EUROPEAN SPACE AGENCY INDUSTRIAL POLICY COMMITTEE GENERAL SUPPORT TECHNOLOGY PROGRAMME GSTP-5 ELEMENT-2 INITIAL WORK PLAN

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1 Att.: Annexes Paris, 9 April 2009 (English only) EUROPEAN SPACE AGENCY INDUSTRIAL POLICY COMMITTEE GENERAL SUPPORT TECHNOLOGY PROGRAMME GSTP-5 ELEMENT-2 INITIAL WORK PLAN SUMMARY This document presents the GSTP-5 Element 2 draft Initial Work Plan consisting of a list of key GSTP-5 items that are proposed for subscription and initiation in 2009 as part of the proposal for the 5 th Period of GSTP, Element 2, that was submitted for information to IPC 251 st as a White Working Paper. As per Article 4.2(b) of the GSTP Implementing Rules, a set of 2 Common Activities and 6 Development Activities is presented. GSTP participating States are invited to indicate their level of contribution to GSTP-5 Element 2, at the latest at the time of approval of the attached Initial Work Plan. In accordance with Section 2(e), Annex B to the GSTP Declaration, such contribution may be transferred from Element 1 to Element 2 on request of participating States. The tables of figures included in Annex B of GSTP Declaration will be updated accordingly. After the approval of the attached Initial Work Plan, GSTP participating States not participating in Element 2 may still request to join that Element at a later stage, subject to the approval of those States having acquired the quality of participating States to GSTP-5 Element 2 through their contributions to that Element. REQUIRED ACTIONS 1. GSTP Participating States are invited to indicate their level of contribution to GSTP-5 Element 2, at the latest at the time of approval of the attached Initial Work Plan. 2. States participating to GSTP-5 Element 2 are invited to approve the attached Initial Work Plan. 3. IPC is invited to approve procurement plans associated to the attached Initial Work Plan (activities in Annex 1 identified with the label IPC). ecpb

2 Page 2 VOTING RIGHTS AND MAJORITY REQUIRED 1. Not applicable. 2. Simple majority of GSTP-5 Element 2 participating States. 3. Simple majority of GSTP-5 Element 2 participating States. LEGAL BASIS 1. GSTP Declaration, Section X(b). 2. GSTP Implementing Rules, Article 4.2(f). 3. GSTP Implementing Rules, Article 4.2(f).

3 Page 3 KEY TO TABLES The GSTP Element 2 Work Plan is presented along the following headings: On-board data systems On-board data SW GNC TT&C and data downlink Power conditioning and distribution Propulsion Actuator Technologies Thermal Control Passive Instruments Active Instruments Materials Components Each activity is given a programmatic reference, which will remain unchanged until completion. Additional planning elements associated with each of the activities are: Budget: The total Contract Authorisation (CA) values are given in KEURO, at yearly economic conditions. Together with the activity description the following information is reported: Deliverables: Provides a short description of the tangible outcome, e.g., breadboard, demonstrator, S/W, test data. A final report is standard for every activity. Current TRL/SW Readiness Level: Describes the current NASA TRL or the software readiness level of the product that is going to be developed in this activity. Target TRL / SW Readiness Level: The NASA TRL level expected for the product at the end of the activity. It is understood that TRL levels do not apply to S/W and tools. For these cases description of SW quality, i.e.: algorithm, beta version, prototype, or full operational, achieved at the end of the activity.

4 Page 4 Readiness Levels for S/W and tools Algorithm Single algorithms are implemented and tested to allow their characterisation and feasibility demonstration. Prototype A subset of the overall functionality is implemented to allow e.g. the demonstration of performance. Beta Version Implementation of all the software (software tool) functionality is complete. Verification & Validation process is partially completed (or completed for only a subset of the functionality). S/W Release Verification and Validation process is complete for the intended scope. The software (software tool) can be used in an operational context. Duration: Application: ESTER Reference: Expected duration of the activity (in months). Possible mission application / follow on. Identifies the related Dossier 0 Requirement. Harmonisation Roadmap: Provides information whether the technology activity is related to an harmonised subject and in case the subject is harmonised, provides the link to the relevant harmonisation roadmap.

5 ANNEX I List of the proposed Activities

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7 Annex 1, Page 1 ANNEX I: GSTP-5 Element 2 Work Plan / Procurement Plan ACTUATOR TECHNOLOGIES Approval GSTP-4 Reference Title Budget (K ) IPC G MM Proc. Policy Remarks (Company DN, etc.) Development and qualification of a limited angular range European SADM 1,500 C Development Activities Total ACTUATOR TECHNOLOGIES 1,500

8 Annex 1, Page 2 ANNEX I: GSTP-5 Element 2 Work Plan / Procurement Plan POWER CONDITIONING AND DISTRIBUTION Approval GSTP-4 Reference Title Budget (K ) Proc. Policy Remarks (Company DN, etc.) G EP DC/DC converters catalogue 150 C Development Activities Total POWER CONDITIONING AND DISTRIBUTION 150

9 Annex 1, Page 3 ANNEX I: GSTP-5 Element 2 Work Plan / Procurement Plan SPACE SEGMENT SOFTWARE Approval GSTP-4 Reference Title Budget (K ) Proc. Policy Remarks (Company DN, etc.) G SW Requirements and i/f definition for future OBCP building block 250 C Common Activities G SW On-Board Software Reference Architecture consolidation 350 C Common Activities Total SPACE SEGMENT SOFTWARE 600

10 Annex 1, Page 4 ANNEX I: GSTP-5 Element 2 Work Plan / Procurement Plan SPACE SYSTEM CONTROL /GNC Approval GSTP-4 Reference Title Budget (K ) IPC G EC Proc. Policy Remarks (Company DN, etc.) Second Generation APS for AOCS prototype (Phase 1) and detailed evaluation (Phase 2) 1,700 C Development Activities Total SPACE SYSTEM CONTROL /GNC 1,700

11 Annex 1, Page 5 ANNEX I: GSTP-5 Element 2 Work Plan / Procurement Plan THERMAL CONTROL Approval GSTP-4 Reference Title Budget (K ) Proc. Policy Remarks (Company DN, etc.) IPC G MC Highly Efficient Stand-Alone LHP-based Radiator System 1,000 C Development Activities Total THERMAL CONTROL 1,000

12 Annex 1, Page 6 ANNEX I: GSTP-5 Element 2 Work Plan / Procurement Plan TT&C Approval GSTP-4 Reference Title Budget (K ) Proc. Policy Remarks (Company DN, etc.) IPC G EE Mechanically steerable data downlink Antenna 1,500 C Development Activities IPC G EE Large Cup Antennas for Global Coverage from GEO Satellites 1,000 C Development Activities Total TT&C 2,500

13 ANNEX II Detailed Descriptions of the Activities

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15 Annex 2, Page 1 ACTUATOR TECHNOLOGIES Ref. Number: G MM Budget: 1,500 K Activity Title: Description: Development and qualification of a limited angular range European SADM The main objective is to develop, manufacture and qualify a Model of a fully European limited rotation (< ± 180º) SADM, including qualification of a stepper motor, twist capsule and position sensor. Deliverables: The Solar Array Drive Mechanisms and Electronics used for Rosetta, Mars Express and Venus Express spacecrafts were containing several components, as the stepper motor, twist capsules and position sensors obtained from the USA and are ITAR dependent. In addition, no European Twist Capsules are currently available. The idea of this activity is to review the existing SADM design and to modify it to envelope a range of typical SADM requirements, including future ESA missions. For each of the key parts (stepper motor, twist capsule and position sensor), the contactor shall perform trade-offs and identify the most promising baseline designs and corresponding European suppliers. The contractor shall perform preliminary and detailed design activities in order to support the design definition and justification. In parallel, the contractor shall carry out confidence testing activities (BreadBoarding) in order to validate the critical building blocks before CDR. A full qualification program (Functional, vibration, shock, thermal vacuum life and cyclic and EMC) according to ESA requirements including ECSS-E10-03A for EQM testing will be performed. BBM of stepper motor, BBM of twist capsule, BBM of position sensor, QM of SADM, Design Report and Performance Analyses (including budgets), Assembly and Interface drawings, Verification Control Document, Test Procedures, Test reports with correlation with Analysis. Current TRL: TRL4 Target TRL: TRL6 Duration: 24 Months Application / Science and Earth Observation Missions. Timeframe: Proc. Policy: C ESTER Ref: Harmonisation Roadmap:

16 Annex 2, Page 2 POWER CONDITIONING AND DISTRIBUTION Ref. Number: G EP Budget: 150 K Activity Title: Description: DC/DC converters catalogue In the course of the last decades, a number of DC/DC converters have been developed, qualified and tested to be used for many different purposes in a number of European companies with know-how and expertise in power electronics.. Deliverables: The activity consists in the systematic collection of the in-house BB DC/DC converters data: - design product specifications, with the information about the relevant applicable and reference standards used for the development and the qualification; - relevant supporting qualification data (including all design analyses, test plans, procedures and reports) - electrical diagrams - parts, process and material lists, including relevant PADs - ROM prices, under specific hypotheses - Lead times - Original purpose(s) of the converter development and qualification, other possible purposes of utilisation - History of utilisation Note that a design product specification is required, as opposed to the customer specification that might have been used for the design and development of the converters. The product specification includes all the non-compliances, request for deviation and waivers raised against the original customer specification, plus the extension of possible functional capabilities and performances according to the as designed status of the converter. In case specification extensions are envisaged, the proof of evidence of the actual performance or additional functionality shall be demonstrated vis-à-vis the existing qualification data, on the contrary a delta-qualification program shall be defined in agreement with the Agency. The potential delta-qualification programs are not included in the present activity. In any case, the consistency of the converter documentation shall be matter of design and qualification review by the Agency. The deliverables are identified by the list of documents indicated in the description. The design product specifications and the documentation relevant to the (original and possible) application purposes shall be made available according to a template made available by the Agency. Current TRL: N/A Target TRL: N/A Duration: 12 Months Application / Timeframe: Activity of general interest for all ESA and non-esa projects to have a global overview of BB converters for a wide number of applications, and to facilitate the selection of BB converters for specific purposes. Proc. Policy: C ESTER Ref: Harmonisation Roadmap:

17 Annex 2, Page 3 SPACE SEGMENT SOFTWARE Ref. Number: G SW Budget: 250 K Activity Title: Description: Requirements and i/f definition for future OBCP building block The On-Board Control Procedure (OBCP) is a powerful way to control spacecraft or to implement on-board functions. An ECSS standard on OBCPs is about to be published (ECSS-E-ST-70-01). The software to execute such procedures (also called interpreter) has been identified as a potential building block, and today, a number of implementations exist, however their interface is not standardised and they are in general not compliant with the new standard. An architecture study in the frame of Element2 is needed to identify the requirements for compatibility with open interface architectures and in line with the new Standard. Re-engineering of existing products could be considered as a second step. Deliverables: Several OBCP interpreters have been produced in various projects, but there are no real reusable products. They all use different languages and allow more or less access to the on-board software. Several technologies have been considered for interpreters, in particular Java (but the qualification of a full-sized Java interpreter is out of reach), scripting languages, EGSE languages such as Pluto, ad-hoc languages. This activity will review the Standard and determine which requirements are missing to realize an implementation in the spirit of a building block. It will review the existing OBCP interpreters and the potential language technologies, and will assess them in terms of compliance to the Standard, maturity, qualification effort, etc. The potential of adoption by the overall community shall also be taken into account. For this purpose, the activity will include the interface to a working group (under the umbrella of the SAVOIR Advisory Group) of stake holders that will provide user needs, and will advise on the selection of the final implementation solution, taking into account existing technology and products. A prototype will be produced. The activity will deliver the review of the existing and potential solutions, their assessment against the ECSS Standard and the working group advises the selected technical solution, the requirements of the future building block and a prototype implementation with the compliance to the Standard. Current TRL: N/A Target TRL: N/A Duration: 12 Months Application / Timeframe: The activity is an enabler for a building block production. It will deliver mature requirements in 2010 for availability of a building block in 2012, to be used in any mission where such OBCP are needed, i.e. a majority of ESA missions. Proc. Policy: C ESTER Ref: Harmonisation Roadmap:

18 Annex 2, Page 4 Ref. Number: G SW Budget: 350 K Activity Title: Description: On-Board Software Reference Architecture consolidation This activity is an "architectural activity aiming at consolidating the definition of a building block in this area. The starting point is the result of several activities, in particular one on AutoSar and the two parallel studies Cordet, which delivered a common document about the reference architecture. Many agreed principles are defined there, but they lack the definite specification to implement them. This activity will allow the choice of the implementation technology, in particular it will define the selected component model and computational model. It will then produce the reference architecture using the two above models. In particular, the notion of software bus will be refined and specified based on the defined component model. It will then define the middleware interface, e.g. by referring to SOIS elements and giving guidelines and priorities for the SOIS standardisation. It will define the allocation of the PUS services into the architecture. Finally, it will define the tools and the development logic associated to the use of the reference architecture. This includes a list of building blocks with a precise definition of some of them, in particular the software bus, the middleware and the PUS library. The future business model is based on a common approach on the architecture by the primes, allowing any software supplier to produce and commercialize compliant building blocks. Therefore, the activity shall include the interface to a working group (under the umbrella of the SAVOIR Advisory Group) of stake holders that will bring an harmonized decision on the selected technologies and solutions. Deliverables: Component and computational models; software building block definition and middleware interface definition; reference architecture model; tool and development logic outline; building block list; requirements for the software bus; and middleware and PUS library. In addition, a working group output evidence/summary. Current TRL: N/A Target TRL: N/A Duration: 18 Months Application / Timeframe: The activity is an enabler for the development of on-board software building blocks and associated tools, which could start in Targeted missions are all platform on-board software such as earth observation, science, telecom, or Exomars (carrier type). Proc. Policy: C ESTER Ref: T-7743 Harmonisation Roadmap:

19 Annex 2, Page 5 SPACE SYSTEM CONTROL /GNC Ref. Number: G EC Budget: 1,700 K Activity Title: Description: Second Generation APS for AOCS prototype (Phase 1) and detailed evaluation (Phase 2) Design, manufacture demonstration and detailed evaluation of the next generation of APS for AOCS units. This activity covers the second generation of the HAS development, in contrast to the LCMS2 which is the second generation of the LCMS development. Since the early STAR 250/1000 developments, the APS detector development has taken two separate paths, a high performance HAS, aiming for the best performance, and the LCMS, aiming for a highly integrated detector allowing for miniature and low cost applications. These detector developments are critical for several sensor applications such as star trackers and optical navigation sensors as well as sun sensors and often end up being also used in payloads and ground applications. Currently the HAS and LCMS are the world leading radiation hard APS detectors for space platform use, this development will maintain and protect that position as well as lead to improvements in a number of AOCS equipment types. This activity shall take all lessons learnt from the design and development of the current APS detector (HAS), together with the research performed into new pixel types, packaging technology and 0.18 micron CMOS process under the TRP activities 'New Technologies for future Star Trackers' and shall develop a second generation of APS suitable for AOCS units. The resulting detector will have much improved performances (in particular, effective removal of FPN and DSNU), functions (including on chip reference generation) and a fully custom AOCS and space application optimised ceramic packaging. A second phase of the activity shall update the design with lessons learnt from the prototype, develop the test equipment needed and perform the evaluation/ qualification testing of the device. Testing shall be in line with ESCC Deliverables: Tested APS prototypes (Phase 1); Qualified APS prototypes (Phase 2) Current TRL: TRL3 Target TRL: TRL7 Duration: 38 Months Proc. Policy: C ESTER Ref: T-7815 Harmonisation Roadmap:

20 Annex 2, Page 6 THERMAL CONTROL Ref. Number: G MC Budget: 1,000 K Activity Title: Description: Highly Efficient Stand-Alone LHP-based Radiator System Develop an integrated "stand-alone" cooling system consisting of two Loop Heat Pipes (LHPs) and an associated radiator to provide a thermal building block, i.e. a flexible cooling system allowing to e.g. integrate a dissipating unit (instrument, electronics, etc.) at a certain distance from the location where the associated waste heat can be rejected. Deliverables: In almost all spacecraft design, it is common practice to place/integrate a dissipating unit directly on a shared radiator or physically very close to a dedicated radiator. For potential applications where an instrument or an electronic box will have to be integrated at a given location due to e.g. field of view requirements, proximity to another unit, etc., and where the allocated external area for heat rejection is a certain distance apart, a dedicated thermal design has to be performed to accommodate such a request for each case, which is a costly and time-consuming exercise. The proposed stand-alone LHP-Radiator concept could - for Earth Observation, Science or Telecom missions - provide a flexible and efficient means to respond to such needs. Another application for the proposed concept could be seen in late add-on or piggy-back payloads/experiments where location of the unit and allocated area of heat rejection can be at a certain distance and/or where high flexibility for integration is required. The basic idea is to develop a system consisting of two parallel LHPs, integrated into an LHP coldplate with a given transport length and a dedicated radiator, highly flexible and to a certain extent scalable. The proposed activity shall therefore making maximum use of available, proven technologies (e.g. European LHP designs) develop such a system with the following main features: - an off-the-shelf unit with a certain flexibility/scalability concerning heat transport capability and/or transport length - two parallel LHPs for redundancy, with their evaporators integrated into a LHP cold plate which interfaces directly with dissipating unit or use of an intermediate Heat Pipe-spreader - envisaged heat transport range between 200 and 500 W - envisaged distance from heat dissipating unit and radiator between 3 and 5 meters The following tasks have been identified: - Establishment of a specification to envelop to the maximum extent all potential applications; concept definition and trade-off - Detailed design of a demonstrator; manufacturing of a demonstrator and performance of a complete characterisation test programme - Full ground qualification An integrated "stand-alone" cooling system consisting of two Loop Heat Pipes (LHPs), whose evaporators are integrated in an "LHP coldplate", and an associated radiator Current TRL: TRL4 Target TRL: TRL7 Duration: 30 Months Proc. Policy: C ESTER Ref: Harmonisation Roadmap:

21 Annex 2, Page 7 TT&C Ref. Number: G EE Budget: 1,500 K Activity Title: Description: Mechanically steerable data downlink Antenna At present all European Earth Observation (EO) satellites use isoflux antennas operating at X-band for the data downlink. Such antennas are necessarily low gain and are expected to cause a bottle-neck for future EO missions requiring higher data-rate. There is a strong interest for making available steerable pencil beam antenna at Ka-band given the higher attenuation and free space losses and at X-band where issues regarding eavesdropping and interference due to the wide coverage have been experienced. A cost effective solution consist in generating a steerable pencil beam pointed by a one or two axis mechanism. This as been already implemented in many EO satellites outside Europe and deserves attention. Today, several mechanisms are available on the market but with too high mass wrt the relatively small radiating aperture expected for such application. This activity deals with the development of a mechanically steerable antenna (single element or small array) including a detailed assessment of microvibrations and reliability aspects. It will be performed in two phases. The first one up to a PDR level will address both Ka and X-band antennas ensuring that mechanism development is compatible with both frequency bands, while phase 2 will develop the Ka-band antenna up to an EQM level. Two axis mecanism is considered as the baseline but simpler solution implementing only one axis shall be traded-off. Activities will cover the RF, mechanical and thermal design/analyses at antenna level, followed by the detail design, or procurement if/where available, of all its subsystems. At the time of lightweight rotary actuator selection, compatibility with other applications will have to be investigated to enlarge its application field. All subsystems will be made available/developed and tested at least at EQM level preferably implementing dual polarisation. Regarding the Small Rotary Actuator, the activity will cover the design, analyses, development and testing of a European source Qualification Model (QM). It is not foreseen the development of a specific electronic command in the frame of this contract but discussion on how this might further reduce the microvibrations shall be addressed. Final antenna assembly and RF/mechanical/thermal/lifetime tests will be performed to validate the development. This activity proposal replaces two previous GSTP-4 activities G601-51MM "Small rotary actuator dedicated for Small antenna deployment and pointing operations" and G103-03EE "Steerable pencil beam X-band data downlink antenna". Deliverables: Antenna designs and analyses at X and Ka-band; Fully tested QM at actuator level; Fully tested EQM at antenna level at Ka-band Current TRL: TRL3 Target TRL: TRL6 by 2012 Duration: 24 Months Application / Timeframe: GMES, future Explorer (No. 7) and Post-EPS This type of development might also be of interest for GEO/LEO inter-orbit satellite links. Proc. Policy: C ESTER Ref: T-57 Harmonisation Roadmap: Not related to an harmonised subject

22 Annex 2, Page 8 Ref. Number: G EE Budget: 1,000 K Activity Title: Description: Large Cup Antennas for Global Coverage from GEO Satellites The objective of the activity is the design and development of medium gain communication antennas for Earth Observation satellites in geostationary orbit - the principle mission identified being GOES-R. Such antennas are required operating at UHF (400 to 470MHz), L-band and S-band, polarisation is single/dual linear or circular and high radiation aperture efficiency is requested. The activity will provide designs in these frequency bands and an EQM for the UHF antenna which is considered the most critical in terms of volume, mass and mechanical constraints. The UHF antenna design may also be applicable to MTG depending on any accommodation constraints imposed by the MTG payload. Antenna shall be compatible with Tx/Rx operation. The activity will be organised in 2 phases with phase 1 covering the trade-off and designs for all frequency bands and phase 2 the RF, mechanical and thermal design and analyses of the UHF EQM to be submitted to a full qualification sequence. Deliverables: Antenna designs and analyses at UHF and L/S-bands; Fully tested EQM at UHF band. Current TRL: TRL3 Target TRL: TRL6 by 2012 Duration: 20 Months Application / Timeframe: GOES-R Proc. Policy: C ESTER Ref: T-57 Harmonisation Roadmap: Not related to an harmonised subject