineering telemetry, from the related modelling andanalysis work, and from the enhancement of key accelerometer elements.Deliverables:BreadboardCurrent TRL: 3 Target TRL: 5Duration(months)24Applicable THAG Roadmap: AOCS Sensors and Actuators (2009)Page 80/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain17 OptoelectronicsRef. Number:G617-095MMBudget(k€):450Title:Objectives:Description:Development of low-noise laser-diode drive source for ultrastablecoherent CW laser sources applicationsThe objectives of the following activities are to develop to TRL5 an ultrastable laserdiode drive source as required for driving ultra-coherent lasers employed in opticalclocks and cold atom devices. The focus of the development will be to engineer acurrent source of ultra-high stability in amplitude and frequency as to driveefficiently the critical laser diodes. Further to injection current amplitude andfrequency stability engineering aspects, this activity will also cover the realisationof an accurate regulation system of the laser diode temperature. The designtopology to be implemented shall lead to optimization of (reduce)mass and powerand to achieve high reliability for the envisaged space environment.Stable laser operation, as for optical clocks and cold atom devices, require accurateinjection current with ultra-low noise as well as accurate regulation of diodetemperature. In fact the laser diode frequency and power characteristics stronglydepend on the diode junction temperature values and stability and how theinjection current is generated and controlled. This activity will address the design,developemnt and test in relevant environment of a complete assembly of a laserdiode drive consisting of a voltage reference part, a voltage to current converter andcurrent boot stage. The design will carefully address and trade-off differenttopologies and implementation schemes with aim to achieve maximum driveperformance in enviroment at lowest resource budget. The work will be carried inthree pahses: the first of requirements analysis and specifications, then a secondphase of design and development, and a finally MAIT.Deliverables:Engineering ModelCurrent TRL: 4 Target TRL: 5Duration(months)18Applicable THAG Roadmap: Frequency & Time Generation - Space (2005)Page 81/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain17 OptoelectronicsRef. Number:G617-096MMBudget(k€):800Title:Objectives:Description:Low cost, low power, medium performance resonant-micro-opticalGyrosope (RMOG)based on resonant ring lasersMedium Performance gyro (1-10 deg/hrs) are a critical European technology not asmuch explored/developed as the high peformance gyros (FOG, RLG: < 10-3deg/hrs)where several excellent European products exist.The range of medium-performance gyros has received increased interest for spaceapplications. The technology proposed here stems from previous proof-offeasibilityactivities perfromed under the TRP programme. These activities havesuccessfully demonstrated the potential of several optical resonant gyro concepts toachieve 1 - 10 deg/hours performance in a small optoelectronic package. Integratedoptical technologies have allowed the demonstration of both micro-scale devices,with outstanding performance, and integrated circuits including hundreds ofactive/passive optical components monolithically integrated on the same chip.These technologies are seen as critical for the development of new generationoptical gyroscopes with resolution of 1 - 10 deg/hour and with mass, volume andpower consumption comparable to MEMS angular velocity sensors. Further,innovations in optical fibre technology have resulted in the potential for new fibrebased gyros that can result in significant improvements to FOG designs. Theobjective of the proposed GSTP activity is to bring the most promising of thesedesigns, either integrated-optics resonant cavity based or fibre based, from thecurrent TRL3 to TRL5.The preceding proof-of-feasibility activities have focused on the use of discretefibre coupled optical components and laboratory electronic equipment todemonstrate the feasibility of the technology. This activity will look into improvingthe TRL through the integration of the opical components and electronics, andoptimisation of the packaging of the gyro into an elegant breadboard. This is withthe aim to demontrate both the form and fit elements of the technology.The development steps shall include:- Miniaturisation and optimisation of the optical elements (lasers, detectors, phasemodulators, couplers and waveguides) through integration to minimise power andvolume requirements.- Monolithic/hybrid integraton approaches will be investigated to bring allelements together in a compact form.- Miniaturisation of the microelectronics required for interrogating the gyro(phase-locking) to be addressed, including ASIC design.- Packagaing of the miniaturised optical components, sensor and microelectronicsshall also be addressed to demonstrate the form and fit of the device.- The critical components/breadboard shall be demonstrated in a relevantenvironment to bring the TRL up to 5.Deliverables: BreadboardCurrent TRL: 3 Target TRL: 5Duration(months)Applicable THAG Roadmap: AOCS Sensors and Actuators (2009)24Page 82/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain17 OptoelectronicsRef. Number:G617-097MMBudget(k€):220Title:Objectives:High performance optical filters based on Si fine grid supported ultrathin SiN foilsDevelopment of high-TRL, ultrathin optical filter technology for use in X-ray, UVand IR instrument applications.Description:Many instrument applications (both space and ground) require the detector to beshielded, either to prevent unwanted radiation or to allow the detector to operatecooled (or both). In this situation, a window or filter is required that, whileblocking the unwanted radiation, provides minimal attenuation of the signal to bemeasured. Ultrathin windows of SiN foils supported by a fine Si grid, successfullydemonstrated in previous ITI-A and ITI-B activites, provide a strong, hightransmissionbase on which to deposit custom layers for application in X-ray, UVand IR wavebands. This activity aims to produce and characterise a set of filterstargeted at agreed applications and in doing so demonstrate both a high-TRLprocess and the commercial availability of this important technology. The activitywill investigate specific requirements of filters for space applications. Based on thisinvestigation a target set of filters will be defined and applicable coatings designed.The target set of filters will be manufactured and characterised (both optically andenvironmentally). In addition, windows (filters under differential pressure) willalso be investigated for more extreme environments.Deliverables:Engineering ModelCurrent TRL: 4 Target TRL: 5Duration(months)18Applicable THAG Roadmap:N/APage 83/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Use3.1.18 TD 19- PropulsionCore /Specific AreasCORETechnologyDomain19 PropulsionRef. Number:G617-099MPBudget(k€):1000Title:CUSP ION ENGINEObjectives:Description:The use of electric propulsion (EP) for orbit raising manoeuvres from GTO to GEOwill allow to reduce huge amounts of propellant in telecommunication spacecraftand Galileo Evolution satellites. For example the Boing platforms will reuire only375 kg of Xenon to perform this manoeuvre instead of the 1700 kg of Hydrazine.The use of EP will nevertheless increase the amount of time of such manoeuvre.The Boeing platform will employ several months to rise the orbit from GTO toGEO. Therefore it is very important to reduce the power to thrust ratio of EPsystems. The current ion engine requires 30 W/mN, the cusp engine will allow toreduce this figure to around 25 W/mN. This figure will allow to reduce the transfertime in some months.The same argument is required for Galileo Evolutionsatellites.This activity should be used to design, manufacture and test a cusp ion engine inspace conditions.Deliverables:BreadboardCurrent TRL: 2 Target TRL: 4Duration(months)30Applicable THAG Roadmap: Electric Propulsion Technologies (2009)Page 84/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain19 PropulsionRef. Number:G617-100MPBudget(k€):300Title:Objectives:Description:Improvement of the lifetime of Electric Propulsion Thrusters usingdifferent propellant by reducing sputtering effects on materialsActual Hall Effect Thrusters (HET)proposed for telecommunication, science andGalileo Evolution missions are running with Xenon gas due to its high molecularweight. Because of cost and difficulty of production, this gas tends to be replaced byother mixture. Many labs and companies are working on the use of Argon, Neon,Helium, liquid metals or Fullerene C60; However, the impact on thrust, specificimpulse and other performances is still under research. Sputtering resistance of theceramic chamber is an important parameter which has to be considered,bombarding the ceramic target with different type of ions generated by theionisation of these alternative gases.The activity proposes the assessment of the effect on ion sputtering from thevarious gas combinations Xe, Ar, Kr, on the electric propulsion criticalcomponents. It is planned to use a representative sputtering facility able toreproduce energy dose, angle and impact velocity of electric propulsion plasmaions. Targeting this variety of ions over the ceramic walls of Ion thrusters it will beevaluate its erosion resistance. This parameter is easily transferable to the life timeof thrusters. Complementary to test modelling of plasma wall interaction withvarious sputtering energy will be perform.Deliverables:Study ReportCurrent TRL: 3 Target TRL: 4Duration(months)18Applicable THAG Roadmap: Electric Propulsion Technologies (2009)Page 85/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Use3.1.19 TD 20- Structures & PyrotechnicsCore /Specific AreasCORETechnologyDomain20 Structures & PyrotechnicsRef. Number:G617-101MSBudget(k€):300Title:Objectives:Verification of Composite Laminates under Cryogenic Thermo-Mechanical LoadingObjectives are to answer to the following questions:- Are the currently used failure criteria that are available in most commercial FEcodes appropriate for the thermo-mechanical loading conditions induced bycryogenic environments?- Are the current common practices to determine material allowable values withUD laminate samples appropriate for the strength verification for thermomechanicalloading in combination with the commonly used failure criteria?- If above questions are answered negatively: How can the the strength verificationfor laminate structures under severe cryogenic thermo-mechanical loading beimproved?Description:Proposed activities:- Assess and identify the limitations of the commonly used approach for strengthverification of composite laminates under cryogenic thermo-mechanicalenvironment (including modelling, failure criteria with supporting test methods todetermine allowable values)- Assess relevance of stacking sequences of plies in the laminate for resistanceagainst cryogenic thermo-mechanical loading.- Propose and develop alternatives for currently applied strength verificationmethods. These alternative methods can be based on alternative modellingapproaches, alternative failure criteria and alternative methods to determineallowable material values using revised sample test methods.- Verify the alternative strength verification methods for laminates under cryogenicthermo-mechanical loading with tests on laminates with various lay-ups subjectedto cryogenic environment.- Prepare guidelines for:1. The strength verification of composite laminates under cryogenic thermomechanicalloading in combination with the guidelines for obtaining the requiredmaterial properties. Preferably these guidelines shall aim on using existingfunctionality of commercial finite element codes. If needed proposals shall be madeto extend of these FE codes.2. Design of laminates subjected to severe cryogenic thermo-mechanical loading.Deliverables:Other: Guidelines for the strength verificCurrent TRL: 3 Target TRL: 5Applicable THAG Roadmap: Composite Materials (2005)Duration(months)18Page 86/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain20 Structures & PyrotechnicsRef. Number:G617-104MSBudget(k€):450Title:Objectives:Development of modular multifunctional structure panel prototypeThe activity aims at the development of a structural panel prototype withintegrated multifunctional structure capabilities. The purpose of this prototypeshall be to demonstrate the applicability of MFS technology to typical and existingspacecraft structures, and to reach a TRL 6 level, i.e. system prototypedemonstration in a relevant environment (ground or flight).Description:The activity shall be performed with the following steps:1) Identification of a relevant existing structural panel (expected to correspond toTRL 9 spacecraft) with various subsystem functionalities attached, e.g. thermalcontrol, AOCS and OBDH units, etc.2) Redesign of the panel and the attached functionalities as multifunctionalstructure panel where the non-structural functionalities are integrated into thepanel.3) Testing of the MFS panel under relevant environmental conditions (e.g.mechanical, thermal, radiation) in order to verify the robustness of the MFStechnology under those conditions.The structural panel with the integrated MFS technology shall be designed suchthat it can be easily integrated (with only minor design changes) as flight modelinto a spacecraft or replacing the original existing panel where it was derived from.The development plan shall include the following activities (in chronologicalorder):identification of potential user needs, requirement specification, conceptual andpreliminary design followed by a PDR, detailed design followed by a CDR,hardware procurement and manufacturing of the panel, performance verificationtests.Deliverables:PrototypeCurrent TRL: 5 Target TRL: 6Duration(months)24Applicable THAG Roadmap:N/APage 87/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain20 Structures & PyrotechnicsRef. Number:G617-106MSBudget(k€):500Title:Demonstration of Thermoplastic CompositesObjectives:Description:The objective is to replace current technology in metallic or thermoset CFRP withthermoplastic CFRP components.Because of the increased performance compared to thermoset composites, thethermoplastic composites has the potential to extend the application range forcomposites, replacing metallic and/or thermoset composite components for massoptimisation and increased performance.By developing a direct replacement for an existing and qualified part, a significantTRL push can be achieved and could enable a flight application for thethermoplastic composite technology.The following activities should be accomplished:State of the art review and establishment of application range.Selection of demonstration application for replacement of existingtechnologies. The application to be selected shall be a qualifiedpart/subcomponent on an existing, qualified, space productDesign and materials trade-off, including fibre and resin system, andpreliminary design.Technology development test campaign and detailed design and analysis.Demonstrator manufacturing, test and test evaluation. The evaluation shallalso asses the qualification status for the developed technology for apotential direct replacement of the qualified part/subcomponent andidentify remaining qualification efforts in the form of a development plan.Deliverables:BreadboardCurrent TRL: 3 Target TRL: 5Applicable THAG Roadmap: Composite Materials (2005)Duration(months)24Page 88/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain20 Structures & PyrotechnicsRef. Number:G617-107MSBudget(k€):600Title:Objectives:Description:MATS: Multilayer Adaptive Thin Shell Reflectors for Future SpaceTelescopesDemonstrate the feasibility to control the shape of a lightweight mirror consistingof a multilayer adaptive thin shell. This technology can be envisaged forreconfigurable and large deployable telescopes and lightweight adaptive opticsinstruments for operating in the visible and near-infrared.Thin polymeric shells with active shape correction capabilities have the potentialfor enabling large and reconfigurable optical apertures and adaptive opticsinstruments while offering unrivalled advantages in terms of mass, compactnessand foldability. Such telescopes can be envisaged for high resolution imaging forAstronomy and Earth Observation from GEO.Auto-actuation of optically coated polymeric shells has been recently achieved inthe US, paving the way to their complex shape adjustment with optical quality. InEurope, the matured technology of piezoceramic-based deformable mirrors forterrestrial astronomy and the polymer industry supplying flexible electronics andconsumer goods form the building blocks for attaining that goal.The proposed GSTP aims at demonstrating the shape-control with optical accuracyof a multi-layer flexible thin-shell mirror. The project is intended in two phases:I - A first phase for demonstrating the feasibility for the consortium in developinga demonstrator of an adaptive thin shell mirror:(1) Analyzing and optimizing the multilayer thin-shell structure for maximumcontrollability of surface figure error. It includes the optimization of the active layerorthotropic properties and the elastic properties (E and ) of the passive core (usingpossibly auxetic materials with ; < 0).(2) Selecting smart materials and manufacturing coupons to be tested for actuationand optical capabilities.(3) Testing the coupons.(4) Investigating the means for integrated shape sensing, based on the activepolymer thin layers.II - A second phase for designing the demonstrator, constructing and testing it anddeveloping a software for predicting instability of active thin shells:(5) Designing, constructing and testing a small size demonstrator of a thin shellmirror with multiple actuators and sensors.(6) Developing a software for predicting thin shell instability under coupledPage 89/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Usethermal and piezoelectric loading.Deliverables:Other: Breadboard and Study ReportsCurrent TRL: 3 Target TRL: 4Duration(months)30Applicable THAG Roadmap:N/APage 90/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain20 Structures & PyrotechnicsRef. Number:G617-108MSBudget(k€):500Title:Objectives:Description:Improved design and verification of cryocoolers subjected to very highnumber of fatigue load cycles ('gigacycles')To improve design, verification and acceptance approach for hardware subjected tovery high number of fatigue load cycles.Fatigue life verification methods for spaceflight hardware, as e.g. specified instandards for structures, mechanisms and fracture control, and implemented inESACRACK/ESAFATIG software module, is primarily applicable for relativelysmall to medium number of fatigue cycles (typically below 1E6 significant cycles).Nowadays, mission critical cryocoolers (e.g. MTG) are under development that mayexperience more than 1E10 (e.g. 6.5 years at 50Hz) significant fatigue cycles duringtheir lifetime, i.e. may experience very high cycle fatigue (VHCF) or 'gigacycle'fatigue. In literature it is indicated that a true fatigue limit may not exist at veryhigh numbers of cycles as is sometimes assumed.The development, verification and qualification is complicated by the fact thatdevelopment and qualification testing have potentially very long duration (e.g.factor 4 wrt lifetime, in nominal condition, (e.g. 1E11 cycles)), and may have to beperformed in parallel (to a certain extent) with associated development risks.A critical appraisal and further development of design, verification, qualificationand acceptance methods/standards for these structural elements shall beperformed and implemented on a demonstrator programme, addressing thefollowing:* Design, verification and qualification guidelines, addressing risks of overtestingand potentially high scatter in achieved life in the gigacycle regime;* Accelerated testing methods, e.g.:- representative specimens (development models), cycled with margin on load to alimited number of cycles;- basic specimens, cycled with margin on cycles at representative stress levels(20kHz may be achievable, with limitations);- number of test articles recommended.* To assess potentially significant variables affecting fatigue life at high number ofcycles: e.g. material factors, processing defects and variations, size effects, surfacecondition, material combinations, environmental effects (incl. temperature!),fretting, residual stress, ...;* Availability of suitable material data for design in e.g. literature, and selection ofthe most suitable material and development test methods (incl. accelerated testmethods) to generate design data;* Recommendations for acceptance tests and inspections to ensure that criticalflight hardware elements are 'within family' of the qualification hardware;* To demonstrate implementation on a representative demonstrator programme.NOTE 1: The main focus of this activity is foreseen on metallic materials, but maybe extendable to other materials: e.g. ceramic materials as may e.g be encounteredin ball bearings.Page 91/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseNOTE 2 (info):- accelerated testing of 1E11 cycles will take around 3 years at 1kHz, or 4 months at10kHz;- testing to 1E7 cycles at 50Hz will take around 55 hours (2-3 days), testing to 1E8cycles will take around 25 days.NOTE 3: The activity assumes that fracture control requirements will probably notrequire (by design) verification of crack growth due to intial flaws of the itemssubjected to gigacycle fatigue. Otherwise the verification may become significantlymore complicated.Deliverables:Other: whole demonstrator + reportsCurrent TRL: 3 Target TRL: 5Duration(months)24Applicable THAG Roadmap: Cryogenics and Focal Plane Cooling (2007)Page 92/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Use3.1.20 TD 22- ThermalCore /Specific AreasCORETechnologyDomain21 ThermalRef. Number:G617-110MTBudget(k€):300Title:Objectives:Description:Low Profile, Low Thermal Conductivity and Highly Stable Stand-OffsThe objective is to develop thermally insulating stand-off for generic applicationwithout compromising on the height as well as on the mechanical stability.Thermal insulation washers are used throughout a spacecraft to thermally isolatecomponents from the mechanical structure. The standard washers have some issueregarding mechanical stability over a large temperature range which can affect thealignment of the equipment or payload. In addition, the standard washer may notprovide the required thermal decoupling. Carbon fibber and Glass fibber struts areused to thermally isolate components and payload. However, they are expensiveand require significant height between the payload and the structure to beaccommodated.. A Generic low profile stand-off with excellent mechanical stabilitywould be alternative to the existing technologies. It will be possible to use the lowprofile stand-off within a typical bolted interface used for equipment withoutcompromising significantly on mass, height and cost. The stand-off will be designto support the mechanical loads of the payload or equipment and would have astandard bolted interface design for M4, M5 and M6 bolts.Deliverables:PrototypeCurrent TRL: 3 Target TRL: 5Duration(months)18Applicable THAG Roadmap:N/APage 93/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain21 ThermalRef. Number:G617-111MTBudget(k€):150Title:Objectives:Description:Enhancement of Loop Heat Pipe (LHP) Modelling ToolTo develop further the LHP module in terms of performance, accuracy andflexibilityTo create a database of tuned LHP module & plugins& representing existingcommercial LHPsThe current Loop Heat Pipe (LHP) module distributed by Astrium (F) isincreasingly needed to support thermal control design and modelling activities forvarious missions such as Aeolus, MTG and ExoMars. It is fully operational but onlyfor a limited number of LHP architectures and analytical scenarios and they do notcover current needs. The proposed activity aims to further develop and extend thismodule the following ways:- Tuning of the module to improve performance and steady state convergence- Generalisation of the supported LHP architectures to support, for example,bypass configurations (heat switches)- Characterisation of existing LHP designs so that manufactures can provide prevalidatedmodels of the H/W for integration at system level.Deliverables:SoftwareCurrent TRL: 5 Target TRL: 6Duration(months)12Applicable THAG Roadmap: Two-Phase Heat Transport Systems (2009)Page 94/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain21 ThermalRef. Number:G617-112MTBudget(k€):300Title:Objectives:Description:Bi-Metallic Junctions for Loop Heat Pipes and Heat PipesDevelop a process to manufacture Bi-Metallic junctions between Aluminium andStainless steel to be used in Ammonia filled Heat Pipes and Loop Heat-Pipes.Perform testing to verify the mechanical integrity as well as to perform life testingin order to verify that non-condensable gases are not generated both in an LHP andHPs.Loop heat pipes are generally made from stainless steel mainly for mass issue sincewall thicknesses of the piping can be less compared to aluminium. Also, thetendency is to use the same material throughout the LHP in order to reduce therisk of creating non-condensable gases due to potential differences between metals.However, if the condenser section was made with Aluminium, the heat transfer tothe radiator will be improved compared to the conventional stainless steel. As forthe application in Heat pipes, diode heat pipes are generally made from stainlesssteel in order to reduce the heat leaks when the heat pipe is off. Stainless steel doesnot provide a high performance on the evaporator and condenser sections due tothe lower thermal conductivity. Hence a bi-Metal junction would provide flexibilityin optimising sections of heat pipe or LHP by using materials with the desiredproperties. Bi-metallic junctions are used by Russian and American companies.However, in Europe they are not used since the issue of generating noncondensablegases is unknown.Deliverables:PrototypeCurrent TRL: 3 Target TRL: 5Duration(months)12Applicable THAG Roadmap:N/APage 95/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Use3.1.21 TD 22- Environmental Control Life Support (ECLS) and In-SituResource Utilisation (ISRU)Core /Specific AreasTechnologyDomainCORE22 Environmental Control Life Support (ECLS) and In-Situ Resource Utilisation (ISRU)Ref. Number:G617-115MMBudget(k€):350Title:Objectives:Description:Study of countermeasures against microbial contamination ofspacescraft and payloadsThe objective is to define countermeasures against all microbial contamination in aclosed environment, either on flight hardware, clean rooms (AIV/T), or in amanned space vehicle during operation.Exploration missions as well as manned space missions require a high degree ofbiological cleanliness. This degree of cleanliness can only be reached withappropriate countermeasures (sterilisation and disinfection).A systematic and scientifically-based approach is required to fulfill the needs of acorrect assessment of the efficiency of the microbioal contaminationcountermeasures. The result shall be the identification of an adequate controlprogramme and countermeasures, and validation of these strategies in groundfacilities. The milestones in can be defined as:- Correct translation of microbial contamination understanding into a monitoringstrategy with optimized sampling frequency and determination of preferredsampling locations.- Successful activation and implementation of countermeasures when the thresholdlevels of microorganism are exceeded.Deliverables:Study ReportCurrent TRL: 2 Target TRL: 4Duration(months)18Applicable THAG Roadmap:N/APage 96/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Use3.1.22 TD 23- EEE Components and qualityCore /Specific AreasCORETechnologyDomain23 EEE Components and qualityRef. Number:G617-116QTBudget(k€):700Title:Objectives:Description:Prototyping and characterization of 600V SiC MOSFETDevelopment, prototyping and characterization of medium voltage SiC MOSFETfor generic power switching function in space power distribution and controlfunction and motor driverThe study will be focused on the developing of SiC Power MOSFET medium voltageand medium power with the main goal to characterize the performances of thedevices in terms of switching capability, stability of the technology and maincharacterization of static and dynamic parameters as a function of temperatures aswell as to characterize the technology in radiation environment in order to evaluatetheir suitability for future application in space missions.The study will have the goal of prototyping devices with stable well characterizedparameters that could be appealing w.r.t. the same class Si MOSFET available onthe market. The prototypes should be packaged in a suitable package that alloweasy and safe handling and that can allow the full characterization in temperatureof the devices.The main features of SiC base material (high energy gap, high electric fieldbreakdown in combination with reasonably high electron mobility and highthermal conductivity) led to the following expected and in some cases alreadyproven capabilities for power application: low on-state voltage, low recoverycharge, fast turn-on and turn-off, high blocking voltage, higher reliable operatingjunction temperature, high power density.These characteristic together with the important point that SiC can be easilythermally oxidized to form high quality SiO2 are promising for generic powerswitching application. At the present stage, the SiC MOSFET devices are still in aR&D level or in US in a early industrialization phase, but there is an increasingdiffuse interest in realizing high performance SiC MOSFET that shows a betterswitching capability of their Si based equivalent devices showing lower Ronresistance with a comparable Qc in a wider temperature range.The study will be organized with the following work structure:- Task 1: critical analysis of the technical requirements, definitions of goal valuesfor the mainkey parameters- Task 2: trade-off analysis of the main design structure and topology with relevantsimulation- Task 3: manufacturing processes definition and main trade-off analysis, first issueof draftPID, first run in foundry- Task 4: Electrical characterization of first run in foundry and analysis of theresults- Task 5: Review of the manufacturing processes implementing any correctiveactions comePage 97/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Usefrom the previous phase, second issue of PID and second run in foundry- Task 6: Definition of the electrical characterization, stability assessment andradiation testprogram. For the overall test program the sample size should be at least 30 devices.- Task 7: critical analysis of test results. Identification of future activities needed toindustrialize the prototypes, analysis of manufacturing cost and forecast of yield.Deliverables:Other: Full report and packaged samplesCurrent TRL: 2 Target TRL: 4Duration(months)24Applicable THAG Roadmap: Power Management and Distribution (2008)Page 98/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain23 EEE Components and qualityRef. Number:G617-118QTBudget(k€):300Title:Objectives:Evaluation of high density optical links for high speed transmission.The main objective of the activity is to perform a full evaluation of high densityoptical links for high transmission rate (40 Gb). The optical links will include 12channels MM MPO connectors with optimized termination process.Two parallel GSTP activities have been initiated in early 2011 to get ESA approvalof their optical link assembly capability. The first phase of the activity which is nowcompleted was aimed at confirming the need of the end users in term opticalassembly and making a survey of the components available in the market(connectors, cables, fibres). A list of different possible assembly combinations wasselected and proposed for tested during the second Phase. The second phase thatwill be completed end of 2012 consists in the assembly of the different selectedtechnical solutions followed by on-ground preliminary validation testing. Fromthese activities, according to end-users and preliminary testing results, it has beenconcluded that multi fibre solution for MM transmission is one of the very suitablesolution for coming need for capacity and number of systems will that require highfibre numbers.In the frame of Proba V, a Technology Demonstrator was proposed to test one theselected multi-point assembly with highest interest expressed by European spaceend-users. This optical payload has been assembled in Proba-V platform in October2012 for a launch expected in March 2013 with Vega. This IOD mission is toconfirm that assemblies is suitable in regards of transmission loss and also thatassemblies can stand all environmental challenges as they occur in a typical launchand during operation. The focus is mainly to show that attenuation of assembly willstay unchanged under these conditions.As a next step forward, the goal of this proposed activity will be to continue withoptimizing termination process, in particular polishing process. Normal IECconnectors is specified with 1-3 um protrusion. Initial investigations shows thatthis high protrusion could be difficult for extreme vibration load. To reduce tensionon fibers by less protrusion in combination with angled connectors these problemswill be reduced. Since this kind of polishing is not specified by any standards so far,more investigations should be carried out. This could be confirmed during thisactivity with higher transmission speed than used at current program. In additionto confirming that insertion loss is good, also return loss will be checked. Newtransmission system including OTDR functionality in system could be very usefulto find in which part of the assembly additional reflection or insertion loss occur.Description:The activity will include the realization of the MM MPO assemblies based on theoutput of the current GSTP activities, integrated in a high transmission speed testmodule (40 Gb). The termination process from the current GSTP activities shall beoptimized to survive harsher environment than the initial testing. An extensiveevaluation will be carried out on these assemblies including optical testing duringshock and vibration.Page 99/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseDeliverables:Engineering ModelCurrent TRL: 5 Target TRL: 7Duration(months)24Applicable THAG Roadmap:N/APage 100/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain23 EEE Components and qualityRef. Number:G617-119QTBudget(k€):300Title:Objectives:Radiation testing of non-volatile memories for space applicationsNon-volatile memories are of strategic importance for advanced, innovative andhigh performance digital data processing and data storage in spacecraft systems.They are used in literally all satellites and spacecraft's, either embedded in complexICs or as stand-alone devices. For example, non-volatile memories are typicallyused as program memories for microprocessors, microcontrollers, and FPGAs,driving the satellite on-board computers and other critical functions. Anotherexample is data storage in mass-memory systems, for which non-volatile memories(in particular NAND-Flash) are replacing more the traditional DRAMs when largecapacity and low-power are required. Recent examples of NAND-Flash used formass-memory are Spot6 (launched in September 2006) and Sentinel-2 (to belaunched in 2014); NAND-Flash were/are also considered for other missions likeEarthCare, Gaïa, EDRS, and SmallGEO.Terrestrial applications drive a rapid evolution of technologies and device products.This demands a correspondingly dynamic and efficient radiation assessment ofthese memories for space applications. In this activity, the main types ofcommercially available non-volatile memories will be studied and radiationassessed for a potential space utilization. The following actions will be undertaken:1) quantify the risk and increase the confidence in NAND Flash memories forspace, by analyzing total dose effects with lot-to-lot and intra-lot variations instatistically relevant sample populations;2) investigate functional interrupts and dynamic errors in the new high-speeddouble data rate interface implemented in modern NAND Flash devices, ascompared to the standard asynchronous interface;3) evaluate the impact of technology scaling on single event effects in floating gatecells, in terms of single and multiple bit upsets;4) investigate synergistic effects between total dose, single events, and intrinsicwear-out mechanisms in NAND and NOR Flash device types5) investigate root causes of (possible) destructive events induced by heavy ions inNAND devices6) explore radiation effects in alternative non-volatile storage technologies, such asphase change memories (PCM) and other maturing device concepts that willbecome available during the course of this projectDescription:This activity aims at improving our knowledge of radiation effects in non-volatilememories and validate their utilization for space applications.The increased variability (lot-to-lot, sample-to sample, cell-to-cell etc.) of radiationsensitivity is an established attribute and consequence of the continuous decreasein feature size of modern electronic devices. To maximize memory capacity percomponent NAND Flash devices are among the first to use new processtechnologies providing higher integration density and scaling. In order to optimizetesting and to permit probabilistic methods to determine parameter spreads,relevant statistics have to be produced to describe component behavior under TotalPage 101/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseIonising Dose exposure. The data collected will be analyzed, by randomly picking asmall subset of the tested devices and evaluating the difference with the full dataset, taking advantage of proper statistical tools to evaluate the device variability.To exploit the increasing capacity of NAND Flash memories, high speed I/Ointerface circuitry is implemented. Double Data Rate (DDR) interfaces in the mostrecent device types are competing with the conventional asynchronous I/O design.This DDR interface is similar to that used in SDRAM and may bring about anincreased SEFI and dynamic error sensitivity in NAND Flash. Single Event Effectstesting of this new type of interface is necessary to establish the factual behavior ina space radiation environment and to determine the appropriate applicationconditions.As the feature size is scaled, the amount of charge stored in floating gates decreasesaccordingly. It is possible that the next device generations may become sensitive todirect ionization by protons, which would largely affect error rates in space. Thisrequires an evaluation of single and multiple-bit upset rates.Even at ground level, ensuring the reliability of NAND Flash memories is arecognized concern and the characterization is becoming more and more complex.Although recent results on current component types have ruled out synergisticeffects between intrinsic wear-out and environmental radiation effects, thesecannot be excluded in the next generations of devices. This is based on theexperience that, interactions between total dose and single events have beenobserved in the past. Therefore it is foreseen to include the evaluation of possiblesynergistic effects in advanced NAND and NOR Flash memories.Destructive events on NAND Flash memories tested under radiation have beenreported but there is no conclusive proof that radiation is the root cause of thesefailures. Clarification is needed.Manufacturers are increasing development efforts on alternative non-volatilestorage technologies, such as phase change memories (PCM), starting from the 45-nm node. The PCM technology concept bears the potential of being very radiationhard and is therefore of potentially very high interest for space applications. Earlyradiation characterization of these devices is therefore highly advisable.The following documents will be delivered:- Report on statistical variations of total dose failures in NAND Flash memories: abenchmark NAND device (e.g. an SLC device with feature size below 32 nm) will beselected for this study. Many (e.g. 50) nominally identical samples will be tested inthe same conditions under gamma irradiation.- Report on functional interrupts and dynamic errors in NAND Flash memorieswith DDR interface: a benchmark NAND device with DDR interface will be testedat speed under heavy ion irradiation. SEFIs and dynamic errors will be assessed.- Report on scaling of floating gate errors: NAND and NOR memories withdifferent feature size will be exposed to heavy ions in off conditions. Errors infloating gate cells will be assessed.- Report on alternative large size non-volatile memories. Available phase changememories (PCM) with feature size equal or below 45 nm will be tested undergamma and heavy ion sources. Total dose tolerance and single event effects will beevaluated.Page 102/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseDeliverables:Study ReportCurrent TRL: 4 Target TRL: 6Duration(months)36Applicable THAG Roadmap: Data Systems and On-Board Computers (2011)Page 103/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain23 EEE Components and qualityRef. Number:G617-122QTBudget(k€):500Title:Miniature Solderless Interposer Type ConnectorObjectives:To develop, characterize and to carry out the ESCC evaluation of next generationminiature solderless interposer connector for space applicationDescription:Interposer Connectors can be used for board to board interconnection or to mountcomponent on PCB without soldering. By allowing high number of contacts, thoseproducts represent a pertinent way to decrease size of equipment by saving spaceon printed circuit board. One major advantage is to facilitate the mounting anddismounting process by avoiding issues associated with traditional solderingtechniques.ESCC qualified Solderless interposer connectors already exist for board stacking.However these products are hardly compatible with small devices (flat package orLGA package) and may be considered quite thick for some applications where sizeis the driving factor.The development of miniature solderless interposer connector shall take intoaccount the following objectives :o high data rate capability (10Gbps)o fine pitch (0.5mm to 1mm)o small dimension (max 2mm thick)o heat managemento compatible with LGA type packagesA technology survey and a trade-off shall be carried out in order to determine thetechniques and materials able to meet the electrical and physical requirements aswell as the constraints of space applications.Selected solution and application domain will be described through detailspecification, Process Identification Document.Characterization of the interposer connector shall be performed and an evaluationtest plan proposed in order to determine physical margin of the product and theassociated failure modes. Based on successful evaluation test results, the productwill be presented for ESCC Preferred Part List introduction.In order to ease the procurement of these products, by decreasing paper work,delivery time and overall cost, the last step toward ESCC qualification shall beperformed with particular attention being paid on mounting capability andrecommendation for users. This will allow to introduce the products in the ESCCQualified Part List.Deliverables:- Technological survey- Definition of technological solutions and associated application domain- Process Identification Document, Procurement specification, FMEA, FTA- Evaluation Test report- Utilization recommendation and guidelines- Samples / Test VehiclesPage 104/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseDeliverables:Study ReportCurrent TRL: 2 Target TRL: 6Duration(months)36Applicable THAG Roadmap:N/APage 105/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain23 EEE Components and qualityRef. Number:G617-123QTBudget(k€):2000Title:Objectives:Improved thermal management capability of power semiconductorsImprovement of AgD metal matrix composite material manufacturing capability toreduce production costsDescription:The ESA-EC FP7 coordinated project AGAPAC (Advanced GaN Packaging) wascompleted in 2012 and has been highly successful. The aim of AGAPAC was todemonstrate advanced packaging concepts using silver-diamond (AgD) metalmatrix composites with improved thermal dissipation capability that can allow thefull performance advantages of GaN technology to be realized. The AgD materialhas been manufactured in Europe and used to design and fabricate a 182W L-bandSSPA using UMS GaN HEMTs. The AgD based package offers a 5 foldimprovement in thermal conductivity compared to more traditional materials (e.g.CuW, CuMo) and has allowed a 50% reduction in transistor channel temperatureto be achieved, giving better electrical performance and improved reliability. Theseresults show that a major improvement in the thermal capability of microwave andpower transistor packages can be realised with the AgD approach.Further work is now required to improve the manufacturing capabilities of the AgDmaterial and to consolidate the European supply chain. To-date the material hasbeen fabricated using an experimental manufacturing line. However, for thismaterial to be able to be considered for commercial manufacture a pilot productionline needs to be established in order to benefit from economies of scale and reducemanufacturing costs. In the AGAPAC project both hot pressing and liquid basedinfiltration manufacturing techniques were investigated. The infiltration approachwas found to give the most stable material performance and hence this approachshall be adopted for larger scale manufacturing.In Phase 1 (1000KEuro) of the project a new production orientated furnace will beprocured and commissioned for this purpose. At present the AgD material costsapproximately x10 the price of standard CuW or CuMo material. The outcome ofthis Phase 1 work will be to reduce the price such that the AgD material can bemanufactured with approximately x2 the price of CuW. Considering that AgD offersa thermal conductivity of 700-800W/mK compared to 180W/mK offered by CuW,the price-performance benefit will allow many new application markets to beconsidered and provide a disruptive route for implementing GaN (and other highpower dissipation) technology on space based platforms.In Phase 2 of the project(1000 KEuro), a range of space product applications shallbe identified and bespoke packages manufactured using a commercial supplier andsubjected to a preliminary ESCC evaluation (e.g. in terms of material robustness,hermeticity, reliability, outgassing etc). The packages shall then be used todemonstrate an application for realization of (i) a high power SSPA and (ii) a highpower DC-DC converter to stimulate space market interest.Page 106/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseDeliverables:BreadboardCurrent TRL: 3 Target TRL: 6Duration(months)24Applicable THAG Roadmap: Critical RF Payload Technologies (2004)Page 107/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain23 EEE Components and qualityRef. Number:G617-124QTBudget(k€):800Title:Development of Standard Interface ComponentsObjectives:The objective of this activity is to develop a set of standard interface componentswhich are commonly used in space applications but which are not readily availablefrom European sources. The targeted component functionality from simple linedrivers, receivers and tranceivers to more complex functionalities. Ultimately, theaim is to establish an alternative for the manufacture of European SpaceComponents Coordination (ESCC) evaluated and qualified integrated circuits (ICs)in Europe with the goal of having standard interface component(s) listed on theEuropean Preferred Parts List (EPPL).Description: Phase 1:As an example, flash based re-programmable FPGAs can be used to implementcontrol logic, covering everything from command processing and loop control, towaveform generation. This can be achieved in a single, given FPGA componentwhich provides a large scale of integration. However, the number of external logiccomponents still required to handle the different voltage domains, to perform thedata bus buffering, together with the buffering of external communication lines canbe of the order of twenty or more per flight unit. As a consequence the availabilityof standard interface components is crucial to space electronics development andtheir availability is sometimes dwarfed by the availability issues surrounding thelarger FPGAs or micro-processors, but it is nevertheless as critical.Task 1 - Technology and Design Trade-Off AnalysisThe objective of Task 1 is to identify and consolidate the standard interfacecomponents which are needed by space users and space agencies. In this regard, atechnological process trade-off analysis and a standard component design trade-offanalysis shall both be performed. In addition, a commercial evaluation addressingtarget market, end user review/commitment, target price and marketing plan of thecomponents to be developed shall be completed. Only following the preliminarydesign review (PDR) of Task 1 shall the authorisation to proceed to Phase 2 begranted. As an input to Task 1 a preliminary list of candidate components for thisactivity is:Equivalent part FunctionHS-26CLV31RH Quad Differential Line DriverHS-26CLV32RH Quad Differential Line ReceiverUT63M143 1553 bus transceiverUT54LVDS 217 LVDS SerializerUT54LVDS 218 LVDS De-serializerUT54LVDS 031LV Low voltage Quad LVDS DriverUT54LVDS 032LV Low voltage Quad ReceiverAt a minimum 2 device types among the above candidate components shall bePage 108/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Useselected for design, manufacture and characterisation in Tasks 2 & 3.Phase 2:Task 2 - Process Preparation and Design ActivitiesFollowing the successful completion of Phase 1, the preparation of the full end-toendfabrication processes shall be completed. The detailed design of the standardcomponents with design reports, detailed design documentation and updateddatasheets shall be completed in accordance with the appropriate ECSS standard.On successful completion of the detailed design review, the layout generation andverification of the standard components shall be inputs to the critical design review(CDR). At this point in the activity a draft detail specification shall be defined.Task 3 - Standard Component Manufacture and Electrical CharacterisationThis task shall only commence following a successful CDR. The objective of thistask shall be to complete the standard component wafer manufacture, conduct thepackage development and manufacture activities and perform the standardcomponent assembly processing according to the process identification document(PID) and design defined in Task 2. All prototype devices shall be fullycharacterised by comparing the electrical performance with the draft detailspecification defined in Task 2.Phase 3:Task 4: ESCC Evaluation of One Standard interface Component TypeWithin Task 4, a minimum of one standard interface component type shall beESCC evaluated. The Evaluation Test Plan (ETP) shall be defined in accordancewith the ESCC Basic Specification No. 2269000 and shall also include the radiationtests as per Sub-Group 2B. Following the successful completion of Task 4 thecontractor shall be in a position to apply for EPPL1 listing of one standard interfacecomponent type at a minimum. In addition, the contractor shall investigate thepossibility for ESCC qualification of the developed standard componentsdepending on customer demands and shall be prepared to develop new standardcomponents for the space community using the same production flow.Deliverables:Other: ESCC evaluated partsCurrent TRL: 3 Target TRL: 6Duration(months)24Applicable THAG Roadmap: On-Board Payload Data Processing (2011)Page 109/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Use3.1.23 TD 24- Materials and ProcessesCore /Specific AreasCORETechnologyDomain24 Materials and ProcessesRef. Number:G617-125QTBudget(k€):1500Title:Objectives:Description:Friction Stir Welded Low Cost Titanium Elegant BreadboardThe present work is split in two phases with two main objectives:1. The objective of the first phase is to develop, characterize and validate a FSWprocess and tooling system able to weld Ti-15-3-3-3 as well as Ti-6Al-4V Titaniumalloys, starting from sheets up to formed shells.2. In the second phase and provided that the welding parameters and tools areproven to deliver the required quality, repeatability and costs effectiveness, theobjective is to manufacture a Friction Stirred Welded Titanium tank. The achievedimprovements in terms of of costs reduction, industrial manufacturing aspects, andenvironmental friendliness compared with a tank made using conventional weldingtechniques be quantified.FSW is considered to be the most significant development in metal joining indecades. In addition it has demonstrated exceptional environmental friendliness.Ti-6Al4V titanium is the baseline alloy for aerospace rocket propellant tankage formany years. These tanks have been made of machined forged Ti-6Al4V titaniumalloy. The tanks were normally TIG and EB welded and showed substantiallylighter weight than if made of other materials and, furthermore, they show reliableperformances. Despite the manufacturing improvements, the tanks are still one ofthe most costly items in the rocket motor system. High cost is due primarily toexcessive machining labour and discard of high quantity of material lost as chips.The evolution of larger motor systems is demanding still larger tankage whichthreatens to become prohibitively costly if manufactured by traditional methods.The use of the new excellent formable beta titanium Ti-15V-3Cr-3Al-3Sn (Ti-15-3-3-3) alloy in combination with the Friction Stir Welding (FSW) process wouldmake possible to significantly reduce costs also leading to design simplification andreduction of material wasting.The proposed study is split into two phases: the objective of the first phase is todevelop, characterize and validate a FSW process and tooling system able to weldTi-15-3-3-3 as well as Ti-6Al-4V Titanium alloys, starting from sheets up to formedshells. Extensive characterisation will be performed at sample level. The possibilityto scale-up the validated processes will be addressed.In the second phase and provided that the welding parameters and tools are provento deliver the required quality, repeatability and costs effectiveness, the objective isto manufacture two full-size Titanium tank welded using the FSW welding process;one made of Ti-15-3-3-3, the other from Ti-6Al-4V.Both tanks will undergo a full verification and test campaign to prove the suitabilityof the materials and technologies. Their performances will be compared withequivalent titanium tanks welded by conventional techniques including cost,reliability, industrial efficiency and environmental friendliness aspects.Page 110/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseDeliverables:Other: Test plans, test reports, breadboards, EQMCurrent TRL: 4 Target TRL: 6Duration(months)24Applicable THAG Roadmap: Chemical Propulsion - Components (2012)Page 111/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain24 Materials and ProcessesRef. Number:G617-127QTBudget(k€):700Title:Objectives:Evaluation of the potential of the Thin Ply Technology for spaceapplicationsEvaluate the spin-in of carbon-fibre thin ply technology for use in the space domainon structures such as antennas, solar array, structural panelsQuantify the improvements in terms of specific strength and stiffness of thinlaminates wrt existing typical laminate configurationsInvestigate the suitability of the technology for processing and manufacturing withhigh modulus fibres.Assess the manufacturing requirements for use and processing of the thin-plytechnology.Manufacture and evaluate laminate and sandwich level coupons to quantify thesuitability of the technology for space use.Assess machinability for the inclusion of inserts, doublers, feed through holes andother design features.Assess the suitability of the technology for bonding to doubler or other features.Manufacture and test a demonstrator sandwich panel containing a range of theabove design characters to a configuration which could be proposed as analternative for a specific subassembly and demonstrate the improved performance.Description:A number of companies and institutes have been developing carbon fibrecomposite thin ply technologies primarily for use in the high end composite marketassociated with certain marine and automotive sporting activities (formula one,Americas cup rigid sails etc.). Thin ply technologies utilise a process to spread towsof fibres to make ultra thin unidirectrional prepreg tapes that allow a reduction inthe fibre weight from typically 120-150gsm (grammes per square metre) to around30gsm using the M55J 6k fibres. In addition the development of thinner plies thenenables the layup of a more complex multidirectional composite skin compared toconventional CFRP laminates. Processing of these composites as thinner laminatesalso enables a reduction in manufacturing defects such as resin porosity (due toshorter diffusion paths) again with an associated performance improvement. Thereduced areal weight coupled with improved mechanical performances achieved bythe use of thin plies using conventional materials already familiar to the spaceindustry offers an opportunity to develop and utilise a technology whilst retainingthe historical heritage already known from the materials previous use.This project proposes to characterise, manufacture and test the use of thin plytechnologies to assess their compatability with known space materials, evaluatetheir suitability for typical processing (use of inserts, doublers etc). for spaceapplications and determine the performance improvements achieved using thisprocessing technology. System level benefits shall be assessed both in terms ofperformance gains as well as cost impact.Page 112/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseDeliverables:BreadboardCurrent TRL: 2 Target TRL: 5Applicable THAG Roadmap: Composite Materials (2005)Duration(months)30Page 113/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain24 Materials and ProcessesRef. Number:G617-128QTBudget(k€):500Title:Objectives:Description:Evaluation of low temperature processing capabilities of novel thin andflexible ceramic coatingsThe use of ceramic coatings has recently been required driven by the harsh missionenvironment from ESAs inner planetary missions like Bepi Colombo (BC). Oneceramic coating processing development for that mission is requiring the use ofTitanium alloys as substrates as it is a high temperature process requiring severalhundred degrees. This is not a problem for BC but it excludes the possible use ofthe developed coating on lower temperature resistant materials. A possibleadaption of the processing window would enable a much wider use of the currentlyavailable coating. A second point that shall be addressed is to increase theflexibility of the coating by further reducing the thickness by at least a factor of 2without impairing the functional properties such that the coating can be appliedflexible substrates like thin foils.The following tasks shall be carried out.Within task 1, a reduction of processing window (curing temperature) by varyingthe binder matrix and the curing procedure eg. vacuum or room temperaturecuring. The target substrates under study shall be at least be compatible with Alalloys (200C) but should also be evaluated (in terms of temperature as well asadhesion) on CRFP.Within task 2, a reduction of layer thickness of the current technical thermalcontrol coating basis with target layer thickness below 10µm shall be addressed.The flexibility of improved coatings from task 1 shall be assessed on flexiblesubstrates such as foils and thin metallic sheets.Both tasks shall be accompanied by a comprehensive materials and processingevaluation programme and shall include ground as well as space environmentalassessments. In addition an economic and environmental evaluation shall beperformed.Deliverables:Study ReportCurrent TRL: 3 Target TRL: 4Duration(months)24Applicable THAG Roadmap:N/APage 114/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain24 Materials and ProcessesRef. Number:G617-130QTBudget(k€):500Title:Objectives:Description:Evaluation of lighter and more efficient radiation protection forelectronic and sensitive parts.Manufacture and evaluate the multi-layered shielding technology for use in spaceapplications: replacement of currently used boxes (aluminium) for radiationprotection and improvement of protection of currently used boxes by adding thismulti-layer shieldingAssess the machinability of the technology.Assess the suitability of the technology for bonding on typical substrates used forelectronic boxes.Investigate the suitability of the technology for the processes involved inmanufacturing boxes for radiation protection.Investigate the suitability of the technology for the processes involved inintegration (AIT) activities.Manufacture a demonstrator and perform an evaluation test campaign to assessthe effects of the relevant environment (vacuum, thermal cycles, radiation).Radiation shielding mainly depends on particles species and energies: a multilayeredshielding approach could therefore be seen as the most effective shieldingat the lowest mass. In the Jura study [CDF Study Report: CDF-61(A), July 2007 ] itwas seen that a potential gain of 40% to 50% in shielding effectiveness with respectto Aluminum shielding (at equivalent mass) could be achieved with materials likeTantalum, Polyethylene-Tantalum, Polyethylene-Tungsten and Kapton-Tungsten.While the manufacturing is technically easy to realise as there is no real TRLproblem foreseen, the best materials have to be identified and mature enoughmanufacturing processes have to be set so that a solution can easily beimplemented on S/C. Activities will aim at applications for different phases ofsatellite integration:1. replacement of aluminium boxes: identify materials and processes tomanufacture boxes to protect electronics or sensitive hardware, with all theassociated processes (as drilling, bonding...).2. rework activities on electronic boxes already manufactured: for shieldingimprovement at later stage of the project. Activities to obtain a finished productthat is easy to handle during AIT activities, bonding procedures on aluminiumboxes, other fixation processes.Preliminary qualification tests will also have to be performed to evaluate aging ofall the processes.This activity will be divided in 2 phases:1st phase:- Trade-off analysis of the available materials based on definition of key properties.The trade-off shall include manufacturing and reworkability processes, radiationprotection efficiency.- Manufacturing of breadboards with different candidate materials- Preliminary testing of candidate materials (radiation, mechanical, thermal;) tochoose the best candidatePage 115/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Use- Evaluation of candidatesDeliverable: breadboards.2nd phase: from phase 1, selection of 1 or 2 most promising candidatesmanufacture- Manufacturing of demonstrator- Testing and characterisation of the demonstrator: functional, mechanical andthermal characterisation, vibration, shock and EMC tests.Deliverable: Engineering modelDeliverables:Other: breadboard Ph1, Engineering model Ph2Current TRL: 2 Target TRL: 5Duration(months)24Applicable THAG Roadmap:N/APage 116/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain24 Materials and ProcessesRef. Number:G617-131QTBudget(k€):2500Title:Filament winding TISICObjectives:Description:Filament winding of continuous silicon carbide fibre metal matrix compositesTISIC is a titanium alloy reinforced with continuous silicon carbide fibres aimed athigh-end applications e.g. in the aeronautical and petrochemical industries. Theadvantage of ceramic fibre composites is that they can be stronger and stiffer thanthe equivalent carbon structures. For instance the silicon carbide fibres used toreinforce TISIC are 4 times stronger and 5 times stiffer than carbon fibre offeringthe possibility of significant weight savings. The difficulty with ceramic fibres isthat with increased stiffness and strength comes reduced toughness which canmake handling difficult. This proposal is divided into 2 phases.The objective of Phase 1 is to modify the SiC fibre processing route to include atitanium coating step then to use these fibres to filament wind a structure. Thefilament winding equipment (which exists but needs to be modified to deal with thestiffer fibres) and processing and the HIPing parameters to consolidate thestructure need to be mastered. As a demonstration of the possibilities of thematerial a high pressure tank will be built using the current design codes with theaim of producing a tank that is less than half the weight of the equivalent currentdesign.Phase 2 will build on the results of this study whereby the materials and processeswill be validated and verified in accordance with the relevant standards and aEngineering model of a tank will be fabricated. The overall cost of the combinedprogrammes is expected to be 2.5 MEuro.Deliverables:Other: Phase 1 breadboard phase 2 prototypeCurrent TRL: 3 Target TRL: 6Duration(months)42Applicable THAG Roadmap: Chemical Propulsion - Components (2012)Page 117/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasCORETechnologyDomain24 Materials and ProcessesRef. Number:G617-132QTBudget(k€):500Title:Objectives:Description:Electron Beam Welding for Safety Critical Space ApplicationsTo develop and adapt the Electron Beam Welding process for safety criticalapplicationsThe precision welding of metallic joints plays an important role in the productionof components for space applications. In order to meet the demanding levelsrequired, metallic joints must be produced which have the correct dimensionaltolerance, are free from defects and exhibit the correct mechanical and corrosionperformance. In particular, in propulsion systems all valves and pipes have weldswhich must be leak tight and prevent safety hazardous propellants from leaking. Inrecent years, there have been a significant amount of anomalies related to weldingquality issues documented valves, and welding failures have jeopardised SpaceProjects Qualification activities and (in some cases) Missions causing substantialcosts and delays.It is therefore mandatory to develop and qualify welding methods which canconsistently deliver the production of high quality defect free welds. One suchtechnique is that of Electron Beam Welding (EBW) which is currently used in anumber of safety critical applications in manufacturing sectors includingAutomotive, Nuclear and Aerospace. By developing and adapting such a techniquefor safety critical space applications, the costs and delays associated with weldingfailures will be significantly reduced, leading to improved confidence in users.Since the EBW process is performed in a vacuum, shielding gases are notnecessary, making the process particularly desirable for alloys such as Aluminium,Titanium, and Stainless Steels. For some difficult to weld materials such asCopper, and Molybdenum, EBW is the only acceptable welding method available.High welding speeds are possible with a low overall heat input resulting in lowdistortion. Furthermore, since there is the possibility to accurately manipulate theelectron beam, intricate welding can be performed on very thin sheets (100microns) or on small orbital welds, making this an ideal technique for applicationssuch as safety critical flow control valves.Industry is currently qualifying the methodology required to produce high qualityreliable joints for Flow Control Valves. An existing design will be adopted and remanufacturedusing the EBW process, and the results compared to the standarddesign which is currently welded using a Laser Beam welding process.Deliverables:Other: see commentsCurrent TRL: 3 Target TRL: 6Duration(months)24Applicable THAG Roadmap:N/APage 118/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official Use3.2 SAVOIRCore /Specific AreasSAVOIRTechnologyDomain5 Space System ControlRef. Number:G61V-001ECBudget(k€):400Title:Objectives:Description:AES/SAVOIR New models for the AOCS Unit Simulation ModelsLibrary (AOCS UnitSim)To enlarge the AOCS Unit simulation Library with new sensor/actuator models andto tune new representative datafiles for an existing library model (star tracker)The TRP activity "AOCS Unit Simulation Models" (2009-2013) had led to create alibrary of generic simulation models of AOCS units: gyro, star tracker and reactionwheel.These models are high-fidelity functional models coded in Matlab/Simulink andfully compliant with use of code generation tools. All along their design anddevelopment, guidelines were followed to ensure portability of these functionalcores on AOCS validation benches other than functional benches (SW and Avionicsbenches).The preliminary testing of the portability of the gyro and star tracker models hasbeen successfully performed on real time benches by Astrium and TAS.Another important feature of the previous development is that all models weretuned for two differing real units and the tuning was validated against tests andsimulation results of the real hardware units in cooperation with their supplier.The interest and support of the AOCS community (AOCS prime, AOCS hardwaresuppliers and AOCS benches suppliers) in these models has been expressed inseveral conferences and workshops where the study was presented (ESA GNC 2011,ICAT 2012, SESP 2012, ADCSS 2010, ADCSS 2011 and ADCSS 2012).The final version of the TRP models will be distributed in early 2013.Models will be made available to the European community under licenseagreement via ESA central source repository.The proposed activity intends:1- to enlarge this simulation models library with new sensor/actuator models(magnetometer, magnetotorquer, sun sensor) with a program of work similar toprevious development:a. simulation model specificied by an AOCS prinme who is an experienced user ofthe unit, in line with the TRP study guidelines ensuring genericity and portability,b. simulation model developed and coded by a company with simulatordevelopment and AOCS skillsc. tuning and validation of the complete simulation models against real hardwaretest and simulation results in collaboration with the unit supplier2- to complement the set of validated tuning for the existing models developed inthe TRP study (star tracker model tuned for a COTs star tracker unit) and for thenewly developed models.Page 119/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseDeliverables:PrototypeCurrent TRL: 3 Target TRL: 6Duration(months)18Applicable THAG Roadmap: AOCS Sensors and Actuators (2009)Page 120/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseCore /Specific AreasSAVOIRTechnologyDomain1 On-board Data SystemsRef. Number:G61V-005EDBudget(k€):800Title:AES/SAVOIR Electronic Data sheet definitionObjectives:To establish an electronic standard for interface definition, consistent with all knowavionics units (sensors actuators and subsystems) and interfaces (standard I/O orspecific, various protocol). This will include a Dictionary of Terms, the functionalspecification of the exchange, and the associated model.To use this standard as the means to capture ICD information in machine readableformat such that it can be directly imported in to spacecraft databasesDescription:An integral part of the spacecraft development process is the population of thespacecraft database with information related to the interfaces of individual units.This is a significant task involving the manual entry of enormous amounts of data(150,000 items for a typical spacecraft). The content of the information, which isprovided by unit suppliers to the Primes, is not standardised and subject toinconsistencies, immaturity and incompleteness, and this is clearly prejudicial tosystem development.A way forward has been identified within the SAVOIR initiative in the form ofelectronic data sheets (EDS). If the paper ICD traditionally provided by unitsuppliers is supplemented, and ultimately replaced, by a standard machinereadable input the whole process of database input can be automated. In additionpre-checks can be made on the completeness and accuracy of the providedinformation.Such an approach has been confirmed by Primes as providing the possibility forconsiderable streamlining of the integration process.A TRP activity has already been initiated to support the preparation of a standardformat to capture AOCS related interface information. This is being coordinatedwithin SAVOIR and with the international standards organisation CCSDS SOISworking group. It covers the both an XML based schema and a so called dictionaryof terms (DOT) used to unambiguously describe the terminology used in theinterface specification.As a compliment to the EDS study, the XML Schema and DOT will be extended tocover the complete needs of Primes by agreeing with unit suppliers an electronicstandard for interface definition which addresses the full ICD requirements -electrical, communication, calibration, etc. Thus, it would cover all data needed tobe compiled in Spacecraft Data Base, including software aspects compatible withthe SAVOIR-FAIRE software architecture.The activity is proposed to be managed in 3 phases: a requirements capture phaseresulting in an update to the schema and DOT delivered by the TRP activity. Animplementation phase prototyping a wide selection of ICDs from unit suppliers.Finally, a consolidation phase where the schema and DOT are updated andsubmitted as a draft ECSS standard.Page 121/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1

ESA UNCLASSIFIED – For Official UseDeliverables:PrototypeCurrent TRL: 0 Target TRL: 0Duration(months)14Applicable THAG Roadmap: Data Systems and On-Board Computers (2011)Page 122/122GSTP-6 E1 SD7 Compendium - 2013Date 26-02-2013 Issue 1 Rev 1