ESA Unclassified – For official use only ESA/IPC(2010)119 Att.: Annexes Paris, 29 September 2010 (English only)
EUROPEAN SPACE AGENCY
INDUSTRIAL POLICY COMMITTEE
BASIC TECHNOLOGY RESEARCH PROGRAMME
Preliminary Selection of Activities for the TRP 2011-2013
SUMMARY The present document aims at:
Presenting the preliminary selection of TRP 2011-2013 activities in compliance with programmatic needs
Supporting bilateral meetings with Delegations
Summarising the process and logic which have led to this selection
REQUIRED ACTION Delegations are invited to take note of the attached document.
NEXT STEPS Following the presentation of this preliminary selection at the October 2010 IPC, bilateral contacts will be established with Delegations. The procurement plan for the activities to be initiated in 2011 will be presented to the November 2010 IPC.
eCPB-2010-1255 ESA/IPC(2010)119 Page 2
Page intentionally left blank
ESA/IPC(2010)119 Page 3
Basic Technology Research Programme 2011-2013
Preliminary Selection of Activities
Table of Contents
Scope of the document
The E2E Process - The Need for Technology Development - The Technology Programmes Landscape - The E2E Process
The TRP 2011-2013 Work Plan - Budgetary Perspectives of the TRP 2011-2013 - TRP 2011-2013 Preliminary Selection Overview - Main Results of the TRP Work Plan Preparation per SD - Conclusions and Issues
Activities for 2011-2013 - Key to Tables - Activity Template - ANNEX I: Detailed TRP Plan 2011-2013 - ANNEX II: Descriptions of the activities
ESA/IPC(2010)119 Page 4 Scope of the Document
This document introduces the preliminary selection of activities for implementation in the Work Plan of the Basic Technology Research Programme (TRP) for 2011-2013. The plan attached in Annexes I and II has been established as part of the Agency’s end-to-end process for the management of technology development defined in ESA/IPC(2008)61, rev. 1, refined with the lessons learned in the previous exercise and under the supervision of the Directors’ Subcommittee for Technology.
1 The E2E Process
1.1 The Need for Technology Development
The need for timely development of enabling technology is undisputed. Failure to assure the availability of technology at the right Technology Readiness Level (TRL), commensurate with the project phase, is one of the most frequent causes for cost overruns and projects delays (ESA/C(2010)20). Figure 1 schematically shows the risk associated with initiating a project phase (as in ECSS-M-ST-30) with the relevant technologies being at a given TRL: at the beginning of each project phase, the higher the achieved TRL, the lower the risk associated to the phase (ranging from red to green). Pacing the developments of technology to the needs of user projects is an Agency objective. Technology development is one of ESA’s enabling activities that deserve attention at the highest corporate level as shown by the establishment of a dedicated Directors’ Subcommittee for Technology (see section 2.3).
System Test, Launch & Operations TRL 9
System/Subsystem TRL 8 Development TRL 7 Lower risk Technology Demonstration TRL 6
TRL 5 Technology Development Risks TRL 4 Research to Prove Feasibility TRL 3
Basic Technology TRL 2 Research TRL 1 Higher risk 0ABCD Project Phases
Figure 1: Technology Readiness Levels, project phases and risks ESA/IPC(2010)119 Page 5
1.2 The Technology Programmes Landscape Technology is developed in ESA under several general (TRP, GSTP) and domain specific programmes (EOEP, CTP, etc). Some are mandatory (TRP, CTP) whereas the rest are optional. The TRP is the sole programme that addresses all applications and technology domains. The GSTP addresses all applications except telecommunications. Each programme has its own rules and applicability along the scale of Technology Readiness Levels, as illustrated in Figure 2. It is therefore of the utmost importance to coordinate the definition and implementation of the Agency’s technology programmes.
TRL
Technology Readiness Levels 123456789 Basic principles Concept and/or Analytical / Component or Component or System / System Actua l syste m Actual system observed and application experimental breadboard breadboard subsyste m prototype completed and flight proven reported formulated critical function Validation in validation in model or demonstration "flight qualified" trhough / characteristic laboratory relevant prototype in a space through test and succe ssful k proof of concept environment environment demonstrated in environment demonstration mission relevant (ground or operations Programmes Programmes environment spa ce ) Applications
TRP All CTP Science
EOEP EO
ARTES, 345 Telecom GNSS Evolution Navigation FLPP Launchers Aurora - MREP Robotic Expl
ETHE European Transportation and Human Exploration Hum. Expl. Transp
GSTP All but Telecom Figure 2: ESA Technology Programmes Landscape
1.3 The E2E Process
1.3.1 General The ESA end-to-end process for the management of technology development was presented in 2005, consolidated in the following years (ESA/IPC(2008)61, rev. 1), and successfully adopted e.g. during the preparation and implementation of the TRP plan 2008-2010. The main goal of the process is to drive ESA technology programmes by requirements for technology, which are set up together with users, along four main objectives: - Preparing and maturing technologies for future projects - Stimulating technology innovation - Supporting industry’s competitiveness in the global markets - Ensuring European non-dependence on critical technologies.
ESAESA LongLong TermTerm PlanPlan
EuropeanEuropean andand ESAESA TechnologyTechnology StrategyStrategy andand LongLong Worldwide TechnologyTechnology ESAESA ProgrammeProgramme TermTerm PlanPlan AssessmentAssessment NeedsNeeds PrioritizedPrioritized technologytechnology TechnologyTechnology PushPush requirementsrequirements andand roadmapsroadmaps EuropeanEuropean National Missions National Missions ESTER HarmonisationHarmonisation (THAG) (THAG) Prioritized ESA Technology Work Plans IndustryIndustry ConsultationConsultation ESA Technology Work Plans
TechnologyTechnology ImplementationImplementation TechnologyTechnology Monitoring/ EvaluationEvaluation IndustrialIndustrial productsproducts
Figure 3: E2E process ESA/IPC(2010)119 Page 6
The process consists in a top-down approach complemented by a bottom-up approach (see Figure 3). The top-down goes from the users needs, expressed in terms of requirements, to the plans of activities, whereas the bottom-up lies in the development activities proposed by the experts.
The process was improved thanks to the lessons learned in previous exercises. In particular: - The process friendliness is continuously increased by improving the ESTER (European Space Technology Requirements) database and facilitating the process of inputs and outputs. - Missions are provided by ESA Programmes; however, National entities and industry needs (especially through EUROSPACE) might also be flagged, mainly in support to competitiveness and innovation, and where necessary added. - Mission and Technology Requirements were derived by the TECNET Service Domain groups. - A standard form was used to formulate activity proposals (implemented via a dedicated proposal collection tool, called STAT). This approach ensures that all proposals are presented with the same contents. This facilitates analysis and evaluation of such proposals.
In parallel to the preparation of this 3-year plan, the update of the Technology Strategy and long-term Plan (TSLTP) and the review of the Technology Harmonization Process have synergically taken place.
1.3.2 Organization The process is schematically shown in Figure 4. It is organized by Service Domains (SDs): - seven application oriented SDs (SD1, SD2, SD3, SD4, SD5, SD6, SD9) - one generic technology SD (SD7), targeting the development of multiple application technologies, innovative technologies, cross-sectorial technologies - one inter-directorate working group (SD8) transversally earmarking potential dual- use technologies identified within the other SD’s.
TECNET A working group has been set up for each SD, all working groups together forming the so called TECNET Technology Network. Applications (hence Programmes) driven SDs are chaired by a representative of the Programme Directorate concerned and include experts from the relevant programmes and from the D/TEC and D/OPS Directorates. SD7 is chaired by TEC and includes representatives of Programme Directorates, D/TEC and D/OPS. A secretary from D/TEC assures for each SD the homogeneity of the process and supports the technology assessment process, in particular by bridging with transversal initiatives (e.g. harmonisation, ad hoc WG’s, etc.) and across programmes. Each SD addresses the relevant domain specific technology programmes, e.g. EOEP, ARTES, etc as well as the corresponding part of the TRP and GSTP corporate programmes.
The chairmanship by a programme representative guarantees that user requirements are fully taken into account within the available means. SD7 on the other hand guarantees progress in basic technologies. The focused composition, namely Programmes + D/TEC + D/OPS, facilitates the work of TECNET.
TECNET is in charge of defining the domain perimeter, identifying the missions, deriving and prioritizing the requirements. TECNET is also calling for technology development activities that met the requirements, evaluates the proposals and allocates the selected proposals to the programmes. ESA/IPC(2010)119 Page 7
SD Domain Chair Members Programmes TRP, GSTP, 1 Earth Observation EOP EOP, SRE, TEC, OPS EOEP TRP, GSTP, 2 Space Science SRE SRE, EOP, TEC, OPS CTP Human Space Flight and TRP, GSTP, 3 HSF HSF, SRE, TEC, OPS Human Exploration ELIPS, THEP Space Transportation and TRP, GSTP, 4 LAU LAU, HSF, TEC, OPS Planetary Entry FLPP, ETHE 5 Telecommunications TIA TIA, TEC, OPS TRP, ARTES TRP, GNSS 6 Navigation NAV NAV, TEC, OPS Evolution, GSTP 7 Generic / Basic TEC All SD chairs, TEC, OPS TRP, GSTP TRP, GSTP, 9 Robotic Exploration SRE SRE, HSF, TEC, OPS MREP Table 1: Service Domains’ composition and scope
Coordination across Service Domains Coordination across SDs is assured in TECNET by the chairs of the TECNET domain specific and generic groups. They are also supported by the Department Heads of D/TEC and D/OPS. This organization guaranteed that first hand knowledge is involved in the coordination process. TECNET meets 4 times per year to review progress and provide guidelines for further action.
Directors’ Subcommittee for Technology (DSCT) The DSCT has been set up by Director General with the mission of overseeing the Agency’s technology development activity. Chaired by D/TEC, it includes Programme Directors, D/OPS and D/RES or their appointed representatives. The primary task of DSCT is to ensure that technology development is an ESA wide corporate undertaking.
As a first step towards the preparation of the technology plans, and in particular regarding the TRP plan 2011-2013, the DSCT agreed upon the preliminary financial allocations to the various SDs and where possible correlated them to other Programmes. Moreover, the DSCT endorses the results achieved in the E2E process, prior to submitting the resulting Preliminary Selection to the IPC (and/or relevant Programme Boards).
Directors’ Subcommitte e
+ HoD TEC Chair Chair Chair Chair Chair Chair Chair Chair Chair EO SRE SRE HSF LAU TEL NAV SEC TEC TECNET TECNET TECNET TECNET TECNET TECNET TECNET TECNET TECNET EO Science REX HSF S/TLAU TEL NAV SEC GEN TRP TRP TRP TRP TRP TRP TRP TRP TRP GSTP GSTP GSTP GSTP GSTP GSTP GSTP GSTP EOEP CTP MREPETP THEP FLPP ARTES EGEP STPs STPs
EOEP CTP MREPETP THEP FLPP ARTES EGEP GSTP ELIPS TRP TRP Figure 4: From TECNET to DSCT ESA/IPC(2010)119 Page 8
2 THE TRP 2011–2013 WORKPLAN
The plan of work for TRP 2011–2013 has been defined as part of the E2E process described in chapter 2.
Although, the TRP is based on yearly budgets and yearly procurement plans, with an overall budgetary envelope defined in the level of resources, the preparation of three- year plans is maintained. The obvious advantage of a three plan is that it provides planning horizon for the technology end-to-end process, to user programmes, Delegations and industry.
The TRP is the only Agency programme that covers all present and future space applications pursued by ESA. Considering the spirit of mandatory programme, the needs of potential user programmes and the availability of resources in other technology programmes, priority is given to: - Supporting the development of advanced technologies of interest to all domains, - Maintaining the central position of science and earth observation.
2.1 Budgetary Perspectives of the TRP 2011-2013 The following section summarises per Service Domain the main results of the E2E process applied to the preparation of the TRP plan 2011-2013.
Due to programmatic reasons within the individual service domains the TRP plan is established in two steps. The first step targeted the following Service Domains:
- SD1 (Earth Observation), - SD4 (Space Transportation and Planetary Entry) - SD5 (Telecommunication) - SD6 (Navigation) - SD7 (Generic Technologies and Techniques)
A second step is planned for 2011, covering the other SDs namely SD2, SD3, SD9, in detail: - For both Science (SD2) and Robotic Exploration (SD9) the plans approved by the IPC in November 2009 are still applicable, and activities span the 2009- 2011/12 timeframe. The next update to these plans is expected after mission downselection. - For Human Space Flight (SD3), the domain mission and technology requirements are expected in Q4 2010./ Q1 2011.
The total budget allocation for the applicable SD’s within the TRP 2011-2013 is: SD1 – Earth Observation 21 M€ SD2 - Space Science 21 M€ SD3 - Human Space Flight and Human Exploration 8.5 M€ SD4 - Space Transportation and Planetary Entry 10 M€ SD5 – Telecommunication 7 M€ SD6 – Navigation 3 M€ SD7 - Generic Technologies and Techniques 51 M€ SD9 – Robotic Exploration 8.5 M€ ESA/IPC(2010)119 Page 9
The budgetary perspectives were presented at a dedicated DSCT meeting. Besides the allocations controlled by TECNET SDs, about 9 M€ are reserved for initiatives such as the Innovation Triangle Initiative (ITI) and STARTIGER and possibly new cross sectorial actions if required.
An over-programmed budget is normally planned to provide the Programme with flexibility and efficiency, ensure a smoother implementation and bridging with the next cycle. This over-programming is represented by the activities from the previous 3-year plan (2008-2010) that were approved, but not committed within the cycle. Depending on the individual SD technology needs, at the end of 2010, before starting the Plan 2011 of the new TRP cycle 2011-2013, a final review of the plan 2008-2010 implementation will be carried out to identify the non initiated activities and consolidate the individual SD’s overprogramming. In general, during the life cycle, the 3-year plan is regularly reviewed by TECNET and if necessary outdated or reprioritised activities are replaced with new activities.
It is recognized that the TRP does not have the resources to cover all SDs in a sufficient manner, as it should be the task of a mandatory technology programme. This is largely the result of accommodating new SD – or new fields within existing SDs – and new technology domains (TDs) through budget re-allocations within the stable TRP budget.
The present exercise has focused on the TRP, however, in order to exploit the preparation effort and the synergies with other Programmes, all collected proposals have been assessed and when recognised as potentially valuable to other Programmes, e.g. the EOEP or GSTP, have been retained and addressed to those programmes,.
2.2 TRP 2011-2013 Preliminary Selection Overview The plan of work for TRP 2011–2013 has been defined as part of the E2E process described above. Although, the E2E process is continuous, it must be emphasized that definition of a new three year plan, requires a significant effort from TECNET. For illustration the list of TECNET meetings dedicated to the TRP 2011-13 is shown in Table 2.
TECNET meeting dates SD1 7/4 25/5 4/6 22/6 SD4 7/6 28/6 8/7 SD5 9/4 28/5 4/6 SD6 23/4 27/6 11/6 SD7 13-14/4 1-2/6 9-10/6 16/6 SD7 - E2E 29/4 17/5 26/5 SD7- Avionics 4/5 12/5 12/6 SD7- Components Continuous process 24/6 SD7- Miniaturization 28/4 10/5 28/5 7/6 15/6
Table 2: TECNET Meetings dedicated to TRP 2011-2013
ESA/IPC(2010)119 Page 10
The effort is primarily due to the time required to screen requirements, including those coming from industry, and especially to handle and evaluate the very large number of proposals and match them to the available budget, implying very difficult choices by all participants. However, as mentioned before, in order to exploit the effort and the synergies with other Programmes, all collected proposals have been assessed and when recognised as potentially valuable to another Programme, e.g. the GSTP, have been retained and addressed to such a programme. The exercise involved a total number of 1400 proposals, out of which 289 are proposed as part of this TRP plan.
Dow nselection, number of proposals
700
600
500
400 Total proposals entered TDR approved 300 Preselected for TRP WP Number of proposals 200
100
0 14567 Service Dom ain
Figure 5: TRP 2011-2013 Proposal Downselection
The plan preparation results are summarized hereafter:
TRP plan 2011-2013: Target allocation vs Actual allocation Target Actual Domain Budget (M€) # of activities Budget (M€) SD1 21 63 20.98 SD4(1) 10 44 11.00(1) SD5(1) 7 25 7.50(1) SD6 3 15 3.40 SD7 (2) 51 142 49.30(2) Total TRP 2011-2013 92 289 92.43
Table 3: TRP 2011-2013 selection results
(1) DSCT decided that budgetary targets should be achieved by deleting planned activities from TRP 2008-2010 Cycle (2) This includes a planning wedge for non decided activities
ESA/IPC(2010)119 Page 11
2.3 Main Results of the TRP Work Plan Preparation per SD 2.3.1 SD1 – Earth Observation Context, Missions and Requirements As mentioned in the Earth Observation Technology Challenges and Plans document (reference ESA/PB-EO/DOSTAG/63/RoomDoc(2010)18) Earth Observation will continue to be based on the dual mission strategy consisting of two classes of related user driven missions:
- Earth Explorer: Earth research oriented missions and missions to demonstrate new observation techniques prior to operational use; - Earth Watch: operational service driven missions, including GMES.
Earth Explorer Missions The missions include those down selected in the frame of the 7th Earth Explorer (EE7) as well as new concepts under assessment for the 8th Earth Explorer (EE8.) Moreover, they include missions selected for assessment studies as well as missions not selected but commended by ESAC, the Earth Science Advisory Committee.
Biomass, CoReH2O and PREMIER were selected as the 7th Earth Explorer (EE7) mission candidates to be studied at phase A level. The technology preparation for these missions has already been planned in detail and is already being implemented in the framework of all relevant programme lines (TRP, GSTP, EOPA, IPD). Therefore these three missions have not been addressed in the TRP 2011-2013 cycle.
The Call for Proposals for Earth Explorer Opportunity Mission EE8 was released in October 2009 (ESA/PB-EO(2009)96 rev.1). It requires that proposals demonstrate sufficient technology readiness, in particular of the payload, so that a minimum TRL of 5-6 is achievable by the end of Phase-A. The selection of the EE8 candidates for Phase- A studies will be completed by November 2010 and will take these aspects into special account. There is therefore limited need for planning technology development activities in support of EE8 within TRP or EOPA, although some activities may still be required under IPD or GSTP, to achieve the transition to TRL 5 and above.
Further EO technology development needs are linked to future mission concepts that address the scientific challenges for ESA’s Living Planet Programme, which should be proposed essentially in response to a Call for Proposals for Earth Explorer Core Mission EE9. Therefore the TRP 2011-2013 is very much influenced by the scientific challenges and the derived technology needs as detailed below.
Considering current plans for EE7 and EE8, it is expected that EE9 and later Earth Explorer missions will be launched as from 2020. This implies Phase-B to be completed by end 2015 and technology having reached TRL 6 by that time.
Earth Watch Missions Concerning Earth Watch, the operational meteorological systems of EUMETSAT, namely MTG and Metop 2nd generation, and the GMES Sentinels 4 and 5, the latter first with a Precursor mission and afterwards as part of Post-EPS are already being addressed. Technology developments are driven by the new mission concepts for next generation of Sentinels and satisfying existing and new user communities including ESA/IPC(2010)119 Page 12 security Earth observation user communities. These include for instance new mission concepts based on observations from the geostationary or geosynchronous orbits, high resolution SAR operating in traditional and new bands, etc.
These new Earth Watch missions could be launched in 2020. TRL 6 should be achieved by 2015-2016 for all enabling technologies.
General Considerations It is also proper timing to advance the TRL of technologies that may be considered in the formulation of proposals in response to future Call for Earth Explorer missions. Particularly those technologies that may support truly new observation techniques should be given specific attention in the definition of the work plans for research- orientated (i.e., low TRLs) technology activities.
Particular effort should be put on the technologies that may enable potential cooperations with other Agencies, e.g. NASA, for instance through provision of innovative sensors, as well as to support other flights of opportunity, including in-orbit demonstrations of critical technologies for future missions, consistently with the in- orbit demonstration strategy (ESA/IPC(2008)113 rev.1).
Scientific Challenges and related Technology Needs The scientific objectives of ESA’s EO activities represent the prominent motivation to identify new observations achievable from space and the related technological challenges. The Science Strategy for the ESA’s Living Planet Programme was formulated under the guidance of the Earth Science Advisory Committee (ESAC), which included wide consultation of the Earth science community. The vast field of the Earth Sciences was addressed according to five topics corresponding to key Earth sub- systems: - Oceans, - Atmosphere, - Cryosphere, - Land, - Solid Earth.
The summary of potential mid-term EO ESA missions presented in the Table below has been elaborated taking into account the current scientific “drive” and other inputs such as the likely evolution of the GMES programme (ref. ESA/PB-EO(2008)68) and its long-term scenario (ref. ESA/PB-EO(2009)68). The summary defines potential ESA EO missions, i.e. Earth Explorer and GMES candidate missions, based on current knowledge and understanding of priorities, as well as on completed, on-going or planned relevant concept studies (e.g. Next generation gravity mission, Geo-Oculus, Laser-based occultation demonstration mission, Micro-WAT, EO Convoy,..) under the EOPA, GSP, STSE and GSC programmes or programme lines. The Table also indicates key technology areas that need to be advanced as a matter of higher priority to enable the identified missions, and a preliminary set of technology development requirements within those technology areas (in no special order and at different levels). It is important to recall once more that technology preparations are already on-going for several mission concepts such as commended missions (FLEX, ASCOPE and WALES lidars, etc) as well as in a number of areas (particularly under the TRP) for which innovative technologies are the driving factors rather than any specifically identified mission concept. ESA/IPC(2010)119 Page 13
Covered in Potential missions Technology areas Technology development requirements TRP plan
Future gravity field Next generation satellite-to- laser interferometer tracking system: T117-309MM mapping and satellite tracking for gravity monitoring (global time-variations laser frequency stabilisation; mass redistribution) digital interferometer phasemeter
drag-free technologies: in-orbit lessons learned; electrostatic accelerometer evolution; T105-302EC Next generation gravity micro-thrusters for 6DOF control; gradient measurements low-noise attitude actuators;.. atom interferometry gradiometers T117-306MM
Ocean mesoscale Wide-swath (“IRAC”-type) interferometric radars at Ku- and Ka- T107-307EE, currents altimeters band with modest baselines: ultra-stable structures, (miniaturised) on-board T117-308MM (possibly in distance metrology, high-performance combination with attitude estimation and stabilisation, reference altimetry) microwave calibration, interferometric
radar advanced on-board processing Wavemill concept T107-310EE
squinted dual-beam antenna Constellation of miniaturised altimeters T106-301ET miniaturisation of altimetry electronics, T107-306EE on-board processing
In-land waters Ka-band SAR interferometer as above for wide-swath but with longer T106-303ET antenna baseline
interferometric radar elements and advanced on-board processing T107-309EE
Air-sea interactions Hi-resolution all-weather momentum compensation for large T106-312ET SST radiometry antenna rotation
stable well-calibrated receivers
Ice sheet (sounding) Interferometric P-band and antenna and RF component technologies, T106-302ET, L-band SAR; e.g. high-power amplifiers and glaciers Ka-band single-pass SAR;
P-band sounder; laser technologies for altimetry T116-306MM tandem missions; laser altimeters as for Ka-band SAR above
Atmospheric processes Lidar technologies highly accurate, stable and spectrally- T117-301MM, and air quality pure lasers T117-302MM, T117-307MM,
Enhanced UV, VIS, NIR, T117-305MM, SWIR, TIR spectrometers polarisation scramblers T117-304MM, T116-311MM
enhanced large-format detectors T117-303MM
ESA/IPC(2010)119 Page 14
on-board calibration
compact high-performance spectrometers T116-304MM, T116-307MM
High-resolution TIR detectors micro-bolometers; No thermal infrared mission cooled HgCdTe detectors
High-resolution AOCS, image processing on-board image processing for LOS T116-312MM, imagery from geo- and navigation for motion estimation and image T105-301EC synchronous orbit, observations from geo- interpolation especially for coastal synchronous orbit no monitoring and ocean high-speed digital processing technology T116-309MM colour large-aperture monolithic telescopes T116-303MM Large telescope and relative large dichroic plates T116-302MM opto-electronic elements on-board calibration for large aperture no large focal plane detectors no image stabilisation techniques High-resolution soil enhanced (spatial and RFI rejection processing (on-board, on- T107-304EE moisture and ocean radiometric) resolution ground) salinity (operational) interferometric radiometers L- and C-band receiver miniaturisation
Internal calibration
GMES/security: Ka-band single-pass digital beam-forming T107-301EE, interferometric SAR imaging T107-302EE SAR imagery for land change detection, T106-303ET, topography Ka-band units and components T106-310ET
SAR receive modules
GMES/security: very wide swath high- beam-forming and scan-on-receive no maritime surveillance resolution SAR for moving processing elements target detection large antenna at X-band and its deployment structure
GMES evolution: high-resolution wide-swath digital beam-forming T106-308ET next-generation SAR C-band SAR imagery scan-on-receive no full-polarimetric SAR elements no algorithms for information extraction no from full-polarimetric data
GMES evolution: enhanced resolution super- large detector arrays in VNIR and SWIR T117-310MM next-generation high- spectral sensor resolution land optical imagery integrated focal planes T116-301MM, T116-305MM
T101-301ED, on-board processing e.g. ad-hoc data T107-312EE compression
high-rate data downlink
Table 3.1-1 Potential Future EO Missions, related Technology needs and the respective activity proposals accepted in the TRP Plan
ESA/IPC(2010)119 Page 15
Additionally, other two sets of technology requirements can be derived from complementary considerations regarding specific needs identified across multiple EO missions (‘common EO technologies’) and the evolution of requirements on platforms (‘generic space technologies’). The former are identified in the Table below.
Subject Technology area Covered in TRP plan
Structures ‘non-standard’ spacecraft configurations, e.g. to support very T117-308MM large antenna (interferometric) systems
Thermal control ultra-stable (temporal and spatial) temperature control (e.g. for No calibration blackbody, optical bench, laser metrology source);
high power (highly dissipative) sensor thermal control (e.g., laser head); No enhanced cryo-cooling architectures (double stage cryostat T121-301MT using double stage cooler, multiple cold fingers driven by single compressor, distributed on chip cooling); T121-302MT vibration-free heat transportation and cryo-cooling
Data handling on-board very high speed (> 3 Gb/s) data interfaces T101-302ED
Communications very high rate downlink e.g. at 26 GHz T107-303EE
Ground segment cost-effective receiving stations for very-high-rate downlink; No
increased autonomy and maintainability in PDGS operations; T126-303GT, T126-304GT
inter-operability across ESA and non-ESA missions; T126-301GT
multi-sensor data fusion e.g. for automated processing of imagery from EO formations; T126-305GT
automatic information extraction; T126-302GT
Table 3.1-2 Recurrent Technology Needs for Future EO mission concepts
Results In answer to the call for activity proposals, 190 proposals amounting to 82.8 M€ were received. All activity proposals were reviewed through several dedicated TECNET meetings. Activities were selected, rejected, transferred to other SDs or actions were given to combine or update the proposals. Selected activities were allocated to TRP or recommended for other programmes.
63 activities were selected for the TRP amounting to 20.98 M€. ESA/IPC(2010)119 Page 16
Earth Observation: Target allocation vs Actual allocation Target Actual Budget Budget Sub-Domain (M€) Overprog. # of activities (M€) 1 - 01 - Microwave Payloads 20 5.70 1 - 02 - Optical Payloads 21 4.2 25 9.98 1 - 03 - Platforms / Others 18 5.30 Total TRP 2011-2013 21 4.2 63 20.98
2.3.2 SD2 – Science The technology development plans (ESA/IPC(2009)NN) was approved end 2009. Updates will be required to consider the selection of M1, M2 missions, dowselection of L1 missions and response to the call for M3 candidates. Resources have been reserved.
2.3.3 SD3 – Human Space Flight and Exploration
As the definition of the future missions is ongoing, the preparation of technology development plans is postponed. Resources have been earmarked.
2.3.4 SD4 – Space Transportation (and Planetary Entry) Context, Missions and Requirements This SD straddles two Programme Directorates in ESA, D/LAU (launchers and associated re-entry) and D/HSF (human spaceflight) as required for Exploration.
Concerning launchers, the European launcher sector High Level Requirements are: - To maintain a guaranteed access to space for Europe (available, reliable, independent at affordable conditions), through a family of launchers and the associated ground infrastructures to better respond to present and future institutional needs while keeping competitiveness on the commercial market, - To safeguard industrial capabilities and engineering know-how, which is needed to implement the guarantee of access to space today (exploitation) and to maintain such a guarantee in the future through new developments, - To prepare the Next Generation Launcher, which allows maintaining a guaranteed access to space in the long term future, - The fulfilment of the above requirements, for both the development and the exploitation phase, must be compatible with resources (affordability).
The European access to space is today guaranteed by Ariane 5 and after 2010 by a family of launchers which includes Ariane 5, Vega and Soyuz operated from the CSG. While some adaptations of the Ariane and/or Vega launcher might be needed in the short term for specific mission requirements, major evolutions are currently considered, to be potentially introduced in exploitation from ~2015 onwards to better respond to European institutional needs and to maintain launcher competitiveness in the commercial market.
ESA/IPC(2010)119 Page 17
Furthermore, the preparation of the Next Generation Launcher (NGL) is continuing so , as to maintaining guaranteed access to space for Europe in the long term, in line with requirements to be consolidated in due time, with a target initial operational capability around 2025. The preparation of the Next Generation Launcher (NGL) is instrumental to provide Europe and its industry with the appropriate technological basis and system level expertise for making an informed decision on the most suitable launch system to respond to future space transportation requirements from institutional (e.g. space exploration) and from commercial markets.
An essential part of the preparation of the future is represented by the technology development and verification of promising and enabling technologies, in particular for High Thrust Engine and Cryogenic Upper Stage Technologies, through ground demonstrators and in-flight experiments. The flight of the Intermediate eXperimental Vehicle (IXV) will represent a major step in the mastering of re-entry technologies by Europe.
Human Spaceflight and Exploration activities heavily rely on space transportation and atmospheric re-entry technologies. With the completion of the International Space Station (ISS), its full exploitation phase began with the operations of the European Columbus laboratory and the supporting cargo transportation missions by the ATV. The development of new transportation capabilities for cargo / experiments upload and download is of great interest to enable full ISS utilization after the Space Shuttle withdrawal (> 2011) and the initial studies have been undertaken by the Agency already since 2008.
The decision taken by the ISS stakeholders in 2010 to extend the operations of the ISS until 2020 and beyond provides a sufficiently long period of operations, which will be of fundamental importance for the development of new capabilities, including a versatile tug for payload transfer with return capability and a new Crew Space Transportation System.
In parallel the next step, that is human exploration, is being prepared, focusing in particular on the progressive development and demonstration of in-orbit assembly methodologies, modern docking systems, modular propulsion and refueling systems. Such new systems and capabilities will allow Europe and its International Partners to increase their ability to operate in space, at the ISS first and at new orbital facilities later on. Only once sufficient maturity of these in-space operational capabilities will have been achieved, the actual implementation of the initial human exploration activities might be undertaken, which is being prepared through the European participation to the development of common international space exploration architecture.
The transportation aspects relevant to human spaceflight can be articulated over three periods, in the short/medium term future: - 2008-2015: characterized essentially by the exploitation of the International Space Station (ISS), based on the operations of the European Columbus laboratory and the cargo transportation missions by the ATV. - 2015-2020: corresponding to the ISS life extension. For this period the development of complementary transportation systems for cargo / experiments upload and download may be of interest to increase the robustness of the exploration scenario. ESA/IPC(2010)119 Page 18
- 2020-2025: involving the development of a post-ISS space infrastructure designed to support initial human exploration activities, with the first human missions to the Moon orbit and the European participation to the development of international space exploration architecture. This represents a period of fundamental importance for the development of new capabilities, including a new Crew Space Transportation System, as well as the technologies for in-orbit assembly, modern docking systems, space tugs and refueling systems. On the basis of the above directions, the following three groups of reference missions in the area of orbital transportation may be identified.
The corresponding three groups of systems are: 1. Cargo transportation system in support to ISS, including – cargo upload and return capability, 2. Crew transportation system in support to post ISS orbital infrastructure and exploration missions, – the crew transportation and return vehicle, – the human rating of the corresponding launch vehicles, – the demonstration of the required crew escape systems – the inter-planetary transfer stages. 3. Supporting technologies demonstration missions, including – Atmospheric re-entry demonstrators for LEO missions, – High-velocity re-entry demonstrators for exploration missions, – Transonic and descent systems demonstrators, – Automatic rendezvous and low-impact docking demonstrations, – Nuclear thermal propulsion for human exploration.
Technology requirements were defined following the launcher and space transportation mission trends, development activities were proposed and scrutinised leading to the selection for the TRP 2011 - 2013.
Results It was noted that there was significant mismatch between needs and resources. A considerable effort was thus devoted to the prioritization and down-selection of activities.
105 Proposals were received covering TRP, GSTP and FLPP. Proposals were evaluated according to 3 priority levels. The evaluation led to a first selection of proposals in Priority 1 for TRP, representing a total budget of 44 activities at 11 M€. In addition to the nominal allocation, some over-programming has been allowed, as some activities remaining from the previous TRP plan 2008-2010, that will be deleted at the end of 2010.
The distribution of funding among activities under the relevant Technology Domains correlates with the identified Technology Requirements.
ESA/IPC(2010)119 Page 19
Space Transportation & Planetary Entry: Target allocation vs Actual allocation Target Actual Sub-Domain Budget (M€) # of activities Budget (M€) 4 - 01 - Launchers oriented Technologies 27 6.30 4 - 02 - Human Space Flight oriented Technologies 10 10 29.25 4 - 03 - Generic Space Transportation Technologies 7 17.75 Total TRP 2011-2013 10 44 11.00
2.3.5 SD5 – Telecommunications
Missions and requirements The ESA Telecommunications Programme is designed to maintain and further develop a competitive state-of-the-art satellite telecommunications industry in Europe and Canada through improvement of the technological basis and through implementation of satellite telecommunication systems.
This is achieved by promoting innovation in all elements of satellite communication systems through research and development and including demonstration of complete systems. The scope of the activities of the ESA’s Telecommunications Programme is reflected in the Telecommunications Long Term Plan.
The satellite telecommunication domain is fundamentally dominated by the demand of the commercial Telecommunications market. However, there is an increasing demand of the institutional/public sector for satellite telecommunication systems which is of strategic importance. To maintain the competitiveness of European industry in this market segment, the Telecommunications programme incorporates lines of action addressing the preparation of industry to be able to respond timely to user needs with adequate products, services and applications and to ensure a strong knowledge base. In the coming years it is expected that the satellite telecommunication services will, to a large extent, be a continuation of today’s services with the addition of some new services. The services are: - Fixed, direct Broadcast and Interactive Broadband Satellite Services - Mobile Broadcast Services - Mobile Interactive Services - Institutional and Data Relay Services.
In conjunction with ARTES, the TRP focuses on the following technology requirements: - Fixed and Mobile Satellite Services / Broadcast Satellite Services - Propagation model and fade mitigation techniques for fixed Satcom Services - On board digital processors and Deep Sub-micron Technologies - Telecom Payload Technologies - Ku- and Ka-band multi spot beam antennas - Modelling and Testing Techniques for RFC - Platform Technologies specific to Telecom Satellites - Data Relay System - Advanced signal processing techniques (ground and space) inherited from terrestrial networks - Higher capacity for space and ground, addressing Optical and Q/V bands, both user’s terminals, ground infrastructures and space segment. ESA/IPC(2010)119 Page 20
The TECNET SD5 group reviewed the requirements in ESTER and worked on the preparation of the TRP 2011-2013 work plan taking into account the ARTES 5 plans, using the TRP funding to advance the more immature technologies, so to decrease the missions risks.
Results The TRP 2011-2013 work plan has been set up, fully co-ordinated with ARTES 5. The inputs from an Interdirectorate Working Group on Large Deployable Antennas have been also considered. The group has been active in 2010, with the task to review the mission/market requirements and identify technology needs and technical solutions for large reflectors.
90 activities were presented of which 23 were retained for TRP, encompassing platform and payload techniques and technologies. The total budget requested for all activities retained for the plan is 7.5 M€.
Further activities have been judged of high priority, but are not included for budgetary reasons. However, the TECNET SD 5 will review regularly review the progress on the current plan and adjust the yearly work plans accordingly compliant with the overall budgetary allocation.
Telecommunications: Target allocation vs Actual allocation Target Actual Sub-Domain Budget (M€) # of activities Budget (M€) 5 - Telecommunications 7 25 7.5 Total TRP 2011-2013 7 25 7.5
2.3.6 SD6 – Navigation
Missions and requirements The European GNSS infrastructure comprises two main elements: EGNOS and Galileo.
EGNOS is an augmentation system improving the accuracy, integrity and availability of GPS with the broadcast of GPS-like signals from three geostationary satellites over Europe. Galileo is a joint project of ESA and the EU aiming to deploy a global constellation of 30 MEO satellites and the related ground segment. A first experimental Galileo satellite, GIOVE-A, was launched end 2005, followed by GIOVE-B in 2008. The first operational satellites of the In-Orbit Validation phase are planned to be launched in 2011.
The capabilities of other systems are evolving, namely GPS, but also GLONASS and new global and regional initiatives emerging in China, India and Japan, there is a need for a comprehensive programme of R&D on the evolutions and next generation of the European GNSS infrastructure. The objectives are to keep the competitiveness of European industry and enhance the performance of the European systems so as to be at pace, if not surpassing, the capabilities of those others systems, to anticipate and meet future user needs.
The TRP concentrates on the following activities, coordinating with the GSTP and GNSS evolution programmes: ESA/IPC(2010)119 Page 21
- System and Signal-in-Space Performance Monitoring and accurate investigations - Techniques and Technologies for GNSS Reflectometry - Navigation satellites platform technology - Signal processing techniques - Future GNSS Services User Receiver Technologies - Technologies for intersatellite link - On-board Time and Frequency References - Ground clock technology developments - GNSS Clock Modelling - Timing and synchronisation architectures and techniques - Ionospheric and tropospheric modelling and correction techniques - Improvement of radiation model and design techniques for MEO satellites (GIOVE radiation data exploitation) and geodesy experimental measurements.
Results
43 activity proposals for a total budget of 13 M€ were assessed by TECNET SD6. 15 activity proposals were selected for TRP representing a total budget of 3.4 M€. A number of additional subjects have been earmarked high priority, but are not included for budgetary reasons. However, TECNET SD 6 will review regularly review the progress on the current plan and adjust the yearly work plans accordingly compliant with the overall budgetary allocation.
Navigation: Target allocation vs Actual allocation Target Actual Sub-Domain Budget (M€) # of activities Budget (M€) 6 - Navigation 3 15 3.40 Total TRP 2011-2013 3 15 3.40
ESA/IPC(2010)119 Page 22
2.3.7 SD7 – Generic Technologies and Techniques
SD7: Generic Technologies complements the application driven SDs by taking care of technologies common to two or more application domains, e.g. platform technologies, ground segment technologies, payload technologies such as antennas for Earth Observation and Telecommunication, detectors for Space Science and Earth Observation, etc.
Two elements constitute the main drivers for SD7:
- Technology pull satisfying the need for programme driven multi-domain technologies required for at least two applications, e.g. satellite platform technology, ground segment, payload technology, e.g. RF for telecommunications and Earth Observation, etc. - Technology push, aiming at ambitious objectives in the long-term and as required to allow the evolution of the technology base dictated by non-space drivers. Technology push, should be organized so that it increases performance and reduces costs drastically, and assures European non-dependence.
Approach
The SD7 TECNET is addressing mainly TRP and GSTP. The definition of the plans of work is organized along two lines:
- Sectorial line, where requirements and plans are created along individual Technology Domains (TDs).
- Cross-sectorial line, where requirements and plans are created in a multi- disciplinary fashion, so as to deal with the increasing complexity and system impact of technology developments. This approach shall also enable a more homogenous outcome. An obvious example is S/C avionics where computer H/W, S/W, AOCS and S/C operations have to collaborate closely. Four cross sectorial themes were established considering the priorities and resources available in the overall context of the E2E process. For each cross-sectorial theme an expert group exists with a leader for establishing requirements and evaluating proposals and selecting activities. The group also follows the implementation.
Due to the good progress achieved in the previous TRP cycle it was decided to maintain the previous cross-sectorial lines:
- Improving the way we deliver an operate space systems : Developing technologies, techniques and tools that significantly contribute to reduce time and cost of developing and operating space missions.
- Disruption by evolution: Technology that imply significant spacecraft evolution in S/C avionics. IP in space, Plug-&-Play style avionics, software and software reuse, spacecraft management (FDIR, command and control), AOCS, data integrity.
ESA/IPC(2010)119 Page 23
- Miniaturisation: “How can we bring the terrestrial advances of miniaturisation and the promise of MNT into space?”
- Electronic Components: Focus is on securing development/evaluation of standard components, evaluation and radiation testing. Recent developments in the context of standardisation of onboard architecture, ground-space interfaces, consistency software development and operations have shown the need for a cross sectorial action on technologies for space-ground development, verification and operations.
Generic Technologies and Innovation
During the 16th/17th February of 2010, the ESA Director of Technical & Quality hosted a workshop and a round table, addressing the issue of space and innovation.
The critical question was whether space can be regarded as innovative. In particular, the workshop aimed at trying to understand the state of innovation for space and what would be necessary to preserve the innovative edge of European space. The key themes emerging from this exercise:
- Innovation processes - The role of generic technologies
It was shown that, though sometimes perceived otherwise due to the time scales of space projects, space is very innovative in techniques, technologies and products, processes, markets and business models. It was also shown that space drives innovation and brings innovation back to Earth in a multitude of applications. However, most surprising was the link made by workshop participants between generic technologies and innovation. It was recognised that the availability of advanced generic technologies is critically linked to the future ability of the space sector to innovate. Recent undertakings have largely focussed on the effect of export restrictions on European non-dependence and the ability to freely address the world markets. Although undoubtedly important, this misses the important aspect of innovation. The question here is not related with a level playing field in competing with US and others but with the general question of space systems being able to compete with terrestrial solutions.
Generic technologies in many instances lay the foundation for innovation. If the same level of generic technologies available for ground applications was available to space, the pace of innovation in space systems could significantly increase. This is very well illustrated by the technology stack for electronics. The bottom contains the basic foundry processes, followed by electronic components (e.g. ASICs) with Satellite Avionics System equipment on top of the stack. SMEs that often drive innovation tend to focus on one or two very specific aspects within this stack (e.g. development of microprocessors)
ESA/IPC(2010)119 Page 24
The whole system can only function if all levels are properly funded.
Results: Generic Technologies within the TRP 2011-2013
Proposals in the sectorial line, per individual TD, were evaluated by the TECNET SD7 together with the TD responsible. For the cross sectorial line, working groups worked out a comprehensive programme, evaluated against a dossier established for each of the four lines. Despite the known financial limitations the proposal reflecting the actual needs largely exceeded the means.
SD7 sectorial downselection overview
TD01 - On-board Data Systems TD02 - Space System Software TD03 - Spacecraft Electrical Power TD04 - Spacecraft Environment & Effects TD05 - Space System Control TD06 - RF Payload Systems TD07 - Electromagnetics Technologies and Techniques TD08 - System Design & Verification TD09 - Mission Operations and Ground Data Systems TD10 - Flight Dynamics and GNSS TD11 - Space Debris TD12 - Ground Station System & Networking TD13 - Automation, Telepresence & Robotics TD14 - Life & Physical Sciences TD15 - Mechanisms & Tribology TD16 - Optics TD17 - OptoElectronics TD18 - Aerothermodynamics TD19 - Propulsion Budgetproposals of (k€) TD20 - Structures & Pyrotechnics TD21 - Thermal TD22 - Environmental Control Life Support (ECLS) and ISRU TD23 - EEE Components TD24 - Materials & Processes TD25 - Quality, Dependability and Safety TD26 - Others 0 5000 10000 15000 20000 25000 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 Technology Domain
Approved by TDR After TDR prioritization Preselected for TRP WP
During the exercise some clear priorities emerged.
ESA/IPC(2010)119 Page 25
DSM (Deep-submicron) Technologies IC technology significantly defines what can be cost effectively implemented, drawing the limits of the levels of integration, power consumption and performance that can be achieved in payload instruments and platform avionics. The analysis presented to the IPC in 2006 on DSM capabilities (Ref: ESA/IPC(2006)57)) showed that the European manufacturers were approximately 5 years behind their US counterparts. Export licence free access to these DSM technologies would improve and sustain European competitiveness and a goal was set to challenge the US space qualified DSM by 2014.
In the previous cycle, the TRP started activities for establishing a 65 nm Deep Submicron (DSM) technologies space qualified foundry process in Europe with ST Microelectronics. Furthermore, activities on a new generation of microprocessors were started. During the preparation the current TRP it became clear that there is a significant lack of funding and that the issue if not properly addressed will pose a significant risk to European space. It must be emphasized that IC technology performance significantly defines what can be cost effectively implemented at an equipment level. Moreover, IC performance has significant knock on consequences, effectively limiting the equipment level performance.
The space qualified range of 350nm ASICs have already been declared obsolete with the announcement in 2010 of last buy orders. The 180nm based ASICs will become obsolete within the next 5-7 yrs. ICs built on these processes will be systematically dropped from the product catalogues as the niche markets for these devices continues to diminish in favour of more profitable terrestrial product lines based around the DSM processes (90nm, 65nm and below). DSM, driven by the consumer electronics market, but if properly adapted to survive the space environment, is necessary for achieving the higher processing and performance requirements envisaged for the next generation ESA missions. Consequently, in order to meet the requirements of ESA future missions, access to space qualified DSM process is mandatory for the next generation ICs.
Giving the performance increase and the obsolescence of the previous generation, all European space programs require ITAR free access to DSM processes in order to maintain European competitiveness in the global market and serve the European Space programme with state-of-art technology.
Without independent European access to DSM technology, there would be a bigger reliance upon US IC suppliers and the large commercial IC foundries in the Far East e.g. via DARE-library approach. This scenario would have the apparent advantage of not having to invest in our own new European DSM ASIC and FPGA technology, but it would in reality bring the disadvantage of not having visibility and control on the stability and space quality of these IC manufacturing processes and IPs, since the Asian foundries are driven by the needs of the much lager terrestrial commercial markets (typically several hundred devices for space versus several hundred thousand devices for terrestrial applications). Space IC vendors in the US are subject to tight export controls and limitations. This would subsequently result in increasing lead times and procurement uncertainties, and additional large investments to define and implement space quality screening of the ASICs and FPGAs coming from non European foundries/vendors. ESA/IPC(2010)119 Page 26
Consequently, a European solution is clearly preferred in order to avoid ITAR (or any other export control issues further down the line), but most importantly to minimize the difficulties and large costs of ensuring the necessary space quality of the design (IP & tools) and manufacturing aspects. Because industry recognised a major opportunity to enter the DSM market, DSM activities are already co-funded by industry as the spin-ins from their commercial processes. However, due to risky nature of the development and uniqueness of the testing and assembly requirements for space applications (e.g. hermetic sealed packaging), outside (public) funding has been and will still be required to share these risks.
The development of DSM for space applications was started through a number of initiatives in 2006, funded through significant investments by the TRP. The TRP will continue to provide significant funding (~6 M€) in the coming years (2011-2013) for following main lines:
- 65 nm process (ST Microelectronics) - Next Generation Microprocessors (LEON) - Field Programmable Gate Array (FPGA)
However, giving the very large investment required, it is also clear that the TRP is not the solution and an end to end commitment for the remaining development and qualification via various funding instruments needs to be defined.
The issue is so important that it is proposed to include a new cross-sectorial theme on DSM within SD7.
Solar Cells All ESA missions rely on large solar arrays. Therefore solar cells can be a significant mass, size and cost driver. The objectives are to increase the efficiency of solar cells to reduce the needed area and complement this with mass optimisation at substrate level.
The only European company having a worldwide competitive product is AzurSpace with their GaAs based triple junction cells 3G28 cell (28% efficiency). Large system integrators have long term agreements with Azur. However, there is strong competition from US companies Spectrolab, Emcore which have access to much greater R+D funding via US government. (18M$ in 2009). Development of fully European cells from Azur has resulted from successive TRP contracts from 2002, with parallel and harmonised developments funded directly by DLR, and qualification funded by ARTES.
So far only the Europe and USA are global players in the space solar cell market, but China may enter this market segment as well. The development cost for the next generation solar cell to arrive at a commercial product may be as much as 20 M€.
The performance of the present triple junction technology is at its limit does not allow for efficiencies >30%. There are several new technical approaches to initially achieve efficiencies around 32% and in a next step 35%. For the time being all these approaches are equally promising. There are two routes of development to accomplish this: - By an IMM (inverted metamorphic) growth approach. This solar cell type will be by design a ultra-thin cell requiring that a commercially attractive approach is found to arrive at a 20 micron cell. ESA/IPC(2010)119 Page 27
- The evolution of the classic cell build-up resulting in a solar cell of either the standard thickness (90mm – 150mm) or use an equivalent approach like for the IMM cell to arrive at an ultra-thin product
It is essential the both developments are treated equally. Even if the classic cell build- up takes the lead and becomes a product first, the IMM technology might be required to arrive at higher efficiencies in the future.
Considering the limited funds available from the 2011-2013 TRP work-plan, it is proposed to pursue both approches within a single substantial activity on “Next Generation Solar Cells With 33% Target Efficiency”. Milestones will be established at which it will be decided which technology has a better chance to become a commercial product first and what are the optimum development steps and technologies to focus on.
At the time a smaller activities on Quantum Well Solar Cells will look into longer-term aspects.
APS Detectors Optical detectors are the core of optical instruments and payloads in research and service driven missions.
In the visible spectral range, Charge Coupled Device (CCD) and Complementary metal-oxide-semiconductor (CMOS) sensors or Active Pixel Sensors (APS) are the two possible alternatives for forthcoming missions. CCD is a very mature available technology. CMOS APS detectors are already being used and this technology will probably replace CCD in the coming years due to attractive features and simplification of payload architectures.
APS works differently as compared to CCD technology and this could be exploited to achieve the reduction of mass and power demands, and also to simplify the manufacture and test of such instruments and payloads.
However, there is no solution inside Europe for a complete CMOS detector supply chain. Within the current space programs the foundry operations are performed in Israel (Tower), Taiwan (TSMC, UMC), Malaysia (XFAB).
Considering the importance of visible detectors for the future space programs, the availability of a European CMOS Detector Supply Chain is seen as a priority for the space community. Activities are foreseen within SD1 and SD7. APS detectors will also be considered for SD2. Total funding should be around 2.5 M€ within the TRP 2011- 2013.
ESA/IPC(2010)119 Page 28
Cross-sectorial themes
Disruption by evolution: Avionics The activities are centred on standardising the interfaces between onboard hardware and software elements or “building blocks”. Interfaces between ground and flight systems to harmonise space/ground interfaces are also covered.
To increase the level of cooperation between the disciplines, a number of joint prototyping activities are being undertaken. Prototyping includes end-to-end activities with test-beds located in ESOC and ESTEC, specifically targeted the use of file based mass memories and the upgrade and use of ECSS and CCSDS standards.
The vast majority of activities have been coordinated with industry and national space agencies through the SAVOIR initiative. Resulting from the harmonization of avionics embedded systems, the SAVOIR initiative has become a successful forum for agreeing and harmonising the approach to avionics embedded systems. This is essential to support the establishment of a product policy in the domains. SAVOIR is coordinated by the SAVOIR advisory group (SAG) which consists of representatives of ESA, National Space Agencies and industry at all levels.
System Services Application BB OBCP PUS library/ interpreter Plan/ TMTC Autonomy AOCS Framework MTL services OBT Mgmt Thermal Mission TL/ Ground Equipment Mode mgmt Context Mgmt Power Segment Mgmt Libraries: Central FDIR P/L Manager SSMM Mgmt Math, Security, CFDP Payload,…
PUS Software bus Sensors (Star Trackers, Sun sensors, Gyros, Earth sensors, magnetometers)
Execution framework Actuators (Reaction wheels, magneto torquers, Payloads & Middleware services thrusters, etc) Instruments Application Layer SOIS High Speed SOIS Subnetwork Standardized Legacy Standardized Telemetry Layer Communication devices devices devices Encryption RTOS ECSS Datalink Services TM/TC SSMM P rotoc ols DSU support Storage Compression Essential Essential TM TM BSP
TC CFDP Payload Data decoder Processing OBC Hardware DSP CPU/ HW Safe Guard TM Compress DSU Encoder Encrypt Multicore watchdog Memory
RTU Pa yload Control Security Filing CAN RS422 RAM OB Timer Time synch Micro Digital Computer Unit System controller Se nsor bus Boot MIL-1553 SpW EEPROM Reconfig SOIS SOIS PROM Module SOIS ADCs / DACs SOIS SOIS Layers Layers Layers Layers Layers
Onboard Communications H/W (e.g. MIL-ST D-1553B, SpaceWire, CAN RS422)
The figure above shows the conceptual reference architecture and the key building blocks where standard interfaces will assist in implementing embedded systems and plug and play.
ESA/IPC(2010)119 Page 29
CPU CPU CFDP
PUS SOIS PUS SOIS AOCS AOCS FDIR Algorithms DSU SGM DSU SGM
FDIR SpaceWire Reconfiguration TM/TC Protocols unit Standard I/Fs CPU
RTU P&P Filing System SpW SpW FDIR COTS Memory AOCS AOCS Digital I/O MMU Devices Devices
Combined RASTA and FDIR Test-bench AOCS-Test bench
TM/TC
CFDP
PUS
SM&C Ground Test-Bench
Data systems technology will use the latest Packet Utilisation Standards (PUS) (with associated library update) to provide standardised mass memory access. For Failure Detection Isolation and Recovery (FDIR), basic capabilities will be defined in addition to the relevant SpaceWire network management prototyping. An assessment of commercial bus and local interfaces will be done to prepare the establishment of appropriate ECSS standards. Device virtualisation and electronic data sheets for onboard devices will be evaluated and the best method for defining characteristics of onboard devices using machine readable formats will be selected. Plug and play prototype techniques to automatically discover, connect and configure onboard devices will be developed. Advanced multi-layer error correction techniques will be prototyped to build a general purpose solid state mass memory building block based on commercial memory. Protocol standards will be defined for data communication between AOCS units and the data handling system as identified by the SAVOIR working group.
The avionics theme will also include an AOCS element including a test bench for SpaceWire units.
For the ground segment the following are to be investigated. File based operations is the future of spacecraft operations and will provide a platform for extensive cooperation in many areas between ESOC and ESTEC test-bed elements. The relationship between SM&C, PUS and Spacecraft Onboard Interface Services (SOIS) and the potential impact on flight and ground systems will be addressed. Increasing autonomy requires flight dynamics ground operations to shift from classical commanding and execution to preparation of GNC inputs. GNC onboard aspects require a close interaction with the operations experts.
With regards to software, the objectives are to master complexity while coping with increasing functionality, e.g. security, autonomy, etc, to strengthen the links system – software and software – hardware and to establish more robuts industrial process for software development... ESA/IPC(2010)119 Page 30
These initiatives are increasingly coordinated with CNES ISIS initiative.
Improving the way we deliver an operate space systems : E2E System Engineering This theme addresses system design and verification concerns in all domains, in all phases of the life-cycle to assist the process of space system engineering. It is a continuation of the initiative begun in the frame of TRP 2008-2010.
The overall goal of improving the way to deliver space systems has as driving objectives: - to reduce the cost and schedule in projects - to manage increasing complexity - to assure quality - to strengthen competitiveness
This is part of the Agency continuous effort for innovation in processes and is consistent with actions in e.g. Concurrent Engineering evolution, laboratories, etc. It is an effort to move from document to model driven engineering.
There is an actual need to improve system engineering: - “Stovepipe” approaches (i.e. domain specific with limited cross-sectorial harmonisation) imply multiplication of efforts and are prone to errors - There are costly inconsistencies in System Data across actors and along project life-cycle - There are bottlenecks in AIT / AIV - Weak initial verification leads to late problem detection and high fixing costs - The interfaces between actors (e.g. ESA / industry) are not optimal
There are advances in techniques and technologies being successfully applied in key industrial domains that used for space would allow achieving the objectives: - Model-Based System Engineering - Virtual Design / Testing capabilities - System modelling / simulation - Standardisation
Operations AIV Design feedback and improvement Anomalies Analyses Simulations Top-Down Bottom-Up Design Production, V&V V Mission Need & Validation V Feasibility Study V Deployment Phase E ly & r V Conceptual Design a Phase A E ly r Verification a E System / Preliminary Integration Phase B Design Assembly Phase D Manufacturing
Detailed Design
(Development & Phase C Qualification)
Model-based Validation & Verification
ESA/IPC(2010)119 Page 31
The action addresses the end-to-end engineering process and includes as main axis of action:
1. Model-based System Engineering (MBSE), a paradigm to support the system development process - Mission/System specification supported by modelling and prototyping - End-to-End (E2E) mission performance simulations in order to allow a more capability / service oriented system engineering; this includes the establishment simulation frameworks, standards, etc - Analysis and design support by simulation, including also the establishment of references architectures, standards ETM 10-21, ETM 40-07 - Application of concurrent engineering principles throughout the lifecycle 2. Space system data repository to be made operational and introduced in the industrial context to enable the MBSE elements. It also includes establishment of standards ETM-10-23, ETM-10-25 3. Methods for complex AIV/AIT and feedback of experience acquired during AIV (discoveries during tests, effectiveness, etc) and during operations (anomalies mining and traceability, how to avoid by design, how to discover by verification, etc)
Miniaturisation This disruptive theme is intended to drastically reduce the needs for resources, foot- print, volume, mass, power, of space missions. The objective is of general validity for all space missions but is critical for space science and exploration missions and for systems in micro-sat range.
Two main ways can be considered when addressing miniaturization: - Miniaturisation by technology: Adoption of a disruptive technology that reduces both mass and size (volume) and power of a given spacecraft functionality - Integration: Multiple functionality in a single/fewer modules or units
Several non-linear effects become apparent when miniaturisation technology and concepts are implemented at spacecraft and mission level: - The introduction of microsystems at the component level of avionic, data- handling and payload components, amongst others. - Integrating these smaller components, units and systems together in new manners reduces the number of boxes and the amount of harness. - Sub-system savings resulting from a reduction of mass/power/envelope of others and further iterations as necessary. E.g. propellant savings from general spacecraft dry mass reduction, structural mass savings from both lower load demands (smaller/fewer units) and new materials or reduced power demands requiring lower battery capacity and solar array size.
The theme was started in the previous 3-year plan around strawman mission called NEOMEX driven by technology push. The approach is complemented with a top-down approach, need to reduce by a factor 2 the mass of the 1 ton (dry mass) class spacecraft.
A reference study, Minimex, was carried out in concurrent engineering in ESA’s Concurrent Design Facility looking for ways to implement the well known Mars Express mission for a fraction of the resources. In particular, advantages are expected ESA/IPC(2010)119 Page 32 from GaN based power amplifiers for communications, integrated avionics, solar arrays implementing ultra-thin cells and sensors on chip.
The theme targets activities for which TRL 5 can be achieved no later than 2017 and includes: - Breadboards and demonstration of new disruptive concepts - Space qualification of advanced miniaturisation enabling components - Equipment options for focus based upon MiniMEX: - Sensors-on-a-chip - Integrated RF spacecraft telecommunications - Passive reconfigurable thermal control - Antennas: smaller, lighter and multi-functional for interplanetary X-band applications
The activity selection was based upon technology priorities within the allocated budget for the cross sectorial theme. To facilitate this, a miniaturisation cross sectorial working group was established to propose a set of activities that were presented to the SD7 TECNET. Activities selected are those that have shown to provide the highest impact on S/C level.
Components The European Component Initiative (ECI) is aiming at providing an alternative supply chain within Europe for space qualified Electrical, Electronic, Electro-mechanical (EEE) components that had previously only been available from the US and are subject to potential export restrictions (ITAR).
The TRP plan for electronic components has to be seen in connection with the ECI, supporting the ECI’s objective and maintaining f innovation. In the overall context priorities within the TRP 2011-2013 are: - Mixed signal IC technology & devices - Very large gate count FPGA technology - Compound semiconductor technology - MEMS Devices & Processes
Mixed Signal IC Technology & devices: Recent progresses in terrestrial consumer electronics e.g mobile telephones and cameras are enabled by mixed signal IC technology. There is an increasing need for applying mixed signal technology also for space, examples are APS imagers and analogue digital converters (ADC). Priorities for the TRP 2011-2013 are APS based imagers and ADCs for Earth Observation and Space Science instruments. A first evaluation and characterisation of mixed signal ASIC flow will also be addressed.
Very Large Gate Count FPGA Technology: The increasing costs and complexities associated with developing project specific ASICs (Application Specific Integrated Circuits) has led to projects switching to the use of more flexible Field Programmable Gate Arrays (FPGA). There is a clear market opportunity to supply more powerful ITAR-free space qualified FPGAs, being addressed through the European FPGA roadmap. Currently there are 280K FPGA ATF280 prototypes available. Fully qualified devices are now expected by Q4 2010. However, compared to terrestrial used FPGA’s, these are still relatively small devices. In order for FPGA’s to be a viable alternative to increasingly costly ASICs, the ESA/IPC(2010)119 Page 33 available gate count must increase significantly. Another feature is reprogrammability, reprogrammable FPGAs also offer less expensive design and manufacturing phases. The FPGA development will be included in the new cross-sectorial line on DSM.
Compound Semiconductor Technology: Within the previous TRP/GSTP cycle, a European Gallium Nitride (GaN) component development strategy has been kicked off to improve GaN device reliability for space applications and to establish an independent, space compatible, European supply chain for discrete GaN devices. The target is to have a purely European sustainable supply chain for GaN-based space technologies in place by 2014. This will form the basis for proposed device development within the TRP 2011-2013 e.g. see SD1. Complementing this effort on GaN, there are several activities foreseen on the evaluation of Silicon Carbide devices.
MEMS devices and processes: The activities proposed for the TRP are based on the European Micro/Nano- Technologies (MNT) Development Strategy for Space Applications: ESA/IPC(2009)147.
Results
Generic Technologies: Actual allocation # of Budget Sub-Domain activities (M€) 7 - 01 - On-board Data Systems 5 1.55 7 - 02 - Space System Software 1 0.4 7 - 03 - Spacecraft Electrical Power 3 3.7 7 - 04 - Spacecraft Environment & Effects 2 0.65 7 - 05 - Space System Control 5 1.35 7 - 06 - RF Payload and Systems 3 0.85 7 - 07 - Electromagnetic Technologies and Techniques 6 1.35 7 - 08 - System Design & Verification 3 0.85 7 - 09 - Mission Operations and Ground Data Systems 6 1.15 7 - 10 - Flight Dynamics and GNSS 1 0.225 7 - 11 - Space Debris 2 0.375 7 - 12 - Ground Station System & Networking 4 1.25 7 - 13 - Automation , Telepresence & Robotics 1 0.4 7 - 14 - Life & Physical Sciences 2 0.4 7 - 15 - Mechanisms & Tribology 3 1.23 7 - 16 - Optics 2 0.5 7 - 17 - Optoelectronics 2 0.75 7 - 18 - Aerothermodynamics 5 0.65 7 - 19 - Propulsion 5 1.57 7 - 20 - Structures & Pyrotechnics 5 1.75 7 - 21 - Thermal 5 1.55 7 - 22 - Environmental Control Life Support (ECLS) and In-Situ 0.25 Resource Utilisation (ISRU) 1 7 - 24 - Materials & Processes 6 1.4 7 - 26 - Spacecraft Avionic System 18 5.35 7 - 27 - End to End System Design Processes 11 3.00 7 - 28 - Electronic Components 18 6.00 7 - 30 - Deep Sub Micron Development 6 5.35 7 - 31 - Miniaturisation 12 5.45 Total TRP 2011-2013 142 49.30
ESA/IPC(2010)119 Page 34
2.3.8 SD9 – Mars Robotic Exploration
The work plan ESA/IPC(2009)79, add1 presented end 2009 is being implemented. Updates are expected in 2011 when the needs of new Robotic Exploration mission candidates are defined.
2.4 Conclusions and Issues
- The E2E process for the development of technology has been applied, the TRP 2011-2013 has been prepared, inputs have been collected that can be applied to the GSTP and the application specific programmes, - The E2E process is an Agency wide undertaking supervised at the highest level by a Directors’ Subcommittee for Technology, - The essence of the process is that user drive and technology advances are balanced. - The effort spent in the E2E process is significant and care must be taken so that it is justified by gains in performance,
The exercise shows lack of assured resources in all domains. The lack of funding is most evident in the basic technologies, such as semiconductors, sensors, materials etc. This may impact in the future Europe’s ability to innovate in space. It has to be clearly stated that there is wide gap between European ambitions and European reality.
ESA/IPC(2010)119 Page 35 TRP 2011-2013 Preliminary Selection by Technology Domain
12
TD01 - On-board Data Systems TD02 - Space System Software TD03 - Spacecraft Electrical Power TD04 - Spacecraft Environment & 10 Effects TD05 - Space System Control TD06 - RF Payload Systems TD07 - Electromagnetics Technologies and Techniques TD08 - System Design & Verification TD09 - Mission Operations and Ground Data Systems 8 TD10 - Flight Dynamics and GNSS TD11 - Space Debris TD12 - Ground Station System & Networking TD13 - Automation, Telepresence & Robotics TD14 - Life & Physical Sciences 6 TD15 - Mechanisms & Tribology TD16 - Optics M€ TD17 - OptoElectronics TD18 - Aerothermodynamics TD19 - Propulsion TD20 - Structures & Pyrotechnics TD21 - Thermal 4 TD22 - Environmental Control Life Support (ECLS) and ISRU TD23 - EEE Components TD24 - Materials & Processes TD25 - Quality, Dependability and Safety TD26 - Others 2
0 TD01 TD02 TD03 TD04 TD05 TD06 TD07 TD08 TD09 TD10 TD11 TD12 TD13 TD14 TD15 TD16 TD17 TD18 TD19 TD20 TD21 TD22 TD23 TD24 TD26
1 - Earth Observation 4 - Space Transportation & Re-entry Technologies 5 - Telecommunications 6 - Navigation 7 - Generic Technologies
ESA/IPC(2010)119 Page 36
3 ACTIVITIES FOR 2011-2013
3.1 Key to Tables
The TRP Preliminary Selection for 2011-2013 is presented along the following headings:
– Technologies related to Earth Observation
– Technologies related to Science
– Technologies related to Human Spaceflight & Exploration Preparation
– Technologies related to Space Transportation & Re-entry Technologies
– Technologies related to Telecommunication
– Technologies related Navigation Payloads
– Generic Technologies & Techniques
– Technologies related to Mars Exploration
Budget: The total Contract Authorisation (CA) values are given in KEURO, at yearly economic conditions.
3.2 Activity Template
Together with the activity description the following information is reported:
Objectives: Provides short summary of the main goals of the activity.
Description: Describes the activity, providing the context information, the purpose of the activity and the main tasks.
Deliverables: Provides short description of the tangible outcome e.g. breadboard, demonstrator, S/W, test data. A final report is standard for every activity.
Application Need/Date: Describes the required TRL level and date for the technology development of which the respective activity is part of on the base of the maturity required by the application. The general rule is that a requirement specifies the need date for a product. For equipments/payloads this is in general TRL 5/6, - the level ESA/IPC(2010)119 Page 37
generally required for Phase B of a project. For S/W and tools separate readiness levels are defined below
Current TRL: Describes the current TRL level of the product that is going to be developed in this activity.
Target TRL: The TRL level expected for the product at the end of the activity. For equipments TRP usually concludes with TRL 3/4, GSTP at level 5/6. However in the case of components target TRL level in TRP could be higher.
Technology Readiness Level, as stated by NASA, to be achieved at end of the activity
TRL1 - Basic principles observed and reported TRL2 - Technology concept and/or application formulated TRL3 - Analytical and experimental critical function and/or characteristic proof-of-concept TRL4 - Component and/or breadboard validation in laboratory environment TRL5 - Component and/or breadboard validation in relevant environment TRL6 - System/subsystem model or prototype demonstration in a relevant environment (ground or space) TRL7 - System prototype demonstration in a space environment TRL8 - Actual system completed and "flight qualified" through test and demonstration (ground or space) TRL9 - Actual system "flight proven" through successful mission operations
Technology 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 (Months): Duration of the activity (e.g. 24 month)
Reference to ESTER: Identifies the related Dossier 0 Requirement
SW clause: Special approval is required for activities labelled: either “Operational Software” or “Open Source Code”, for which the Clauses/sub-clauses 42.8 and 42.9 (“Operational Software”) and 42.10 and 42.11 (“Open Source Code”) of the General Clauses and Conditions for ESA Contracts (ESA/C/290, rev.6), respectively, are applicable. ESA/IPC(2010)119
Page intentionally left blank ESA/IPC(2010)119
ANNEX I
TRP Work Plan 2011-2013
List of Preselected Activities TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX I: List of Preselected Activities
1 - Earth Observation
1 - 01 - Microwave Payloads
Technology TRP Ref Activity Title Budget Domain
TD06 T106-301ET Study of a Miniaturised Altimeter 200
TD06 T106-302ET P-band Multiphase Centre SAR and Ice-Sounder 200
TD06 T106-303ET Study of Multi-channel Ka-band SARs for moving target indication 200
TD06 T106-304ET Single GaN chip HPA/LNA for Radar Applications 550
TD06 T106-305ET Digital receiver for radiometers 500
TD06 T106-306ET Switch mode amplifier for P /L band 500
TD06 T106-307ET Integrated receiver front-ends for radiometers 500
TD06 T106-308ET Study of ocean currents with multi-channel C-band digital beamforming SAR 200
TD06 T106-309ET Mm-wave mixers with low-barrier diodes 250
TD06 T106-310ET Feasibility study on pulsed HPA for Ka-band SAR instruments 150
Study on advanced radiometer for sea surface temperature (SST) TD06 T106-312ET 250 observations
TD07 T107-301EE Ka-band SAR backscatter analysis in support to future applications 150
TD07 T107-302EE SAR Wave INteraction for Natural Targets Over Land (SWINTOL) 150
TD07 T107-304EE RFI Detection and Mitigation techniques for EO passive missions 200
TD07 T107-305EE Improvements of the understanding of microwave sea surface scattering 100
TD07 T107-306EE Compact Ku-Band or Ka-Band Altimetric antenna for LEO constellation 200
Interferometric antennas at Ku- and Ka-band with modest baselines for wide TD07 T107-307EE 400 swath altimetry
TD07 T107-309EE Study on advanced multiple-beam radiometers 300
TD07 T107-310EE Wavemill Antenna concept and critical breadboarding 500
TD07 T107-311EE Innovative SAR based on Sparse Direct Radiating Array antenna 200
TD23 T123-301QT Preliminary Reliability Assessment of Millimetre-Wave Low Noise Amplifiers 300
TD23 T123-302QT Preliminary Reliability Assessment of Millimetre-Wave Detectors 300
Page 1 of 20 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX I: List of Preselected Activities
Total 1 - 01 - Microwave Payloads 6300
1 - 02 - Optical Payloads
Technology TRP Ref Activity Title Budget Domain
TD07 T107-308EE Synergy between lidar and passive optical measurements 250
TD07 T107-312EE Red edge positioning (REP) techniques for Earth Observation optical missions 150
Focal plane direct deposited detector filters with high peak transmittance and TD16 T116-301MM 300 out of band rejection
TD16 T116-302MM Innovative Materials for Super Black Low-Weight / Low-Cost Baffle 300
TD16 T116-303MM Ultralight Reflective Telescope with Low Surface Roughness 300
Design and manufacturing of spectral filters with low "Large Angle Scatter" TD16 T116-304MM 180 (LAS)
TD16 T116-305MM Imaging Liquid Crystal Tuneable Filter (LCTF) technology demonstrator 400
TD16 T116-306MM Advanced laser ranging technologies for altimetry 600
TD16 T116-307MM Advanced large FOV UV/VIS/NIR/SWIR spectrometers 250
Large field-of-view static imaging FTS with Stationary Wave Integrated Fourier TD16 T116-308MM 350 Transform Spectrometer (SWIFTS)
Alternative polishing layers on ceramic materials for high performance optical TD16 T116-309MM 400 mirrors
TD16 T116-310MM Polishing techniques for low-scatter surfaces 250
TD16 T116-311MM Non-polarising broadband optical coatings 200
TD16 T116-312MM Optical Correlator testbed for high-resolution imaging from geostationary orbit 500
TD17 T117-301MM InAs APD development for NIR and SWIR LIDAR applications 500
2.05 Microns Pulsed Holmium-Laser for Atmospheric CO2 and Methane TD17 T117-302MM 600 Monitoring
TD17 T117-303MM CMOS APS spectral sensitivity optimisation 750
Investigation of Harmonic Conversion efficiency for space qualified Non Linear TD17 T117-304MM 400 Optical (LNO) crystals
TD17 T117-305MM Generic frequency converter unit for spaceborne lidar instruments 500
Compact vacuum chamber for an Earth gravity gradiometer based on TD17 T117-306MM 400 laser-cooled atom interferometry
Versatile high-fidelity reference gas cell as laser wavelength stabilisation unit TD17 T117-307MM 400 for DIAL measurements of atmospheric trace gases
TD17 T117-308MM Compact Optical Attitude Transfer System 200
Page 2 of 20 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX I: List of Preselected Activities
TD17 T117-309MM Laser Stabilisation Unit for Interferometric Earth Gravity Measurements 500
TD17 T117-310MM Large area SWIR detector array development 900
TD23 T123-303QT Back end microlenses deposition process evaluation for CMOS image sensors 400
Total 1 - 02 - Optical Payloads 9980
1 - 03 - Platforms / Others
Technology TRP Ref Activity Title Budget Domain
New Techniques for lossy multi/hyperspectral compression for very high data TD01 T101-301ED 150 rate instruments
TD01 T101-302ED SpaceWire SpaceFibre network bridge 500
TD05 T105-301EC AOCS and image navigation and registration for Earth observation from GEO 400
TD05 T105-302EC Next Generation Gravity mission: AOCS solutions and technologies 350
TD07 T107-303EE Test-bed for channel modeling in EO Ka band DDL systems 150
Miniaturised Gridded Ion Engine breadboarding and testing for future Earth TD19 T119-301MP 350 Observation missions
Development of a Functionally Graded / Composite Spacecraft Thruster TD19 T119-302MP 150 Nozzle
TD19 T119-303MP Consolidation of micro-PIM Field Emission Thruster Design 300
TD21 T121-301MT 2-stage cooler for detector cooling between 30K and 50K 500
TD21 T121-302MT Development of a 40-80K vibration-free cooler 400
TD24 T124-301QE Fast contamination modelling tool 250
TD26 T126-301GT Enriching EO ontology services using Product Trees - PTREE 150
TD26 T126-302GT EO Ground Segment elements automation: feasibility - GEAF 300
TD26 T126-303GT PDGS e-Collaboration - PDGSE 200
TD26 T126-304GT Virtual workspaces for EO Scientists - VIRES 150
TD26 T126-305GT Optical Multisensor Radiance Data Fusion Techniques - OPTIRAD 400
Total 1 - 03 - Platforms / Others 4700
Page 3 of 20 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX I: List of Preselected Activities
4 - Space Transportation & Re-entry Technologies
4 - 01 - Launchers oriented Technologies
Technology TRP Ref Activity Title Budget Domain
TD02 T402-301SW Hardware-Software Dependability for Launchers 300
TD03 T403-301EP Enhanced power sources compatible with extended thermal environment 300
TD03 T403-302EP Sources for high power / energy demanding devices 200
TD04 T404-301EE Improvement of solar flare prediction 100
Feasibility study of in-flight model validation and performance analysis of TD05 T405-301EC 300 launchers GNC
TD05 T405-302EC Launcher GNC Simulation Sizing Tools 300
TD06 T406-301ET GPS/Galileo Receiver Signal techniques for Launchers 200
Robust TM System for Future Launchers - exploring space-time coding TD06 T406-302ET 300 (MIMO)
TD18 T418-301MP Waterhammer tests with cryogenic fluids 100
TD18 T418-302MP Physical modelling of scale effects on cryogenic fluid flows 250
TD18 T418-303MP Hot Testing Facilities for ELV Propulsion Characterization 150
Advanced measurement techniques for validation of CFD for cryogenic flows TD18 T418-306MP 250 in reduced gravity
TD19 T419-301MP Environmentally friendly hydrogen production 150
TD19 T419-303MP Experimental Characterization of Cavitation Erosion 300
TD19 T419-304MP Laser Ignition Technology 200
Space propulsion applications for High enthalpy solid Hydrogen gas TD19 T419-305MP 450 generation
Feasibility of a shock attenuation system for heavy payloads on Ariane 5 ECA TD20 T420-301MS 300 launcher
TD20 T420-303MS Demonstrator of Carbon anisogrid payload adapter 300
Impact of thermo-mechanical loading history on mechanical properties and TD20 T420-304MS 300 verification of aerospace materials
TD20 T420-305MS ELV fatigue load spectra development 250
Equivalent Modal Damping Method for Condensed Solid Rocket Motor Finite TD20 T420-306MS 50 Element Models
Identification of dominant modes in the dynamic analysis of free-free systems TD20 T420-307MS 50 with high modal density
TD21 T421-303MT Advanced foams for cryogenic tanks insulation 200
Page 4 of 20 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX I: List of Preselected Activities
Assessment of existing plastic optical fibers and associated optical connectors TD23 T423-301QT 200 for launcher application
TD24 T424-301QE On-board particulate contamination sensor 250
TD24 T424-303QT High temperature characterization of phenolic materials used in rocket engines 300
TD24 T424-304QT Advanced aluminium based material for cryo-reservoir applications 250
Total 4 - 01 - Launchers oriented Technologies 6300
4 - 02 - Human Space Flight oriented Technologies
Technology TRP Ref Activity Title Budget Domain
Characterisation of high enthalpy facilities and streamlining of calibration and TD18 T418-304MP 300 tests
TD18 T418-305MP Dynamic stability of capsules and blunt bodies at angle of attack 300
TD18 T418-307MP Aerodynamic design tool for parachutes 200
TD18 T418-308MP Enhancing Test Facilities for Aerodynamic Decelerators 150
TD18 T418-309MP EXPERT PFA on General Hypersonic Fluid Dynamics 500
TD18 T418-310MP Modelling for future light-weight ablating materials 275
EXPERT Experimental investigation of the spatial flow organization around TD18 T418-311MP 300 roughness elements in a hypersonic boundary layer
TD19 T419-307MP 10-kW Hall-effect thruster optimized for space transportation 400
TD20 T420-302MS Parachute Deployment Device 250
Ablative Material Optimisation and Definition of Material Families adaptable to TD21 T421-302MT 300 various Applications
Total 4 - 02 - Human Space Flight oriented Technologies 2975
4 - 03 - Generic Space Transportation Technologies
Technology TRP Ref Activity Title Budget Domain
Ultra-wideband as a multi-purpose robust and reliable wireless communication TD01 T401-301ED 500 technology for tests, spacecraft and launchers
TD02 T402-302SW Missionisation process for multi-vehicle missions 300
TD07 T407-301EE Characterisation of the electrostatic environment of launchers 200
Page 5 of 20 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX I: List of Preselected Activities
TD07 T407-302EE Magnetic window technique for mitigation of RF blackout for re-entry vehicles 200
TD19 T419-302MP Models for Solid Rocket Motors Nozzle Erosion and Ablative Shields 200
Applying acoustics for positioning and trapping cryogenic propellants in TD21 T421-301MT 175 microgravity
TD24 T424-302QE Biodegradable materials for launcher systems 200
Total 4 - 03 - Generic Space Transportation Technologies 1775
Page 6 of 20 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX I: List of Preselected Activities
5 - Telecommunications
5 - Telecommunications
Technology TRP Ref Activity Title Budget Domain
TD01 T501-301ED Deep Sub Micron 65nm, high speed serial link and PLL (Phase 2) 1000
TD04 T504-301EE Compact hot plasma monitor for telecom satellites 300
GEO telecoms radiation tools efficiency improvement with methods and TD04 T504-303EE 200 geometry exchanges for industrial tools
TD06 T506-301ET On-Board Processor for Dual Polarization Mobile Payloads 200
TD06 T506-302ET Interference management techniques for satellite networks 200
TD06 T506-303ET Ultra low phase noise reference oscillator 300
TD06 T506-304ET Concepts and Techniques for Reconfigurable Multiplexers 300
TD06 T506-305ET Diamond supporting rods for high power helix TWTs 300
TD06 T506-306ET Lossless Beamforming Networks for Overlapped Sub-Array Antennas 300
TD06 T506-307ET Techniques for ultra wide stopband IF filters 250
TD06 T506-308ET Advanced modem techniques for future satellite access networks 250
TD07 T507-301EE Lens-Like Multiple Beam Antenna 250
TD07 T507-302EE Shared aperture reflector antenna 150
Antenna architectures and technologies for reduced beamwidth multiple beam TD07 T507-303EE 300 coverage
TD07 T507-304EE Transmit-Receive multiple beam antennas based on direct radiating arrays 200
TD07 T507-307EE Reflectarray antennas with improved performances and design techniques 250
TD07 T507-308EE Advanced fuse blowing models for accurate transients prediction 150
TD15 T515-301MS Innovative scalable large deployable antenna reflectors 750
TD16 T516-302MM Validation of turbulence mitigation techniques for high data rate optical link 300
Assessment of carbon ion engine technology targeting competitively TD19 T519-301MP 300 improvement of electric propulsion for telecoms applications
TD19 T519-302MP Development of a device to avoid transfer of Xenon propellant 200
TD20 T520-301MS Thermally conductive RTM CFRP 200
TD23 T523-301QT CSP and MCM-L (non hermetic): Low TCE HDI substrates for flip-chip 300
Page 7 of 20 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX I: List of Preselected Activities
TD24 T524-301MS Low cost reflector moulds 250
TD24 T524-302QT Long lasting white thermal control coatings for GEO (Oxygen donors) 300
Total 5 - Telecommunications 7500
Page 8 of 20 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX I: List of Preselected Activities
6 - Navigation
6 - Navigation
Technology TRP Ref Activity Title Budget Domain
3-D Time-Dependent Modelling of Internal Charging in MEO and Model TD04 T604-301EE 150 Validation Through Experiment
Exploitation of Giove In-Orbit Radiation Data for Environment Model and TD04 T604-302EE 150 Effects Tools Update
Navigation message Techniques and Concepts for fast Time To First Fix TD06 T606-301ET 200 (TTFF) without Aiding
Development of Techniques for the calibration of Satellite-Sensor station TD06 T606-302ET 200 Hardware biases in GNSS
TD06 T606-303ET Signal Processing Techniques for the Integrity of Navigation for Land Users 200
TD06 T606-304ET Techniques for Synthetic Beam-Former for reference GS sensor stations 200
Techniques for Robust Carrier Phase Tracking (under High Dynamic/Strong TD06 T606-305ET 200 Fading/Scintillation conditions)
Interference Mitigation Based on Novel Signal Processing Cancellation and RF TD06 T606-306ET 200 Front End
TD06 T606-307ET Adaptive Tracking Techniques for Navigation Signals 200
TD06 T606-308ET Techniques for High Sensitivity GNSS Receivers 200
High Fidelity Channel Modelling for GNSS Receiver Performance TD07 T607-301EE 400 Characterization
On-board Navigation Antenna Architectures and Technologies for Pattern TD07 T607-302EE 400 Flexibility and High EIRP
Improved Modeling of Short and Long Term Characteristics of Ionospheric TD07 T607-303EE 200 Disturbances During Active Years of the Solar Cycle
Study of Techniques for Combination of Space Geodetic Observations in the TD10 T610-301GN 200 Generation of Terrestrial Reference Frame
TD12 T612-301GS Integration of Optical Cryoresonator Components in Dilution Refrigerators. 300
Total 6 - Navigation 3400
Page 9 of 20 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX I: List of Preselected Activities
7 - Generic Technologies
7 - 01 - On-board Data Systems
Technology TRP Ref Activity Title Budget Domain
TD01 T701-305ED SpaceWire node interface IP core 250
TD01 T701-306ED SpaceWire-D detailed specification and prototyping 200
TD01 T701-309ED Future Digital busses spacecraft testbench reference architecture 500
TD01 T701-310ED Development of new SystemC IP models and OCP-IP sockets 100
Microcontroller for embedded space applications: Specification and design TD01 T701-317ED 500 verification
Total 7 - 01 - On-board Data Systems 1550
7 - 02 - Space System Software
Technology TRP Ref Activity Title Budget Domain
TD02 T702-305SW Model Based Software Development Lifecycle 400
Total 7 - 02 - Space System Software 400
7 - 03 - Spacecraft Electrical Power
Technology TRP Ref Activity Title Budget Domain
TD03 T703-301EP High specifc energy Li cells based on high voltage materials 400
TD03 T703-302EP Next Generation Solar Cells With 33% Target Efficiency 2800
TD03 T703-306EP Development of quantum well solar cells 500
Total 7 - 03 - Spacecraft Electrical Power 3700
7 - 04 - Spacecraft Environment & Effects
Page 10 of 20 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX I: List of Preselected Activities
Technology TRP Ref Activity Title Budget Domain
Multi-scale high accuracy engineering tools for single event effects analysis in TD04 T704-301EE 400 modern technologies
TD04 T704-302EE Improvement of energetic solar heavy ion environment models 250
Total 7 - 04 - Spacecraft Environment & Effects 650
7 - 05 - Space System Control
Technology TRP Ref Activity Title Budget Domain
Estimation and Filtering techniques for space applications: Beyond the Kalman TD05 T705-301EC 300 Filter
TD05 T705-302EC Mitigation of wheel friction torque instabilities 300
TD05 T705-303EC Detailed FDI analysis of AOCS mode 300
Nonlinear Propagation of Uncertainties in Space Dynamics based on Taylor TD05 T705-307EC 150 Differential Algebra
TD05 T705-309EC Innovative autonomous navigation techniques 300
Total 7 - 05 - Space System Control 1350
7 - 06 - RF Payload and Systems
Technology TRP Ref Activity Title Budget Domain
TD06 T706-302ET Millilab frame contract 2011-2013 300
TD06 T706-303ET Techniques for GNSS navigation at High Orbits (GEO/GTO/HEO) 250
Novel investigations in Multipactor effect in ferrites and dielectrics used in high TD06 T706-304ET 300 power RF space hardware
Total 7 - 06 - RF Payload and Systems 850
7 - 07 - Electromagnetic Technologies and Techniques
Technology TRP Ref Activity Title Budget Domain
Page 11 of 20 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX I: List of Preselected Activities
TD07 T707-303EE Alternative approaches to radiated susceptibility testing at unit level 200
TD07 T707-304EE Multi-Magnetometer Methods for Magnetic Dipole Modelling 250
TD07 T707-305EE Uncertainty Budgets for Magnetic Dipole Models 150
TD07 T707-306EE ESD test method for spacecraft equipment 250
TD07 T707-307EE Phaseless Near Field Antenna Measurements 250
TD07 T707-309EE Ultralight reflector mesh material for very large reflector antennas 250
Total 7 - 07 - Electromagnetic Technologies and Techniques 1350
7 - 08 - System Design & Verification
Technology TRP Ref Activity Title Budget Domain
Automated testing using ECSS-E-70-32 Test and Operations procedure TD08 T708-301SW 500 language
TD08 T708-303TC Calibration and Verification of micro vibration test facilities 200
Development of a vacuum compatible rotative dynamic seal for cryogenic TD08 T708-315TC 150 liquids.
Total 7 - 08 - System Design & Verification 850
7 - 09 - Mission Operations and Ground Data Systems
Technology TRP Ref Activity Title Budget Domain
TD09 T709-302GI High Rate Telemetry Transfer Services 200
Advanced Ergonomics on HCI for Satellite M&C, Problem Analysis, TD09 T709-303GI 200 Design&Planning Activities and Support for Critical Operation Phases
TD09 T709-304GI State-aware user actions recorder and replayer 150
TD09 T709-305GI Advanced Planning & Scheduling Technology Research 250
Annotation of spacecraft telemetry and exploitation by Web 2.0 like TD09 T709-307GI 150 applications
Automatic Behaviour Detection and Interpretation from low Level Data Sets TD09 T709-308GI 200 such as Telemetry
Total 7 - 09 - Mission Operations and Ground Data Systems 1150
Page 12 of 20 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX I: List of Preselected Activities
7 - 10 - Flight Dynamics and GNSS
Technology TRP Ref Activity Title Budget Domain
TD10 T710-302GN GNSS Service for the Onboard Real-Time Precise Orbit Determination 225
Total 7 - 10 - Flight Dynamics and GNSS 225
7 - 11 - Space Debris
Technology TRP Ref Activity Title Budget Domain
TD11 T711-301GR Streak detection and astrometric reduction 200
Improvements of space object observation strategies and processing TD11 T711-302GR 175 techniques through using silicon-based hybrid CMOS detectors
Total 7 - 11 - Space Debris 375
7 - 12 - Ground Station System & Networking
Technology TRP Ref Activity Title Budget Domain
TD12 T712-301GS Next generation very low noise cryogenic amplifiers in K/Ka (26-34 Ghz) band 325
TD12 T712-302GS Ka-Band 100 W Solid State Power Amplifier (SSPA) 350
TD12 T712-303GS Coupled enhanced Turbo codes demodulator and decoder 350
Breadboard of simultaneous ranging and high rate telemetry transmission for TD12 T712-304GS 225 band-efficient suppressed carrier modulation schemes
Total 7 - 12 - Ground Station System & Networking 1250
7 - 13 - Automation , Telepresence & Robotics
Technology TRP Ref Activity Title Budget Domain
TD13 T713-301MM Real-time Dynamic Library for Space Robot Control 400
Total 7 - 13 - Automation , Telepresence & Robotics 400
Page 13 of 20 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX I: List of Preselected Activities
7 - 14 - Life & Physical Sciences
Technology TRP Ref Activity Title Budget Domain
TD14 T714-301MM Low mass/power high leak tightness flow controller 150
TD14 T714-302MM Experimental evaluation of Contamination contact transfer 250
Total 7 - 14 - Life & Physical Sciences 400
7 - 15 - Mechanisms & Tribology
Technology TRP Ref Activity Title Budget Domain
TD15 T715-301MS ESTL R&D frame contract 2011-2013 750
TD15 T715-302MS Surface Treatment prior to Tribo-Coating 280
TD15 T715-303MS Development of European lubricants for space mechanisms 200
Total 7 - 15 - Mechanisms & Tribology 1230
7 - 16 - Optics
Technology TRP Ref Activity Title Budget Domain
TD16 T716-301MM Feasibility of Diffraction Gratings on Freeform surfaces 200
TD16 T716-302MM High-precision manufacturing of optical thin-films by Atomic Layer Deposition 300
Total 7 - 16 - Optics 500
7 - 17 - Optoelectronics
Technology TRP Ref Activity Title Budget Domain
TD17 T717-301MM CMOS APS operation optimisation 375
TD17 T717-302MM CMOS APS Pixel Design Optimisation 375
Page 14 of 20 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX I: List of Preselected Activities
Total 7 - 17 - Optoelectronics 750
7 - 18 - Aerothermodynamics
Technology TRP Ref Activity Title Budget Domain
TD18 T718-304MP Uncertainty-Quantification Methodologies Applied to Aerothermodynamics 100
TD18 T718-305MP Comparison of deorbiting technologies 150
TD18 T718-306MP 3D radiative transfer code development 150
Miniaturization of Electron Beam Fluorescence for hypersonic-flow in-flight TD18 T718-307MP 100 characterisation.
TD18 T718-308MP Catalogue of European materials and performance for heat shield applications 150
Total 7 - 18 - Aerothermodynamics 650
7 - 19 - Propulsion
Technology TRP Ref Activity Title Budget Domain
Assessment of the use of non-intrusive diagnostics for Electric Propulsion TD19 T719-302MP 250 testing (performance and qualification)
Rapid Manufacturing as a Key Enabler for Enhanced Monopropellant Catalyst TD19 T719-303MP 220 Bed Design
Qualification of the AEPD system as a standard on-ground tool for electric TD19 T719-304MP 400 propulsion thrusters
Development and Test of a plasma Bridge Neutralizer based on TD19 T719-305MP 300 Radio-Frequency Ionization for Electric Propulsion Applications
TD19 T719-306MP High Voltage Single Stage Hall Effect Thruster 400
Total 7 - 19 - Propulsion 1570
7 - 20 - Structures & Pyrotechnics
Technology TRP Ref Activity Title Budget Domain
TD20 T720-301MS Large Apertures Based on Ultrastable Membranes (LABUM) 650
TD20 T720-302MS Methodology for microvibration management at system level 300
Page 15 of 20 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX I: List of Preselected Activities
TD20 T720-303MS CFRP Grid structures for dimensionally stable structures 300
TD20 T720-304MS SAFE (Shock Attenuator For Equipment) 300
TD20 T720-305MS Shock Release system classification 200
Total 7 - 20 - Structures & Pyrotechnics 1750
7 - 21 - Thermal
Technology TRP Ref Activity Title Budget Domain
TD21 T721-301MT Multiple-evaporator multiple-reservoir Loop Heat Pipe 400
TD21 T721-302MT Advanced Solver Technology for Thermal and ECLSS Simulation 150
Passive by-pass valve for single and two phase mechanical pumped fluid TD21 T721-304MT 500 loops
TD21 T721-305MT Non-centrifugal pump for Mechanical Pump Driven Loops 300
Applying CNT for thermal interfiller performance enhancement and TD21 T721-306MT 200 high-performance thermal straps
Total 7 - 21 - Thermal 1550
7 - 22 - Environmental Control Life Support (ECLS) and In-Situ Resource Utilisati
Technology TRP Ref Activity Title Budget Domain
Study of Countermaesures against bio-contamination of exobiology research TD22 T722-301MM 250 spacecraft, manned vehicle and payloads. nvironmental Control Life Support (ECLS) and In-Situ Resource Utilisation (ISRU) 250
7 - 24 - Materials & Processes
Technology TRP Ref Activity Title Budget Domain
TD24 T724-302QT Metallic Materials Characterisation 250
TD24 T724-303QT Metal Matrix Composites (MMCs) as high performance metallic material 300
TD24 T724-304QE Nano-hybrid transparent materials 300
Page 16 of 20 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX I: List of Preselected Activities
Use of Nanocomposite reinforced Foams for Manufacture of Superlightweight TD24 T724-305QE 200 Stiff Sandwich Panels
TD24 T724-306QT Metallizing ceramic structures 100
TD24 T724-307QE Advanced in-situ/real time on ground contamination monitoring; phase 1 250
Total 7 - 24 - Materials & Processes 1400
7 - 26 - Spacecraft Avionic System
Technology TRP Ref Activity Title Budget Domain
Adoption of Electronic Data Sheets and Device Virtualisation for onboard TD01 T701-303ED 200 devices
TD01 T701-304ED Deploying Plug and Play Avionics 250
TD01 T701-307ED Network management and FDIR for SpaceWire networks 250
TD01 T701-312ED Packet Utilisation Standard (PUS) library using SOIS services 300
Standardization of Digital Interfaces for Sensors (Temperature, Pressure, TD01 T701-314ED 200 Position, Velocity, Acceleration)
TD01 T701-315ED FDIR Validation Test-Bed 350
TD02 T702-301SW FDIR Development and V&V Process 400
TD02 T702-303SW System-Hardware-Software co-engineering 200
TD02 T702-306SW Avionics Architecture Modelling Language 200
TD02 T702-307SW Catalogue of system and software properties 250
TD02 T702-309SW IMA-SP System design toolkit 400
TD02 T702-310SW Security building blocks for flight software applications 200
TD05 T705-304EC AOCS SpW test bench preparation 200
TD05 T705-305EC RS-422 protocol standard for AOCS equipments 200
TD05 T705-308EC RDV and Docking 3D camera technology trade-off and BB demonstration 400
TD09 T709-301GI SM&C Services implementation for a PUS/SOIS based spacecraft 250
TD09 T709-306GI File based Operations 500
TD10 T710-301GF Autonomous S/C manoeuvres 300
Total 7 - 26 - Spacecraft Avionic System 5050
Page 17 of 20 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX I: List of Preselected Activities
7 - 27 - End to End System Design Processes
Technology TRP Ref Activity Title Budget Domain
TD08 T708-302QQ System Level Integrated Failure Analysis 150
TD08 T708-304GD Improvement of functional validation by analysis of operational problems 150
TD08 T708-305SW Formal approach to Space System Data Modelling 350
TD08 T708-306SW System Functional Simulations in the Concurrent Design Process 250
TD08 T708-307SW System Verification throughout the life-cycle 300
TD08 T708-308GI Standardised M&C interfaces for ground equipment 250
TD08 T708-310SY Integration of early system modelling into the concurrent design process 250
TD08 T708-311EE Interoperability for Space Environment Analysis Tools 200
Efficient Multi-Disciplinary product data exchange for Space System design TD08 T708-312MS 150 and development
TD08 T708-316IR Analysis of S/C qualification sequence & environmental testing 500
TD08 T708-309EE Parametric electromagnetic models 450
Total 7 - 27 - End to End System Design Processes 3000
7 - 28 - Electronic Components
Technology TRP Ref Activity Title Budget Domain
TD01 T701-316ED Dynamic Latchup protection chip for COTS components 600
Utilisation of a Heavy and Light Ion Facility at UCL for Component Radiation TD23 T723-301QE 540 Studies
Utilisation of the High Energy Heavy Ion Test Facility at JYFL for Component TD23 T723-302QE 360 Radiation Studies
Utilisation of the Proton Irradiation Facility at PSI for Component Radiation TD23 T723-303QE 360 Studies
TD23 T723-304QT 16-bit ADC 600
TD23 T723-305QT Evaluation and characterisation of a harmonised mixed signal ASIC flow 510
Radiation Characterisation of GaAs MESFETs in support of European TD23 T723-306QE 310 Radiation Hardness Assurance Standard and Irradiation Test Guideline
TD23 T723-307QT Development of a monolithic pulse-width-modulated (PWM)IC. 350
Validation and experimental verification of ESA MEMS qualification TD23 T723-308QT 400 methodology
Page 18 of 20 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX I: List of Preselected Activities
TD23 T723-309QT Prototyping and characterization of 1200V, Schottky SiC shottky diode 320
Device simulation of the single-event-burnout (SEB) and gate rupture (SEGR) TD23 T723-310QE in Si Power MOSFETs in support of European Radiation Hardness Assurance 120 Standard and Irradiation Test Guidelines
TD23 T723-311QT Development of Semi-Conductive Layer Insulation Cables 180
Manufacturing and preliminary space assessment of a new multi-channel TD23 T723-312QT 210 silicon photodiode for optical encoders.
TD23 T723-314QE Part to part and lot to lot variability study of TID effects in bipolar linear devices 190
TD23 T723-316QT Characterization of SiC JFET commercially available devices 320
TD23 T723-317QT Enabling of embedded RF MEMS microwave Integrated Circuit Process 230
Investigation of microwave devices using diamond as a semiconductor TD23 T723-318QT 250 material
TD23 T723-319QT Development and evaluation of chips film capacitor for space application 150
Total 7 - 28 - Electronic Components 6000
7 - 30 - Deep Sub Micron Development
Technology TRP Ref Activity Title Budget Domain
High density European Rad-Hard SRAM-based FPGA: Abound-Logic-based TD01 T701-301ED 2000 first validated prototypes
Next Generation General Purpose Microprocessor (NGMP) Engineering TD01 T701-302ED 1000 Models
TD01 T701-313ED Deep Sub Micron 65nm rad hard library (Phase 2) 1500
TD02 T702-302SW Development Environment for Future Leon Multi-core. 300
TD02 T702-304SW Emulators of future NGMP multicore processors 300
Schedulability analysis techniques and tools for cached and multicore TD02 T702-308SW 250 processors
Total 7 - 30 - Deep Sub Micron Development 5350
7 - 31 - Miniaturisation
Technology TRP Ref Activity Title Budget Domain
Modular and miniaturised secondary power conversion and distribution based TD03 T703-304EP 300 on Point of Load converters
TD03 T703-305EP Miniaturised core element for Point of Load (PoL) conversion 500
Page 19 of 20 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX I: List of Preselected Activities
TD05 T705-306EC Miniature MEMS based IMU feasibility demonstrator 1200
Miniaturised and Low Power Communications Architectures for Small TD06 T706-301ET 450 Platforms
Modular and customisable accommodation-friendly antenna system for TD07 T707-301EE 500 satellite avionics
TD07 T707-302EE Scalable low-mass low-envelope high-to-very-high gain antenna 350
TD15 T715-304MS Polymer based tape-spring type, ultra-light actuator. 150
TD21 T721-303MT Miniaturised Heat Switch Technology 300
TD23 T723-313QT Miniaturisation of Power/Coaxial Connectors 250
RF MEMS switch technology for space application: Phase 1: Benchmarking TD23 T723-315QT 800 and selection
TD23 T723-320QT Embedded passive component: a way to miniaturization 400
High Density Interconnect Technology and Thermount replacement with TD24 T724-301QT 250 assembled devices.
Total 7 - 31 - Miniaturisation 5450
Page 20 of 20 ESA/IPC(2010)119
Page intentionally left blank ESA/IPC(2010)119
ANNEX II
TRP Work Plan 2011-2013
Descriptions of preselected Activities TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
1 - Earth Observation
1 - 01 - Microwave Payloads
TRP Reference T106-301ET Activity Title Study of a Miniaturised Altimeter Objectives The study shall investigate the potential of altimeter miniaturisation and shall identify technology needs. Description Current dual frequency altimeter designs with SAR mode as SRAL for Sentinel 3 have a mass of 64 kg and a power consumption of around 100 Watts. This is a typical figure for state-of-the-art instruments of this kind. However for a potential constellation of altimeters improving temporal coverage, the mass and power consumption is too high for desirable cost effective micro satellites. Within the literature figures of around 15kg and 24 Watts are discussed and considered feasible.
The power and therefore the mass of the altimeter is too large, determined by the antenna size in relation to the wavelength. The shorter the wavelength the higher antenna gain and less RF power is needed. On the contrary, the overall power consumption depends on the efficiency of the used semiconductor devices, which is less at shorter wavelength. However semiconductor technology is evolving fast. A first altimeter is built at Ka-band frequencies.
The study shall investigate into advanced Ka-band and Ku-band altimetry and the possibility of mass and power reduction by means on utilisation of highly integrated circuits, advanced semiconductors, overall design of the radar. Furthermore the study shall look into system level aspects as there is a need for dual frequency and radiometer channels for atmospheric correction. Also satellite level aspects will be considered as well. A time horizon of 5 to 10 years shall be considered.
A conceptual design of a mini altimeter shall be carried out, technology definition shall be derived and roadmaps shall be created.
Deliverables Study Report Application/Need Date Constellation of low-cost miniaturised altimeters, GMES 2nd generation. TRL 5 by 2016 Duration (Months) 12 Estimated Current TRL 1 Target TRL 2
SW Clause N/A Reference to ESTER T-8880
Consistency with Harmonisation N/A
TRP Reference T106-302ET Activity Title P-band Multiphase Centre SAR and Ice-Sounder Objectives Study into a Digital Beam Forming P-band Ice Sounding Instrument and Biomass Mapping. Description P-band Ice sounding instruments have been proposed already for Earth Explorers (CARISMA) and are becoming now more and more an important tool to improve the understanding of the cryosphere in particular for ice sheets over solid surfaces as in Greenland. Flight experiments in this field are ongoing with the Polaris airborne instrument.
A potential space borne instrument for this application would be reflector based or based on phased array techniques. While SAR processing allows the improvement of the resolution in along track, in across track a real aperture is needed with sufficient nadir echo suppression at the ice/air interface. Multiple phase centre beam forming in across track has the potential to arrive at sufficient level of suppression which calls for phased array antennas.
Beam forming would be done on board, ideally in the digital domain.
The use of a lightweight but still large antenna in across track, however flat in flight direction has a significant advantage in terms a drag over a large reflector based system. The fact that all phase centres are accessible would allow in addition side looking SAR with ScanSAR mode for supporting biomass applications, within certain limits, which have to be studied. The study shall investigate the feasibility of such instruments for ice sounding with potential secondary use of instruments for side looking SAR. Deliverables Study Report Application/Need Date GMES 2nd Generation, TRL 5 by 2016 Duration (Months) 18 Estimated Current TRL 1 Target TRL 2
SW Clause N/A Reference to ESTER T-8195
Consistency with Harmonisation N/A
Page 1 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
TRP Reference T106-303ET Activity Title Study of Multi-channel Ka-band SARs for moving target indication Objectives The study shall first perform a survey of multi-channel processing options. The study shall then define instrument architectural options and trade-off them with respect to performance, technical budgets and technology maturity. Simulation models shall be developed in order to investigate end-to-end instrument performance. Description Ka-band SAR have been recently considered as a very promising solution for civil security applications, since the small Ka-band wavelength would enable at the same time, high resolution imaging and Cross Track-Interferometry (XTI) and Along Track-Interferometry (ATI) applications with the adoption of a single platform while still guaranteeing high performance. In addition, in the recent years, the capability of detecting ground moving targets (usually referred as GMTI, Ground Moving Target Indication) from space based SARs is attracting enormous interest, since it would enable traffic monitoring applications with high performance and flexibility to detect a wide range of target classes. However, the optimal detection of ground moving targets by a space based SAR requires careful design of both the instrument RF-front-end and data processing. Indeed, for space based radars, due to the motion of the satellite, it is of primary importance to discriminate the target signals from the clutter echoes, since the latter is distributed over a large Doppler spread. In order to overcome this limitation, different multi-channel SAR concepts have been proposed, such as ATI, Displaced Phase Centre Antenna (DPCA) and Space Time Adaptive Processing (STAP). It is well known that the adoption of more than 2-3 channels would guarantee almost optimum performance for GMTI. However, current systems are operating at lower frequencies than Ka-band and they can provide only few apertures in a single platform, since instrument dimensions/mass and performance limitations arise. On the other hand, the adoption of a multi-channel Ka-band SAR would allow the implementation of multiple apertures within an instrument of moderate dimensions and with high performance.
The objective of the study is to investigate instrument architecture options of multi-channel Ka-band SAR optimized for ground moving target indication. In order to define the most promising instrument architectures, the study shall carry out a detailed analysis of multi-channel processing options (STAP, DPCA, etc..) and, consequently, a detailed trade-off of different instrument technological options (e.g. phased array vs reflector antennas). The final instrument trade-off shall then be done on the basis of instrument end-to-end performance analysis, instrument budgets (dimensions, mass, power) analysis and complexity. The instrument models shall be delivered in CDF compatible format Deliverables Study Report Application/Need Date Next Generation Ka-band SAR with ATI/XTI for civil security applications. GMES 2nd Generation, TRL 5 by 2016. Duration (Months) 15 Estimated Current TRL 1 Target TRL 2
SW Clause N/A Reference to ESTER T-8334, T-8878, T-8888
Consistency with Harmonisation N/A
TRP Reference T106-304ET Activity Title Single GaN chip HPA/LNA for Radar Applications Objectives Develop a single chip HPA+LNA including power protection for radar based on GaN technology. Description Gallium Nitride (GaN) technology has demonstrated significant capability to provide robust Low Noise Amplifier (LNA) with enhanced power survivability. Using GaN standard process, LNA with good Noise figure performance have also been demonstrated.
In order to further reduce the price of phased arrays, this activity proposes integrate both the LNA and Higher Power Amplifier (HPA) on the chip (size reduction).
GaN offers the capability to reduce the size of HPA and LNA by a factor of 5 when compared to equivalent GaAs based circuits. Due to the usage of GaN technology no input power protection is expected on the LNA which both improves the compactness of design and compensates for a limited noise figure degradation induced by the usage of GaN power process.
Additionally, in the frame of simplified Transmitter/Receiver (T/R) modules, where all the beam steering elements are part of a centralised digital unit, the simplification of the remaining RF elements in T/R modules, i.e. reduction of number of chips and removal of power protection is extremely key to reduce the overall assembly cost and finally the price per module.
Due to the capability of GaN to operate at higher junction temperature, phased array shall fully benefit of the use of GaN technology by further simplification of heat control/removal systems. The LNA, being of the same technology as the HPA, the baseplate temperature shall not be limited by the LNA device technology.
Follow on of Sentinel 1 and corresponding national programs shall benefit of application of the proposed integrated GaN chip. The aim of this activity is to develop a single GaN chip providing HPA and LNA functionality for highly integrated T/R modules applications at C or X band.
HPA in the 20-40W range shall be developed. The LNA shall feature embedded power protection in order to avoid any external additional circuitry.
Operation at high temperature shall be investigated. Deliverables Prototype Application/Need Date Earth Explorer 9, GMES 2nd Generation, TRL 5 by 2015 Duration (Months) 24 Estimated Current TRL 1 Target TRL 4
Page 2 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
SW Clause N/A Reference to ESTER T-7736
Consistency with Harmonisation TBD
TRP Reference T106-305ET Activity Title Digital receiver for radiometers Objectives The objective is to design and breadboard highly integrated microwave receiver function based on the use of novel European processes for EO applications Description The mixed signal (SiGe BiCMOS) technologies have been under interest in the specific area of signal generation due to good achievable signal quality. Meanwhile, the technology has been improved to reach higher operating frequencies and lower noise figures, too. The SiGe is very well suited for digital receiver implementation at L-band.
The advantage of SiGe over GaAs in space use is foreseen in the high degree of integration due to the feasibility of mixing analogue and digital functions on a single chip. This means that the complete microwave system (e.g. receiver) can be implemented in a volume that is a fraction of the volume needed in a GaAs-based system where hybrid implementation is required. The power consumption would also be lowered in a single chip solution in comparison with the GaAs-hybrids. SiGe can have substantial potential in low-power applications that need a number of highly integrated receivers. For example, for THE Soil Moisture and Ocean Salinity (SMOS) mission, the number of hybrid receivers had to be reduced due to mass constraints which led to compromised system performance. The digital concept will also facilitate new functionalities in interference detection and mitigation. The need for effective mitigation is evidenced by early observations by SMOS.
This activity aims at design, manufacturing and test of a highly integrated digital receiver at L-band with digital output interface. In addition to direct L-band operation, the receiver lends itself as a building block (IF stage) for higher mm-wave heterodyne receivers. The development will support Post-EPS Radio Occultation receiver, synthetic aperture highly integrated synthetic aperture receivers with interference detection and mitigation, and the next generation of Sentinel-3 radiometer. A receiver-on-chip shall be targeted if it is justified. Deliverables Breadboard Application/Need Date Highly integrated synthetic aperture receivers. Earth Explorer 9 TRL5 by 2015, GMES 2nd Generation Duration (Months) 24 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-8206
Consistency with Harmonisation TBD
TRP Reference T106-306ET Activity Title Switch mode amplifier for P /L band Objectives Develop a switch mode amplifier (Class D, E or S) based on European GaN technology for radar application at P band (or L Band). The switch mode amplifier provides significantly improved efficiency compared to classical Class AB, or C amplifiers. Targets are 80 to 90% efficiency at P-band for 100-150W class amplifier. Description The proposed development will apply to all Radar missions at relatively low frequency P, L band (e.g. Ice sounder at P Band , Biomass, L-band radar). The activity is in line with IPC paper ESA_IPC(2006)89.
The work will consist in 3 main parts: 1)Trade-off between class D, E & S for radar applications at P-band (or L Band). 2)Development of fast driver switching circuit to shape the input signal to the amplifier in a square wave form. In a class E the switching frequency shall be the same as the RF carrier (i.e. 435 MHz or 1.2 GHz). For class D and possibly for class S operation the switching frequency shall be higher than the RF carrier frequency (typically 3 to 5 times higher). 3)Development of the HPA output stage (100-150W class ) and Transistor output filtering circuit. Deliverables Breadboard Application/Need Date Earth Explorer 9, TRL 5 by 2015 Duration (Months) 30 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-7736, T-8196, T-8448, T-8405, T-7825
Consistency with Harmonisation Critical RF Technologies roadmap does not extent to 2011
TRP Reference T106-307ET Activity Title Integrated receiver front-ends for radiometers Objectives
Page 3 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
The objective is to develop highly integrated receiver front-ends for radiometers at frequencies compatible with the Post EPS and synthetic aperture instruments including internal calibration concept. Description Synthetic aperture radiometry concept is under validation at L-band (Soil Moisture and Ocean Salinity (SMOS) mission) and the preliminary results are very encouraging. Meanwhile, new developments are being carried out to extend the frequency range to X-band (SMOS-OPS), mm- and even sub-mm range (Geo sounding) where the integration becomes very critical.
An important new aspect in the radiometry is the use of internal calibration concept that could benefit the future EO radiometers by more efficient calibration. The technique could eliminate the need for mechanical calibration systems (e.g. rotating mirrors) and thus improve the payload performance and mission efficiency.
There are several activities already performed to investigate the feasibility of the concept and to develop the active cold load: - Active calibration of radiometer (previous TRP contract), - Active cold load for radiometer calibration (previous TRP contract), - Advanced internal calibration techniques for post Eumetsat Polar System (EPS) Radiometers (previous EO contract) and very encouraging results have been obtained which show that calibration uncertainties could be reduced by the internal calibration concept.
In addition to the noise sources, one critical element in the calibration is the RF switch that has to be used for switching between the calibration loads and the antenna. Key parameters of the switch are insertion loss, isolation, switching speed, repeatability, low excess noise, low self-heating, and stability. Throughout the RF spectrum and especially at the mm-wave range, meeting these requirements is evidently very challenging. Although commercial switches are available in a numerous types and qualities, no specific designs exist for the needs of radiometry.
For the best noise performance, Metamorphic High Electron Mobility Transistor (M-HEMT) technology should be applied at least in the Low Noise Amplifier (LNA) but at frequencies above 20 GHz also in the first down conversion.
This activity aims at developing highly integrated receiver front-end blocks (Monolithic Microwave Integrated Circuits (MMIC)) based on the internal calibration concept. Technologies for LNAs, mixers, and calibration switches at selected frequencies between 10 GHz to 183 GHz will be traded-off and designed. Representative front-end configurations comprising the LNAs, mixers, and switches, as applicable, will be built and tested. (The IF processing, detection, and AD conversion will be subject of another activity, "Digital receiver for radiometers").
The developments support the future synthetic aperture radiometers (LEO & GEO) as well as Post-EPS instruments. In addition, technology push aspect for Earth Explorers is provided. Improvements in the calibration accuracy and the observation effiiency are expected as well as considerable simplifications in the calibration mechanics, and mass and power reduction. Deliverables Breadboard Application/Need Date Internal calibration techniques, LEO/GEO arrays, Post-EPS, Earth Explorer 9, TRL5 by 2014. Duration (Months) 24 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-8206, T-8755
Consistency with Harmonisation TBD
TRP Reference T106-308ET Activity Title Study of ocean currents with multi-channel C-band digital beamforming SAR Objectives he study shall investigate state-of-the-art multi-channel azimuth processing and select the most suitable for both ocean current estimation and ground moving target indication. The study shall then analyse the adoption of multi-channel processing on the C-band SAR DBF and analyse the associated performance for the different applications. Recommendations and way forward shall be defined. Description Recent studies have demonstrated that next generation C-band SAR instruments based on the adoption of digital beamforming (DBF) with multiple azimuth channels will be able to guarantee at the same time large swath and high resolution (i.e. swath ~400Km and ~5m resolution with 7 azimuth channels). This C-band SAR DBF instrument so conceived, being based on multiple azimuth channels, can also be also exploited for along-track multi-channel applications such as the detection of ocean currents, which is attracting high interest in the recent years. In addition, multi-channel processing can also be exploited for GMTI (ground moving target indication) which has been recently demonstrated with the 2-channel processing capabilities of Terrasar-X and Radarsat-2.
The aim of the study is to investigate the multi-channel processing options and associated performance of future C-band SAR based on digital beamforming in order to exploit along-track applications such as the ocean currents estimation and ground target moving indication. Deliverables Study Report Application/Need Date C-band SAR with digital beamforming, GMES 2nd Generation, TRL 5 by 2016 Duration (Months) 15 Estimated Current TRL 1 Target TRL 2
SW Clause N/A Reference to ESTER T-8890
Consistency with Harmonisation N/A
TRP Reference T106-309ET Activity Title Mm-wave mixers with low-barrier diodes
Page 4 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Objectives To reduce Local Oscillator (LO) power requirement of (sub)mm-wave mixers by using novel low-barrier Schottky diodes. Description Low-barrier mixer diodes offer significant reduction in Local Oscillator (LO) power requirement. In addition to reducing the overall power consumption, this makes large heterodyne arrays feasible. This activity aims to demonstrate a high-performance mixer with very low LO power using European low-barrier Schottky technology. Deliverables Breadboard Application/Need Date (Sub)mm receivers for EO and Science. Earth Explorer 9, TRL 5 by 2015 Duration (Months) 12 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-8229
Consistency with Harmonisation TBD
TRP Reference T106-310ET Activity Title Feasibility study on pulsed HPA for Ka-band SAR instruments Objectives The objective of this study is to assess the capabilities of existing High Power Amplifiers for use in Ka-band SAR, to evaluate the necessary modifications in order to achieve the desired requirements and finally, to provide a detailed plan for the future development of a flight model Ka-band pulsed HPA. Description Synthetic Aperture Radar (SAR) instruments have become essential for Earth Observation purposes since the first instrument in space back in 1978. The operational frequency has evolved from L- to C-, S- and X-band. New frequency bands currently under study in Europe are P-band for BIOMASS and Ku-band with CoReH2O. Ka-band has been used for Unmanned Aerial Vehicles (UAV) but has not been utilized for SAR from space so far, although the suitability of Ka-band of SAR imaging has been proven in various airborne demonstrators and instruments. An ESA internal study on the feasibility of a Ka-band SAR instrument and interferometer has pointed to the need of a Ka-band High Power Amplifier (HPA) with capabilities beyond what is currently available on the market. The study shall investigate the feasibility of such a Ka-band HPA and will complement a TRP activity that will begin mid 2010 to study Ka-band SAR missions.
Starting from the preliminary requirements identified for the Ka-band HPA (3.5 kW, 14% duty cycle, 500MHz BW), the activity will cover the following tasks: - detailed review of the HPA preliminary specification, - thorough market and literature survey of existing space and ground pulsed HPA technologies and related concepts, - trade-off among the various existing solutions in order to propose viable solutions for the target application, the identification of a baseline technology and design.
These analyses will allow consolidating and refining the preliminary specification. Dedicated simulation will support the assessment of the baseline solution performance and will show where improvements are still possible. Finally, a detailed programmatic description of the necessary development steps needed up to Flight Model will be provided, together with a realistic estimation of the duration and cost of each development phase. Deliverables Study Report Application/Need Date HPA for Ka-band SAR instruments, GMES 2nd Generation, TRL 5 by 2016 Duration (Months) 12 Estimated Current TRL 1 Target TRL 2
SW Clause N/A Reference to ESTER T-353
Consistency with Harmonisation TBD
TRP Reference T106-312ET Activity Title Study on advanced radiometer for sea surface temperature (SST) observations Objectives The objective of the study is to define innovative microwave radiometer architectures for sea surface temperature observations. In order to define the most effective instrument architecture, the study shall carry out a detailed trade-off of both scanning and synthetic aperture configurations. The definition of the instrument shall be based on the analysis and implementation of RFI mitigation technique(s). The final instrument selection shall then be done on the basis of instrument end-to-end performance analysis (e.g. sensitivity, spatial resolution), instrument budgets (dimensions, mass, power), technology and complexity. Detailed instrument definition and technology requirements analysis shall follow. Description
Page 5 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
The study shall first perform a consolidation of SST observation requirements and preliminary instrument concepts proposed in the frame of other studies. The study shall then define instrument architectural options and trade-off them with respect to performance, RFI mitigation capability, technical budgets and technology maturity. Analysis of frequency range shall be carried out within the activity. Simulation models shall be developed in order to investigate end-to-end instrument performance. The study shall conclude with the definition of a demonstrator of the proposed instrument concept. The instrument models shall be delivered in CDF compatible format.
BACKGROUND: The measurement of sea surface temperature (SST) from space is of fundamental importance for understanding, monitoring and predicting the ocean circulation. SST measurements are also needed for correcting ocean salinity and soil moisture observations taken at 1.4GHz, for example. Microwave radiometers would have the capability of observing SST with much higher availability with respect to infrared observation instruments, since they can observe SST also trough dense clouds. In the recent years, SST measurements have been demonstrated by the 6.9GHz channel of the AMSR-E scanning radiometer capable of a spatial resolution of 25Km (with the adoption a 2m reflector antenna). The Japanese GCOM-W satellite will continue the legacy of AMSR-E with the AMSR-2 radiometer which includes design upgrades to mitigate RFI using an additional 7.3 GHz channel and improved hot load calibration design. Indeed at this frequency range, RFI (Radio Frequency Interference) is present and is a critical issue, therefore effective on-board means for its mitigation shall be defined and applied in next generation radiometers. This year a new ESA activity (“Microwat”) is being initiated, which has the objective of consolidating scientific requirements and performing a preliminary analysis of different observational principles and concepts to measure contemporaneous high resolution Sea Surface Temperature (SST) and Ocean Vector Winds (OVW). On the basis of the outcomes of the Microwat activity, this study will carry out a detailed definition of microwave radiometers for sea surface temperature measurements. The instrument definition will be based on the trade-off between different architectural solutions (scanning vs. synthetic aperture) and on the analysis and definition of effective on-board RFI mitigation techniques Deliverables Study Reports and Software Modelling Application/Need Date GMES 2nd Generation, TRL 5 by 2016 Duration (Months) 15 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-8881
Consistency with Harmonisation TBD
TRP Reference T107-301EE Activity Title Ka-band SAR backscatter analysis in support to future applications Objectives To arrive at consolidated Ka-band backscatter levels for a wide range of natural targets (both land and sea). Description Better knowledge is required of backscatter levels of natural targets imaged with Ka-band SAR in order to assess the overall potential of Ka-band single-pass interferometry for the different envisaged applications. The output of the study will also support instrument parameterisation and requirements such as SNR, SCR, NESZ and imaging ambiguities. Applications from Ka-band SAR are seen in imaging for Civil Security (DEM, cartography, disaster management, object recognition on land and water, GMTI) and Environmental tasks (snow and ice coverage, ocean currents, inland waters, bathymetry, subsidence, vegetation height). The study shall investigate into the wave interaction for these applications in connection with Ka-band InSAR including polarimetry. The criticality of atmospheric distortions shall be studied as well. Available intensity datasets at Ka-band (airborne) shall be studied supported by available forward EM models for the variety of natural targets (including its related variability). Deliverables Study Report Application/Need Date GMES 2nd Generation, TRL 5 by 2016 Duration (Months) 12 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-8153
Consistency with Harmonisation N/A
TRP Reference T107-302EE Activity Title SAR Wave INteraction for Natural Targets Over Land (SWINTOL) Objectives To create a standard methodology for increased understanding of SAR wave interaction with natural surfaces To reach this global objective, the study shall: - re-evaluate, assess applicability of and update surface roughness models to make these appropriate to short wavelength, high resolution SAR systems - evaluate interactions with land surfaces and vegetation to arrive to a detailed understanding of the scattering mechanisms and its impact on the SAR image by including system dependent SAR parameterisation whenever necessary (i.e. geometry, applicability of processing gain for coherent contribution of backscatter) - raise the awareness of the community on these issues that were (conveniently) ignored in the past Description
Page 6 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Retrieval accuracies of high-frequency SAR applications over natural targets can be affected due to an incomplete understanding, description and interpretation of the SAR backscatter levels. Current surface roughness (asymptotic) models are insufficient to address short wavelength interaction over land surfaces. Although these effects have also been reported at L- and C-band, it is envisaged that these effects will become increasingly important when going to shorter wavelengths. The models do not seem applicable in this range or lack the ability to include specific SAR imaging parameters necessitated for describing the full backscatter behaviour. In most SAR wave interaction models (e.g. vegetation, snow), surface scattering is often present and when ignored or poorly represented can lead to significant inversion errors. The study shall explore interactions with land surfaces and vegetation to arrive to a detailed understanding of the scattering mechanisms and its impact on the SAR image by including all contributions (e.g. anisotropy of the surface, coherent/incoherent and nadir return) . Whilst doing so, the activity shall also be the opportunity to consolidate and integrate the knowledge of surface interaction for wavelengths> 3cm and medium resolution systems in order to address gaps in the current knowledge. Such as, coherent vs incoherent and isotropic versus anisotropic surface interactions. Study report Deliverables Updated surface interaction models ATBDs Application/Need Date Earth Explorer 9, TRL 5 by 2015 Duration (Months) 18 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-8888
Consistency with Harmonisation TBD
TRP Reference T107-304EE Activity Title RFI Detection and Mitigation techniques for EO passive missions Objectives The main objective of this activity is to develop algorithms for data analysis of space borne passive microwave sensors (e.g. radiometers) for detection, localization and mitigation of Radio Frequency Interference (RFI) emissions within protected bands , generated from ground or space borne emitters. In particular the activity shall identify the procedures to permit: a) A controlled degradation of the retrieval of physical parameters from channels affected by RFI b) The assessment of EO data integrity, for the assimilation process performed by Numerical Weather Prediction systems. In short it will try to give guidelines on operation and data analysis of EO missions to minimise disruption due to RFI. Description The issue of Radio Frequency Interference (RFI) generated by artificial sources is an increasing problem. Areas affected by the radio spectrum pollution include: Earth Observation using passive and active microwave remote sensing, ground based remote sensing of the atmosphere, space based radio experiments and radiostronomical observations.
The current level of RFI contamination on ground based and spaceborne passive sensors is already an issue. Analysis of the AMSR-E, SMOS and reports from ground based earth atmospheric sites already reveal that in areas highly populated and industrially developed the level of man-made RFI can easily cover the weak signatures of natural sources (atmosphere, sea or land surface). As well Space Ground stations and Space Telescopes, even if located in remote areas, are experiencing more interference due to the concurrent increase of inhabitants and radio appliances.
The use of protected bands is the main solution and the development frequency monitoring techniques is the only way to ensure that international regulations are respected. Nevertheless the risk of disruption of radio based observations is increasing (e.g. an atmospheric campaign or the radio navigation services for science missions).
This situation has originated a number of studies that defined the statistical characteristics of RFI currently observed by space-borne passive sensors and signal processing techniques for detecting and separating RFI from natural signatures have been identified.
The proposed study will address the issue of RFI detection and mitigation by starting from the experience gained on systems operating at L and X band and focussing on the projection effects operating at frequencies from Ka to W band (like the atmospheric sounders for post_EPS) to identify procedures and techniques to be used for frequency management and for assimilation of data into NWP systems. The new techniques shall be delivered in CDF compatible format. Deliverables Study Report Application/Need Date Earth Explorer, TRL 5 by 2015 Duration (Months) 18 Estimated Current TRL 1 Target TRL 2
SW Clause N/A Reference to ESTER T-7769
Consistency with Harmonisation N/A
TRP Reference T107-305EE Activity Title Improvements of the understanding of microwave sea surface scattering Objectives The objective of this activity is to review the status of microwave sea surface scattering models, to identify gaps in the understanding and to propose and implement improvements. Description
Page 7 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
If for some configurations of observation (C-band, Ku-band at nadir), the amount of accumulated observations has led to a reasonably good confidence in our understanding of the microwave scattering of sea surfaces and in the related models. This is not yet the case for other configurations of observation (Ka-band, Ku-band off-nadir, L-band specular, along track interferometry). This gap in the understanding can be detrimental when trying to assess the feasibility of new missions (e.g. what happens on the edge of the swath at Ku-band for a wide swath altimeter, what is the expected current velocity contribution in the signal observed by a Ka-band along-track interferometer, ...). This study shall review the status in the field, identify gaps in the understanding (which can be EM related or surface description related) and consolidate the knowledge in order to ensure that there is confidence in the models used to support future microwave missions over the seas. Deliverables Study Report Application/Need Date Active Microwave Missions, Earth Explorer, GMES 2nd Generation, 2014 Duration (Months) 12 Estimated Current TRL N/A Target TRL N/A
SW Clause N/A Reference to ESTER T-8754
Consistency with Harmonisation N/A
TRP Reference T107-306EE Activity Title Compact Ku-Band or Ka-Band Altimetric antenna for LEO constellation Objectives The objective is to design and analyse a unique multi-frequency compact reflector antenna for a Ku band or Ka-Band Altimeter and K/Ka Radiometer taking into account LEO platform accommodation constraints and low-cost constraints for satellite constellation. Description Recently the possibility to embark miniaturised altimeters as a secondary payload of a LEO constellation of satellites has been raised (see NEXT Iridium constellation). The objective is to develop a unique multi-frequency compact reflector antenna for a Ku-band or Ka-band Altimeter and K/Ka Radiometer taking into account LEO platform accommodation and low-cost for satellite constellation constraints. The feasibility of such an antenna shared by both the altimeter and the radiometer has been demonstrated with the SARAL/ALTIKA qualified antenna. It is proposed to evaluate new antenna designs for the same purpose with emphasis on compactness and low cost approach required by LEO constellation.
The study will consist of a Literature review of state of the art technology, definition of antenna specifications, a tradeoff and selection of one antenna architecture and a detailed analysis (RF, mechanical, thermal). The technical data of the proposed antenna shall be delivered in CDF compatible format. Deliverables Study report Application/Need Date Earth Explorer 9, TRL 5 by 2015 Duration (Months) 16 Estimated Current TRL 1 Target TRL 2
SW Clause N/A Reference to ESTER T-8880
Consistency with Harmonisation TBD
TRP Reference T107-307EE Activity Title Interferometric antennas at Ku- and Ka-band with modest baselines for wide swath altimetry Objectives The objective is to develop an interferometric antenna at Ku-Band and Ka-Band with modest baseline (~2.5m) Description Based on the outputs from an on-going ESA General Studies Progamme (GSP) system study “Scientific Assessment of Fine Scale Altimetry Using a Constellation of Small Satellites”, the objective is to study possible antenna architectures for Ku-Band and Ka-Band radar interferometer instrument with modest baseline for wide swath altimetry. The instrument design would require one transmit/receive and one receive antenna (see e.g. CRYOSAT/SIRAL antenna concept), each being separated by 2.5 meters, that shall be accommodated on a single satellite. The antenna baseline shall be nadir looking. The antennas shall be designed to generate 2 mirror off nadir beams in elevation (across-track) of few degrees (typically +/-3deg). The interferometric baseline vector needs to be both very stable in orbit and known with a very high accuracy in orbit.
The following tasks shall be performed: - A literature search shall be done to investigate possible material, technologies and antenna architectures (radiating aperture and feeding system) for both Ku and Ka-Bands. - Based on the outputs from ESA GSP system study “Scientific Assessment of Fine Scale Altimetry Using a Constellation of Small Satellites”, the relevant mission and instrument requirements shall be provided as justification for the establishment of the antenna specifications. The antenna specifications shall be provided accordingly. - Antenna architectures (reflector based or Dielectric resonator antenna solutions) shall be proposed while meeting overall system requirements, with a particular attention paid on stability requirements, deployment requirements and launcher accommodation constraints. - A trade off analysis shall be performed and two different antenna architectures shall be selected for further detailed analysis. - A detailed analysis (RF, mechanical , thermal) for the two architectures shall be carried out - Solutions to accurately obtain the in-orbit stability of interferometric baseline (attitude and length) shall be proposed with an associated error budget . - Solutions for calibrating the antenna baseline (calibration) shall be investigated and their accuracies shall be assessed.
Deliverables: 1/State of the art/literature search, 2/Brief description of the mission and the instrument , relevant mission and instrument requirement and antenna specifications.
Page 8 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
3/Tradeoff analysis and selection of 2 concepts (2 concepts per frequency bands Ku and Ka, ie 4 concepts total) 4/RF, Mechanical, Thermal and Thermoelastic analysis of the 2 concepts (+antenna contribution to instrument error budget) 5/ Solutions to accurately obtain the in-orbit stability of interferometric baseline 6/ Internal calibration scheme of the antenna The technical data of the proposed antennas shall be delivered in CDF compatible format. Deliverables Study Report Application/Need Date Earth Explorer 9, TRL 5 by 2015 Duration (Months) 16 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-8878
Consistency with Harmonisation TBD
TRP Reference T107-309EE Activity Title Study on advanced multiple-beam radiometers Objectives The objective of the study is to investigate novel architectures for real aperture multi-beam radiometers. The activity shall investigate and trade-off real aperture radiometer architectures based on multiple beam array-fed reflectors. The final instrument trade-off shall then be done on the basis of instrument end-to-end performance analysis (sensitivity, spatial resolution and FoV), instrument budgets (accommodation, mass, power) and complexity. Description It is well known that real aperture radiometers feature very high snapshot sensitivity, if compared with synthetic aperture radiometers. On the other hand, synthetic aperture interferometric radiometers can provide wide FoV and high spatial resolution thanks to the synthetic aperture processing. Real aperture radiometers may become very attractive from the sensitivity performance point-of-view if a simultaneous multiple beam coverage is achieved in the entire FoV (i.e. both in across-track and in along-track directions). This implementation could lead to very high sensitivity, since the presence of along track beams would allow for high multilooking, hence yielding to accuracy improvement on the estimation of brightness temperature. An attractive RF-front-end/Antenna solution can be based on the adoption of an array fed reflector in a multiple feed per beam configuration. An optimized definition of the array configuration and associated beam forming should be carried out in order to evaluate the actual benefits of this concept and the drawbacks in terms of complexity and overall instrument budgets. Different reflector configurations (cylindrical, toroidal) which may exploit pushbroom techniques should be traded off as well. The study shall also analyse the possibility to exploit dense focal arrays, thus allowing for oversampling which, in turn, could improve beam efficiency. The activity shall start with a review of requirements and analysis of possible applicable frequency range. The study shall then define different instrument options and carry out a system level trade-off in order to select the most promising solutions. The instrument models shall be delivered in CDF compatible format.Comparison of performance with state-of-the-art radiometers will be carried out as well. The study shall end with the proposal of an instrument demonstrator. Deliverables Study Report, Models and Breadboard Application/Need Date Earth Explorer 9, TRL 5 by 2015 Duration (Months) 12 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-8220
Consistency with Harmonisation TBD
TRP Reference T107-310EE Activity Title Wavemill Antenna concept and critical breadboarding Objectives The objective is to study possible antenna concepts for Wavemill instrument and manufacture a breadbord for the most promising concept. Description
Page 9 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Based on an ESA feasibility study, the Wavemill concept has shown that extremely interesting results can be achieved in terms of ocean current retrieval for both velocity and direction. There is a strong interest for optimising the antenna architecture and demonstrating feasibility and performance. Among possible antenna architectures, the javelin concept looks interesting since it can provide the required along- and across-track baselines with a compact spacecraft at launch having a nearly optimal configuration for AOCS (long and thin in flight direction). This design calls for an antenna capable of producing up to four squinted beams with a swath width of around 100km at an incidence angle of 25 degrees. The antenna as a key component needs to be elaborated and simulated in order to make possible the Wavemill concept. Due attention shall be given to space qualified technologies and lessons learnt from previous programs. The following tasks shall be performed: - A literature search shall be done to investigate possible material, technologies and antenna architectures - Antenna architectures/concepts shall be proposed while meeting overall system requirements, stability requirements, deployment requirements and launcher accomodation constraints. - A trade off analysis shall be performed and one antenna architecture/concept shall be selected for further detailed analysis. - A detailed analysis (RF, mechanical , thermal) for the selected architecture shall be carried out. - A breadboard of the selected antenna concept shall be manufactured and RF tested.
Deliverables: 1/Literature search/state of the art, 2/Instrument and antenna specification, 3/Tradeoff analysis report, 4/Detailed analysis reports for the selected antenna concept 5/Antenna BBM manufacturing and testing. The antenna model shall be delivered in CDF compatible format. Deliverables Breadboard Application/Need Date Earth Explorer 9, TRL 5 by 2015 Duration (Months) 16 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-8879
Consistency with Harmonisation TBD
TRP Reference T107-311EE Activity Title Innovative SAR based on Sparse Direct Radiating Array antenna Objectives The objective is to reduce the complexity and cost of active SAR antennas by reducing the number of elements and maximizing the efficiency of the power amplifiers (especially important in transmission). The reduction in the number of elements can be obtained by employing layouts characterized by a tapered element density, while the need of maximizing the amplifiers efficiency suggests using a uniform amplitude excitation. A preliminary successful investigation has been recently done at ESA in collaboration with antenna engineers who have been deeply involved in the design of flying active SAR antennas. The results of this activity indicate that a reduction in the number of elements in the order of 20-30 % may be achieved without sacrifying the antenna performances. Description The study will be organized in 3 parts: 1) identification of an existing array-based SAR antenna to be used as reference; 2) implementation of a numerical tool for the design of aperiodic sparse array antennas able to replace conventional periodic array antennas; 3) preliminary comparison between the conventional antenna and the new one, optimization and refinement. In particular, the design procedures recently proposed for non regular arrays generating pencil beam like patterns will be extended to the case of complex shaped patterns required in SAR instruments. The algorithms combining deterministic and numerical procedures seem particularly suitable for the objective. For the optimization and refinement, several further constraints will be imposed including the electromagnetic coupling between contiguous radiators. The study will be done considering as inputs the requirements of an existing mission and the RF performances but also the mass, cost and complexity aspects of the new architecture will be compared with a conventional reference case. Deliverables Study Report Application/Need Date Earth Explorer 9, TRL 5 by 2015 Duration (Months) 24 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-8200
Consistency with Harmonisation TBD
TRP Reference T123-301QT Activity Title Preliminary Reliability Assessment of Millimetre-Wave Low Noise Amplifiers Objectives Millimetre wave Low Noise Amplifiers (LNA) (frequency: 50GHz, 89GHz, 166GHz, 183GHz, 229GHz) are required by the Post-EPS mission and more specifically for microwave radiometer receivers at Microwave Sounder instrument and at Microwave Imager instrument level. The objectives of this activity are to define and to perform millimetre wave LNAs evaluation testing (through temperature step stress tests, endurance tests, environmental tests, others) in order to perform the preliminary reliability assessment of the parts for the Post-EPS mission. Description
Page 10 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Based on the environmental and operational lifetime requirements of the Post-EPS mission, this activity will be divided into 4 major tasks: -Definition and manufacturing of the structures/packages dedicated to the test of existing LNAs -Assembly and initial DC and RF testing of the LNAs -Reliability Test plan definition -Reliability testing and results analysis Deliverables Breadboard Application/Need Date Post-EPS mission, Microwave Sounder (MWS) instrument and Microwave Imager (MWI) instrument. Need date: 2012 Duration (Months) 24 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-8217, T-8218, T-8219, T-8216
Activity A18 from Technolo for Passive Millimetre and Submillimetre Wave Instruments roadmap ( proposed Consistency with Harmonisation 2010 version)
TRP Reference T123-302QT Activity Title Preliminary Reliability Assessment of Millimetre-Wave Detectors Objectives Millimetre wave detectors (detector diode frequency: 89GHz, 166GHz, 229GHz) are required by the Post-EPS mission and more specifically for microwave radiometer receivers at Microwave Sounder instrument and at Microwave Imager instrument level. The objectives of this activity are to define and to perform millimetre wave detector evaluation testing (through temperature step stress tests, endurance tests, environmental tests, others) in order to perform the preliminary reliability assessment of the parts for the Post-EPS mission. Description Based on the environmental and operational lifetime requirements of the Post-EPS mission, this activity will be divided into 5 major tasks: -Manufacturing of the detector diodes (frequency: 89GHz, 166GHz and 229GHz) -Manufacturing of the detector blocks -Initial DC and RF electrical measurements -Reliability Test plan definition -Reliability testing and results analysis Deliverables Breadboard Application/Need Date Post-EPS mission, Microwave Sounder (MWS) instrument and Microwave (MWI) Imager instrument. Need Date: 2012 Duration (Months) 18 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-8217, T-8218, T-8219, T-8216
Activity A46 from Technolo for Passive Millimetre and Submillimetre Wave Instruments roadmap ( proposed Consistency with Harmonisation 2010 version)
1 - 02 - Optical Payloads
TRP Reference T107-308EE Activity Title Synergy between lidar and passive optical measurements Objectives The objective is to improve atmospheric monitoring and atmospheric correction, particularly of aerosols, using a synergy of active lidars and passive optical sensors Description Current atmospheric and surface imagers assume aerosols which are modelled from experimental data and ground measurements assuming simple generalized conditions and aerosol composition. These models make further assumptions on aerosol vertical distribution, refractive indices for different size ranges, and differing dependence on relative humidity. The models are subsequently used in remote sensing to process satellite data and derive atmospheric, land and ocean products. Existing atmospheric products from imagers make pre-assumptions on the vertical structure of the aerosol size distribution and often misclassify the aerosol types. Land surface algorithms, such as MERIS terrestrial vegetation index, produce significant errors in the presence of large aerosol loading interpreted with current models. Ocean colour atmospheric correction in coastal zones and in-land seas can fail or produce substantial errors due to incorrect aerosol models used in the processing. Aerosol vertical distribution is needed to resolve surface properties below absorbing aerosols, such as dust and smoke.
Despite several years of experience with lidar and optical instruments in space and on the ground, there is still limited research and no operational applications envisaged concerning the synergy of these measurements to improve atmospheric correction and monitoring of aerosols. The lidar measurements provide vertically resolved aerosol optical and microphysical properties giving an unprecedented opportunity to build the knowledge of global empirical aerosols, their distribution and the consequent impact on climate and environment, including atmospheric pollution. On the other hand, the imagers provide significant advantage due to their wide spatial coverage compared to lidars. Their observations can be substantially improved across different applications using lidar-derived information.
At present, the most common approach to model and validate aerosol products derived from imagers is using the AERONET (AErosol RObotic NETwork) ground-based data that provides amongst other parameters aerosol optical depth, size distribution, and single scattering albedo. To derive these products certain assumptions are made, for example, it is assumed that the vertical distribution of the aerosol is homogeneous or bi-layered. From lidar
Page 11 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
measurements is clear that the vertical structure and distribution of the aerosol properties is much more complex and the modelling and validation of imager aerosol products would strongly benefit from the lidar information. Furthermore, in the aerosol retrieval the aerosol absorption is poorly characterized for important aerosol types, like urban, smoke and dust. In this respect the Earlinet network (Pappalardo et al., 2004), provides quality controlled lidar ground-based measurements that are very well suited for the purpose of this study.
The objective of the project is to develop and test synergistic retrieval methodologies based on passive and active satellite and ground measurements. The project will also provide scientific requirements in support of future measurement needs that can improve the synergy between lidars and imagers. Three possible synergy scenarios are to be investigated: a) lidars could support the improvement of aerosol modelling and correction, including non-spherical aerosols (volcanic ash and soil dust), pollution aerosols and biomass burning, as well as a better understanding of the impact of vertical aerosol distributions on imager column observations; b) atmospheric correction and atmospheric monitoring of passive instruments could be directly improved using collocated lidar aerosol products, such as total aerosol type and optical depth (Tian et al., 2009); c) atmospheric product validation could be further enhanced using the synergistic approach that provides the 3-d information on the aerosols distribution. The availability of an already mature database containing lidar ground-based measurements collocated with satellite-based data will facilitate the analysis and verification of the aerosol parameters derived from the satellite retrievals (GSP, 2008).
The outcome of the study is particularly relevant for all ESA imaging missions where aerosols and atmospheric correction are of high importance. The deliverables will be a review of current aerosol modelling and atmospheric correction using imagers and lidars, development of synergistic retrievals of aerosol models, development of atmospheric corrections, the review and acquisition of adequate imager data along with validation of the developed methods, delivery of aerosol models and recommendations on measurement requirements (ground and space borne) to improve the synergistic modelling capability between lidars and imagers.
References: 1. Pappalardo, G. et al., Aerosol lidar intercomparison in the framework of EARLINET. 3. Raman lidar algorithm for aerosol extinction, backscatter and lidar ratio, Appl. Opt., 43, 5370-5385, 2004a. 2. TIAN Liqiao, CHEN Xiaoling, ZHANG Tinglu, GONG Wei, CHEN Liqiong, LU Jianzhong, ZHAO Xi, ZHANG Wei, YU Zhifeng, “Atmospheric correction of ocean color imagery over turbid coastal waters using active and passive remote sensing”, Chinese Journal of Oceanology and Limnology Vol. 27 No. 1, pp. 124-128, 2009. 3. GSP Aerosol and Clouds: Long-Term Database from Space-Borne Lidar Measurements, 2008 Deliverables Study Report, ATBDS Application/Need Date Post-EPS, new algorithm by 2014 Duration (Months) 16 Estimated Current TRL N/A Target TRL Algorithim
SW Clause N/A Reference to ESTER T-8888
Consistency with Harmonisation TBD
TRP Reference T107-312EE Activity Title Red edge positioning (REP) techniques for Earth Observation optical missions Objectives This activity aims at evaluating the feasibility, the accuracy and the robustness of REP techniques for possible applications in Earth Observation Description Red Edge Positioning (REP) techniques are gaining more and more importance in the retrieval methodologies for their capability of providing additional information in support to vegetation and natural surfaces observation. Studies initially made by the use of mathematical models are now supported by on ground measurements and by remote sensing data coming from hyperspectral airborne flights, which however remain localized to few pre-defined areas. The preliminary results seem promising for the future systematic exploitation for the space systems. However there are still question mark with respect to the applicability of these techniques to spaceborne EO (effects of the atmosphere, spatial and spectral resolution...). Indeed these effects could impact the accuracy of the methods. On that direction, the study would investigate the feasibility, the potential and also the limitations of REP methods applied to the optical satellite missions (multispectral, hyperspectral at high and medium resolution), and provide tentative solutions whenever possible. The expected outputs are a set of methods and algorithms with a demonstrated accuracy and feasibility which could be proposed in support to future and potential optical missions. The new methods and algorithms shall be delivered in CDF compatible format. Deliverables Study Report Application/Need Date Earth Explorer 9, TRL 5 by 2015, GMES 2nd Generation Duration (Months) 18 Estimated Current TRL 1 Target TRL 2
SW Clause N/A Reference to ESTER T-7770
Consistency with Harmonisation TBD
TRP Reference T116-301MM Activity Title Focal plane direct deposited detector filters with high peak transmittance and out of band rejection Objectives The objective of the proposed activity is to develop a coating technology for the fabrication of Band Pass and Linear Variable Filters with high spectral resolution, peak transmittance and out-of-band rejection for direct deposition on the surface of photodetectors (linear or 2D-arrays). Description
Page 12 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
High quality Band Pass and Linear Variable Filters (LVF) are key components in many types of optical devices including pushbroom multispectral and hyperspectral imagers. The combination of LVF with a compact wide FOV telescope, such as a TMA, results in a highly compact, lightweight and relatively inexpensive hyperspectral imager. Currently focal plane filters are implemented by assembly from individual strips in a complex mechanical structure that must be accurately aligned over the detector arrays. LVFs presently available are typically deposited on glass substrates and demonstrate a spectral resolution of 10-15 nm and an operating range of about 400 nm in the visible region. The LVF out-of-band rejection is about 15% and peak transmittance is about 60%, which degrades SNR of an instrument which uses such a LVF.
The objective of the proposed activity is to develop coating technologies for the fabrication of BP strip line and LVF with high spectral resolution (<10 nm, preferably <5 nm), peak transmittance (> 90 %) and out-of-band rejection (< 15%, goal: 1-2%). Moreover, such technologies shall allow the deposition of the filters directly on the surface of the photodetector. The availability of a technology which allows direct coating onto detector surfaces significantly simplifies the design and assembly of the instruments avoiding the complex detector-filter mechanical interface. This has not been done before and will require a well thought out and careful collaborative approach between coating producers and detector manufacturers. Of critical importance are two problems: 1) Design and control of the coating process so as to avoid damage to the detector and 2) Spectral performance verification of the final breadboard filter-detector package response.
The outcome of this activity shall include the developed BP and LVF coating fabrication technology with precision geometric deposition control, BP and LVF deposited on a glass substrate, Si wafers and finally on representative operational detectors. Optical and spectral response performances shall be experimentally measured and verified, for each step and particularly on the final fabricated devices. Deliverables Prototype The availability of this technology will be of benefit for many missions in future Earth Explorer Core missions (e.g. EE-9) and Application/Need Date GMES 2nd Generation, TRL by 2015 Duration (Months) 18 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-8444
Consistency with Harmonisation TBD
TRP Reference T116-302MM Activity Title Innovative Materials for Super Black Low-Weight / Low-Cost Baffle Objectives To develop and test materials and surface treatment achieving low reflectivity suitable for low cost baffles. Description Performance, volume, and mass of an optical instrument may be driven by the capability of the baffle to absorb or reject straylight coming from spurious sources, as the Sun, the Moon or bright objects close to the field of view. Surface treatments on materials commonly used in space optical systems have relatively modest optical properties. Very low reflectivity coatings, like Martin Black, are usually very expensive and used only for small internal critical elements.
The need of better performing baffles is increased by the increased number of missions using large field of view telescopes, where the in-field stray-light may become a limiting factor. This is true in particular for the instrument measuring gas concentration as NOx by differential measurements. The stability of the instrument is of paramount importance in these measurements. Any spurious oscillation of the signal, caused for instance by stray-light, hampers the capability of the instrument to perform the measurement. Furthermore, the increased pressure on budget rules out the use of the existing end very expensive surface treatment.
The objective of the activity is to identify and test a suitable combination of materials and surface treatments to improve the straylight rejection of baffles to be used on board of EO missions.
The work is divided in two phases: Phase 1) -To perform a survey of possible light weight materials and black coatings suitable for cost effective manufacturing of baffles to improve absorption of straylight, -to identify materials and surface treatment suitable for production low cost baffles that significantly enhance the attenuation of straylight with respect to materials commonly used for baffle (e.g. carbon fibre, aluminium), Phase 2) -to manufacture a test sample -to measure optical characteristics as the Bidirectional Reflectance Distribution Function (BRDF). Deliverables Prototype Application/Need Date Earth Explorer 9, TRL 5 by 2015 Duration (Months) 12 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-8442
Consistency with Harmonisation TBD
TRP Reference T116-303MM Activity Title Ultralight Reflective Telescope with Low Surface Roughness Objectives
Page 13 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
The objective of this activity is firstly to build and test electro-formed mirror(s) with mass/surface ratio lower than 12 kg/m^2 and a surface roughness below 0.2 nm (phase 1) and secondly to design, manufacture, assembly and test a complete telescope made with such electro-formed mirrors (phase 2). Description Recent advancement on manufacturing of electro-formed mirrors allows the production of very thin and highly aspherical mirrors with very low surface roughness.
This technology, used in the past to manufacture x-ray mirrors of XMM and now for eROSITA, can now be used for mirrors of conventional telescopes as Ritchey-Chretien, Schmidt-Cassegrain, and Three Mirror Anastigmatic (TMAs). This technology allows producing mirrors with very low surface roughness and unprecedented low mass/surface ratio. Value of 12 kg/m^2 is anticipated by analysis. Surface roughness as low as 0.5nm has already been achieved on XMM, and it is expected that surface roughness as low as 0.2nm is obtainable. The improvements are related to the recent advancements on the manufacturing of the mandrels and of polishing techniques. These new technologies enable the manufacturing of telescopes suitable to meet the most demanding requirements of low stray-light, wide field-of-view, low mass, and low recurrent costs. Furthermore, the telescope structure can be built with materials whose Coefficient of Thermal Expansion (CTE) is similar to the CTE of the mirror substrate, ensuring a near athermal design suitable for harsh thermal environments.
Electro-formed mirrors, produced by replication on a mandrel, can be manufactured with a low recurrent cost, irrespective of the complexity of the mirrors, offering a competitive advantage for small satellite constellations.
The objective of the activity is to build and test a medium size telescope (200 - 300mm pupil diameter) able to cover a very wide wavelength band from UV up to FIR for spectrographic, multispectral or hyperspectral sensors.
The activity is divided in to two phases: Phase 1 (10 months, 300k euros): Manufacturing of critical mirrors. Phase 2 (8 months, 200k euros): Telescope Manufacturing Assembly Integration and Test.
Target applications: -Earth Observation: applications requiring very low stray-light. -Planetary Exploration (Rovers & Landers): to be used in ultra-light telescope, and harsh thermal environment. -CubeSats: low mass, low recurrent cost.
The technology has already raised the interest of European industry players, e.g. SSTL world leader in small satellite missions, which consider this technology highly beneficial to future EO missions and Space Exploration to reduce cost and schedule and to enable new sensor configurations. Deliverables Breadboard Application/Need Date Earth Explorer missions, TRL 5 by 2015 Duration (Months) 18 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-7861, T-8443
Consistency with Harmonisation TBD
TRP Reference T116-304MM Activity Title Design and manufacturing of spectral filters with low "Large Angle Scatter" (LAS) Objectives The objective of this activity is to investigate the origin of the "Large Angle Scatter" effect in spectral bandpass filters, to establish design guidelines for the reduction of this effect and to demonstrate the achievable improvement by manufacturing and testing of a demonstrator. Description Modern spectral bandpass filters have been reported to exhibit an effect of out-of-band scattering, which can detrimentally affect the performance of the instruments using such filters (e.g. OLI, Sentinel-2, SeoSat, Proba-V). Although the effect has been observed and verified for specific filters, the mechanism generating this unwanted out-of-band scatter is not understood. The purpose of the activity is to identify the origin of the "Large Angle Scatter" based on a detailed testing of filters with a known layer stack. Guidelines shall be given for the design of spectral filters to reduce the LAS effect. The given guidelines shall be implemented in a demonstrator filter design with equal performance of the initial stack, which shall be manufactured and tested in order to confirm the validity of the guidelines. Deliverables Breadboard Application/Need Date Earth Explorer 9, TRL 5 by 2015 Duration (Months) 18 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-7760, T-8442
Consistency with Harmonisation TBD
TRP Reference T116-305MM Activity Title Imaging Liquid Crystal Tuneable Filter (LCTF) technology demonstrator Objectives The objective of this activity is to design, build and test a liquid crystal (LC) tuneable filter technology demonstrator for future Earth observation and remote sensing missions from GEO.
Page 14 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Description Background, Motivation & Application:
A typical spectrometer on board an Earth observing satellite is implemented using spectral separation over the space domain (detector area) either by means of a diffractive element or via a series of dielectric narrowband filters. An imaging tuneable filter, on the contrary, is used alternatively to measure the spectral data-cube by multiplexing the spectral channels of a 2D scene over the time domain (hence making use of the full detector array for each wavelength). A LC tuneable filter (LCTF) consists of a number of cascaded tuneable LC waveplates (LC Variable retarders or LCVRs) sandwiched between polarisers (Lyot-type arrangement). In the case of a Lyot-type LCTF, the total tuning range can be rather large (e.g. 400-700nm or 700-1800nm, or otherwise designed) while the bandwidth is rather moderate (1-10nm). In addition, although they deliver lower transmission figures (lower for UV - higher for NIR) than conventional interferometric filters (they are inherently polarisation sensitive), they can be built with relative large apertures (30-40mm). A pre-requisite for the implementation of the LCTF technologies is obviously the mastering of manufacturing of LCVR components which shall form the critical components.
The purpose of this activity shall be the technology demonstration of a LCTF for future GEO EO missions.
An LCTF has no moving parts, can be made compact, lightweight and with a large clear aperture, can be reprogrammed and be used for random access to a set of spectral channels. The LC provides solid state like switching and therefore ensures vibration free spectral tuning, which helps to avoid pixel mis-registration, a major issue for observations from GEO. The reconfiguration speed of an LCTF could be a limiting factor for its application to LEO orbits or in similar situations where the scene changes rapidly. For GEO however, or in similar situations of "static" spectral content scenes (e.g. an imaging spectrometer on board a planetary rover, or for solar astronomy applications), a reconfiguration speed of several to several 10s of milliseconds (currently within reach with typical LC materials) can be considered adequate.
Looking beyond the applications and services supported by the GMES Sentinels presently under development, new mission concepts based on observations from the geostationary or geosynchronous orbits are likely to be considered for the future GMES missions. This technology therefore could clearly play a role in this context. Deliverables Breadboard Application/Need Date GMES 2nd Generation, TRL 5 by 2016 Duration (Months) 16 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-8444, T-8442
Consistency with Harmonisation TBD
TRP Reference T116-306MM Activity Title Advanced laser ranging technologies for altimetry Objectives The objective of this activity is to design, manufacture and test a breadboard for technology demonstration of novel laser ranging techniques and critical technologies that can be implemented for future Earth Observation altimeter missions. For example: 3D imaging (using novel CMOS detector technologies), waveform analysis or advanced continuous wave modulation techniques. Description Novel laser ranging techniques (like pseudo-random-noise or frequency-chirped CW modulations) and technologies (like APD arrays) can offer significant improvement in terms of system performance (including reduction of mass and power consumption, while promoting the increase of spatial resolution) for future long-range laser ranging systems for altimetry. Examples of future Earth Observation applications that could take advantage of novel laser ranging technologies include canopy height and structure, 3D surface topography, snow and ice depth and cover, and bathymetry (potential candidates for Earth Explorer 9).
A recently started GSP study ('Laser altimeter for Earth Observation and planetary missions') shall identify and define scientific requirements for future Earth Observation applications involving laser altimeter concepts and technologies and will establish conceptual instrument designs.
Based on these instrument concepts the proposed TRP activity will demonstrate the feasibility and maturity of critical technologies and techniques identified during a General Studies Programme study in view of the selected EO altimeter applications by breadboarding and testing the critical subsystems of the selected altimeter instrument concept. Deliverables Breadboard Application/Need Date Earth Explorer 9, TRL 5 by 2015 Duration (Months) 18 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-8193
Consistency with Harmonisation TBD
TRP Reference T116-307MM Activity Title Advanced large FOV UV/VIS/NIR/SWIR spectrometers Objectives The objective of this activity is to define advanced concepts and new architectures for large field of view spectrometers. Description
Page 15 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
A large field of view (FOV) of 60 degrees or more can be currently achieved at the cost of great complexity at instrument level. For instance the MERIS instrument on ENVISAT has a 68.5 degrees FOV shared by 5 identical modules. Each one of those modules needs to be calibrated independently and co-registered inducing tight constraints at system level in terms of stability. Reducing the number of modules, but still achieving large FOVs, will have beneficial impact on the mass and volume of the instrument and will ease the calibration and co-registration process. The goal of this activity is to assess the limits of the currently available spectrometer architectures (including the collecting optics) and to identify the needed technology developments to achieve the requirements of future GMES missions (like Sentinel-3 next generation). Also new instrument concepts, techniques and instrument architectures will be investigated. The targeted application is ocean/land colour measurements with a FOV up to 70 degrees, a spatial ground sampling of 100m and a spectral resolution of 1 nm over a large spectral band covering the UV UV/VIS/NIR/SWIR. The most promising concept will undergo a more detailed opto-mechanical design and its theoretical performances will be assessed. The instrument models shall be delivered in CDF compatible format. Deliverables Study Report Application/Need Date Earth Explorer 9, GMES II, TRL 5 by 2015 Duration (Months) 10 Estimated Current TRL 1 Target TRL 2
SW Clause N/A Reference to ESTER T-8178, T-8884
Consistency with Harmonisation TBD
TRP Reference T116-308MM Activity Title Large field-of-view static imaging FTS with Stationary Wave Integrated Fourier Transform Spectrometer (SWIFTS) Objectives The objective of this activity is to design, manufacture and integrate a breadboard for experimental characterization of the performances of a high resolution, large FOV spectrometer based on the SWIFTS technique. Description The Stationary Waves Integrated Fourier Transform Spectrometer is a new family of innovative high resolution micro-spectrometers. This technique aims at the miniaturization of static FTS instruments to an extent never reached before. A prototype with a volume smaller than 1mm3 has already been developed by the Laboratoire d'Astrophysique de l'Observatoire de Grenoble (LAOG). With such prototype, a spectral resolution of 0.150 nm has been achieved in the visible spectral range. Contrary to classical FTS instruments, a SWIFTS instrument is mechanism-free and is highly integrated with no need for additional optics. This technique can be extended to realize instruments with large field of view and high spectral resolution. In view of the increasing need for imaging FTS in Earth observation (PREMIER, PostEPS, IASI next generation, future Earth Explorer missions), the SWIFTS is a potential alternative to bulky and heavy instruments requiring high accuracy and high stability mechanisms and metrology. A previous Technical Assessment Study executed in 2009 has identified numerous potential applications in Earth observation. However, no instrument concepts for space applications using this technique are known. Furthermore, the SWIFTS technology is currently under development and its performances and characteristics have to be experimentally assessed. Hence, this activity aims at the definition of a large field of view and high spectral resolution static imaging FTS instrument using the SWIFTS technique for future Earth observation missions. Possible concepts for a large field of view static imaging FTS will be first proposed and analysed. In particular, for each concept, the constraints at system level will be identified and quantified. The instrument models shall be delivered in CDF compatible format. A trade-off of will be performed and a concept selected for experimental characterization. A breadboard will be designed and specified. The breadboard may have a complete array of SWIFTS modules or only a reduced number, depending on the cost and procurement time. Then the SWIFTS components will be manufactured or procured according to the breadboard specifications. Finally, the breadboard will be integrated and its performances experimentally assessed in laboratory environment. Deliverables Breadboard Application/Need Date Earth Explorer-9, TRL 5 by 2015 Duration (Months) 18 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-8175, T-8178
Consistency with Harmonisation TBD
TRP Reference T116-309MM Activity Title Alternative polishing layers on ceramic materials for high performance optical mirrors Objectives The objective of this activity is to investigate alternative polishing layers on ceramic materials for high performance optical mirrors. It is aimed at a reduction of the polishing time as well as at an improvement of the surface finish. A trade-off shall be performed between new alternative layer polishing technologies, which can be applied on the full aperture of large mirrors to achieve high performance optical mirror surfaces. Description
Page 16 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Telescope mirrors made of Silicon Carbide (SiC) substrates, which have to be of optical quality for operation in the visible spectrum, require a Chemical Vapour Deposition (CVD) SiC polishing layer to cover the porosity of the SiC bulk material. This is the case for both the SiC100 and the HB-Cesic ceramic material. For mirror apertures larger than 80cm diameter a brazing of the mirror segments is needed, if the standard CVD SiC polishing layer shall be applied, due to the size limitations of the available processing vessels. The mirror segments have first to be CVD coated and then, after the coating, be brazed, which complicates the mirror production process and introduces additional risks. Therefore alternative materials and techniques for layer deposition and polishing are strongly desired. The development shall be started on sample level for different sources of ceramic materials. An environmental qualification of the process(es) shall be performed with thermal cycling, humidity test, stress measurement etc. The thermo-mechanical analyses for cryogenic mirror applications shall be performed. In a second stage the process shall be demonstrated on a spherical medium size ceramic mirror with a critical slope. The scalability of the process to large diameters (3m class mirror) shall be demonstrated. Deliverables Breadboard Post-EPS, TRL 5 by 2014. All missions with SiC mirrors larger than 80cm (to avoid brazing of CVD-coated parts): Application/Need Date Geo-Oculus, High-resolution imaging from GEO Duration (Months) 12 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-7760, T-7855
Consistency with Harmonisation TBD
TRP Reference T116-310MM Activity Title Polishing techniques for low-scatter surfaces Objectives The objective of this activity is to develop and optimise super-polishing technologies for optical surfaces with a roughness below 0.5nm in order to achieve low optical scattering. Description Demands for straylight control in optical instruments for Earth observation are continuously increasing. Within an optical instrument typically two sources of straylight have to be controlled: Whereas out-of-field straylight can be suppressed with sophisticated baffles, in-field straylight can only be controlled by the surface roughness of the optical surfaces in the system. Although a surface roughness of about 1nm is de-facto standard, lower values are increasingly difficult to achieve but will be required in future applications. During the development new super-polishing technologies (e.g. chemo-mechanical techniques) shall be studied, developed, optimised and experimentally evaluated for a number of standard substrate materials used in space applications, e.g. Zerodur, SiC and CeSiC. Samples shall be polished and measurements of roughness, Power Spectral Density,Bidirectional Reflectance Distribution Function and microscopic inspection methods shall be used to drive the optimisation of the techniques and to assess their performance. Deliverables Breadboard Application/Need Date Earth Explorer 9, TRL 5 by 2015 Duration (Months) 18 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-8442, T-7855
activities B11 and B12 of the Technologies for Optical Passive Instruments - Strable and Lighweight Consistency with Harmonisation Structures, Mirrors- roadmap
TRP Reference T116-311MM Activity Title Non-polarising broadband optical coatings Objectives Post-EPS, TRL5 by 2014. To develop highly reflective and anti-reflective coatings operating throughout the entire wavelength range from the UV to the SWIR, which do not introduce polarisation. Description Earth observation instruments are often required to feature a low polarisation sensitivity. This is mainly addressed by suitable design measures such as reducing the angle of incidence on the optical surfaces as much as possible. The remaining polarisation sensitivity is given by the properties of the optical elements involved. For the most common elements like mirrors, dioptric beamsplitters or lenses the polarisation sensitivity is determined by their optical coatings. Currently the lack of availability of sufficiently wide bandwidth coatings significantly drives system designs and has a direct impact on mission level resources. (e.g. a single optical imaging system must be split in two, to ensure performance requirements are met with the consequent increase of mass and complexity). This activity shall address the design, manufacturing and testing of spectrally highly reflective/transmissive and non-polarising coatings. Typical angles of incidence, f-numbers and a wavelength range from UV to SWIR shall be taken into account as boundary conditions. In addition polarisation sensitivity shall be below 1%.
The produced coating samples shall be spectrally tested for wide bandwidth, reflectivity and polarisation properties. Deliverables Breadboard Future high resolution and high sensitivity broadband multispectral and hyperspectral Earth observation instruments. Application/Need Date Post-EPS, TRL 5 by 2014 Duration (Months) 18 Estimated Current TRL 3 Target TRL 4
Page 17 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
SW Clause N/A Reference to ESTER T-341, T-7760, T-7861, T-8444, T-8442, T-8884
actiivities B07, B08, B09 and B10 of the Technologies for Optical Passive Instruments -Stable and Consistency with Harmonisation Lightweight Structures, Mirrors - roadmap
TRP Reference T116-312MM Activity Title Optical Correlator testbed for high-resolution imaging from geostationary orbit Objectives The objective of this activity is to develop a test-bed for real-time testing of an optical correlator for high-resolution imaging from geostationary orbit. This test-bed shall simulate scene images like they will be generated by optical imagers in GEO orbit with short integration time, which will not be identical but drifting due to the satellite relative pointing error. The pointing vector of each short integration image will be measured with the optical correlation method. By integrating all slightly shifted images, but simultaneously correcting for the pointing error due to the satellite motion, which is known from the correlator measurements, the "final" high-SNR image will be generated. The impact of this correlator-based pointing compensation on the image quality (Modulation Transfer Function loss) and on the radiometric performance will be estimated by detailed image simulation and modelling. The required algorithms for the image construction will be developed within this activity. Description For high resolution imaging from geostationary orbit long integration times will be needed. This requires either an ultra-low satellite relative pointing error over the integration time or, alternatively, the determination of the telescope pointing vector during the integration of sub-images, which are taken with a short integration time, and the final post-integration of the several successively taken images into the "final" image with a high SNR. A new technique for measuring the telescope pointing vector is based on the optical correlator concept, which allows the measurement of the telescope pointing vector in the millisecond regime. However, in order to limit the required amount of data to be transmitted to ground, the post-integration processing shall be performed onboard of the spacecraft. The proposed activity includes: - To perform a system analysis of the Optical Correlator concept for a geo-stationary high-resolution imaging mission (sensor definition, correlation image size, location in the Field-of-View, number of sensors, scene requirements, correlation frequency), - To develop a test-bed for real-time tests, generating as an input short integration time images drifting due to the satellite relative pointing error, - To implement necessary adaptations and modifications of the interfaces of the Optical Correlator model, which has been developed within a GSTP activity, to the testbed, - To develop the algorithms for the integration of the sub-images and define an electronic architecture, which allows the quasi "real-time integration" of the sub-images. The Optical Correlator model and associated algorithms shall be delivered in CDF compatible formats. Deliverables Model (CDF Format) Application/Need Date High-resolution imaging from GEO, Earth Explorer 9, TRL5 by 2015 Duration (Months) 16 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-8887
Consistency with Harmonisation TBD
TRP Reference T117-301MM Activity Title InAs APD development for NIR and SWIR LIDAR applications Objectives Development of NIR/SWIR single and/or few photon counting detectors using InAs III-V technology for EO LIDAR missions and communication applications. Description Single and few photon counting detectors in the NIR/SWIR have application in both communications and EO LIDAR missions. This activity will further progress the basic technology developments that have been made under both a previous TRP programme and externally funded research. The previous work demonstrated a number of important results including 1. Very low excess noise factor (matching that of mercury-cadmium-telluride (MCT)), 2. Low dark current density, 3. High multiplication factors, 4. High sensitivity at 2.1 microns and with a cut off extending to 3.5 microns. Even so, a number of areas need further development and the main aim of this activity would be to develop a planar process to replace the current mesa etch fabrication technique. This would lead to lower leakage currents, stable devices and more repeatable production. Deliverables Breadboard Application/Need Date EO Lidar Missions, Post-EPS TRL5 by 2014 Duration (Months) 24 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-8187
Consistency with Harmonisation TBD
TRP Reference T117-302MM Activity Title 2.05 Microns Pulsed Holmium-Laser for Atmospheric CO2 and Methane Monitoring
Page 18 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Objectives Demonstration of a lidar transmitter laser breadboard at 2.05 microns based on Holmium-doped solid-state materials. In particular the development shall demonstrate both the extremely challenging spectral performance as well as the pulse energy levels of the transmitter required for the measurements. Description The measurement of atmospheric greenhouse gases from space represents a technical challenge in terms of laser transmitter and receiver technology. Previous studies have identified the spectral bands around 1.57 microns and 2.05 microns as the best candidates for active sensing of CO2 and methane. For the generation of laser radiation at any of the considered frequencies in the targeted bands there is either the possibility of frequency conversion (FC) of an established laser source, e.g. Nd:YAG, to the target wavelength or the option of direct generation (DG) from a suitable laser material. While the FC approach in general benefits from a certain flexibility with respect to the choice of target wavelength, the DG approach shows potential for a lower overall system complexity and increased wall-plug efficiency. In the 2 microns spectral domain powerful Holmium-lasers have been demonstrated suitable for (terrestrial) atmospheric water vapour Differential Absorption LIDAR (DIAL). Such a laser source offers the potential of DG generation of laser radiation at 2.05 microns for CO2 and methane spaceborne monitoring. This activity shall complement ongoing TRP activities on the development of source (laser + FC or fibre laser) and receiver technology in the 2.05 microns domain by exploring the feasibility and performance of a Holmium solid-state laser source at 2.05 microns for spaceborne DIAL measurements of CO2 and methane. Deliverables Breadboard Application/Need Date Earth Explorer 9, TRL5 by 2015 Duration (Months) 24 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-7757, T-8883
Consistency with Harmonisation activity C6 of Lidar Critical Subsystems roadmap proposed in June 2010 (not yet endorsed by IPC)
TRP Reference T117-303MM Activity Title CMOS APS spectral sensitivity optimisation Objectives Development and validation of CMOS APS detector designs covering UV, visible and NIR wavebands. Description This activity forms a part of the wider strategic programme to develop, stabilise and industrialise European capability in providing high-performance and practical Complementary metal-oxide-semiconductor (CMOS) Active Pixel Sensor (APS) detectors for space and related applications. CMOS APS detectors can be sensitive across a wide waveband from the UV to the NIR with performance optimisation in any particluar region achieved through a number of optimisations. This activity aims to develop and demonstrate various optimisation techniques for improved sensitivity at different wavelengths, including but not limited to, back-thinning (including related perfomance enhancing techniques), anti-reflection coatings and depletion depth. Deliverables Breadboard Application/Need Date All Remote Sensing EO misions/ TRL5 by 2015 Duration (Months) 24 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-8173, T-8757, T-7886
Consistency with Harmonisation TBD
TRP Reference T117-304MM Activity Title Investigation of Harmonic Conversion efficiency for space qualified Non Linear Optical (LNO) crystals Objectives The objective is to optimise the Conversion efficiency of materials LBO, KTP.fr, BBO, BiBO and KTA in non linear optical crystals. Second harmonic conversion should be aprox. 60% and third Harmonic conversion should be over 38%. This activity is not restricted to bulk crystals for frequency conversion but also comprises periodically-poled versions of the above mentioned and other materials (e.g. ppLN, ppKTP) that are needed in the context of optical parametric oscillators (OPO) and amplifiers (OPA), as envisaged in the context of greenhouse gas monitoring missions. Description In the frame of contract 4200021747, ESA investigated potential candidates for Non linear optical Conversion. Within the scope of this contract testing was performed and space qualification of additional NLO crystals apart from LBO. Within this contract, DLR irradiated, vibrated and TV tested BBO, BiBO, KTP, KTP.fr, as alternatives for LBO. During these tests some of the above crystals demonstrated better performances compared to LBO as far as Conversion Efficiency. This is currently one of the most notable deficiencies of the European Space industry in Lidar technologies, since European systems struggle to achieve 30% 3rd harmonic conversion efficiency, NASA system tests indicate efficiencies up to 45%. Deliverables Study Report Earth Explorer 9, TRL 5 by 2015. Future Lidar missions as well as free space optical telecom links benefit directly from more Application/Need Date efficient optical to optical frequency conversion. Duration (Months) 24 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-7757, T-7862, T-8883, T-8885
Consistency with Harmonisation No
Page 19 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
TRP Reference T117-305MM Activity Title Generic frequency converter unit for spaceborne lidar instruments Objectives This activity shall complement the developments undertaken in the previous TRP activity 'Pulsed laser source in NIR for lidar applications' (PULSNIR), ESA contr. No. 19813, on the development of a frequency converter in the 2.05 microns domain for spaceborne DIAL measurements of CO2. The technological approach adopted (doubly resonant Optical Paramatric Oscillator [OPO] and subsequent Optical Parametric Amplifiers [OPA]) turns out to be highly versatile such that it could be used for other wavelengths and trace gases (e.g. CH4, H2O, N2O,..) without major conceptual modifications. It is intended to carry on the PULSNIR work, making use of and complement the existing PULSNIR breadboard, by addressing the following missing performance demonstration / technical issues: 1. A second doubly resonant oscillator for the off-line wavelength to be implemented, and amplified using the same amplifier as the on-line oscillator. 2. A switch to alternate the on-line and off-line wavelength to be implemented. 3. Technical study and definition of a Frequency Reference Subsystem to be performed, in order to measure and lock the PULSNIR frequency converter unit's oscillator frequency with a reference gas cell. Coupling with the frequency converter unit should be achieved. 4. Separate and global functional tests to be performed with the bench and laboratory demonstration of gas detection. 5. Identification of the critical components of the PULSNIR frequency converter unit regarding a space environment to validate the adequacy of the architecture. 6. Investigate the necessary adaptations of the PULSNIR architecture / components for use at different wavelengths, in particular at 1.57 microns for CO2 monitoring (alternative) and for the monitoring of other greenhouse gases (CH4, H2O vapour, N2O). Description Future lidar instruments are expected to provide high accuracy measurements with no bias of main greenhouse gas concentrations in the lower troposphere. Such precise measurements are useful to determine where the sources and sinks are located and so to provide essential inputs to atmospheric transport and mixing models. However, more than two decades after initial developments, the technological maturity of lasers for space is still an issue to achieve the very challenging specifications that have to be fulfilled for spaceborne lidars. In this context the EC-ESA-EDA joint task force in March 2009 established a list of critical space technologies for European strategic non-dependence amongst which frequency converters form a key element.
Despite the fact that the Advanced Space Carbon and Climate Observation of Planet Earth (ASCOPE) mission proposal dedicated to the observation of atmospheric CO2 from a spaceborne lidar was not selected by the ESA mission assessment group due to technical immaturity the demand for such technology still exists, e.g. in the frame of the Agency's upcoming call for proposals for implementation in a Earth-Explorer-9 core mission. Also, a French/German collaboration has been selected to measure CH4 from a spaceborne lidar (MERLIN mission).
It has been demonstrated in a previous TRP activity 'Pulsed laser source in NIR for lidar applications' (PULSNIR) that most of the technical limitations of such a frequency converter laser can be overcome by an original approach based on optical parametric converters (OPOs in combination with an OPA) developed by ONERA (F). Compared to other approaches, the ONERA architecture shows two main advantages in the sense that it is (A) generic, i.e. it can be easily applied to various wavelengths and thereby green house gases: CO2, CH4, H20, N20,.. and (B) very compact and robust since it does not require an external laser source (injection seeder) to achieve the spectral specifications of the emitted radiation.
The PULSNIR design, converting from a 1.06 micron established pump laser source (similar to the ones on ALADIN or ATLID) to 2.05 microns, was based on a proprietary doubly resonant optical parametric oscillator (DROPO) design, followed by amplifier stages. In such optical parametric oscillator, narrow linewidth (single longitudinal mode), frequency stable operation is achieved without any seeding device. In this development activity, frequency measurement and locking were achieved using a commercial wavemeter.
Following this successful step, some more efforts are required in order to complete the demonstration of performance of this new architecture by having in the same autonomous bench both lidar frequencies, generated and alternately emitted, including their own frequency control units directly with respect to the frequency reference unit. Deliverables Breadboard Future missions, e.g. in the context of an Earth Explorer 9 Core Mission, incorporating a lidar instrument for the Application/Need Date measurement of atmospheric trace gases.TRL5 by 2015 Duration (Months) 20 Estimated Current TRL 3 Target TRL 4
SW Clause N/A Reference to ESTER T-7757, T-8883
Consistency with Harmonisation TBD
TRP Reference T117-306MM Activity Title Compact vacuum chamber for an Earth gravity gradiometer based on laser-cooled atom interferometry Objectives The provision of a compact vacuum chamber to be used for a gravity gradiometer based on atom interferometry as payload demonstrator for future Earth gravity missions. Description This activity will develop a critical component for the realisation of a compact atom interferometer sensor system for inertial sensing and metrology. The development of laser-cooled atom (Rb) interferometry systems requires the integration of several subsystems, including: laser systems for cooling, manipulating (atom optics), and detecting (e.g. by fluorescence) ensembles of atomic species; atom traps and atom beam sources; vacuum chamber with optical windows; atom detection systems. While activities to develop the required laser systems are being planned, the present activity will focus on the development of the vacuum chamber where the atom interferometry measurement takes place culminating in a breadboard. Deliverables Breadboard
Page 20 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Earth Gravity Post-GOCE type missions, by 2018. Also ideal for any space mission requiring inertial sensing and/or control to Application/Need Date a higher accuracy than currently available with macroscopic capacitive accelerometers. For instance: the metrology and control of inertial satellite platforms for future Fundamental Physics and Earth gravity missions. Duration (Months) 36 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-8644, T-8649
Consistency with Harmonisation TBD
TRP Reference T117-307MM Versatile high-fidelity reference gas cell as laser wavelength stabilisation unit for DIAL measurements of atmospheric trace Activity Title gases Objectives The present activity aims at the development and miniaturisation of an elegant breadboard of a laser wavelength stabilisation unit (LWSU) for lidar applications. The LWSU shall be based on a low power continuous-wave semiconductor laser that is referenced to the selected absorption feature of a target trace gas, e.g. CO2, CH4, H2O vapour, N2O, etc. For this purpose the semiconductor laser is locked to a miniature gas cell filled with the target gas. The LWSU shall demonstrate the aimed functionality not only for locking to the centre of a molecular absorption feature but also be capable of generating a wavelength with substantial offset (e.g. several GHz to several tens of GHz) from centre. The locking technique and electronics shall be versatile such that the same system architecture can be used without major modifications for various molecular species and a variety of their absorption features. The activity shall also comprise a trade-off study of the gas-cell-based LWSU vice-versa the use of an optical frequency comb in terms of performance, versatility, power/mass/volume, space-worthiness and cost. Description The use of lidar systems for spaceborne monitoring of atmospheric constituents and processes offers a number of advantages as compared to passive optical instruments. In general such transmitter lasers require at least a very precise knowledge of the emitted laser wavelength, e.g. for Doppler wind measurements (ALADIN) or aerosol detection (ATLID). Although for this type of lidar a stabilisation of the output to an absolute wavelength reference is not mandatory and a continuous wavelength monitoring is sufficient it might nevertheless offer significant advantages on system level (transmit/receive/data processing). However, in the context of differential absorption lidar (DIAL) measurements, the measurement principle relies on determining the relative absorption of two close by laser wavelengths to retrieve the concentration profile of an atmospheric constituent, like e.g. CO2, CH4 or various other trace gases. Therefore, it is essential to lock the output laser wavelength(s) very precisely and with a very high degree of stability to a specific molecular absorption feature. The outcome of two parallel ESA system level studies on the spaceborne monitoring of CO2 and CH4 has clearly indicated the highly challenging requirements on the wavelength accuracy (few tens of MHz) and stability (several hundred kHz) in order to achieve the necessary level of precision in trace gas concentration retrieval. The most straightforward way to produce such an absolute wavelength reference in a single step, i.e. without the need of on-board calibration or two-stage referencing, is to use the monitored species itself to generate this wavelength reference. To this end a low power semiconductor laser (subsequently used to seed the laser oscillator of the DIAL transmitter laser) is locked to a reference gas cell, e.g. containing CO2, using the transmission gradient of a molecular absorption feature. As most DIAL measurements from space require to place the transmitter laser wavelength into the wings of the chosen molecular absorption feature, i.e. off-centre, it is crucial that the LWSU provides the possibility to generate a minimum of two output wavelengths. These can be swept with high precision over a large range (several GHz for the ON line to several tens of GHz for the OFF line) from the centre of the absorption feature. The activity shall also investigate the pros and cons regarding a competitive approach to wavelength stabilisation and referencing as presented by an optical frequency comb (OFC). While the OFC forming a tightly spaced ruler across a wide frequency range is capable of covering a large number of wavelengths at the same time it still requires the use of additional technologies (highly accurate RF local oscillator, self-referencing or gas absorption cell) in order to achieve absolute wavelength reference properties. In this sense the gas-cell-based LWSU could form a necessary subunit to an OFC frequency ruler. Deliverables Breadboard Future missions, e.g. in the context of an Earth Explorer 9 Core Mission, incorporating a lidar instrument for the Application/Need Date measurement of atmospheric trace gases Duration (Months) 20 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-7757, T-8883, T-8885
Consistency with Harmonisation TBD
TRP Reference T117-308MM Activity Title Compact Optical Attitude Transfer System Objectives The provision of a compact optical attitude transfer system for use in a system of distributed sensing elements with a view to increase the collecting area of the signal to be detected. Description A number of future Earth observation space missions could strongly benefit from the use of distributed sensing elements with a view to increase the collecting area of the signal to be detected and, thereby, the amount of information that can be obtained from a given altitude. For instance, radar altimetry would greatly benefit from separate antennae positioned tens of metres apart in order to increase swath coverage and surface sampling by means of interferometric methods. In general, knowledge of the position and attitude of the distributed sensing elements is of paramount importance in the associated data processing and information extraction. When the sensing elements are attached to the main satellite by means semi-rigid structures, however, the knowledge requirement is relaxed to the attitude alone. Deliverables Breadboard Application/Need Date WatER and Wavemill. GMES 2nd Generation, TRL5 by 2016
Page 21 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Duration (Months) 24 Estimated Current TRL 2 Target TRL 3 T-8878 SW Clause N/A Reference to ESTER T-8220 Consistency with Harmonisation N/A
TRP Reference T117-309MM Activity Title Laser Stabilisation Unit for Interferometric Earth Gravity Measurements Objectives This activity aims at the development of a breadboard of the high-precision laser stabilisation unit necessary to stabilise the laser for the LDI mission. It is closely linked to the delvelopment of the laser source itself as undertaken in the TRP activity T116-044MM "High-Stability Laser with Fibre Amplifier for Interferometric Earth Gravity Measurements" in the 2010 TRP plan. Description The Directorate of Earth Observation is currently in the process of defining a follow-up mission to GOCE, that offers both higher spatial resolution and measurement accuracy in the mapping of the Earth's gravity field. A previous GSP study 'Laser Doppler Interferometry Mission for Earth Gravity' [LDI]) has shown the principal feasibility of such undertaking based on optical interferometry between two satellites in 10-200 km distant formation flight. As a first development step the TRP activity 'Laser Interferometry High-Precision Tracking for LEO' has demonstrated the measurement principle with reduced performance requirements in a laboratory setup. The final mission-representative measurement precision relies crucially on the availability of an extremely long-term stable laser source, the specifications of which are close to but a bit more relaxed than those of the lasers for LISA. This activity aims at the development of a breadboard of a high-fidelity stabilisation loop based on an extremely stable optical cavity that shall be used to stabilise the laser source to implemented in the LDI mission. The implementation of the present development activity relies on the availability of a suitable laser source in order to be able to demonstrate the performance of such a stabilisation loop. Therefore the activity is strongly linked to the TRP activity T116-044MM "High-Stability Laser with Fibre Amplifier for Interferometric Earth Gravity Measurements" in the current 2010 TRP plan. Deliverables Breadboard Application/Need Date Satellite-to-satellite interferometry missions for Earth gravity mapping, Earth Explorer 9 TRL5 by 2015 Duration (Months) 24 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-8194, T-8883
Consistency with Harmonisation N/A
TRP Reference T117-310MM Activity Title Large area SWIR detector array development Objectives Development of large format, small to medium pixel detector arrays for high dynamic range, high performance operation in the NIR and SWIR. Description Future Earth observation missions will require larger detector arrays than currently available for use in the NIR and SWIR wavebands and with higher resolution. This will require not only the production of uniform MCT material and reticle stitching capability for the ROIC design but also the capability for hybridisation of large devices with a high number of pixels. The detectors will also need to offer both low signal, low-noise operation and high signal, photon shot noise limited performance, possibly simultaneously, implying the implementation of novel techniques to support such operation. This activity aims to develop a large format(2k x 2k), high performance array with high resolution (pixel size of order 15 microns) that demonstrates these features. Deliverables Breadboard Application/Need Date All EO Missions, TRL5 by 2015 Duration (Months) 24 Estimated Current TRL 3 Target TRL 4
SW Clause N/A Reference to ESTER T-8891
Consistency with Harmonisation TBD
TRP Reference T123-303QT Activity Title Back end microlenses deposition process evaluation for CMOS image sensors Objectives
Page 22 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Micro lenses are today widely used within consumer imaging products, not only in order to compensate for non 100% fill factor but also in view of improving Modulation Transfer Function (MTF) (e.g. for back side illuminated devices). In modern consumer Complementary metal-oxide-semiconductor (CMOS) image sensors, such microlenses are mainly directed for small pixel pitch in the 1-5 µm range and are routinely manufactured within the standard flow of CIS foundries. For space application, microlenses are not yet used while there is a need for such devices for performance improvements of CMOS image sensors (fill factor, MTF, Parasitic Light Sensitivity…). The standard process deposition in commercial applications, generally small semi sphere of few µm are deposited, is not compatible with the usual space applications pitch range for CMOS sensor (10 to 100 µm). It is therefore proposed to evaluate European capability for microlenses deposition processes at back end manufacturing level for space application. Different materials can be evaluated (such as non organic material which are more robust for space) and different process technologies such as for example microjet printing. Some work is ongoing at European level in microlenses fabrication: Fraunhofer Institue, CSEM (optical fill factor enhancement for smart pixels)… Description The first step of this study is to review the existing European processes dedicated to microlenses deposition in terms of technological capabilities (pitch, available geometry…), performances (dead zone/fill factor, transmission, deposition accuracy, uniformity …) and space environment (radiation, ageing, temperature…). Based on the selection of the most appropriate process and materials, the second part of the study will consist in the design and manufacturing of a Demonstrator which specifications will take full benefit of microlenses deposition for performance improvements. Deliverables Breadboard Application/Need Date Earth Observation missions, TRL5 by 2015 Duration (Months) 30 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-8442, T-7886
Consistency with Harmonisation TBD
1 - 03 - Platforms / Others
TRP Reference T101-301ED Activity Title New Techniques for lossy multi/hyperspectral compression for very high data rate instruments Objectives Develop a new algorithm for lossy multi/hyperspectral compression that is suitable for space. Description In the frame of GMES evolution, next-generation high-resolution super-spectral land optical imagery will require ad-hoc multi/hyperspectral lossy compression. The actual techniques (based on transforms) are very efficient in terms of compression, but quite demanding in terms of computing resource and also not robust enough to cope with not highly correlated bands. New techniques based on predictors are very promising in terms of robustness and lower complexity. The new technique shall be robust, in order to be able to perform inter-band compression even when the correlation is not very high (e.g., in case of slight mis-registration between the bands). Moreover it shall be efficient and not complex, in order to be implemented on-board in a real time context. The objective of this activity is to develop an algorithm that is feasible for space and suitable for the second generation of Sentinel2-like missions. In order to prove the feasibility of real time operation, a prototype of the algorithm will be implemented in a commercial FPGA, like the Virtex family. The output of this activity will support the standardization activities in the frame of the Consultative Committee for Space Data Systems (CCSDS) committee Deliverables VHDL prototype implemented in a commercial FPGA Application/Need Date GMES 2nd Generation, TRL 5 by 2016 Duration (Months) 18 Estimated Current TRL 2 Target TRL 4 Open Source SW Clause Reference to ESTER T-8331 Code Consistency with Harmonisation No
TRP Reference T101-302ED Activity Title SpaceWire SpaceFibre network bridge Objectives Development of a SpaceWire - SpaceFibre network bridge design validated on a commercial FPGA Description The SpaceWire - SpaceFibre network bridge shall provide a number of SpaceWire as well as SpaceFibre interfaces and none blocking routing function in between all of them. There should be also parallel ports that allow the injection of data to the SpaceFibre links at their full speed. In addition the device shall be traffic schedule conscious and able to act a bus guardian which removes unexpected traffic from the network. This bus guardian function is crucial for sharing the network between high data rate payload and command a control traffic in a fault tolerant way. In this activity a SpaceWire – SpaceFibre network bridge ASIC shall be designed and the design shall be validated on commercial FPGA technology. Deliverables ASIC design validated on commercial FPGA technology
Page 23 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Application/Need Date GMES 2nd Generation, TRL 5 by 2016 Duration (Months) 12 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-7801, T-8897
Consistency with Harmonisation TBD
TRP Reference T105-301EC Activity Title AOCS and image navigation and registration for Earth observation from GEO Objectives To improve the image products by optimising the AOCS and the image processing at system level, using advanced filtering techniques and ground control points. Description Earth observation from GEO is characterised by an extended availability of the full Earth disk which gives the possibility to react very quickly to alerts (e.g. fires, etc).
The extended availability of the Earth disk means that the signal to noise ratio can be increased. This in turn requires the spacecraft attitude to be stable. Agility aspects will also be considered, typically to react to alerts as fast as possible.
The final quality of the image product is achieved by the image processing and the AOCS. This activity will assess the interactions between the AOCS and the image processing to optimise the image quality.
AOCS trade-offs will be done. Filtering techniques will be assessed. The interfaces between the AOCS and the image processing will be investigated. The role and impact of ground control points to improve the image products will also be assessed.
Automatic on-board image correlation by dedicated electronics will be considered.
An AOCS simulator combined with an image simulator is necessary and will be developed as part of the activity. This simulator shall be compatible with CDF formats.
A demonstration model to prove the concept will be built.
Deliverables Demonstration model Post-EPS, TRL 5 by 2014. All missions with SiC mirrors larger than 80cm (to avoid brazing of CVD-coated parts): Application/Need Date Geo-Oculus, High-resolution imaging from GEO Duration (Months) 18 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-8887
Consistency with Harmonisation TBD
TRP Reference T105-302EC Activity Title Next Generation Gravity mission: AOCS solutions and technologies Objectives Following the concept and system studies on the next generation gravity mission (NGGM), which will present a number of AOCS challenges, the objective is to define and evaluate the associated AOCS solutions and technologies, to identify the critical technologies (at hardware and software definition level), to assess their feasibility and the design drivers. Description
Page 24 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
The objectives of a Next-Generation Gravity Mission (NGGM) are to provide the temporal variations of the Earth gravity field over a time span of several years with high spatial resolution (comparable to that provided by GOCE) and higher temporal resolution than GRACE. Preparatory and on-going studies suggest that the NGGM ought to be based on Low-Low Satellite-to-Satellite Tracking (LL-SST). This means that the satellites fly in a loose formation in which they are free to move under the action of the gravity field and air drag perturbations, at very low altitude to increase the sensitivity to the higher harmonics of the Earth gravity field.
Whatever the number of the satellites and the preferred constellation for a proper temporal and spatial sampling of the Earth surface, the distance variation between the satellite centres of mass has to be measured with high resolution by a distance metrology set-up. Moreover, in order to retrieve the gravity signal from the laser metrology measurements, the non-gravitational force measurements need to removed. The proper operation of the accelerometers therefore requires drag-free control in order to reduce the level of the linear and angular non-gravitational accelerations.
This implies a series of technical challenges that have to be carefully addressed, independant of the baseline chosen and the space segment configuration: - Interaction of the formation flying (FF) control loop with the single (each satellite) drag-free controls in the measurement bandwidth; - Authority of the FF closed loop control, in order to address how much loose the control should be without affecting the measurement bandwidth and losing the optical inter-satellite link; - Investigation and analyses on centralized or decentralized FF control; - Feasibility and drivers for the realization of the relative attitude control design for the precise pointing of the laser beam.
Preliminary definition and validation on a simulator of the AOCS solutions for NGGM missions will allow to identify on prototype SW the AOCS drivers and to define in detail the algorithms/hardware developments necessary. Considering that the NGGM system studies run in parallel, it is likely that two different baseline systems will have to be studied separately. Deliverables Study Report Application/Need Date Earth Explorer 9 , TRL 5 by 2015 Duration (Months) 15 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-8876
Consistency with Harmonisation No
TRP Reference T107-303EE Activity Title Test-bed for channel modeling in EO Ka band DDL systems Objectives The objective is to perform the experimental assessment of channel conditions and operational parameters for the implementation of High data rate Down Links (HDRL) for Earth Observation missions operating at 26 GHz. Description The increased requirements for Data down Links (DDL) in terms of data throughput and data timeliness for EO missions, with particular regard to optical and SAR missions, cannot be fulfilled by the limited spectrum available at X band.
To this end the allocated spectrum at Ka band is a primary candidate for future HDRL systems but their implementation depends, in addition to the development of specific technologies for the spatial and ground segment, on accurate channel models.
Indeed, at Ka band the effects of all the atmospheric components on the radio signal are more severe than at X band, considering also the need to operate up to low elevation angles to maximize the overall contact time. A baseline design should address a ground segment including few large ground stations distributed mainly at high and mid-latitudes. Another design option is based on a global network of small terminals connected by a network backbone (ref. SafetyNET ground system) .
Therefore the channel models for system design, simulation and control must provide inputs for a large variety of conditions (climatological, type of orbit, system parameters) but the available propagation models have been derived almost exclusively from measurements at mid-latitudes in Europe or USA with satellites in geostationary orbits. Furthermore in addition to the link budget also some key elements for the operations, like the ground large antenna tracking system and the selection of coding and modulation schemes are affected by propagation effects.
Therefore there is the need to implement a Ka band experimental test-bed for low elevation and/or non-GEO satellites to perform a long-term (more than 1 year) statistical verification of the models, data and algorithms considered for the design of this type of systems making use of beacon, TTC signals, ground based remote sensing techniques (e.g. radar, radiometric and GPS sensors), Numerical Weather prediction data (e.g. ECMWF) and local meteorological measurements (radiosonde data and ground sensors). The current channel models used for system simulation will be updated according to the results of the experimental verification. The experiment should be performed in collaboration between propagation experts and industrial entities designing and operating EO DDL systems. Deliverables Test Report Application/Need Date GMES 2nd Generation, TRL 5 by 2016 Duration (Months) 24 Estimated Current TRL 2 Target TRL 3 Operational SW Clause Reference to ESTER T-5363 S/W Consistency with Harmonisation TBD
TRP Reference T119-301MP Activity Title Miniaturised Gridded Ion Engine breadboarding and testing for future Earth Observation missions
Page 25 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Objectives The main objective is to initiate the development of a miniaturised Gridded Ion Engine capable of delivering thrust up to 2mN for the lateral drag force compensation and the attitude control of the future NGGM (Next-Generation Gravity Mission), as well as other EO missions requiring fine attitude and orbit control by means of low-noise force actuators, e.g. the possible high-resolution GEO imaging mission Description Since 2003 ESA has promoted studies in order to establish scientific requirements, identify the most appropriate measurement techniques, start the associated technology developments, and define the system scenarios for a Next-Generation Gravity Mission (NGGM). Such a mission will make use of the Low-Low Satellite-to-Satellite Tracking (LL-SST) technique to monitor the temporal variations of the Earth gravity field over a long time span but with much higher spatial resolution and with improved temporal resolution.
The low-thrust Gridded Ion Engine (GIE) with variable thrust has been identified as one of the key technologies for the realisation of the NGGM. In particular, it allows: -satellite orbit maintenance at its operational altitude; -satellite formation control; -implementation of the drag-free control at level of each satellite; -attitude control of each satellite; -laser beam pointing control.
For the broad range of NGGM applications, more than one thruster typology is required, depending also on the satellite configuration and on the type of formation geometry. For the simplest in-line formation, in which the satellites chase each other along the same orbit and experience a main drag force always along the same axis, the need of two types of thrusters has been identified (main thrusters and lateral thrusters).
Among the various electric propulsion technologies reviewed for this application, the Gridded Ion Engines (GIE) appears very promising for the NGGM due to its scalability. Indeed, it seems possible to implement the GIE thrusters in the required two typologies:
-main GIE thrusters for the along-track drag force compensation, orbit and formation control; -lateral miniaturised GIE thrusters for the lateral drag force compensation and the attitude/laser beam control.
Development up to breadboard level of the miniaturised GIE has been initiated by the Agency in 2007 leading to a first breadboard demonstrating capability to deliver thrust in the 50 - 500 microN range.
In line with the latest results from the NGGM preparatory studies additional work is required at thruster level to demonstrate capability to fully meet the NGGM specific needs: such as dynamic thrust range increase (50 microN to 2 milliN) to cope with the large variation of the drag forces encountered in a long duration mission, minimisation of the specific power, specific impulse increase.
The activity aims at further investigating the miniaturised GIE thruster and breadboarding a model covering up to 2 milliN thrust. The thruster shall demonstrate compliance to the major NGGM performance requirements via testing. Particular attention is required for the thrust noise density requirement in the frequency region from 1mHz to 0.1Hz for which direct measurements shall be performed.
The technology will be applicable to many other missions, for EO but also for other objectives, which require precise attitude and orbit control by means of low-noise force actuators that are widely configurable. Examples include the high-resolution geostationary (or geosynchronous) imaging mission concept under definition by the Agency and the formations of new missions with EO operational missions (e.g., EO convoy concept). Deliverables Breadboard Earth Explorer 9, TRL5 by 2015. Future Next-Generation Gravity Mission, as well as other EO missions requiring fine attitude Application/Need Date and orbit control by means of low-noise force actuators that are widely configurable, e.g. the possible high-resolution GEO imaging mission. Duration (Months) 24 Estimated Current TRL 3 Target TRL 4
SW Clause N/A Reference to ESTER T-1013
activity required by thrust level requirements for NGGM (Next-Generation Gravity Mission/ Post GOCE) Consistency with Harmonisation application. Preparatory activities for this mission were approved in the Electric Propulsion Technologies roadmap
TRP Reference T119-302MP Activity Title Development of a Functionally Graded / Composite Spacecraft Thruster Nozzle Objectives The ultimate goals are to: -Provide a thruster nozzle design that would allow enhanced performance and increase mission capabilities. -Provide a thruster nozzle design that would give European thruster suppliers a clear advantage.
The specific objectives of this proposal are to: -Define specific thruster technical requirements needed to achieve performance improvement targets. -Define nozzle grading requirements. -Research, identify, critically analyse and down-select material combinations, grading options and manufacturing techniques. Ideally this should yield 2 to 5 options. -Perform preliminary testing to assess material characteristics and further down-select to 1-2 functionally graded thruster nozzle design options that would be further developed in a subsequent study. Description
Page 26 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Spacecraft thruster nozzles must meet extreme environment requirements: -High and low temperatures extremes -Large thermal gradients -Moderate stresses from chamber pressure, thrust and cantilevered nozzle mass -Launcher dynamic loading -Exposure to caustic propellants -Exposure to oxygen at elevated temperatures (oxidation potential) Thruster performance is limited by the nozzle's ability to withstand these environments. That is, higher thruster performance can be achieved with thruster nozzles that can withstand higher temperatures and higher pressures while still meeting the remaining requirements.
Current spacecraft thruster nozzles are primarily made from refractory metals, noble metals and alloys or a combination of these. Noble metal or ceramic coatings or liners are typically used with the refractory metals to ensure resistance to high temperature oxidation. There have also been attempts to develop ceramic nozzles.
When considering performance enhancement many of these have insufficient material properties (e.g. maximum temperature, strength, corrosion resistance). Others have material combinations with incompatible properties (e.g. CTE).
Application of functionally graded composite materials has strong potential to yield a thruster nozzle that can meet the more stringent requirements needed for enhanced performance. Functionally graded materials provide a gradual transition in composition and structure across the material. The associated gradual change in properties eliminates or significantly reduces the incompatibilities.
As an example, a graded transition from ceramic to a high thermally conductive metal to a more structural element could be used. Deliverables Breadboard Application/Need Date Apogee engine, main engine or attitude control thruster for earth orbit spacecraft. TRL5 by 2015 Duration (Months) 18 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-867
Consistency with Harmonisation TBD
TRP Reference T119-303MP Activity Title Consolidation of micro-PIM Field Emission Thruster Design Objectives Following the consolidation of the Micro Power Injection Moulding (µPIM) manufacturing process (done in the frame of a currently running ESA contract), the objectives of the proposed activity are: 1) to consolidate the thruster design and 2) to assess the thruster lifetime and performance evolution over extended firing times. Description To achieve the stated objectives, the following activities shall be carried out: - Consolidation of Thruster Design by implementing the lessons learned from on-going testing into the thruster design (observed propellant contamination, etc.). This shall include a consolidated design of an activation procedure such as the one implemented for the recent long-term tests.
- To design and to implement a focusing electrode in the present thruster breadboard in order to limit the half-angle beam divergence to < 35° as required by most missions.
- To run an endurance test to demonstrate the robustness and the stability of the thruster performance. The goal is to empty one or more full propellant tank = approx. 3000 h at 100 µN. Deliverables Study Report Application/Need Date Post-GOCE, Earth Explorer 9, TRL5 by 2015 Duration (Months) 18 Estimated Current TRL 3 Target TRL 4
SW Clause N/A Reference to ESTER T-1013
Consistency with Harmonisation TBD
TRP Reference T121-301MT Activity Title 2-stage cooler for detector cooling between 30K and 50K Objectives To design, develop and test a 2-stage cooler making use of compressors previously developed for Earth Observation applications (e.g. Large Pulse Tube Cooler, High Power Stirling Cooler). The aim is to provide detector cooling below 50K and an intermediate cooling stage below 120K. In addition, a 2-stage detector cryostat breadboard shall be developed and integrated with the cooler to verify system aspects of 2-stage cooling. Description
Page 27 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
To provide efficient cooling below 50K, required for long wavelength detector arrays, an intermediate cooling stage below 120K is required to minimise the parasitic losses of the detector cryostat. Multistage coolers have been developed and are currently under development for Science applications, reaching temperatures below 20K. But these coolers are considered too large for EO applications and overengineered for applications above 30K. It is therefore proposed to build up a 2-stage cooler based on the single stage coolers currently considered for EO applications and integrate it into a breadboard detector cryostat to verify I/F and MAIT of 2-stage systems. Deliverables Engineering Model Application/Need Date Earth Explorer 9, TR5 by 2015 Duration (Months) 18 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-8179, T-7876, T-8886, T-8902
Consistency with Harmonisation Harmonisation took place in 2007, to be considered for new harmonisation planned for 2011/2012
TRP Reference T121-302MT Activity Title Development of a 40-80K vibration-free cooler Objectives To develop, manufacture and test an Engineering Model of a "vibration-free" cooler that can provide active cooling for a temperature in the range of 40-80K and with a heat lift capacity in the range of 0.5 to 1 W Description With the development of vibration-free AOCS technologies (magnetic bearing reaction wheels, microthrusters), cryocoolers (Stirling, Pulse Tube) will become the main source of microvibrations. To overcome this difficulty and cope with missions (Science and Earth Observation) that have more and more stringent pointing requirements, it is necessary to develop alternate cooling solution or to adapt current technologies to generate no mechanical disturbances. The Darwin development studies covered 15K and 4K class coolers, but a need also exists in the 40-80K range (IR detection).
One possibility for such a system could be Sorption Coolers + Passive Radiators: - The cooling power is obtained by using the Joule-Thomson process/cycle. First, a gas is pressurized from a low pressure to a high pressure by a compressor. The gas reaches the Joule-Thomson restriction and expands adiabatically and isenthalpically. Due to the expansion, the gas cools down and becomes partly saturated liquid. The liquid fraction is evaporated by a heat load. Finally, the vapour flows back and the cycle is closed. - The compressor necessary to run this cycle is not a mechanical compressor but a sorption compressor, which uses the adsorbing-desorbing properties of e.g. charcoal cells to compress the fluid. Therefore no inherent vibration. The adsorbing is done by cooling down the charcoal cell using passive radiators, the desorbing by electrical heating.
The advantages of such system are the following: no moving parts, hence vibration-free & long life-time; easily scalable to different sizes and cooling powers; simple electronics (only management of electrical heaters); possibility of separating compressor and cold stage (linked only by small-diameter tubing) providing flexibility for accommodation & layout. Drawbacks are: need for passive radiator, some temperatures are not reachable with this cooling cycle (typically between 45 and 60K), the figure of merit (Cooling Power)/(Total Radiator Area) is lower than for Pulse Tube/Stirling coolers.
A first assessment shows that such a system for an Earth Observation mission could have the following features: cooling power: 0.5W@70K; mass less than 5kg (without radiator); electrical power less than 50W; passive radiator of about 1 m2 at 200K (depending on the mission). Deliverables Elegant Breadboard Application/Need Date Next generation of Earth Explorer missions > 2015. Duration (Months) 24 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-678, T-8896
Consistency with Harmonisation TBD
TRP Reference T124-301QE Activity Title Fast contamination modelling tool Objectives This study aims to develop a contamination modelling tool to enable fast, preliminary analyses. Description
The increased need to accurately predict in-flight molecular contamination levels has led to the development of complex contamination modelling tools, e.g. COMOVA. Those tools allow for detailed and consolidated analyses but are complex to use and often do not provide a friendly user interface. For such reasons they are rarely proposed in project’s early phases. This study aims to develop a light and user friendly contamination modelling tool to enable preliminary analyses. The tool should provide a way to predict and easily visualize contamination levels on sensitive surfaces due to material outgassing. Also interactions with the surrounding atmosphere, not negligible in LEO, should be considered. In addition, the model can be used for contamination requirements definition and contamination assessment during on-ground vacuum testing of spacecraft and instruments. Deliverables Software Application/Need Date 2013 Duration (Months) 24 Estimated Current TRL Algorithm Target TRL Beta Software
Page 28 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Open Source SW Clause Reference to ESTER T-8392 Code Consistency with Harmonisation TBD
TRP Reference T126-301GT Activity Title Enriching EO ontology services using Product Trees - PTREE Objectives This project aims at developing new technologies capable of improving EO product and service retrieval by considering Product Tree hierarchies; in combination with an ontology framework. This project should be considered in a context such as GMES with numerous Service Operators and Providers and the consequent proliferation of EO Products and Service which require effective retrieval and dynamic classification. More frequently, new EO services are based on the combination of pre-existing processing components; typically using the orchestration of Web-based services but also using specialized frameworks for EO processing like the TRP project Knowledge-centred Earth Observation (KEO). In turn, products delivered by such new services can be classified and, therefore, retrieved considering the logic of their orchestration workflows; or processing graphs. Ontologies devised to effectively retrieve EO products and services operate in synergy with the relations extracted from the processing graphs. Description This project will try to identify innovative technologies capable of overcoming current limitations and in particular the fact that Ontology learning techniques have been developed based on reverse engineering of relational databases and, generally, from formal relations between different data objects. On the other hand, trends on EO data exploitation are moving towards the production of EO high level products using multiple of low level products, from different satellites and service providers; leading to complex data processing chains represented by graphs (e.g. BPMN) which users can directly edit and modify. Deliverables 1- Prototype demonstrator of ontology learning techniques applied to a number of EO applications whose processing chains formally expressed in standard form; BPEL, BPMN or equivalent. Input from reference ESA applications like Knowledge-centred Earth Observation (KEO) and Service Support Environment (SSE). 2- Comparison of the Demonstrator with current ontology used by GMES portal (http://gmesdata.esa.int/web/gsc/home) Deliverables Prototype Application/Need Date All EE and EW missions, 2014 Duration (Months) 12 Estimated Current TRL Algorithm Target TRL Prototype Open Source SW Clause Reference to ESTER T-553 Code Consistency with Harmonisation TBD
TRP Reference T126-302GT Activity Title EO Ground Segment elements automation: feasibility - GEAF Objectives The objective of the activity is to demonstrate the maturity of innovative technologies on data processing automation and to verify the feasibility of their integration into next generation of Ground Segment Processing facilities to move towards autonomy, in order to reduce operational costs and improve quality of EO products.
This will be performed by: - demonstrating the feasibility of improved automation of the management of EO Ground Processing Facilities, currently performed by operators, using various techniques and technologies for the execution of monitoring, diagnosis, reconfiguration and re-planning; - modelling and assessing the specific technologies for a distributed G/S facility architecture based on functional elements linked through standard interfaces suitable for implementing a concept of "Software bus", allowing flexible chaining and reorganisation of the Ground Segment processes (e.g., through dynamic workflows) as well as easy addition of new functions, products or services. Description ESA studies on the subject are focused so far on spacecraft autonomy (SMART-FDIR, Advanced Fault Detection, Isolation and Recovery - AFDIR - and ongoing study about generic FDIR models).
This activity will assess status of the art and applicability to the EO Ground Segment of emerging innovative techniques and technologies, including: automated diagnosis on critical components; Fault Detection, Identification and Recovery (FDIR); intelligent failure tolerant control; probabilistic causal reasoning in diagnosis; Model-Based Reasoning (MBR); software agents for monitoring, diagnosis, reconfiguration, and re-planning; fault and recovery learning; dynamic workflows. The Linear Temporal Logic modelling developed in the last 20 years is possibly the most robust technology which can be applied to the automation within the ground segment. Since its definition, the Linear Temporal Logic approach has been used mainly in formal verification of software, therefore COTS and open source tools like SPIN are available for these purposes. We assume that these tools can be used for the proof that the developed technology meets the objectives of this project and not as baseline for the project technology development.
One of the EO Directorate's objective is to reduce operation costs of EO facilities (acquisition station, processing facility, control centre). This could be achieved by increasing automation (and possibly reaching autonomy) in combination with a new modular and flexible organisation of the various elements. Deliverables: Requirements, new technologies and concepts and their trade-offs, demonstrators, feasibility assessment and evaluation, system architecture. Deliverables Prototype Application/Need Date EO Ground Segment distributed facilities and related element, 2014
Page 29 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Duration (Months) 18 Estimated Current TRL Algorithm Target TRL Prototype
SW Clause N/A Reference to ESTER T-8594
Consistency with Harmonisation TBD
TRP Reference T126-303GT Activity Title PDGS e-Collaboration - PDGSE Objectives The objective of this project is to develop innovative technologies and advance the techniques for eCollaboration within the PDGS. Objective if this project is to identify critical areas of improvement within the PDGS, analyse the available e-collaboration techniques and identify the scenarios where they could be used, identify the metrics for evaluation and the architectural changes eventually needed and finally provide a ranking of selected technologies and prototype most promising use cases. Description The technologies to be addressed include: 1- traditional e-collaboration and group management tools and techniques like shared whiteboarding, multimedia conferencing, calendaring and scheduling, e-mailing; 2- social networking techniques like wiki, forums and blogs and the most recent ones like Twitter ; 3 - tools for information publishing and public use like Google Earth and the tool used by non governmental organisation for disaster response "Ushahidi" which has the goal of aggregating information from the public for use in crisis response. The Ushahidi platform allows to gather distributed data via SMS, email or web and visualize it on a map or timeline and it was used in the Haiti earthquake response. Last but not least the project shall address the collaboration aspect of 4 - peer to peer for data dissemination, as this subject is normally addressed as a telecommunication topic, even if several of the telecommunication peer-to-peer technologies show an improvement (performance, resilience) over traditional telecommunication technologies. Further, only if the data is used in a e-collaboration context where individual user resources (computing, network and storage) are made available to the other users within the community.
All the PDGS components and functions shall be addressed, however priority shall be given to certain horizontal subjects which appear of interest within the PDGS and at the interface between PDGS and users, like monitoring, notification, alerting, issue tracking, product quality and validation, discovery and publishing.
Previous activities on the subject include the THEVOICE GSP Study http://www.esa-thevoice.org/ and the limited experience on the use of social networking techniques for e-collaboration on ground segment interface standardisation, see http://wiki.services.eoportal.org.
Deliverables User Requirement and Operational Scenarios TN Strategy for PDGS e-collaboration TN, including impact and improvements on ground segment performance and operability TN Selected Techniques for PDGS e-collaboration TN Prototype Demonstration Requirements Prototype Implementation Plan Test and evaluation TN Deliverables Prototype Application/Need Date All missions, 2014 Duration (Months) 18 Estimated Current TRL Algorithm Target TRL Prototype
SW Clause N/A Reference to ESTER T-539
Consistency with Harmonisation TBD
TRP Reference T126-304GT Activity Title Virtual workspaces for EO Scientists - VIRES Objectives This project aims at developing the technologies necessary to support Scientists willing to develop additional processing elements and algorithmic applications for Earth Watch and Earth Explorer missions. The objective is to develop the new technologies for the virtualization of the support to the EO processor and application development, validation and - possibly - exploitation; independently of the environment where the actual EO data is run. Given the focus on global programmes and large amount of data to be processed, the Scientists should be able to develop and pre-validate their work on their own workstations/institution with a minimum set of data, later validate, deploy and share their work at the PDGS virtual workspace without the need to moving large amount of data from the PDGS to the Scientist's facilities. Within the same project, also the usage of third-party cloud-computing services (is Internet-based computing, shared resources on demand). will be envisaged; for example for an exploitation phase of the applications.
Virtualization should provide an adequately flexible platform for seeming less portability from deployment, commissioning to exploitation.
Additionally, layering a virtualization layer on current PDGS processing resources should provide an exploitation scenario which entails the dynamic provisioning of processing resources; both from the PDGS and third parties. Description
Page 30 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Third-Party processors are hosted on the PDGS for the purpose of experimentation, validation and exploitation of high-level data processing and information mining. These services are currently provided via Grid-based systems, standard EO libraries/toolboxes and large distributed data banks see G-Pod (http://gpod.eo.esa.int).
Within the project the first Virtual Workspaces scenario (data intensive) will rely on such back-end systems for the necessary data and processing capabilities via a virtualization layer for which a new technology will be developed.
The second scenario (computing intensive) will have to exploit Cloud Computing platforms should offer the bases for the provision of Workspace Services for scientific purposes, e.g. project Cumulus [Wang et al. 2009]. Such platform shall be configured to the specific EO needs, like data-intense processing, access to near-real time acquisitions, combination of data from different instruments/satellites.
This project will set the ground for the large programmatic activities planned in the near future. Furthermore forums for scientific collaboration in the EO domain, like Intelligent and Image Information Mining (IIM) Virtual Laboratory (http://earth.eo.esa.int/rtd/IIMCG/IIMvLab/) need the technology development to enable the workspace services needed to run their algorithms. Deliverables 1- Demonstrator for a Scientist Virtual Toolkit - able to run on the Scientist workstation on a virtual layer and providing an simple deployment path to a PDGS's Virtual Workspace. 2- Prototype an ESA private cloud onto current Grid-based infrastructure for the provision of Virtual Workspaces. 3- Case Studies: For two scientific EO applications perform the full cycle from Scientist's workstation to an ESA cloud service and to a commercial cloud service. Deliverables Prototype Application/Need Date Earth Explorer 9, 2015 Duration (Months) 15 Estimated Current TRL Algorithm Target TRL Prototype Open Source SW Clause Reference to ESTER T-7649 Code Consistency with Harmonisation TBD
TRP Reference T126-305GT Activity Title Optical Multisensor Radiance Data Fusion Techniques - OPTIRAD Objectives The objective of this project is to advance techniques for optical multisensor radiance data fusion by the use of assimilation techniques. This will ultimatively lead to optimized radiance fields from different sensors (a virtual 'super-sensor') which will be of benefit for remote sensing applications such as land cover classification, land use monitoring, optimized quantitative retrieval of bio-geophysical products of use for various applications such as precision farming, and supporting science of land surface processes and their interactions with the atmosphere. Furthermore, such a technology developemnt would be also of benefit for Agencies operating optical sensors for montioring the quality of single sensors in a constellation, and analysing the impact of future sensor concepts.
This activity follows the scientific assessment of different scheme options (EO-LDAS study) and shall provide the users with a library of modules within the Knowledge Centred Earth Observation (KEO) environment, enabling a user driven assimilation test-bed test for different schemes using real EO observations. Description Retrieving quantitatively geo-biophysical variables from remote sensing data, subject of intensive research during the last decade, is more and more finding its way into operational ground segment processing. The benefits are obvious - the extraction of information from EO data is taking a large bulk of work from remote sensing data users and thus allowing less experienced users to directly benefit form the wealth of information provided by the various systems. Provision of higher level data is therefore the key for enlarging and expanding EO user communities.
Geo-biophysical variables are proxies in models aiming at describing land surface processes. As such they are scale (spatial and temporal) dependant. In general the scale dependancy is not linear. In other words, products derived from two sensors with equal radiometric and spectral characteristics but different spatial resolutions and applying one and the same retrieval technique will be different and are not linear in scale. The relationship is even more complex when using different sensors with different retrieval concepts but aiming at the same physical quantity. As an example, it is clear that a soil moisture product derived from Envisat ASAR data will be different from the soil moisture product derived from SMOS data. In addition, retrieval techniques applied are adapted to sensor characteristics and have to account for the operationality of the ground segments further constraining the use of the derived higher level products. The retrievals implemented in the ground segments are not necessarily physically based (empirical, semi-empirical methods), and in general rely heavily on auxiliary information (partly derived from other EO systems) with often unknown uncertainties which makes it very difficult to assess accuracies and trace possible error sources. Considering the above, it comes as no surprise that more and more communities complain about data inconsistencies.
Inconsistencies of products derived from different sensor systems are considered the stumbling block for the insertion of different EO data into land surface models as used by the climate modelling communities.
Consequently, a trend towards the direct assimilation of radiance fields instead of higher level data products can be observed in the communities.The advantage is obvious. Submodels which allow the insertion of radiance fields are being used rather than higher level products with unkown uncertainty levels, allowing a better control of possible biases. However, this approach is constrained to the assimilation of single satellite data only, as additional data from other sensors with different characteristics would require additional submodels which would need to be made consistent with other model components.
A possible solution to this problem is the assimilation of radiance fields decoupled from process-models. This requires a generic Radiative Transfer Function (RTF) assimilation scheme, allowing the assimilation of radiance fields observed by sensors with different spatial, spectral, angular, and temporal resolution. Such a system is high on the wishlist of the community for many years and considering the recent advances in RTF modelling, it is now feasible to develop such a system.
Page 31 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
The availability of such a system clearly offers a range of advantages to scientific users, service providers and satellite operators, such as: - consistency in data products, - making full use of synergies between different sensor systems in a consistent way (physically based), - providing uncertainties in radiance fields most important for further processing, - allowing to make full use of sensor constellations and thus decreasing product uncertainties by an improved coverage (temporal, spectral, angular) - providing a tool which allows to assess the value of new sensor concepts in a given constellation - providing a tool which allows cross-sensor calibration in a consistent way
First activities in the respect have been already undertaken by ESA in the frame of a scientific study (EO-LDAS: Earth Observation - Land Data Assimilation Scheme) which analysed the requirements of such a schemes, a possible implementation and the interfaces between the different modules. The next step is now to provide the science community with a library of scheme modules allowing them to test various implementation options.
The activity would also focus on: 1) Expanding the process model capabilities. 2) Add one or more different RT canopy representations in addition to the 1-D model already included in the prototype. eg GORT rather directly or via a LUT interface. 3) Alternatives to existing minimisation. This would address the issue that currently requires an adjoint for the process model and observation operator in order for the system to work neatly, which limits the choice of process model and RT codes. Options include fully implementing sequential smoother approach to add to the VAR approach in the prototype; for the VAR approach, use finite differences (could be cost implications); use a Numerical Algorithm Group/Numerical Recipies (NAG/NR) optimisation routine that does not need gradients (again could be slow and less robust and more sensitive to initial estimates); reconsider the optimisation function through other inverse mapping approaches. 4) Enhance capabilities to deal with / report uncertainties. Include the capability of providing uncertainties for - the retrieved state - the simulated observations via the Hessian, i.e. second derivative code 5) Combined parameter and state estimation: 6) Code optimisation / performance - Speed up codes in general - Improve the trade off of memory / CPU time 7) System wrapper for the Knowledge Centred Earth Observation (KEO) environment Deliverables Prototype Application/Need Date Sentinel 2-3 Duration (Months) 18 Estimated Current TRL Algorithm Target TRL Prototype Open Source SW Clause Reference to ESTER T-8595 Code Consistency with Harmonisation TBD
Page 32 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
4 - Space Transportation & Re-entry Technologies
4 - 01 - Launchers oriented Technologies
TRP Reference T402-301SW Activity Title Hardware-Software Dependability for Launchers Objectives Develop dependability design approach for critical launcher Software. Refine, adapt and specialise the technologies developed in the frame of the COMPASS project to cope with the specificities of the Launcher Systems domain. Provide facilities for automated Model-Based diagnosability analysis and FDIR verification. Description Launcher systems are characterised by high Dependability and Safety demands in general and critical Hard Real-Time operation of the Software-based functions in particular. In this respect the interplay between the continuous and discrete control elements is of major importance. Current development practices suffer from discontinuity between the Software and System RAMS (reliability, maintanability, availability, safety) activities, hindering the System-level analysis of the operational correctness, the reached Dependability levels, and the effectiveness of the FDIR (Failure Detection, Isolation and Recovery). Dedicated Software RAMS processes coherent with the System RAMS approaches are required to facilitate the Launcher Development Process and to enable effective System-level analyses from the early Development Phases. The ESA COMPASS TRP project has developed the basic technologies required to achieve the integration of the Software and System perspectives, the means of formal specification of the nominal and probabilistic fault behaviour, and the automation of the corresponding System-level analyses. These facilities shall be refined and extended for use in the context of the Launcher Software Systems specificities, providing the dedicated support to diagnosability and diagnosis trade-off analyses, RAMS analyses and Probabilistic Risk Assessment, and probabilistic FDIR evaluation. It shall allow building the Launcher systems with the required Dependability and Safety levels. Deliverables Prototype Application/Need Date All launchers (NGL in particular) Software Systems Engineering / TRL5 by 2015 Duration (Months) 24 Estimated Current TRL Algorithm Target TRL Prototype
SW Clause N/A Reference to ESTER T-7743, T-908, T-7660, T-7662, T-303, T-7667, T-7666, T-8414, T-8603
Consistency with Harmonisation TBD
TRP Reference T403-301EP Activity Title Enhanced power sources compatible with extended thermal environment Objectives Current power / energy sources are not compatible with large temperature range, thus inducing specific fitting constraints (e.g. need for heating system on Primary batteries for A5 ECA). The objective of this activity is to investigate new sources compatible with a larger thermal environment, thus simplifying the design and reducing configuration contraints. Description The current Li ion technology used at low temperatures has some limitations: the charge rate is low, the specific energy is low. Standard Li ion technology has been used at low temperature with an adequate thermal management. However, in case of failure of this thermal management, the battery could be lost. Low temperature cells have already been developed for other applications (military), and well as high temperature cells (oil industry). The main change with respect to the current Li ion technology is the electrolyte used. The present activity aims at answering to this problem, focusing on new electrolytes for wider temperature range and optimisation of Li ion cell for low temperature or high temperature. The preliminary assessments show that nanostructure materials could be useful as additive in electrodes, or as electrodes at low temperature (-20°C), however, the manufacturing of electrodes using nanomaterials may cause some health and safety issues that should be taken into account. The activity will deal with primary and secondary batteries, and will focus on electrolyte and material to wider battery temperature range. Deliverables Study Report, test report Application/Need Date TRL5>2015 Duration (Months) 18 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-7808
Consistency with Harmonisation activities D1 and D2 of the batteries roadmap.
TRP Reference T403-302EP Activity Title Sources for high power / energy demanding devices Objectives Investigate power sources for high energy / power demanding devices for launcher application. Description
Page 33 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Background: A TRP activity on "Supercapacitor - high Power Li battery system study" (Contract n° 21814/08/NL/LvH) finished in 2010, including launcher applications. High power Li ion batteries (based on SAFT VL8P) are qualified for VEGA launcher. Several trade-off are / will be performed on potential interest on more electrical actuation: - NGL main stage Thrust Vector Actuation System consider possibility to use Electro Mechanical Actuator (GSTP activity in progress on the actuator part) - NGL command of valves Power sources such as supercapacitor, high power Li ion cell, hybrid power source (i.e supercapacitor/Li ion battery; primary Li battery/Li ion battery shall be considered in these assessments). The proposed activity shall cover: 1) synthesis of needs; 2) review of existing technologies (performance & limitations); this task is a follow on of the TRP activity ("Supercapacitor - high Power Li battery system study") finished in February 2010; 3) selection of promising technologies and preliminary assessment by test. Deliverables Study Report, test report Application/Need Date All launchers / TRL5>2015 Duration (Months) 15 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-8815, T-8062
Consistency with Harmonisation activities F1, F2 and F3 of the batteries roadmap.
TRP Reference T404-301EE Activity Title Improvement of solar flare prediction Objectives The objective of this activity is to improve solar flare prediction applicable for launcher mission of a duration up to 12h Description Background: Launcher on-board electronics are not tolerant to solar flare environment. For Sun Synchronous (SSO) missions as well as for Geostationary (GEO) mission (12h including de-orbiting), the launcher is not protected by the geomagnetic field from solar flare induced radiation environment, particularly resulting in single event effects (SEE). Prediction techniques are needed to avoid to launch while there is a significant risk of solar flare for the mission duration. Proposed activity: 1) review of scientific methods for prediction of solar events that produce SEE at Earth based on solar and other observation 2) characterisation of the requirements, and different methods performance & limitations 3) prototype a system for warning of possible events and informing of magnitudes of events in progress Deliverables Prototype Application/Need Date 2013 Duration (Months) 12 Estimated Current TRL N/A Target TRL Prototype
SW Clause N/A Reference to ESTER T-15
Consistency with Harmonisation C8 activity of the Radiation Environment Model Roadmap (1/C8)
TRP Reference T405-301EC Activity Title Feasibility study of in-flight model validation and performance analysis of launchers GNC Objectives Valuable in-flight results for a new satellite AOCS cannot be obtained without a detailed preparation well ahead of the first flight. This also applies to new launchers and the objective of this activity is to maximise the return of VEGA and FLPP maiden flights in the GNC area. Not only the overall performance will thus be assessed, but it will be possible to validate and refine the pre-flight mathematical models and associated parameters, or to identify discrepancies which, even minor, might have some significant impact in upcoming missions. This activity will assess by analysis and simulations the feasibility of models and parameters identification. It will develop post-flight estimation algorithms and it will propose recommendations for the implementation of monitoring sensors and associated telemetry. In addition, the activity will explore the feasibility of the on-line identification of critical dynamic parameters and GNC stability margins. Description The activity is organised as follows: Task 1: Definition and user requirements for development. In this phase mainly real-time aspects, access of the necessary of input data The activity will consist of: 1. Review the models and parameters of paramount importance for GNC stability and performance. These include launcher structural models and MCI data, disturbing torque and force models, Inertial Measurement Unit and AOCS thrusters models, etc. 2. Propose and trade specific estimation techniques for each model versus potential monitoring sensors and analyse their feasibility and expected accuracy. 3. Select the most promising and challenging activities. Develop associated post flight estimation algorithms and test them through detailed simulations of a flight sequence. 4. Issue recommendations for the implementation and architecture of data acquisition sensors, pre-processing algorithms, and associated telemetry. 5. Explore the feasibility and interest of on-board implementation for on-line identification of critical dynamic parameters and GNC stability margins.
Page 34 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Deliverables Software Application/Need Date VEGA/Ariane/FLPP IXV / IXV2 2015 Duration (Months) 12 Estimated Current TRL N/A Target TRL Prototype Operational SW Clause Reference to ESTER Competitive AOCS and GNC T-8075, T-8303, T-8860 S/W Consistency with Harmonisation N/A
TRP Reference T405-302EC Activity Title Launcher GNC Simulation Sizing Tools Objectives The objective of the activity is to develop a computational infrastructure and software tools for launch vehicles GNC system sizing in both atmospheric and orbital flight configurations. The tools (software suite) shall be used in preliminary phases and up to detailed design phases. The tools shall enable the support of CDF studies as well as the development of alternate launch vehicles control solutions for more advanced support needs. The objective is to create a suite of software tools that would make use of software design templates for launch vehicles and re-entry stages. The software templates to be developed shall include navigation blocks, guidance blocks, and advanced control engineering blocks for rapid development and assessment. The software suite shall be made compatible with CDF data inputs and outputs. Description In order to develop the launcher GNC simulation sizing Tools it is necessary to develop a modular software that allows to integrate the various subsystems. Interface requirements shall be developed to enable the transfer models from subsystem disciplines into the integrated system for closed loop simulation and GNC design. A benchmark design cycle shall be defined in order to capture all processes, involved in the launch vehicle sizing from a GNC perspective enabling the sensitivity studies at all subsystem levels in order to achieve optimized system level objectives satisfying GNC performance and robustness needs. A scalable mission and GNC model manager shall be developed based on an integrated GNC architecture upon which rapid GNC tuning shall be performed. The tool shall allow to provide optimized trade-off solutions which can be negotiated with subsystem designers to manage design margin policy. Task1: Definition phase, for definition mission manager template, LV model template, GNC design template. Benchmark definition Task2: Development plan Templates and Benchmark and test plan Task3: Design phase Mission, Model, Prototype Control and Analysis template design Task4: Detailed Design phase : Application to Benchmarks Task5: V&V phase with test plan execution Task6: Activity Synthesis Deliverables Software Application/Need Date LV VEGA/Ariane/FLPP / IXV / ARV, and potentially ExoMars and any future EDL (Entry, Descent, Landing) mission Duration (Months) 12 Estimated Current TRL Algorithm Target TRL Prototype Operational SW Clause Reference to ESTER Competitive AOCS and GNC, Modern Control Design T-8303, T-8858 S/W Consistency with Harmonisation TBD
TRP Reference T406-301ET Activity Title GPS/Galileo Receiver Signal techniques for Launchers Objectives Study and definition of the GPS/Galileo receiver signal techniques for launchers, for future integration in the HiNAV system. The use of GNSS receivers in the launcher environment has a number of challenges at signal level, and this activity will investigate their mitigation, mainly focusing on the high dynamics, the high attitude change rates, the signal scintillation in the equatorial regions, the fast variation of tropospheric, ionospheric biases and jamming/spoofing of the signal. Description
Page 35 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Currently, two activities are on-going concerning the use of GNSS for launchers. First, the High Integrity Hybrid Navigation (HiNAV) Demonstrator, under TRP contract, defining a hybrid navigation system based on the deep integration of Inertial Measurement Unit (IMU), GPS plus a number of additional sensors. Then, the HiNAV system architecture consolidation, under TRP contract number: 21687, in order to define a consolidated integrated architecture including GPS and Galileo. The ultimate objective of HiNAV is to have a multi-mission (ascent, re-entry, landing) navigation system, which is robust to both the S/C dynamics and external signal perturbations such as ionospheric scintillations, multipath, jamming or interferences. High frequency inertial aiding proposed in HiNAV enables to meet these requirements while decreasing drastically the bandwidth of the receiver ; this has two main interests : low C/N0 tracking capability and possibility to use integrated Doppler measurements instead of code-only (the phase error can be kept low by design, enabling to easily detect cycle slips).
During these two activities, a number of challenges have been identified concerning the use of a GPS/Galileo receiver under the launcher environmental conditions. These key challenges are the dynamics environment of the launcher (vibrations & high dynamics, shocks), the high attitude change rates (up to 30 deg/s for VEGA), the signal scintillation in the equatorial regions, the fast variation of tropospheric, ionospheric biases during the launch,.., and jamming/spoofing of the signal.
Although HiNAV has provided a detailed design of the GPS/GALILEO receiver for such applications, and demonstrated its ability to sustain infinite jerk while providing accurate measurements, the design could further improved at GPS/GALILEO signal processing level within the receiver focusing on the challenges mentioned above, and in particular by improving its anti-jamming capability and its ability to operate in high angular rate environment (with associated antenna management).
This activity will investigate, at GPS/Galileo receiver level, techniques to further improve the HiNAV robustness at signal and signal processing levels, and upgrade the GPS/Galileo receiver architecture to be integrated in HiNAV. Deliverables Test report Applications: launchers, reusable space transportation system, atmospheric re-entry vehicle. HiNAV covers the functional, performance, safety and operational requirements for satisfying AR5 Evolution, Vega Evolution Application/Need Date and Crew Space Transportation System (CSTS) navigation needs. Date: 2014. Duration (Months) 12 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-7753, T-36, T-8057, T-8302
This activity is a consolidation of activities C02 and C03 of the On-Board Radio Navigation Receivers Consistency with Harmonisation roadmap. The need for this activity appeared in the course of activity C03
TRP Reference T406-302ET Activity Title Robust TM System for Future Launchers - exploring space-time coding (MIMO) Objectives To improve robustness, performance and power efficiency of future launcher telemetry (TM) systems using constrained RF links (i.e. Data Relay). Description The use of Data Relay links to support launcher telemetry systems has been a subject of interest for operators like Arianespace given its potential benefits in providing complementary coverage to ground stations on certain launch trajectories (e.g., high-inclination orbits). Launcher telemetry (TM) systems have stringent requirements in reliability and availability. Practical technology and resource limits (e.g., power demands, RF power limits) make it very difficult to achieve the high data rates with the quality of service to which those operators are used with their ground station links. Since launcher TM RF systems typically use several antennas with simultaneous transmission there is an opportunity to explore the potential of using space-time coding techniques, widely researched for terrestrial radio networks, to improve the power efficiency, reliability and availability of those transmissions on space links. Furthermore, the emergence of a European Data Relay system (EDRS) gives a renewed interest in possible applications like launcher support. NASA TDRSS has provided this type of service to operators like Sea Launch in S-band. The EDRS includes a Ka-band payload. While a priori Ka-band is more prone than S-band to atmospheric propagation impairments, a substantial part of launcher trajectories would not be affected by those impairments. Thus, other factors like RF technology and launcher accommodation need to be considered. This activity will investigate and model few selected multi-antenna architectures with space-time coding of launcher TM systems and will evaluate their performance both in S-band and Ka-band as well as its RF technology and accommodation aspects. The result of this activity will be an advanced space-time coding concept able to sustain high data rates with the required reliability and availability, with an identification of further technology improvements required on the RF transmission chain and accommodation aspects. Deliverables System study Technical Notes, Reports, Sim. models Application/Need Date 2012 Duration (Months) 12 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-8059
Consistency with Harmonisation N/A
TRP Reference T418-301MP Activity Title Waterhammer tests with cryogenic fluids Objectives
Page 36 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
The objective of the present activity is to improve the modelling of multi-phase phenomena occurring during transients, start-ups and shut-downs in propulsion systems, particularly with cryogenic fluids. To allow proper modelling, detailed experiments need to be created for typical multi-phase, multi-component flow phenomena allowing realizing and recording fast transient in combination with large pressure gradients enabling flashing conditions Description Achieving the objectives will be done in the following way. Evaluation of the liquid front behaviour during waterhammer prior, during and after impact for different operational conditions and implementation and validation of the derived correlations into existing engineering models. Deliverables Prototype Application/Need Date Launchers, Prototype>2015 Duration (Months) 18 Estimated Current TRL Algorithm Target TRL Prototype
SW Clause N/A Reference to ESTER T-856, T-7568, T-8264, T-8265, T-8858
Consistency with Harmonisation Activities A4 and A7 of the Aerothermodynamic Tools roadmap
TRP Reference T418-302MP Activity Title Physical modelling of scale effects on cryogenic fluid flows Objectives Ground based low gravity drop tower testing offers benefits in terms of repeatability but suffers from short low gravity / free fall periods. To maximise the short low gravity period, test piece miniaturisation shall be here experimentally investigated to quicken the fluid response time and obtain sufficient data for physical modelling development and extrapolation of flight experiment results. Description The limits of miniaturization shall be assessed for testing purposes and to understand which scaling parameters are valid between test and flight at very small geometrical scales. A CFD vs experimental test iteration study shall be performed to determine the size limits where small scale testing is still valid. CFD analysis with solver modification and physical testing in labour will be required for this study. Deliverables Physical modelling and experimental data Application/Need Date Upper stage technology, Prototype>2014 Duration (Months) 18 Estimated Current TRL Algorithm Target TRL Prototype Open Source SW Clause Reference to ESTER T-7899 Code Consistency with Harmonisation No
TRP Reference T418-303MP Activity Title Hot Testing Facilities for ELV Propulsion Characterization Objectives Feasibility study of a test facility that permits to characterize aerodynamically ELV systems, particularly drag prediction including hot engine exhaust plumes and their interaction with the ambient flow field. The prediction of drag for launchers still suffer of large uncertainties due to the absence of dedicates experiments to characterize the interaction of hot plumes with the base of the launcher. An experimental facility for hot plumes and cold subsonic or transonic ambient flow is not available in Europe. Description Feasibility study to develop a new or expand an existing hot facility that should permit to burn fuel resulting in plume temperatures similar to flight, and to simulate ambient flow in low subsonic condition. Higher subsonic Mach numbers should be considered if possible. The study shall include the assessment of measurement devices (force and moment balance and unsteady pressure transducers, temperature and heat flux) for the use in hot reacting flow fields. Deliverables Study report Application/Need Date Launchers, 2011-12 Duration (Months) 18 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-472, T-8257
Consistency with Harmonisation Activities A11, A13 and A18 of the aerothermodynamics tools roadmap
TRP Reference T418-306MP Activity Title Advanced measurement techniques for validation of CFD for cryogenic flows in reduced gravity Objectives Develop and test miniaturized measurement techniques applicable to the validation of CFD for cryogenic flows in reduced gravity. Accurate validation of CFD for cryogenic flows in reduced gravity relies on the availability of accurate detection of free-surfaces and of volumes of gas and liquids present in a component (tank, pipe,...) and hence it requires Improvements in ground and flight sensors.
Page 37 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Description Non-intrusive and intrusive techniques shall be reviewed for the accurate measurement of temperature, the measurement of gas fraction in a liquid flow, and the detection of a three dimensional liquid free-surface. One selected technique shall be further developed as a flight sensor, calibrated and tested to static fluid, and to sloshing. Deliverables Other Application/Need Date Upper stage technology, 2015-2020 Duration (Months) 24 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-7568, T-7652
Consistency with Harmonisation TBD
TRP Reference T419-301MP Activity Title Environmentally friendly hydrogen production Objectives Launchers are major users of hydrogen and each Ariane 5 flight burns 25 tonnes of hydrogen, which is produced by cracking methanol. Hydrogen production therefore has an environmental impact in particular with respect to CO2 emissions.
After a survey of greener H2 production methods (e.g. electrolysis or production by algae), the objective of the study is to carry out a technical feasibility analysis, for a possible small-scale demonstration model of hydrogen production using more environmental friendly processes.
The assessment shall verify if a business case exist (production needs shall ensure at east 6 Ariane5 per year) and trade off among different production methods. The study will be essential to allow the Agency to catch up with undergoing researches and developments related to clean energy production, and potentially ensure Europe a leading role. Description The activity can be broken down as follows to investigate and prepare for demonstration of new hydrogen production.
Task 1: Analysis of environmental impacts of present H2 production Hydrogen used to power the Vulcain engine is produced by cracking of methanol which is imported from Trinidad and Tobago by boat. The cracking is achieved using a combustion chamber which is powered by kerosene, to reach temperature around 300C. At the end of the process, the output is 75% H2, 24% of Co2 and 1% of C0. As a first step the carbon footprint of this process shall be evaluated. Task 2: Survey of alternative methods Alternative methods, such as electrolysis or H2 production by algae could be considered. These methods are being studied and partially already implemented. For example, Air Liquide is producing H2 by electrolysis while the University of Karlsruhe is studying H2 production by algae. In the “electrolytic” approach, an electric current is used to “break” the water molecule and produce hydrogen and oxygen. The electricity can come from different sources and especially from renewable sources: photovoltaics, wind, etc. In this case, the production of hydrogen does not emit any CO2. This production technique does not directly release CO2. If the electricity used is produced from a power plant, fuelled by coal, for example, CO2 will be emitted. If electricity is produced without emitting CO2 , (i.e. by using hydroelectric power or solar power) the hydrogen produced is said to be “green”. Another possibility is biology approaches to develop an economically viable Bio-H2 process. In the first phase of development, a patented high-H2 producing mutant Stm6 is used (increasing Hydrogen production capacity by 50% from that of standard Stm6, through the incorporation of a sugar transporter to produce Stm6glc4). Several renewable energy laboratories have concluded that production efficiencies had to be increased from originally 0.2% photon to H2 conversion efficiency at 20W/m2 illumination to ~7-10% at 230W/m2 illumination (day light) to make the process economically viable. As energy prices rise, the required level of efficiency for the process to be economically viable is predicted to fall. The maximum efficiency of this process is currently ~1.0% from light to H2 and 2% to biomass. The so produced H2 gas has a purity of ~90-95% and typical yields are 500ml H2 for a 1 litre culture (10days; 110W illumination). Without further purification, the H2 gas can be used to power a small-scale fuel cell car. Task 3: Feasibility study of “greener” H2 production in Kourou After the survey of alternative H2 production methods, a feasibility analysis shall be carried out taking into account the requirements of launching from Kourou. These parameters shall be considered: - launch of at least 6 Ariane 5 per year - Kourou ambient conditions - The final purity to be achieved is specified hereunder: molécules niveau property pureté globale (H2) > 99,995% en volume He = 40 ppmv N2+H20+hydrocarbures = 10 ppmv O2+Ar (1) = 1 ppmv CO+C02 = 1 ppmv Parahydrogène > 95% en volume Orthohydrogène < 5% en volume - … This feasibility shall also contain an economic trade-off comparing the present H2 production methods with the new one, evaluating the possible savings and the possible extra recurring costs. An assessment of the investment for the implementation of the new methodologies will also be provided. Deliverables Study Report Application/Need Date Ariane 5 missions, asap Duration (Months) 12 Estimated Current TRL 1 Target TRL 2
SW Clause N/A Reference to ESTER
Page 38 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Consistency with Harmonisation N/A
TRP Reference T419-303MP Activity Title Experimental Characterization of Cavitation Erosion Objectives One of the most evident problems caused by cavitation is represented by the material damage (or erosion) generated by the bubbles when they collapse on solid surfaces. Cavitation erosion does not usually cause relevant problems in space rocket applications (like liquid propellant feed turbopumps), where the typical duty cycle of the device is sufficiently short to avoid the occurrence of significant damages at the end of its lifetime; however, a more in-deep understanding of this aspect could be extremely important for future reusable components, designed in order to withstand longer lifetimes without suffering potentially dangerous damages. Cavitation erosion is a quite complex problem, which involves a combined characterization of the strongly unsteady flow generated by cavitation and the mechanical/fatigue resistance of the solid surface material. Differently to the damages caused by the presence of solid particles in the fluid flow, cavitation erosion damage has a more similar appearance to that of fatigue failure. In rotating devices like turbopumps, cavitation erosion usually occurs in quite localized areas of the blade surface, where most of the cavitation bubbles collapses are concentrated. Additionally, the rate of cavitation erosion damage is usually proportional to a weak power of the surface hardness of the given material. As a consequence of the above considerations, the proposed activity is intended to carry out an extensive experimental characterization of the cavitation erosion effects on typical space rocket turbopumps geometries and materials. The collected information can successively represent a fundamental baseline for the future design of high-performance reusable turbopumps for space rocket applications. Description The first step of the proposed activity will be represented by the definition of a list of turbopump geometries and materials of interest for possible application in high-performance reusable devices. At the same time a reduced-order analytical model for the estimation of the cavitation erosion level on a given pump geometry and material, as a function of the operational parameters, will be developed. Starting from the indications provided by the analytical model, a detailed test plan for the experimental campaign will be defined. Tests will be performed according to one or more of the following configurations: -) Rotating device, exactly reproducing the investigated pump configuration; -) Simplified rotating device, reproducing only the most significant aspects of the investigated pump configuration by the point of view of the generation of cavitation regions able of creating erosion effects; -) Non-rotating device (hydrofoil), able of reproducing in a static 2D or 3D geometry similar cavitation erosion effects to those expected in the actual pump configuration. As a final step, the test results will be compared to the estimations provided by the analytical model, which will be eventually fine-tuned. The validated model is expected to represent an extremely useful tool for the prediction of cavitation erosion effects in space rocket turbopumps, and will be used for defining a preliminary Road Map in view of the design of future reusable devices. Deliverables Other Application/Need Date Cavitating devices in rocket motors Duration (Months) 18 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-8309, T-593, T-595, T-8110
Consistency with Harmonisation TBD
TRP Reference T419-304MP Activity Title Laser Ignition Technology Objectives Development of a customised laser ignition system for rocket engines application Description The proposed activity on laser ignition device complements another TRP activity "Cryogenic RCS Thruster Technology - Laser Ignition" (Contract Number 22483, in 2009), delivering encouraging results. Expected results for the mentioned complementary TRP running contract will demonstrate the technical feasibility of the laser ignition concept using two different laser ignition techniques and 2 different couples of propellants. These results will allow rising the TRL level of this technology up to 3. In order to continue this development beyond the expected ignition techniques demonstration, the present new activity targets the manufacturing and testing of a laser igniter demonstration model, at laboratory level, allowing consolidation of the relevant operating parameters. Expected TRL level at the end of the new TRP activities is 4. The work will be articulated in three main tasks: 1) to investigate laser ignition process for 2 couples of propellants; 2) to identify a robust combination of relevant parameters (design criteria and operating conditions) which guarantees the most reliable and safe ignition; 3) to design and manufacture a customised laser ignition system, taking into account the specific constraints of a rocket engine (thermal, mechanical and environmental loads). Deliverables Study Report Application/Need Date The Reaction Control System (RCS) and propellant settling thrusters for launchers' upper stages and satellites Duration (Months) 18 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-860, T-7884, T-7652, T-8111, T-8871
Consistency with Harmonisation TBD
Page 39 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
TRP Reference T419-305MP Activity Title Space propulsion applications for High enthalpy solid Hydrogen gas generation Objectives Exploit the potential of new propellant formulation generating high enthalpy hydrogen from a compact solid state storage Description The TRP study will start by surveying the possible applications of the new propellant for space propulsion applications. One of the most promising applications currently identified is the generation of hot gases for the powering of turbopumps. This will highly improve the efficiency of upperstage propulsion systems. The study will included the manufacturing and the testing of a representative demonstrator at laboratory scale. Deliverables Prototype Application/Need Date New generation engines (High Thrust and upper stage propulsion systems) - Date of need at TRL 6: around 2015. Duration (Months) 18 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER
Consistency with Harmonisation N/A
TRP Reference T420-301MS Activity Title Feasibility of a shock attenuation system for heavy payloads on Ariane 5 ECA launcher Objectives The objective is to develop a shock attenuation system for (heavy) payloads (mass > 4.5 tons) on Ariane 5 ECA launcher based on elastomer technology (derived from SASSA or ATAM concepts) having a mass lower than 50 kg. Such device should develop at the 1780 interface of the Payload Adaptor System. Description Current shock attenuation systems used on Ariane launcher do present important mass penalty (above 200-300 kg). The work would consist to start from SASSA (and possibly ATAM) activities and to develop an attenuation system compatible with Ariane requirements. In a first step, which is the subject of this TRP, this would require the study of a new damping device (with possibly new elastomer) derived from SASSA and the refinement of the launcher specification in order to better accomodate the SASS. Deliverables Study Report Application/Need Date Ariane 5 and Vega launchers and their payloads (spacecraft, incl. ATV) Duration (Months) 24 Estimated Current TRL 3 Target TRL 4
SW Clause N/A Reference to ESTER T-8286
Consistency with Harmonisation N/A
TRP Reference T420-303MS Activity Title Demonstrator of Carbon anisogrid payload adapter Objectives Available technology in Europe for payload adapters are carbon (sandwich or fibre placement) or aluminium monocoque. Any mass saving on the adapter is directly beneficial for the launch vehicle (LV) capability. The carbon anisogrid technology could be employed for an adapter, reducing its mass while keeping its stiffness and strength properties. Furthermore a carbon anisogrid technology will have a beneficial effect with respect to shock propagation along the LV structure. The objective is to develop a demonstrator of the carbon anisogrid technology, encompassing design optimisation methods, identification of appropriate manufacturing processes, detailed design, demonstrator manufacturing and verification by test. Description
Page 40 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
A building block approach should be followed, with varying levels of complexity ranging from elements to sub-components. This last level is referred herein as the technology demonstrator, and should typically consist in a sector of a payload adapter (featuring a conical part and 2 interface flanges, made either by automatic filament winding or automatic fiber placement). As the size and complexity increases, models of the structure are progressively updated to ensure that the behaviour of the full system can be accurately predicted. Finally the next level of complexity (i.e. complete payload adapter) should be preliminarily addressed by the definition of a DDV plan for a complete adapter based on carbon anisogrid technology. Due to the beneficial impact on mass and shock, VEGA should be considered as application case (in view of a possible replacement of the ACU937VG). Work breakdown: 1. Establish specification for the technology demonstrator 2. Demonstrator preliminary design, including analytical and numerical optimisation methods 3. Identification of adequate manufacturing technology/process at elementary level (material selection / characterisation / manufacturing of elements / NDI / Strength test) 4. Demonstrator detailed design 5. Manufacturing of technology demonstrator 6. Verification by test: Stiffness/strength/shock/rupture tests 7. Synthesis activities and definition of a DDV plan for a complete VEGA adapter based on carbon anisogrid technology Deliverables Prototype The technology of carbon isogrid construction is not available for launch vehicle structures, although it would be beneficial Application/Need Date with respect to mass saving and shock reduction. Duration (Months) 30 Estimated Current TRL 3 Target TRL 4
SW Clause N/A Reference to ESTER T-8286
Consistency with Harmonisation N/A
TRP Reference T420-304MS Activity Title Impact of thermo-mechanical loading history on mechanical properties and verification of aerospace materials Objectives To determine the impact of the thermo-mechanical loading history on the mechanical characteristics of aerospace materials. This includes the effects of ratcheting and complex non-isothermal thermo-mechanical loading history. Description High thrust rocket engines require high pressure and high temperature operating conditions. This leads to components exhibiting a ratcheting effect (i.e. progressive plastic deformation/creep) under cyclic thermo-mechanical loading (e.g. combustion chamber). Also, mechanical properties of materials resulting from isothermal tests performed at different temperatures are normally used for verification of complex thermo-mechanical loading histories. Verification problems may occur, because material properties up to rupture, and in particular the rupture elongation, depend on the entire thermo-mechanical loading history of the material (Example: Consider a material with a rupture elongation of 5% obtained according to a tensile test performed at 800K. The same material may have a rupture elongation of 10% at 300K. The component is first loaded in a displacement controlled way at 300K up to 7% tensile elongation and then it is warmed up to 800K with constant strain level (7%). In such a situation the current verification approach concludes that the material can not withstand the hot operating conditions, while in reality it does, since it has been stretched up to the considered level at another temperature.). When ratcheting leads to an ever increasing tensile residual deformation from cycle to cycle, that residual deformation may become unacceptable from a mechanical standpoint (e.g. lead to rupture or excessive structural deformation). In addition, the fact the material is submitted to cyclic loading with ratcheting makes its effective rupture elongation decrease in an extent that has not been investigated before for rocket engines, while it may become increasingly significant when the engine performance increases more and more. The presence of possible multi-axial stress state on the ratcheting effect has to be included. The impact of the ratcheting effect and effect of complex thermo-mechanical loading history on design and verification methods becomes increasingly important for optimization of the mass budget of the future high thrust engines , where prediction of realistic margins is important. Description of the work to be performed: 2.1) Review of industrial problems and difficulties with design and verification of the thermo-mechanical loading history of high thrust rocket engines, based on contractor's experience, and open literature. Select a limited number of representative examples as a reference for the rest of the work. 2.2) Establish the state-of-the-art of design and verification methodology of the thermo-mechanical loading history of high thrust rocket engines. This includes the impact of cyclic loading and ratcheting effect of the rupture elongation of aerospace materials (incl. effect of multi-axial deformation state), and the impact of complex thermo-mechanical loading history on the mechanical characteristics of applied materials. It also includes possible spin-in of experience in other fields of application (aircraft, process and nuclear industry) 2.3) Identification of open points and possible technical solutions, based on output of 2.2. 2.4) Definition and performance of a limited experimental validation campaign, complementing relevant test data from contractor’s experience and open literature. 2.5.) Tailoring phase (models, methods) of the design and verification methodology based on results of other tasks. 2.6.) Guidelines reporting. Deliverables Study Report Application/Need Date Rocket engine components (thrust chamber, nozzle extension, ...) Duration (Months) 18 Estimated Current TRL 3 Target TRL 4
SW Clause N/A Reference to ESTER T-8318
Consistency with Harmonisation N/A
TRP Reference T420-305MS
Page 41 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Activity Title ELV fatigue load spectra development Objectives To provide improved fatigue load spectra for Ariane 5 and Vega launchers and their payloads, based on measured flight data Description The availability of standard fatigue load spectra with rules and guidelines for their application to specific structures of spacecraft and subsystems is an important ingredient of fatigue and fracture verification of these items. Since many years an ESA derived load spectrum for the Space Shuttle is available in the ESALOAD software (based on analysis of flight measurements). For expendable launchers like Ariane 5 and Vega such spectrum is not available, and verification relies on either using the available Space Shuttle spectrum (conservatism is not known) or other approaches, which may be quite conservative (and hence potentially increasing mass). This activity will derive fatigue load spectra for Ariane 5 and Vega, together with clear guidelines for their application, in the following way: * Evaluation (including cleaning and filtering if necessary) of measured Ariane 5 & Vega flight data, similar to what was done in the past for the Space Shuttle; * Derivation of a launch load curve for Ariane 5 & Vega, similar to the existing standard load curve of ESALOAD software (in terms of accelerations); * Update the ESALOAD Users Manual with guidelines for the application of the load curve to individual payloads and launcher elements; * This includes an example, based upon typical payload (spacecraft) for each launcher, and typical structural part of each vehicle. NOTE: The activity shall also address recommendations for hardware items of the launcher vehicles themselves. Deliverables Report + Load Curves Application/Need Date Ariane 5 and Vega launchers and their payloads (spacecraft, incl. ATV) Duration (Months) 18 Estimated Current TRL 3 Target TRL 4
SW Clause N/A Reference to ESTER T-8289, T-8318
Consistency with Harmonisation N/A
TRP Reference T420-306MS Activity Title Equivalent Modal Damping Method for Condensed Solid Rocket Motor Finite Element Models Objectives Part of the mission analysis of a spacecraft is the so-called launcher-satellite coupled loads analysis which aims at computing the dynamic environment of the satellite for the most severe load cases in flight. To allow such analyses to be processed in short time, the various stages of the launcher finite element model, as well as the spacecraft finite element model, are condensed to super elements. The condensed coupled system can subsequently be solved in transient or frequency response analysis. To obtain accurate predictions for the satellite dynamic environment, it is essential that the damping of the condensed system is defined in a representative way. Non-representative system damping would result to the wrong spacecraft design loads. Very often some form of proportional damping is employed in transient analysis, which results to a correct damping level at the dominant excitation frequency. Below and beyond that frequency the damping will be too low and too high respectively.
The objective is to investigate and implement alternative equivalent modal damping methods that can be employed in direct transient analysis of condensed finite element system models. The methodology should allow the derivation of modal damping levels on a mode by mode basis, using both modal characteristics (frequencies, modeshapes, modal strain energy distribution) as well as measured material structural damping characteristics. The methodology should allow the computation of equivalent modal damping matrices for launch vehicle substructures, in particular solid rocket motors. Description The study shall entail the following points: 1. Proposal of equivalent modal damping methods in line with above. The damping of both the modal and interface partition of the superelement (Craig-Bampton model) shall be addressed. 2. Implementation of the methods in a condensation tool. 3.Testing the new methods in direct transient analysis for a simple benchmark case. 4. Application of new method to compute the damping matrix of a solid rocket motor FEM. Test/analysis correlation on the basis of firing test dynamic simulation. 5. Application of new method in launch vehicle / spacecraft coupled loads analysis. 6. Comparison to flight data. Deliverables Study Report and software tool Application/Need Date Ariane 5 and Vega launchers and their payloads (spacecraft, incl. ATV) Duration (Months) 12 Estimated Current TRL 2 Target TRL 4 Open Source SW Clause Reference to ESTER T-8286 Code Consistency with Harmonisation N/A
TRP Reference T420-307MS Activity Title Identification of dominant modes in the dynamic analysis of free-free systems with high modal density Objectives
Page 42 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
For dynamic systems with a high modal density it can be a tedious task to identify the dominant modes that contribute to a dynamic response. For fixed-free systems one could for instance use the modal effective mass to identify the main modes that contribute to the interface reaction forces. For free-free systems in general, for externally loaded fixed-free systems and for internal responses of fixed-free systems, the effective mass can either not be computed or will not be the appropriate dynamic parameter to identify the dominant system modes. Hence, another criterion is required to identify the dominant system modes in such cases. The objectives of this study are as follows: 1. To work out a method that allows the ranking of modes on the basis of their modal contribution (modal gain) to any type (acceleration, displacement, stress, strain etc.) of dynamic response in both transient and harmonic dynamic analysis 2. To implement the modal gain method into a software tool that is already suited for the post-processing of dynamic response data. Description The following tasks are identified for subject activity: 1. The development of a methodology to rank the modes of dynamic systems with high modal density on the basis of their modal gains. Equations shall be developed and should be compatible with dynamic systems originating from finite element models and/or superelements. In the latter case the dynamic response is computed from output transformation matrices. 2. The method shall be implemented into a software tool suited for the post-processing of dynamic response data (matlab, dynaworks etc.). Input data blocks shall be identified and shall be stored from the FEM/SE dynamic analyses. A list of modes with their mode numbers, natural frequencies, dampings and modal gains shall be stored in an ascii output data file. Furthermore it should be possible to filter the modes on the basis of a threshold (minimal modal gain) and to output the list of selected dominant modes as an ascii datafile. Finally it should be possible to reconstruct the dynamic response on the basis of the selected dominant modes and to compare it against the solution constituted by the full set of (truncated) modes. 3. The software tool shall be tested for dynamic systems with high modal density assembled from either finite element models and/or superelements. The test cases shall cover both transient and harmonic response analyses Deliverables Study Report and software tool Application/Need Date Ariane 5 and Vega launchers and their payloads (spacecraft, incl. ATV) Duration (Months) 6 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-8286
Consistency with Harmonisation N/A
TRP Reference T421-303MT Activity Title Advanced foams for cryogenic tanks insulation Objectives To develop a polymeric foam modified with nanostructures to be used for Future Launchers Program (e.g. to insulate Tanks and/or Bulkheads). The product will comply with technical requirements regarding performance (mass, thermal conductivity) and environment, but also recurrent costs and process. Description Based on the recommendations of a previous screening activity (part of the TRP 2008-2010), one or multiple products will be selected. In the frame of the present activity, the selected products will be enhanced, manufactured, and tested to demonstrate that they meet performance, environmental and cost requirements. Those requirements will be updated at the beginning of the study to reflect the needs for such a technology in the frame of the Future Launchers Preparatory Program. Major tasks include: (i) elaboration of requirements of the expected technical properties of the foam (ii) definition of chemical composition of proposed foam (iii) dispersion of nanostructures in polymer/monomer & foams preparation (iv) foam implementation on the external wall of the metallic tank segment (v) testing of selected properties to derive relations between structure and properties, (vi) optimization of composition (loop ii -> v). Deliverables Insulating foam samples and composition formulation. Application/Need Date FLPP, Launchers Duration (Months) 18 Estimated Current TRL 3 Target TRL 4
SW Clause N/A Reference to ESTER T-8869
Consistency with Harmonisation TBD
TRP Reference T423-301QT Activity Title Assessment of existing plastic optical fibers and associated optical connectors for launcher application Objectives Investigate Plastic optical fibers and associated optical connectors for LV applications in order to save integration constraints & recurrent costs with respect to glass fibers. Description Plastic optical fiber and associated optical connectors are already used in harsh mechanical environment for military application (military tanks). Although plastic fibers present degraded performance compared to glass fibers they have also lower recurrent cost. Their mechanical resistance to harsh mechanical environment could be interesting for launcher types of application where the length of the fiber may allow higher optical losses from plastic fiber. This activity will therefore consist in investigating plastic optical fibres and connectors in LV environments.
Page 43 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Trade off analysis plastic vs glass optical fiber performances (both optical AND environmental), final report + optical fibre Deliverables chains (fibers with connectors) for ESTEC assessment by TEC-MME and TEC-QTC Application/Need Date 2013 Duration (Months) 12 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER
Consistency with Harmonisation TBD
TRP Reference T424-301QE Activity Title On-board particulate contamination sensor Objectives The objectives is to develop a particulate contamination sensor which could be flown under the fairing and measure particulate contamination close to sensitive payloads. Description Inside a launcher fairing, during integration as well as during launch and stage separations, the interest is in those particles that fall on sensitive surfaces under the action of gravity and that are displaced during launch vibrations and shocks. These particles generally have a diameter starting from few microns and since state of the art CCD and CMOS detectors have pixel size of the same order of magnitude, CCD or CMOS detector’s pixel obscuration could then be utilized to measure particle fallout and redistribution in real time. Particular attention should not only be paid to the dimension of pixel, but also to the pixel pitch (i.e. the distance between two adjacent pixels). Appropriate algorithms can be used to detect particles and fibers that interest more than one pixel. The idea is to develop a real time particle fallout detector directly counting particulate falling down on locations close/representative of sensitive items. An alternative concept could also be based on micro-camera. able to take images of a relative small collecting plate (e.g. 100 x 100 mm) where the deposited contamination particles are image captured. The signal/images will be in turn downloaded by telemetry (TM) and used for off-line determination of the number, shape and distribution of particles on the collecting plate by image processing algorithms. The sensor should be able to detect particles with a minimum dimension in the order of the micrometer. Deliverables Breadboard Application/Need Date All launchers. First application could be with sensitive scientific payloads such as JWST, BepiColombo. TRL5 >= 2016 Duration (Months) 24 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-8291
Consistency with Harmonisation N/A
TRP Reference T424-303QT Activity Title High temperature characterization of phenolic materials used in rocket engines Objectives To build on the lessons learned after the failure of the VEGA nozzle. The purpose of the study is to characterize the different influences between pyrolisation and thermal expansion and shrinkage during the high heating rates experienced in the launch phase of rockets. Description During the failure inquiry board of the VEGA Z 9 nozzle a comprehensive materials characterization up to 2000C has been performed on the phenolic nozzle materials. During that activity the need to better characterize the high heating rate effects on phenolic materials has been found. The effects of heating rate, pyrolisation, thermal expansion and shrinkage shall be addressed in this study to be able to better predict the materials behaviour during rocket operation. A better characterization will enable a deeper understanding of the material response and by that will lead to reduction of margin (mass saving). This activity shall be done by systematically performing ground simulations and measure relevant materials properties as function of heating rates experienced during launches. Deliverables Study Report Application/Need Date asap Duration (Months) 30 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-8843
Consistency with Harmonisation N/A
TRP Reference T424-304QT Activity Title Advanced aluminium based material for cryo-reservoir applications Objectives
Page 44 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
- Trade-off the best aluminium based material candidates for a specific application, i.e. cryo-reservoir for an upper stage - Perform verification of the selected candidate material(s) - Establish a cost Vs performance analysis Description Several advanced aluminium based solutions have emerged within the last years (or even decades) for providing materials having higher properties than the conventional aluminium alloys. Among these, are the Al-Li, Al-Sc alloys, metal matrix composites, the rapidly solidified aluminium and the oxide dispersion strengthened (ODS) based aluminium materials. Each of these material classes has the potential to bring savings for tank applications. It is proposed to review the different materials available today and to address their suitability to the intended application e.g. rolling, shaping, welding, and the impact of these on the materials properties. Other aspects of the use of the alloys will be addressed such as NDI, procurement IP, anisotropy etc. After selection of the best candidate(s), tests will be performed to confirm the interest of the technical solution. Tests will be driven by the intended application. A final assessment will be performed presenting the pros-and cons of the solution(s) evaluated, a roadmap for reaching TRL 5 will be proposed. Deliverables Other: TNs, Test plan, Test report, Test samples Application/Need Date 2020 Duration (Months) 15 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-8139
Consistency with Harmonisation N/A
4 - 02 - Human Space Flight oriented Technologies
TRP Reference T418-304MP Activity Title Characterisation of high enthalpy facilities and streamlining of calibration and tests Objectives Increase the reliability of the plasma test procedures, by standardizing them with the aim to improve the accuracy of the knowledge of the achieved heat flux level. High enthalpy facilities, and in particular plasma wind tunnels, are used for the development of thermal protection materials for entry and ascent vehicles. The calibration of a plasma wind tunnel in terms of required heat flux is usually done on copper calibration plates. The inaccuracy of the knowledge of the actual heat flux is typically around 30% or higher. In the frame of a mission development this can lead to an unfavourable limitation of the mission profile (e.g. flight path angles). Description High enthalpy facilities shall be probed and calibrated, in order to provide more details on the state of the flow in various important locations of the wind tunnel: the reservoir where the gas is heated, the nozzle and the free jet in the test chamber. Strict procedures shall be agreed upon, and documented, for the calibration, start-up and performance of plasma tests of TPS materials. Uncertainties shall be analysed end-to-end, accounting for all sources of errors. Deliverables Study Report Application/Need Date Earth atmospheric entries, 2015-2018 Duration (Months) 24 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-8947
Consistency with Harmonisation Activities B04, B18, B19, B24, B25 and B29 of the Aerothermodynamic tools roadmap
TRP Reference T418-305MP Activity Title Dynamic stability of capsules and blunt bodies at angle of attack Objectives To provide accurate CFD unsteady flow data and aerodynamic coefficients. One of the major difficulties for the construction of aerodynamic databases of entry vehicles or launchers is the determination of dynamic derivatives (unsteady coefficients) since the characterisation of the aerodynamic properties of spacecrafts is particularly challenging in relation to the large influence of the wake flow, still difficult to model numerically. Description Validate time accurate CFD codes (expanded with turbulence models based on Large Eddy Simulation) with experimental data obtained in previous ESA activities using free-flight test techniques for very high angle of attack and non-axisymmetric vehicles. Deliverables Other Application/Need Date Entry capsules & launchers, 2015-2020 Duration (Months) 24 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-7904, T-7906, T-8940
Consistency with Harmonisation TBD
Page 45 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
TRP Reference T418-307MP Activity Title Aerodynamic design tool for parachutes Objectives Development an aerodynamic design tool for parachutes based on numerical fluid/structure interaction simulations by carefully calibration the numerical results against available full scale flight experiments. Today ESA has no aerodynamic tool for parachute design. Description Here is proposed to depart from an existing fluid-structure computer code and extends and adapts it (particularly LES turbulence models) to reproduce the flight experiments of the parachute type Disk-Gap-Band (DGB) parachute since it is the most used in space missions since. Full scale flight experiments have been carried out only in USA and Russia at the beginning of the space era but are well documented for three types of parachutes: DGB, Ringsail and Cruciform. Deliverables Software Application/Need Date Earth atmospheric entries, 2015-2018 Duration (Months) 18 Estimated Current TRL Prototype Target TRL Beta Software Open Source SW Clause Reference to ESTER T-7906, T-8873 Code Consistency with Harmonisation TBD
TRP Reference T418-308MP Activity Title Enhancing Test Facilities for Aerodynamic Decelerators Objectives Feasibility study to assess the need for adapt existing facilities to test parachute systems or develop new facilities or alternative techniques like sounding rockets, in order to meet the future requirements for European missions. Many future Projects require parachutes as part of the descent and landing system and therefore it is highly desirable to develop EU capabilities in the field of testing of parachutes Description The study shall research the current facilities, identifying the status in Europe and (if necessary) define the requirements and development costs for enhancing existing facilities or developing new facilities. A cost/performance comparison against flight data obtained using sounding rockets shall be provided. Deliverables Study Report Application/Need Date Earth atmospheric entries, 2015-2018 Duration (Months) 18 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-7906, T-8873
Consistency with Harmonisation activities A12, A13, B06, B30 and B31 of the aerothermodynamics tools roadmap
TRP Reference T418-309MP Activity Title EXPERT PFA on General Hypersonic Fluid Dynamics Objectives Relate EXPERT in-flight measured avionics data to predictions. This includes the restitution of free stream conditions; the assessment, verification and refinement of the state of art of CFD tools with the collected high quality flight data and the distribution of the flight data to different PIs and ensure synergies among all the payload disciplines. Description Collection, preliminary screening and distribution of all the available flight data; consolidation of previous analyses and data predictions; sensors inspection and calibration check; data reduction for PL1 and PL07; restitution of free stream conditions such as free stream density angle of attack etc. and post-flight CFD analysis. Coordination and sharing of all flight/payload data and housekeeping data. Optimization and sharing of all acquired data among all scientific payloads in order to improve the possibilities and the criteria to achieve the important EXPERT scientific goals in a multidisciplinary environment. Deliverables Study Report Application/Need Date Entry capsules & launchers, 2015-2020 Duration (Months) 24 Estimated Current TRL 3 Target TRL 6
SW Clause N/A Reference to ESTER T-7904, T-7906, T-8077, T-8078, T-8093, T-8097
Consistency with Harmonisation activities B02, B14, B20, B21, B24, B25 and B31 of the aerothermodynamics tools roadmap
Page 46 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
TRP Reference T418-310MP Activity Title Modelling for future light-weight ablating materials Objectives Development of an ablation code suitable for classical and future ablation materials. The computer code shall be validated against data obtained in specially designed experiments. Description A numerical code shall be developed to analyse and compare state of the art ablation modelling with available experimental data. The improvement of the physical modelling by including a coupling between the domains in the ablation process allows also to investigate future ablators like low density carbon resin ablators which are under development today. Deliverables Software Application/Need Date Earth atmospheric entries, 2015-2018 Duration (Months) 24 Estimated Current TRL Algorithm Target TRL Prototype Operational SW Clause Reference to ESTER T-7897, T-8090, T-8283, T-8947 S/W Consistency with Harmonisation TBD
TRP Reference T419-307MP Activity Title 10-kW Hall-effect thruster optimized for space transportation Objectives The objective of this activity is to design, manufacture and test a Hall Effect Thruster (HET) configuration in the 10-kW class tailored for orbit transfer from LEO to the Moon or another celestial body where the delta V is high. Space exploration missions can place a large spectrum of demands on thruster requirements, on top of a relatively high Isp because of the large deltaV requirement. The activity proposed in this topic will constitute a first step to prepare the ground for the future development of a Hall thruster in the 10-kW class range and with specifications tailored for those missions where maintaining a minimum thrust-to-power ratio is important, e.g., where a significant time constraint is placed on a particular manoeuvre (deltaV) to be performed with electric propulsion. This is the case, e.g., for planetary orbit insertion manoeuvres; interplanetary missions where phasing is critical to meet arrival epoch constraints or to maximize the duration of on-site windows of operation; or to perform a manoeuvre the closest possible to the maximum-efficiency point in the trajectory.
This activity will focus on the preliminary sizing of a 10-kW class Hall thruster capable of operating at a specific impulse augmented by about 50-60% compared to the current state of the art, while maintaining a total efficiency greater than 50% and a lifetime consistent with large deltaV missions. It shall make use of the existing European experience in the field of Hall-effect thrusters at lower power levels.
Technological aspects to be addressed in this activity involve mechanical structure, thermal design, and above all available raw materials to generate a new magnetic circuit configuration and a new chamber diameter and geometry, allowing to build a thruster configuration sized for operations at up to 12 kW (20 A; 600 V). Description
The proposed activity should be split into three main phases:
- The first phase will be to design the thruster configuration with the objective of achieving a design compatible with prolonged, steady-state operations at a power level of at least 10 kW and an Isp of at least 2600 s. The design will also minimize the number of parts to be upgraded from the existing configurations;
- The second phase will consist in manufacturing the parts and assembling the 10-kW configuration of the thruster;
- The third phase will consist in a performance characterization of this configuration. The expected output will include: confirmation of the sizing options; of the expected throttling range and performance; and of the configuration design, and in particular of the thermal and magnetic design. Deliverables Breadboard Application/Need Date transfer operations from Low Earth Orbit to the Moon and other celestial body where the delta V is high. Duration (Months) 18 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-7758
Consistency with Harmonisation This study is in line with the harmonisation dossier on Electric Propulsion (activity C1)
TRP Reference T420-302MS Activity Title Parachute Deployment Device Objectives Initiate the development of a European parachute deployment device for a descent system.
Page 47 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Description Aerobraking is an attractive solution for de-orbiting of elements in Low Earth Orbit, due to the expected low mass and the fact it does not require large power and/or propellant. In view of the recent Code of Conduct for space debris, inoperative systems (such as launchers upper stages) must be safely disposed within 25 years. Return systems from the ISS may also use this technology for de-orbiting. Proposed activities: Review relevant past work; study update, considering: current requirements, structural options, technology progress for ancillary functions; evaluate impact of spacecraft mass, nominal orbit on aerobrake design; determine most the promising initial product; design iteration; identify priority test items; define, manufacture and test thermo-structural components to support device development. Deliverables Breadboard Crew transportation to and from LEO Application/Need Date 2015 Duration (Months) 12 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-8873
Consistency with Harmonisation N/A
TRP Reference T421-302MT Activity Title Ablative Material Optimisation and Definition of Material Families adaptable to various Applications Objectives To determine the limits of (a) ablative material(s) as function of key material parameters (e.g. density), and to derive semi-empirical models for the optimisation towards the requirements coming from a new application. This eventually shall lead to the definition of material families. Description The design of new ablator materials is currently performed by testing in an ad-hoc manner. The components are mixed together in the designed manner, and the material is then tested to find the bulk properties. If the bulk properties do not meet the required specifications, a modified mixture is developed and tested until the requirements are met. This approach leads to a very large effort to develop/modify a material towards a specific (new) mission environment. Likely such material adaptation would have to be done within the project development when typically no time for material development is available. The goal of the proposed activity is therefore to derive semi-empirical models allowing to easily identify the required steps to modify a material towards a new set of requirements. This shall be done by first determining the influence of key parameters of the material and by identifying the relevant application limits. A very relevant such parameter is the material density, which typically has to be derived as a compromise between low mass and thermal conductivity on one side and required mechanical resistance on the other side. A starting point of the activity shall be a new European ablative material which is currently developed within an ongoing TRP activity. Deliverables Breadboard Planetary Exploration Missions and atmospheric entries from Earth orbit. Application/Need Date 2015-2018 Duration (Months) 18 Estimated Current TRL 3 Target TRL 4
SW Clause N/A Reference to ESTER T-5279
Consistency with Harmonisation N/A
TRP Reference T418-311MP EXPERT Experimental investigation of the spatial flow organization around roughness elements in a hypersonic boundary Activity Title layer Objectives Experimental investigation of the quantitative instantaneous spatial organization of the flow field around roughness elements in a boundary layer in the hypersonic flow regime. An experimental database is established for CFD validation and turbulence model development. Furthermore empirical correlations are established that are to be used as guidelines in TPS design. Description Currently, the phenomenon of roughness induced boundary layer transition is studied by means of fast response point-wise probe measurements and from which flow characteristics are studied in the frequency domain. However, lacking in this approach is the understanding of the instantaneous flow topology as it exists around the roughness elements which is crucial for a better understanding of the flow field, CFD validation and turbulence model development. This activity aims at investigating the instantaneous spatial organization (preferably 3D) of the flow (velocity) field around various roughness elements, ranging from steps to gaps to isolated elements in a hypersonic boundary layer. The experiments should be performed in a high unit Reynolds number facility in order to approach in-flight conditions as close as possible. Furthermore classical fast response transducers are to be used to so that the the frequency information can be correlated to the observed flow organization. Additionally, heat transfer measurements should be performed that indicate the effect of the roughness elements on the local heat transfer rates. These combined measurements then enable to establish an elaborate experimental database that then is used for CFD code validation/development and to extract empirical correlations that can directly be used as guidelines for vehicle TPS design. Deliverables Study Report Application/Need Date Entry capsules & launchers, 2015-2020 Duration (Months) 24 Estimated Current TRL 2 Target TRL 4
Page 48 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
SW Clause N/A Reference to ESTER T-7904, T-7906, T-8077, T-8078, T-8093, T-8097
Consistency with Harmonisation TBD
4 - 03 - Generic Space Transportation Technologies
TRP Reference T401-301ED Activity Title Ultra-wideband as a multi-purpose robust and reliable wireless communication technology for tests, spacecraft and launchers Objectives The objectives are twofold: 1) Assess, demonstrate and prototype a (A) low-medium-speed (100kbps-27Mbps) low-power and robust wireless sensor bus for spacecraft and (B) wireless bridge for high-speed (10-500Mbps) spacecraft payload point-to-point data link (e.g. as a UWB2SpW bridge). 2) Execute EMC characterization activities on Ultra-wideband technologies. Description Compared to traditional wireless systems using 1) a narrow bandwidth (e.g. 2MHz-wide channel), 2) a high transmitting power (creating the typical power spectral density spike) and 3) an already crowded frequency band (e.g. 2.4GHz), Ultra-wideband (UWB) technology modulates the communication on a bandwidth greater than 500MHz at extremely low transmitting power density (typically <-41.3dBm/MHz), barely above the average noise level. It is an extremely promising technology for spacecraft because of the quasi-absence of electromagnetic interferences with onboard payloads and instruments.
Commercial UWB technologies have been developed to allow communication data rates up to 675Mbps on short distance (< 1-5m). These systems could dramatically simplify actual high-speed wired payload data systems onboard spacecraft, without decreasing their reliability. This activity is to adapt and demonstrate the technology for space applications and possibly in space environment. The expected overall advantages are mass savings from harness reduction (nominal, redundant, cross-strapping) and a reduction of design and test complexities. Deliverables Breadboard Typical application: - Even thought the Exomars design is mostly frozen, it could have benefited from a wireless high-speed link on the mast to connect the navigation cameras and the onboard computer. This would have reduced the complexity and the mass of the Application/Need Date data harness in the mast, while simplifying the test phase. - Launchers can use the technology to establish the communication between stages and avoid wires, unbalanced loads and pyrotechnics at separation. The same device would be usable for the communication between the launcher and the payload during launch. Duration (Months) 18 Estimated Current TRL 3 Target TRL 4
SW Clause N/A Reference to ESTER T-7753, T-7756, T-8382, T-8602
Consistency with Harmonisation N/A
TRP Reference T402-302SW Activity Title Missionisation process for multi-vehicle missions Objectives Systematic and early definition of the missionisation process of recurrent mission (i.e. modification of the core design of a mission item to meet mission-specific hardware/software/interface requirements). Use of domain engineering techniques to define the variability factors of flight software, database, EGSE, simulators, ground segment, etc. Potential definition of reusable & configurable building blocks based on reference architecture. Some tools are needed to automate the process. Note: decreasing need for missionisation can include GNC new design control approach for uncertain time varying system to increase performance margins. Description The process of missionisation of recurrent missions based on an initial invariant version shall be defined very early in the project and in a systematic way. Based on domain engineering, it shall include not only the flight software, but also the databases, EGSE, simulators, ground segment, etc. Potentially, reusable building blocks should be defined based on reference architectures. Some tools are needed to automate the process. Deliverables Software Application/Need Date 2014 Duration (Months) 24 Estimated Current TRL Prototype Target TRL Beta Software
SW Clause N/A Reference to ESTER T-7743, T-908, T-7660, T-8603
Consistency with Harmonisation TBD
Page 49 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
TRP Reference T407-301EE Activity Title Characterisation of the electrostatic environment of launchers Objectives This activity shall assess and propose alternatives to the methods currently used for controlling differential charging of external surfaces and for ESD protection. The objective is to demonstrate with on-ground and in-flight experiments that the ESD specifications and the relevant AIT/AIV activities can be reduced with consequent benefits in terms of complexity, schedule and cost. Description Background: The issue of Electro Static Discharge (ESD) during the atmospheric phase was studied by ONERA in the 70's, after some electrostatic phenomena and failures that affected the EUROPA launcher. Experiments were flown on-board aircrafts to collect data (e.g. impact currents) on the electrostatic environment. The requirements and engineering practices for ESD protections resulting from the experiments of the 70's have never been updated and are still applicable today.
The totality of the surface of the launcher is covered by an anti-static paint that must comply with specific requirements on the surface resistance and the continuity resistance with respect to the EMC ground plane. The installation of the antistatic paint is rather complex and delicate and the electrical properties of the paint are unstable. The required resistance values are difficult to achieve and the numerous out-of-specifications are treated with ad hoc solutions employing aluminium tape and conductive glue, which are time costly and expensive.
The proposed activity is consistent with the ESA EMC Technical Dossier, and consists of: an assessment of the electrostatic protections currently used, an update of the requirements and the definition of optimised AIT/AIV activities (supported by results of laboratory experiments). The outme of this activity will constitute the preparatory work for a subsequent experimental activity aimed at validating the results obtained with the laboratory experiments.
The main tasks to be carried out are: 1) Analytical and experimental assessment of the actual methods for electrostatic protections for launchers 2) On-ground tests to quantify the robustness of the paints vis-a-vis physical materials damage induced by ESD events as a function of the surface resistance 3) Definition of AIT/AIV procedures for ESD protection 4) Definition and design of flight experiments to measure E field, voltage and impact current (COTS shall be used as far as possible) 5) Definition of the interfaces with the launcher (mechanical, electrical). Deliverables Study Report Application/Need Date 2013 Duration (Months) 18 Estimated Current TRL 1 Target TRL 2
SW Clause N/A Reference to ESTER T-8857
Consistency with Harmonisation N/A
TRP Reference T407-302EE Activity Title Magnetic window technique for mitigation of RF blackout for re-entry vehicles Objectives RF blackout during re-entry, caused by attenuation and/or reflection of RF communication signals by electrons in the plasma sheath, is a known phenomenon. There are several approaches that can be used to mitigate the RF blackout, each having its own constraints. One method that appears to be promising is the use of a magnetic field window, where a static magnetic field is applied to the plasma and results in a sufficient reduction of the plasma attenuation to permit RF signal transmission.
The objectives of this study are: (i) feasibility assessment of 'magnetic field window' for re-entry vehicles (ii) feasibility study of an on-ground electrodynamic RF shield ground experiment (for prove of concept) (iii) experiment design Description
Page 50 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Background: The crew version of the Advanced Return Vehicle (ARV) will transport crew to the ISS and vice versa. During the descent, landing and recovery phases, a full duplex voice communication channel (in VHF band) shall be established to the recovery team. It is a well known fact that the extreme heating of the air by strong shock waves (originating at all vehicles leading edges) dissociates and ionizes the air and creates a plasma flow that strongly attenuates the radio frequency (RF) signal. This effect, known as 'RF blackout', limits the radio communication with the re-entry vehicle.
A promising technique to mitigate the RF blackout is the magnetic field window, which consist in the creation of a static magnetic field with the field lines in the direction of the intended propagation. This method has been studied in the United States (NASA contract) but its engineering applicability has not been proven yet.
ESA is active on the subject of interactions between the flow of electrically charged gas mixtures and electromagnetic field, with potential applications to the electrodynamics heatshield concept. Theoretical studies and experimental activities have been carried out in the frame of two ESA contracts and have proven the possibility to mitigate the heat-flux (of ionized argon) by the application of a magnetic-induction field. An ESA contract is also running as a preparatory activity for a flight experiment based on electro-magnetic forces. The synergy between the RF blackout and the electrodynamics heatshield and the results obtained in previous studies will constitute a solid background to study and experimentally demonstrate the magnetic window concept for RF blackout mitigation on ground.
The main tasks to be carried out are as follows: 1. Review of existing modelling tools and development of complimentary tools to model the interaction between the RF signal and the plasma flow generated by the shock waves. 2. Design of a ground experiment to demonstrate the 'magnetic window' technique for RF blackout mitigation (prove of concept) 3. Feasibility analysis of the magnetic window technique for re-entry flights (preliminary conceptual design) Deliverables Study Report Application/Need Date Final application are human missions. TRL5 >2018 Duration (Months) 24 Estimated Current TRL 1 Target TRL 2
SW Clause N/A Reference to ESTER T-50
Consistency with Harmonisation TBD
TRP Reference T419-302MP Activity Title Models for Solid Rocket Motors Nozzle Erosion and Ablative Shields Objectives This activity aims to the development of reliable analytical and simulation tools for SRM nozzle erosion and ablative TPS for re-entry shields. Description The erosion of rocket-nozzle materials during motor firing is one of the major obstacles in the advancement of solid-rocket propulsion. The material erosion reduces the area ratio of the nozzle exit to throat, and consequently decreases the overall propulsive efficiency of the vehicle. A non-eroding nozzle throat is desired as it maintains a constant nozzle expansion ratio and optimal thrust performance. Another issue attributed to the nozzle surface recession is the loss of ability to accurately predict the performance of a solid rocket motor, since the chamber pressure is intimately related to the throat area. Over the years, the material used for rocket nozzles include reinforced plastics, different types of graphites (e.g., pyrolytic and bulk/artificial graphites), carbon-carbon composites, refractory metals, and ceramics. Graphite and carbon-carbon composite, which have excellent thermo-physical properties as well as low densities, are most widely used for rocket nozzle inserts. These materials, however, undergo significant erosion at high chamber pressures and surface temperatures. Refractory metals such as tungsten and rhenium, although known to better resist the chemical erosion, suffer from weight and cost penalties. To determine performance reduction caused by nozzle erosion, test firing on full-scale motors are generally conducted. Multiple test firings, however, require considerable time and expense. An efficient and economical approach is to couple the associated full-scale experiments with the modelling studies, in order to predict the recession rate. It is thus fundamental to theoretically study the critical interactions between the propellant combustion products and nozzle materials under severe motor-operating conditions. The development of reliable analytical and simulation tools for erosion prediction can provide designers with important information as to whether certain design changes could improve or degrade the erosion characteristics of a particular configuration. Similarly to the previous problems, ablative Thermal Protection System (TPS) material for re-entry applications accommodate high heating rates and heat loads through phase change and mass loss. Most of the planetary probes to date have used ablative TPS. Most ablative TPS materials are reinforced composites employing organic resins as binders. When heated, the resin pyrolyzes producing gaseous products that are heated as they percolate toward the surface thus transferring some energy from the solid to the gas. Additionally, the injection of the pyrolysis gases into the boundary layer alters the boundary layer properties resulting in reduced convective heating. Furthermore, chemical reactions between the surface material and boundary layer species can result in consumption of the surface material leading to surface recession. Those reactions can be endothermic (vaporization, sublimation) or exothermic (oxidation) and have an important impact on net energy to the surface. In comparison to reusable TPS materials, the interaction of ablative TPS materials with the surrounding gas environment is much more complex as there are many more mechanisms involved. All these complex phenomena can only be modelled with a suitable numerical tool with proper boundary conditions to describe all the relevant physico-chemical interactions taking place at the ablating surface. The development of reliable analytical and simulation tools is fundamental to support the design and analysis process. This activity will perform a comprehensive assessment of the theory behind the above phenomena and develop appropriate modelling tools to address these issues. Deliverables Study Report Application/Need Date SRMs, Planetary and re-entry probes. Duration (Months) 18 Estimated Current TRL 1 Target TRL 2
SW Clause N/A Reference to ESTER T-856, T-578, T-7902, T-492, T-8278, T-8283, T-8947
Consistency with Harmonisation N/A
Page 51 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
TRP Reference T421-301MT Activity Title Applying acoustics for positioning and trapping cryogenic propellants in microgravity Objectives To study and demonstrate methods to exploit sound fields to invoke acoustic streaming leading to trapping of cryogenic propellants in predetermined tank locations during ballistic phases with the objective to:
1.diminish contact with tank wall and ullage gas 2.preserve the necessary quantity of liquid pre-positioned at the feed-line interface to allow for stage re-ignition without propellant settling manoeuvres Description In an acoustic field of standing waves any material (solid or liquid) tends to migrate towards the low-pressure nodal points or planes. This principle is being used e.g. in acoustic levitation of drops (up-to several millimetres in diameter) in ground tests for contactless containment to balance the gravitational potential. Likewise, the use of sound fields for acoustic shaping in microgravity has been the subject of study in the US for the purpose of construction in space and low-gravity environments in the late nineties. While the latter activity focussed on solid particles in air, ground experiments suggest the applicability of the same basic technology with liquids. The current activity will attempt to define a geometrical and acoustic configuration for a cage or trap, based on the deployment of a small number of acoustic sources, inside a reference stage tank geometry, which can generate a pattern of sound fields that is sufficient to retain an adequate quantity of propellant at the feed-line interface. The conceptual solution and arrangement of the acoustic sources shall be such that their accommodation is potentially feasible in an upper stage configuration. The work has to start with the identification of relevant theory and research results and has to pinpoint any further experimentation that will be required to understand the applicability of the technology for the intended use of propellant containment. Basic ground tests, with substitution liquids, and associated CFD/acoustic simulation for validation purposes, together with predictions in weightless environment will form part of the scope as well. The tests and simulations must allow for projection of the results onto a full-scale stage tank design (reference stage tank geometry), which, in conceptual form, constitutes the final step of the proposed activity. Deliverables Study Report The need date will be next generation launcher, to follow after the development of A5 ME, which will have advanced too far Application/Need Date to benefit from the outcome of the current activity. For the target TRL, a need date of 2012 is defined. Duration (Months) 18 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-8259
Consistency with Harmonisation N/A
TRP Reference T424-302QE Activity Title Biodegradable materials for launcher systems Objectives Reduction of environmental impact of materials used on launcher stages impacting on ground, with focus on coatings/paints and composite materials Description Materials used on launcher stages are at the best inert or possibly have adverse effects to the environment after return on ground. Environmental impact can be improved per design with the potential to: - Introduce positive effects to the environment in case the materials serve as biological nutrient - Improve costs as possible commercial solutions are developed primarily for the mass market Some materials applications on launchers are a promising target because the life-time is very limited, including storage under very controlled conditions, and short atmospheric exposure. The aim of this activity is to - Identify promising target applications (e.g. the external ESD paint) - Develop for each application on small scale an alternative biodegradable materials solution - Test the compliance with adequate launcher requirements - Demonstrate ecological and economic benefit Deliverables Breadboard Application/Need Date 2015 Duration (Months) 24 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-8258
Consistency with Harmonisation N/A
Page 52 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
5 - Telecommunications
5 - Telecommunications
TRP Reference T501-301ED Activity Title Deep Sub Micron 65nm, high speed serial link and PLL (Phase 2) Objectives This activity aims to complement and finalise the high speed serial link design work undertaken in the Phase 1 TRP activity (KIPSAT). The activity shall also address the design and prototyping of a PLL delivered as a hard macro embedded in the future DSM ASIC technology. The activity is complemented by T701-313ED. Description Based on the inputs provided by the characterisations of the HSSL proto 1 (Phase 1 / KIPSAT) redesign activities will be needed to correct bugs and improve performances:
- Speed - Power - Radiation hardening - Reliability
Concerning the standalone chip (Quatuor), the device shall be packaged in a Space grade solution (ceramic hermetic) and then undergo evaluation tests according to ESCC procedures.
- Thermal cycling under vacuum conditions - Radiation tests (TID, SEE)
The PLL defined in the Phase 1 (KIPSAT) shall be designed, prototyped and functionally tested. The PLL shall then undergo evaluation tests according to ESCC procedures.
- Thermal cycling under vacuum conditions - Radiation tests (TID, SEE)
Concerning the IP version of the HSSL and PLL, a behavioural model dedicated to simulation purposes shall be made available to speed up simulations and allow complete validation with the final design application. The HSSL and PLL shall be delivered as hard macros, synthesised and layouted. The HSSL shall be delivered as followed: - As a stand alone chip featuring 4 HSSL interfaces (Quatuor device) - As an hard macro ready for integration in future ASIC designs - As a behavioural model ready for simulation purposes
The PLL shall be delivered as followed: - As an hard macro ready for integration in future ASIC designs - As a behavioural model ready for simulation purposes Moreover simulations files and scripts shall be delivered to ease integration with the rest of the design. Deliverables Engineering Model Future digital telecom payloads need these technologies beyond 2012. The DSM technology will also be used for the future Application/Need Date generation of microprocessors and FPGA for Space applications. Duration (Months) 24 Estimated Current TRL 3 Target TRL 5
SW Clause N/A Reference to ESTER T-7795, T-7799, T-7800, T-36, T-8819
Consistency with Harmonisation TBD
TRP Reference T504-301EE Activity Title Compact hot plasma monitor for telecom satellites Objectives Design and breadboard a miniaturised non-obtrusive hot plasma monitor to perform spectrometry in the energy and flux ranges critical for high level surface charging, and related to Electro Static Discharge (ESD), on GEO telecom missions. Description Hot plasma with electron temperatures in the keV range is responsible for high level surface charging and consequent electrostatic discharge, especially on GEO orbit (e.g. Galaxy-15). A miniaturised non-obtrusive hot plasma monitor embarked on geostationary telecommunications platforms as part of the house-keeping equipment, would provide much improved diagnosis of the possible environmental cause of anomalies and better characterisation of this environment for future missions. This activity will design and breadboard a hot plasma monitor which performs electron and ion spectrometry in the range 30eV-30 keV. This range is important in driving high level charging and related ESD. Such a device will fill a gap between current sensors (SEPS (0-100 eV) and LEED (3 keV-100 keV)). Deliverables Breadboard Application/Need Date Telecom spacecraft on GEO Duration (Months) 18 Estimated Current TRL 2 Target TRL 4
Page 53 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
SW Clause N/A Reference to ESTER T-18, T-8395, T-8396
Consistency with Harmonisation N/A
TRP Reference T504-303EE Activity Title GEO telecoms radiation tools efficiency improvement with methods and geometry exchanges for industrial tools Objectives Dramatically improve efficiency of industrial processes, Agency support and partner interaction in the domain of radiation assessment and countermeasures for GEO telecomms. Improve the interfaces between European industry tools and the procedures and advanced tools for radiation analyses that include accurate physics and detailed geometry modelling. Preservation of radiation relevant quantities in geometry exchange with industrial CAD tools. Ensure tools can be used in the context of exchanges between industrial partners (e.g. Prime with respect to sub-contractor). Description Recent years have seen significant improvements in the accuracy of radiation tools in the analysis of radiation impact at spacecraft, equipment and part level. However, despite past efforts, deficiencies still persist in the link between system configuration and design of radiation countermeasures, significantly limiting accuracy and efficiency of industrial process and ESA internal project support. New interfaces and tools will be developed, as discussed in harmonisation, enabling direct communication and exchange of information of radiation relevant parameters (such as material and surface properties) with commercial widely used CAD tools (e.g. CATIA), building on top of existing industrial tool capabilities (e.g. Geant4 and GDML interfaces) and newly developed ESA-supported exchange formats such as STEP for Space Environment (STEP-SPE). The tools will also support interactions between primes and subs where radiation data are needed at platform/unit level and then need to be propagated in a physically consistent but efficient manner to component level. Fast turn-around of analyses is a strong requirement of telecom programmes. Deliverables Software Application/Need Date 2013 Duration (Months) 15 Estimated Current TRL 2 Target TRL 4 Open Source SW Clause Reference to ESTER T-7765, T-7887, T-7930, T-8777, T-19 Code Consistency with Harmonisation Radiation Environment Models, Monitors, Effects Tools, and Test Methods, Aims: 3/A13; 3/C10; 3/C11
TRP Reference T506-301ET Activity Title On-Board Processor for Dual Polarization Mobile Payloads Objectives The objective of the proposed activity is to demonstrate the overall performances of an On-Board Processor for Dual Polarization Mobile Payloads. Description Amongst different techniques required to increase efficiency in satellite resource utilization, reuse of polarization plays a central role. In particular, polarization reuse results of high interest for mobile broadcasting missions where the provided capacity is a fundamental success factor. Reconfigurable beamforming with flexibility in determining beams polarization constitutes a key enabling element of flexible Dual Polarization Payloads and digital implementations (i.e. Digital Beam Forming - DBF) offer a series of advantages including: precision, predictability, freedom from factors such as ageing, drift and component value variations, etc. DBF can be implemented both in transmit and receive; in both cases amplitude and phase control elements of analogue Beam Forming Network (BFN) realizations correspond to complex multiplications of the digitized signals followed by addition. DBF methods are particularly appropriate to match the upcoming trend of digital on-board processing (OBP) payloads.
Transparent On-Board Processors with Digital Beam Forming functionalities have been successfully pioneered in the eighties for mobile narrowband applications and, nowadays, DBF on a single polarization is commercially available on several On-Board Processors of mobile satellites operating at L-band (e.g. INMARSAT 4, Thuraya, etc.). The study and demonstration activity shall aim at extending current OBP capabilities to DBF for dual polarization payloads in mobile bands (i.e. L/S bands). The activity shall cover the following aspects: - analysis of requirements, - architectural trade-offs, - detailed design (including architectural and sub-systems design), - analysis, simulation and optimization of performance, - demonstrator detailed design, - demonstrator assembly/integration and testing/validation of performances, - identification of required technology improvements and necessary developments. The demonstrator shall be limited to a forward processor (from analogue IF input to multiple RF outputs) and build with representative off-the-shelf (OTS) commercial technology. A technology roadmap covering exploitation of on-going developments and longer term needs shall be generated. Deliverables Breadboard Mobile Satellite Services Application/Need Date Mobile Broadcasting Duration (Months) 24 Estimated Current TRL 1 Target TRL 4
SW Clause N/A Reference to ESTER T-7923, T-8819, T-7832, T-7746, T-7917, T-8914
Consistency with Harmonisation TBD
Page 54 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
TRP Reference T506-302ET Activity Title Interference management techniques for satellite networks Objectives The goal of the proposed activity is to investigate new paradigm of interference management techniques applicable to satellite communications scenarios and compare the achievable performance improvement to that of conventional interference avoidance/suppression techniques. Description In today satellite communication systems, interference between transmitters is considered undesirable and is typically dealt with by orthogonal transmissions in time, code or frequency. The remaining interference due to resource reuse is treated as noise. System design efforts are mainly focused on suppressing residual interference components. The ultimate performance of the system is measured in comparison to the capacity of a point-to-point, or a multi-access channel. Although for systems with a limited interference this approach can be acceptable, the scarcity of frequency resources and ever growing demand for capacity will inevitably increase the need for the resource sharing. As a result, the interference will become the ultimate limiting barrier of the system performance.
Recent studies of the performance of interference channel have shown a paradigm shift in dealing with interference; that is to exploit interference rather than to suppress it. Techniques such as network coding, frequency alignment and pre-distortion applied to multi-user detection have shown improved reliability and throughput in certain communication systems. This study shall provide a survey of interference management techniques such as network coding, interference alignment and others with applicability to satellite or hybrid satellite/terrestrial access networks, such as multi-spot beam broadband access, mobile satellite services, meshed network (regenerative and transparent). The study shall provide a comparative analysis of interference management techniques in comparison, or in conjunction with more classical techniques such as Multi Input Multi Output, precoding multi-user detection, etc. with a sufficient level of detail to assess performance and to establish a set of techniques for further detail analysis. In the selection of techniques, the complexity and scalability of techniques shall be taken into account.
For the selected techniques, simulation models and test scenarios shall be established in order to provide sufficient evidence of their performance improvement in comparison to the performance of conventional techniques that are used as the baseline for different system scenarios.
The study shall provide recommendations for potential system architecture as a proof of concept based on the techniques that can offer promising performance improvements. Deliverables Study Report Application/Need Date 2013 Duration (Months) 18 Estimated Current TRL 1 Target TRL 2
SW Clause N/A Reference to ESTER T-8909, T-8912
Consistency with Harmonisation TBD
TRP Reference T506-303ET Activity Title Ultra low phase noise reference oscillator Objectives The objective of the activity is the demonstration of the practical feasibility of a 1 GHz reference oscillator based on the microwave optoelectronic oscillator approach. Description Background: More stringent requirements related to complex modulations as well as flexibility based on multiple frequency conversion schemes call for a significant improvement (up to 10 dB) of the phase noise of the oscillators used on-board future telecom payloads. Recent developments in the field of microwave optoelectronic oscillators have led to the demonstration of unprecedented phase noise performance.
Description: In a first Phase, an exhaustive patent and literature review will be carried out and the two most promising potential topologies will be assessed. In a second Phase, one of the two pre-selected topologies will be breadboarded and the RF performance will be analysed. Deliverables Study report Application/Need Date TRL5 in 2015 Duration (Months) 24 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-283, T-47
Consistency with Harmonisation TBD
TRP Reference T506-304ET Activity Title Concepts and Techniques for Reconfigurable Multiplexers
Page 55 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Objectives Objective of this activity is to develop novel filter and multiplexing concepts for reconfigurable multiplexers. Filter tuning mechanisms shall be developed and demonstrated suitable for long term application in space. Multiplexing concepts shall be demonstrated on full wave models or hybrid circuit/full wave models of a three channel multiplexer. Description Several mission scenarios exist, where reconfigurable input and output multiplexers would offer significant mass and volume reduction. Indeed today fixed frequency multiplexers are a bottleneck for future flexible payloads with in-orbit bandwidth reallocation. Key issues are: - the identification of an adequate tuning concept for the channel filters and - standard multiplexing techniques can not efficiently cope with the interaction of reconfigurable channel filters on the manifold. In a first step existing tuning and multiplexing techniques shall be reviewed, all trade-offs identified including RF performance over temperature and impact on insertion loss. Novel tuning concepts shall be developed and fully evaluated for space application, in particular with respect to RF performance and reliability. The concepts shall be demonstrated on resonator breadboards to be built and tested. In a second step the developed multiplexing concepts shall evaluated by means of equivalent circuit model of a diplexer. Finally, in the last step a 3 channel reconfigurable multiplexer shall be designed at circuit level and RF performance evaluated for different bandwidth settings over an octave range up to a contiguous case. The circuit model shall then be converted into a full wave or hybrid circuit/full wave model for several different channel filter bandwidths to fully demonstrate the multiplexing concept. Deliverables Study Report and CAD Models Application/Need Date 2018 Duration (Months) 24 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-7746
Consistency with Harmonisation TBD
TRP Reference T506-305ET Activity Title Diamond supporting rods for high power helix TWTs Objectives The proposed study aims at preparing the delay line technology for high power Ka-band and Q-band Travelling Wave Tubes (TWTs) for future satellite payloads. The use of the new material will be validated through the design, manufacturing and testing of TWT subassemblies (target: 100 W at Q-band). Description Background: Future satellite payloads will require higher power levels at increasingly higher frequency bands (e.g., 100 W in Q-band) for which new technology bricks become necessary. Diamond helix support rods would allow increasing the power handling capability of helix Travelling Wave Tubes (TWTs) beyond the level achievable today (e.g., from 200 W to 300 W in Ka-band) and would also allow replacing Beryllium Oxyde (BeO) material that is today the baseline for the 100 W Q-band TWT.
Description: The activity will be devoted to a feasibility study of the delay line with diamond rods and will include: 1) the delay line definition and diamond rods specification, 2) the procurement of diamond rods, the characterisation of the rods (in particular behaviour under electronic bombardment, feasibility of attenuation), 3) the technological study of delay line assembling (process and tools), 4) the assembly of short delay line for thermal impedance measurement (DC test).
Based on the results achieved, assembly and tests of RF transmission lines will prove the suitability of diamond rods as a support for high-power/high-frequency helical delaylines. The applicable requirement will be that of the 100 W Q-band downlink, which is today the most stringent in terms of power and frequency but will also cover the requirement of 300 W CW for Ka-band downlink and 500 W CW for the Ka-band uplink. Deliverables Breadboard Application/Need Date 2013 Duration (Months) 24 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-7825
Consistency with Harmonisation N/A
TRP Reference T506-306ET Activity Title Lossless Beamforming Networks for Overlapped Sub-Array Antennas Objectives The objectives are to investigate the feasibility, performance and technical aspects of Lossless Beamforming Networks and to demonstrate (through bread boarding) and test identified solutions. Description
Page 56 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Overlapped Sub-Array Antennas are characterized by a significant reduction in the number of control elements (amplifiers, variable attenuators and phase shifters) with respect to the number required by the corresponding conventional active array (either directly radiating or illuminating an optical system as a reflector). This complexity reduction factor can be quantified in the ratio between the number of radiating elements and the number of sub-arrays. A through complexity advantage of the antenna can be achieved only when the power amplifiers can be directly interfaced at sub-array level, this requiring that the minimum amount of power is wasted in the sub-array analogue BFN.
Overlapped sub-array antennas jointly solve the problem of reducing the number of control elements (through sub-arraying) as well the requirement for adequate control of the pattern performance (through overlapping). These techniques have been broadly studied for Direct Radiating Array (DRA) configurations but are as well applicable to Array Fed Reflector architectures. R&D activities have shown the applicability of the concept to on-board satellite antennas but the standing point remains the capability of realizing analogue beamforming networks with desired functionalities and lossless characteristics (meant in the sense that the power applied at the input ports is preserved at the output ports). An example of a lossless BFN with efficient implementation is the Butler matrix.
An initial trade-off phase shall allow identifying a suitable implementation of the lossless BFN as well as necessary technology evolutions. The BFN implementation shall be assessed with particular attention to the error analysis. The selected configuration shall be brought to a design level such to make possible a thorough analysis of the achievable performances. A breadboarding phase shall allow verification and testing of achieved performances and necessary upgrades. Deliverables Breadboard - Fixed and Interactive Broadband Satellite Services (Ku and Ka-band) Application/Need Date - Mobile Interactive Services (Ku and Ka-band) 2015 Duration (Months) 18 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-7912, T-8909, T-7746, T-7925
Consistency with Harmonisation activities A1, A2, A3, C1, C2, D1 and D2 of Array Antennas roadmap
TRP Reference T506-307ET Activity Title Techniques for ultra wide stopband IF filters Objectives Objective of this activity is the development and demonstration of compact IF filters with ultra-wide stopband. Description Often significant filtering requirements exist for planar and drop-in receiver filters at IF frequencies in the 1 to 4 GHz frequency range of typically 3-7x f0 (centre frequency) to comply with spurious emission requirements and suppression of image bands and spurious outputs from active devices. Filter requirements become even more challenging when a number of up- or down-converter stages are cascaded in advanced payloads and specifications for up to 10x f0 arise. Today to achieve such very demanding requirements a several low- and high-pass filters have to be cascaded. Apart from high design, manufacturing and tuning complexity, this leads to a significant filter footprints which is not acceptable. In this activity new ideas to achieve receive filters in the 1 to 4GHz range with ultra-wide stopbands of up to 10x f0 shall be explored and further developed without the need of cascading a number of low or high-pass filters which often leads to unacceptable footprint size. Instead resonators with spurious suppression and/or frequency selective coupling apertures shall be developed and utilized. In this way the footprint shall be kept to a minimum. Breadboards shall be built to demonstrate the feasibility of the novel concepts, the RF performance and the achieved footprint. Deliverables Breadboard Application/Need Date 2016 Duration (Months) 18 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-7746
Consistency with Harmonisation TBD
TRP Reference T506-308ET Activity Title Advanced modem techniques for future satellite access networks Objectives The main objective of this activity is to design and validate, in a realistic and representative environment, new techniques to enhance the spectral efficiency of air interface by at least 15% compared to what is currently achievable using the existing air interface standard Description
Page 57 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Digital transmission techniques are essential elements of today satellite communications systems. Air interface Standards such as DVB-S2 and the Next Generation of DVB-RCS reflect the evolution of digital modulation and coding and techniques that allow significant improvement in power and bandwidth efficiency. The cost of satellite capacity remains a major factor in the overall cost of satellite communication services. This can hinder the competitiveness of satellite based solutions in comparison to terrestrial counterparts. There is a need for investigations of novel techniques for transmitter/receiver design to further improve the overall spectral efficiency of satellite communications, especially for digital broadcasting and broadband satellite access networks. The proposed activity is aimed to investigate state-of-the art techniques to enhance the flexibility and performance of digital modems in the future satellite access networks targeting different markets such as consumer and professional sectors. For the broadband and broadcasting applications, digital transmission techniques such as new signalling schemes to increase the transponders capacity shall be investigated. Other techniques to extend modulation and coding threshold range, synchronization improvement at low signal to noise operating points, turbo equalization techniques and new physical frame structures shall also be studied and their applicability to satellite communication environment shall be evaluated.
The proposed activity shall also investigate advance digital transmission techniques for the return satellite channel to allow reducing the spacing between adjacent carriers using techniques such as Interleave Division Multiple Access (IDMA) in conjunction with interference cancellation techniques. The use of time-frequency packing techniques to improve the spectral efficiency of Multi-Frequency Time Division Multiple Access (MF-TDMA) access scheme shall also be investigated.
The study of the selected techniques shall be complemented by a thorough simulation campaign to establish a quantitative assessment of the overall proposed air interface under a realistic channel models. Deliverables Study Report Application/Need Date 2012 Duration (Months) 18 Estimated Current TRL 1 Target TRL 2 Open Source SW Clause Reference to ESTER T-120, T-8411 Code Consistency with Harmonisation N/A
TRP Reference T507-301EE Activity Title Lens-Like Multiple Beam Antenna Objectives Investigate lens-like multiple beam antennas for array and imaging array configurations with a large number of beams. Description Multiple beam antennas are of great interest for satellite telecommunication applications as they enable increased capacity through frequency/polarisation reuse. Several technical solutions of multiple beam forming networks are known, each having its advantages and disadvantages. One of them is based on lens-like solutions. It includes lenses, such as the Rotman lens or the Luneberg lens, but also reflector-like structures such as the pillbox antennas. Recently, attention has been given to these solutions including for space applications because the resulting designs are easier to manufacture than their guided wave networks counterparts, specially for large arrays. This range of application is also preferred because these lens-like structures are known to be limited by their efficiency for smaller arrays. Examples of realisations with more than 40 beams are reported. Deliverables Study report Multiple beam antennas (focal arrays and imaging arrays) with a large number of beams (more than 40) for next generation Application/Need Date telecommunication satellites. Need date: 2015. Duration (Months) 18 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-7925
Consistency with Harmonisation This activity is a follow-up to the activity D3 in the array antennas harmonisation roadmap (from 2005)
TRP Reference T507-302EE Activity Title Shared aperture reflector antenna Objectives To study and demonstrate by analysis a reflector antenna architecture able to generate several different beams from a shared shaped reflector aperture. Description The activity focuses on the design of an antenna architecture featuring a single reflecting surface able to generate several different beams. Several feeds can be used to illuminate a shared shaped reflector with locally modified reflection characteristics so has to form separate beams. A dedicated design procedure is required to allow an efficient antenna performance optimisation, including an initial high-level synthesis of the antenna geometry and surface layout, followed by a full-wave optimisation of the reflecting surface. The activity encompasses two steps. The first step involves the definition of applications scenarii and requirements followed by the demonstration of feasibility by analysis. The design procedure will be then defined and implemented in parallel. As a second step, candidate solutions will be designed in detail for the most challenging scenario and their performance demonstrated by analysis, with validation on laboratory test pieces if necessary. Deliverables Study Report Application/Need Date Broadband Services Duration (Months) 12 Estimated Current TRL 1 Target TRL 2
Page 58 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
SW Clause N/A Reference to ESTER T-7925
Consistency with Harmonisation RAFT 2009-A6
TRP Reference T507-303EE Activity Title Antenna architectures and technologies for reduced beamwidth multiple beam coverage Objectives To optimise antenna architecture and design a multifrequency feed compatible with a 2 wavelengths spacing Description Multiple beam antennas are widely used for broadband Ka-band applications. For a given service area, the system capacity increase obtained by implementing a higher level of frequency reuse is directly linked to the antenna beamwidth. The current design beamwidth is around 0.5 degrees, whilst the next generation of multiple beam antennas target beamwidths down to 0.2 degrees. Taking into account typical antenna geometries and spacecraft accommodation constraints, this beamwidth reduction requires the reflector diameter to be significantly increased (typically up to 5 m), resulting in a lower focal-length-to-diameter (F/D) ratio (reduced from 2 to 1). Another consequence is the reduced footprint allocated to the feeds, from 4 to 5 wavelengths down to 2 wavelengths. These two major constraints drastically impact on the performance that can be achieved over the field of view. This activity shall define the proper antenna architecture for providing multiple beam coverage with reduced beamwidth and shall derive the corresponding feed requirements. On this basis, a highly compact feed assembly architecture shall be designed. The resultant feed design shall be validated by analysis and RF testing of the feed critical components. Deliverables Breadboard Reflector based multiple beam antennas combining multiple frequency bands such as Ku and Ka bands for telecom Application/Need Date applications. Need date: 2015. Duration (Months) 18 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-7912
Consistency with Harmonisation Related to C10 in the Telecommunications Reflector Antennas Harmonisation Dossier
TRP Reference T507-304EE Activity Title Transmit-Receive multiple beam antennas based on direct radiating arrays Objectives To study a common aperture transmit-receive multiple beam reconfigurable space antenna based on active direct radiating array. Today several telecom satellites are implementing on the Earth deck single beam mechanically steerable transmit/receive antennas at Ku and Ka band. Recently some developments took place for flight hardware direct radiating array in Transmit or in Receive. There is a strong interest in investigating common aperture transmit-receive multiple beam antennas based on direct radiating array architectures as a way to generate several reconfigurable beams over the Earth with a limited volume. The main challenges consist in: a) obtaining an intelligent partitioning of the functionalities of the antenna in order to have a compact and affordable design; b) minimizing the number of elements; c) properly addressing and solving the thermal issues. A proper trade-off between interleaved transmit-receive apertures and apertures constituted by transmit-receive elements shall be done. Periodic or aperiodic array layouts shall be considered. The possibility to generate spot beams and shaped beams and to operate in dual polarizations shall be investigated. This type of antenna architecture will provide major benefit to obtain in-orbit flexibility in terms of coverage area and allocation of bandwidth and power to a particular zone. Different architectures in transmission and in reception due to technological/cost constraints shall be considered. Description The activity will be divided in three parts. In the first part, some typical requirements shall be defined and a baseline reflector based antenna, providing a reference and target solution, shall be identified. In the second part, several array architectures shall be traded off and their performance compared with the reference one. In the third part, a preferred baseline solution shall be identified and deeply investigated. Today several telecom satellites are implementing on the Earth deck single beam mechanically steerable transmit/receive antennas at Ku and Ka band. Recently some developments took place for flight hardware direct radiating array in Transmit or in Receive. There is a strong interest in investigating common aperture transmit-receive multiple beam antennas based on direct radiating array architectures as a way to generate several reconfigurable beams over the Earth with a limited volume. The main challenges consist in: a) obtaining an intelligent partitioning of the functionalities of the antenna in order to have a compact and affordable design; b) minimizing the number of elements; c) ensuring the proper decoupling between the transmit and the receive function, d) properly addressing and solving the thermal issues. A trade-off between interleaved transmit-receive apertures and apertures constituted by transmit-receive elements shall be done. Periodic or aperiodic array layouts shall be considered. The possibility to generate spot beams and shaped beams and to operate in dual polarizations shall be investigated. This type of antenna architecture will provide major benefit to obtain in-orbit flexibility in terms of coverage area and allocation of bandwidth and power to a particular zone. Different architectures in transmission and in reception due to technological/cost constraints shall be considered. Deliverables Other: Paper Study Application/Need Date 2012 Duration (Months) 12 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-7907
Consistency with Harmonisation No
Page 59 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
TRP Reference T507-307EE Activity Title Reflectarray antennas with improved performances and design techniques Objectives The activity will be devoted to the study of new reflectarray antennas for satellite applications with reduced losses and improved dual polarization pattern performances. A second objective of the activity consists in implementing new algorithms for the effective synthesis of such antennas able to include possible curvature effects, completely non periodic lattices, multi-facets configurations. Description Reflectarray antennas offer several advantages with respect to curved reflectors. Recent ESA activities have demonstrated that still some performances may be drastically improved resorting to new materials, new layouts, new analysis and optimization techniques. A first objective of this activity consists in identifying, optimizing and testing new reflectarray antennas for satellite applications with reduced losses and improved dual polarization pattern performances. A second objective of the activity consists in implementing new algorithms for the effective synthesis of such antennas able to include possible curvature effects, completely non periodic lattices, multi-facets configurations. Deliverables Software Application/Need Date 2012 Duration (Months) 18 Estimated Current TRL 3 Target TRL 4
SW Clause N/A Reference to ESTER T-48
This activity is a follow-up on activities C11 and C12 of the Array Antennas Roadmap, which is proposed in Consistency with Harmonisation order to overcome some of the limitations identified during these activities
TRP Reference T507-308EE Activity Title Advanced fuse blowing models for accurate transients prediction Objectives Development of electrical models of fuses, based on physical and behavioural approaches, to be implemented in power bus electrical simulations, describing fuse melting for the whole range of possible short-circuit currents. Description Background: The power lines of telecom spacecraft are protected by fuses. In case of a fuse blowing event, a very high short circuit current develops in a very short time resulting in high amplitude transients on the power bus that can cause failure propagation including fuse-blowing propagation. Among the verification methods aiming at guaranteeing the absence of failure propagation, simulations are preferable to fuse blowing tests at spacecraft level, as: - fuse blowing tests at spacecraft level can be risky; - the number of tested cases is very limited; - the behaviour of the hardware, including the EGSE is difficult to predict accurately; - only some fuse locations, nameplates and ratings are tested; - the full satellite electrical configuration is required to make representative tests, so the results are known very late in the development; - worst case parameters, especially for the fuses themselves, can be considered in simulations.
Fuse blowing models exist that can be used in electrical simulations to predict the current and voltage up to the fuse melting, and within certain conditions, during and after the fuse melting. However such models do not cover the whole gamut of situations and feature in particular the following shortcomings: - They assume I^2 * dt = constant, although this is only valid for short blowing times (<1 ms), as it corresponds to the adiabatic situation; for longer blowing times, a semi-adiabatic model is needed. - On the other hand, for high short circuit currents, resulting high dI/dt values (up to 1000 A/us) have been reported, likely to result in high voltage transients on the power bus, that are not predicted by the existing models.
Activity: 1) Test campaign on several commonly used fuses covering a wide range of short circuit currents; 2) Development of physical and behavioural models, to be implemented in SPICE, describing the fuse melting for the whole range of possible short-circuit currents, as well as the electric arc during the fuse blow-off and its dependence on the short-circuit current; 3) Calculation of the fuse transient propagation on an example telecom spacecraft power bus featuring cable return (prediction of differential and common mode transients at various points of the power bus); 4) Verification by test of the prediction results on a breadboard. 5) Guidelines for selection of grounding concept with respect to operational configuration (frequency, power, etc.) Deliverables Study Report, test samples, breadboard Application/Need Date Industrial competitiveness (TEL) / 2013 Duration (Months) 12 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-50
Consistency with Harmonisation N/A
TRP Reference T515-301MS Activity Title Innovative scalable large deployable antenna reflectors Objectives
Page 60 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
To identify, design and demonstrate by bread-boarding the feasibility of a European large antenna reflector having intrinsic scaling capability to cover diameter range from 4 to 18 m and frequency range from UHF to Ka-band. Description Despite different attempts performed in the past two decades, Europe is lacking a competitive product for a large reflector with the requested TRL level to embark on a commercial program. Need is identified to cover antenna applications from 4 up to 18 meter and for frequencies from UHF up to Ka band.. American companies are leaders in this domain and are commercially dominating the worldwide market. ESA has implemented a dedicated large antenna working group, which has analysed the state-of –the-art in this domain and identified most promising large reflector concepts, together with design criteria and requirements. The associated Technical Report shall be considered as the basis for this activity. In particular the need for a “scalable” design concept, able to cover the small diameter range, but with growth potentials up to 18 m diameter, has been recognised. Regarding surface accuracy and electrical performances they have to be scalable from lower frequency ranges, up to the highest currently envisaged (Ka frequency band with 5 m diameter).
Overall reflector configuration, accommodation, mass, stiffness, deployment reliability and testability shall be studied.
The activity would proceed with a Phase 1 (target budget 250K€) where consolidation of the requirements, design concept, feasibility and testability would have to be shown. Phase 2 would be devoted to the detailed design and analyses at reflector level and breadboard verification of the consolidated concept. A 4 to 7m reflector model is anticipated.
In addition to ESA working group identified concepts, original ideas, if proposed, will be considered in the early parts of Phase 1, to exploit at maximum creativity and constant progresses in the field of material / component technologies. Deliverables Breadboard Application/Need Date 2013 Duration (Months) 24 Estimated Current TRL 1 Target TRL 4
SW Clause N/A Reference to ESTER T-8854
This activity is within the scope of AIM D of the Reflector Antennas for Telecommunications roadmap. Consistency with Harmonisation However, the proposition of new activities within this AIM to THAG was delayed.
TRP Reference T516-302MM Activity Title Validation of turbulence mitigation techniques for high data rate optical link Objectives This activity is to demonstrate reliable bidirectional optical transmission (up to 100Gbps) through the atmosphere in a scenario representative (in terms of link attenuation and optical turbulence) of an optical feeder link between a GEO telecom satellite and an Optical Ground Station.
For that purpose, this activity shall design, manufacture and test an end-to-end optical communications breadboard (OCB) representative of an optical feeder link. The technical feasibility and the performances of such OCB (e.g., maximum achievable data communications rate, bit error rate statistics, availability) shall be demonstrated under relevant field conditions (e.g., inter-island link using the ESAs Optical Ground Station in Tenerife). Description Next generation broadband access missions will pose stringent demands on the communication feeder links between gateways and telecom satellites (e.g., EUTELSAT claims a total system throughput of 70 Gbit/s for its KaSat satellite using a network of about 10 Ka-band gateways). With increasing capacity needs, new microwave frequency bands beyond Ka-band are being explored (e.g., Q and V-bands). At such frequencies, signal degradation due to atmospheric propagation effects (e.g., rain fading) becomes a critical issue and microwave component technology at those frequencies and has currently not yet reached a mature state.
Free-space Optical Communication Links (OCL) constitute an attractive alternative to microwave communication links (higher antenna gain, higher data rates, security aspects, EMC/EMI immunity, frequency regulation issues, etc.). However, OCL between a GEO satellite and an optical ground station entails propagation through the atmosphere, which degrades the quality of the optical signal (due to the atmospheric turbulence) and the link availability (due to cloud coverage). European heritage in laser communications is not directly applicable to an optical feeder link scenario (SILEX technology is limited to <300Mbps; EDRS's technology based on high-sensitive coherent receivers is capable of >1Gbps but suffers from atmospheric-induced phase degradation effects and limited multiplexing / scalability performances).
Specific optical technologies / techniques have been assessed in the frame of the ARTES-1 study & "Feasibility Assessment of Optical Technologies & Techniques for Reliable High Capacity Feeder Links" (Co No 21991) to mitigate cloud and fading effects (e.g., optical ground station network, mobile ground terminal, adaptive data rate, adaptive transmit power, adaptive optics, telescope array, wavelength diversity, wavelength division multiplexing, high-power sources, high-sensitivity modulation format and detection techniques, channel coding). In addition, the ARTES-1 study included the system design of a bidirectional high capacity optical feeder link.
The present activity shall design, develop and test an end-to-end optical communications breadboard (OCB) representative of an optical feeder link. The breadboard shall implement the necessary optical (Single Mode and Multi Mode) technologies / techniques to demonstrate reliable bidirectional optical transmission (up to 100Gpbs) through the atmosphere. The performances of the OCB (e.g., maximum achievable data communications rate, bit error rate statistics, availability) shall be verified under representative field conditions (e.g., inter-island link between La Palma and Tenerife using the ESA Optical Ground Station in Tenerife). Based on the attained results, the system design of a bidirectional high capacity optical feeder link shall be revisited (mission architecture, space optical communications terminal and optical ground station) and the technology development roadmaps of the space optical communications terminal (up to FM level) and the optical ground station shall be updated. Deliverables Breadboard Application/Need Date Fixed Satellite Services, Direct Broadcast Services, 2015 TRL6 Duration (Months) 24 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-7914, T-7927
Page 61 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Consistency with Harmonisation activities A5 and D2 of the Optical Communications for Space Roadmap
TRP Reference T519-301MP Assessment of carbon ion engine technology targeting competitively improvement of electric propulsion for telecoms Activity Title applications Objectives Starting from flight proven technology concepts, the design and demonstration of an Ion Engine in which all of the components exposed to plasma and involved in radiative cooling are fabricated from amorphous or carbon-carbon composite, to target the following objectives: - High thrust density resulting in increased thrust at lower operating temperatures. - Physically smaller thruster capable of delivering 150mN or more. - Lower dry mass (potential for at least 2kg saving). - Lower production costs for a carbon ion thruster, supporting lower mission prices. - Longer life screen grid to >25MNs (elimination of screen grid erosion as a life-limiting factor). - Simplification (mass & price) of PPU design through improved thruster robustness/margins. Description The 22cm gridded ion engines have already demonstrated that beam currents equivalent to a thrust level of up to 230mN can be extracted. This in turn requires a high plasma density within the discharge chamber to be produced. More recently however the limitations on thruster performance imposed by the Screen grid material and harness interface temperatures would prevent thrust levels in excess of 145mN from being considered without further a dedicated development programme.
Building an ion engine in which all of the components exposed to plasma and involved in radiative cooling are fabricated from amorphous or carbon-carbon composite will address both of these current limitations. A carbon-carbon composite screen grid would dramatically increase the tolerance to grid erosion. An added benefit would be that the coefficient of thermal expansion of such a grid would be virtually zero and hence the increase in the grid spacing during thruster operations would be dramatically reduced. This will provide a higher grid perveance limit allowing even higher ion beam current densities to be extracted, and hence thrust levels to be produced (>230mN for a 22cm size device).
Manufacturing the discharge chamber and external Earth-Screen from amorphous or carbon-carbon composite would both reduce mass and provide radiating surfaces with an inherent high emissivity. The high emissivity will reduce operating temperatures resulting in an engine design more tolerant to higher thrust densities. An added advantage would be that the thermo-optical properties of the external radiating surfaces would not be influenced by ground based facility interactions; i.e. the deposition of carbon sputter deposits from the facility ion beam targets would not change the thermo-optical properties.
A corollary benefit of this approach would be the possibility of reducing the physical size of the engine. Currently 22cm Ion Thruster is perceived to be physically large and limits its potential use on smaller telecoms platforms and for other telecoms applications, in particular east-west station keeping. Designing an ion engine that is physically smaller but maintaining high thrust performance would allow the benefits of ion engines to be more fully exploited in the telecoms market. For example, the 145mN delivered by the existing 22cm thrusters could be achieved with a smaller thruster if it were scaled appropriately.
Consequently, it is proposed to undertake a study that incorporates the following key activities: - Assess and implement the design of a 22cm sized carbon-carbon Screen grid, taking into account manufacturing/production processes and limitations imposed by the environmental (vibration) requirements. - Assess the performance of a standard (metal components) ion engine using a carbon-carbon screen grid. - Assess and implement the design of a 22cm sized carbon discharge chamber, anode, baffle and earth-screen, taking into account manufacturing/production processes and limitations imposed by the environmental (vibration) requirements. - Assess the performance of a ion engine (fitted with carbon-carbon screen grid) using components manufactured from carbon-carbon/amorphous carbon (discharge chamber, anode, baffle and cathode keeper) at higher thrusts (>200mN). - Preliminary assessment and scaling of a physically smaller gridded ion engine offering >150mN performance.
The benefits of this study would be as follows: - High thrust density resulting in increased thrust at lower operating temperatures. - Physically smaller thruster capable of delivering 150mN or more. - Improved performance of grids (no differential expansion of carbon and screen grids since they are manufactured from the same material). - Lower dry mass (potential for at least 2kg saving). - Lower production costs for a carbon ion thruster, supporting lower mission prices. - Longer life screen grid to >25MNs (elimination of screen grid erosion as a life-limiting factor). - Trade-off between high thrust and high specific impulse: benefits for telecoms and science missions. - Trade-off between thruster and Power Processor Unit (PPU) performance; simplification of PPU design through improved thruster robustness/margins. Deliverables Breadboard Due to scaling study incorporated within this activity proposal, applications cover complete range of existing GEO Telecom platforms for NSSK and extend opportunities (over existing thruster designs) to use EP for Orbit Raising/Repositioning (High Application/Need Date Thrust) and EWSK (compact thruster envelope) Expected application readiness: 2015 Duration (Months) 18 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-1048
Consistency with Harmonisation A3: Assessment of lifetime issues in electric propulsion systems.
TRP Reference T519-302MP
Page 62 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Activity Title Development of a device to avoid transfer of Xenon propellant Objectives The growing demand of propellant tankage leads to multiple tanks configuration and hence exposes the mission to the risk of large centre of mass shift as large amounts of propellant flows between the tanks. This calls for an increase of the ACS actuator capacity, and/or propellant required for dumping of angular momentum. The problem is mostly highlighted in electric propulsion due to the highly variable density of Xenon when stored under supercritical conditions. Although mass transfer between tanks in principle can be prevented by the implementation of latching valves at every tank outlet, such a solution would increase the system mass, add system complexity and lower the overall reliability. Exploring and bread boarding a reliable, light and settable anti transfer device would reduce the criticality for most of the future telecommunication missions using Xenon. Description The activity should consist in a design feasibility study based on an existing component survey and in a second phase of breadboarding to demonstrate the ability of the proposed design in meeting the targeted functions. Deliverables Study Report Application/Need Date any spacecraft using Xenon as propellant Duration (Months) 18 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-8119
Consistency with Harmonisation TBD
TRP Reference T520-301MS Activity Title Thermally conductive RTM CFRP Objectives Develop and qualify a thermally conductive RTM CFRP material Description Carbon fibre-reinforced polymer or carbon fibre-reinforced plastic (CFRP) housing for electronic boxes could be produced using Resin Transfer Molding (RTM) technology. However, the material needs to be thermally conductive. This activity aims at developing and qualifying a thermally conductive RTM resin, adding e.g. copper powder. Deliverables Breadboard Application/Need Date Mostly for telecom even if other applications could benefit Duration (Months) 18 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-7750, T-8840
Consistency with Harmonisation N/A
TRP Reference T523-301QT Activity Title CSP and MCM-L (non hermetic): Low TCE HDI substrates for flip-chip Objectives Assessment of new technological design to make non hermetic Chip Scale Packaging (CSP) and Multi Chip Modules with multilayer laminate (MCM-L0 with flip chip bonding and low TCE High density Interconnect (HDI)substrates. Description There are non hermetic chip and wire solutions with good reliability in moist environment. When the die is large, to manage the thermo-mechanical stresses between die and substrate, the die is mounted on a ceramic sub-mount. In this case the area increase sensibly leading to a situation where the intrinsic integration advantage of CSP or MCM-L is lost. Going toward the needed large area and high pin count dies flip-chip would be the best interconnection candidate. This absolutely requires an assessment of a solution using a low TCE substrate to minimize the stress on the bumps, bumps made of high fatigue resistance alloy, and at the same time High Density Interconnect (HDI) with micro vias. Deliverables Study Report Application/Need Date TRL5 by Q2 2015 Duration (Months) 18 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-8448, T-7891, T-7795, T-7798, T-7801
Consistency with Harmonisation TBD
TRP Reference T524-301MS Activity Title Low cost reflector moulds
Page 63 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Objectives The main objectives of this activity are research and trade-off antenna reflector moulding techniques and tooling methods that could be applied with the aim of reducing cost and lead time. Develop the selected tooling method by providing a mould for the manufacture of a demonstrator model of a Ku-band antenna reflector. Characterise the selected materials of the mould within the temperature and pressure range of interest. Carry out the reflector demo test campaign. Description Current reflector molding methods are based on expensive and long lead-times technologies. Low cost method are available in other engineering disciplines and can be adapted to this particular application. An implemented ARTES 5 activity is addressing this point as well, but focusing on the improvement of established methods. The intention here is to explore new techniques, widely available. Deliverables Breadboard The application is the necessary cost reduction of telecommunications antennas for competitiveness in the world market. Application/Need Date Need date: 2013 Duration (Months) 12 Estimated Current TRL 1 Target TRL 2
SW Clause N/A Reference to ESTER T-7907
Consistency with Harmonisation TBD
TRP Reference T524-302QT Activity Title Long lasting white thermal control coatings for GEO (Oxygen donors) Objectives This study aims to review the use of white ceramic coatings which are to be modified such that they contain oxygen donors that shall enable a reduction of the degradation of the solar absorbance by a factor of 2 compared with today technology. Description The radiation belts of GEO that ESA's TELECOM spacecraft encounter lead to detrimental effects and degradation of more than 300% of the solar absorption has been observed by ground and in-orbit results for GEO spacecraft. (J. Marco et al., 11th ISMSE, France 2009) The activity shall evaluate the incorporation of various oxygen donors strategies on white ceramic coatings and shall evaluate their space radiation resistance aiming at typical 15 years GEO applications - Best candidate coatings will be further investigated. Deliverables Other: samples, TN, breadboards Application/Need Date Immediately Duration (Months) 24 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-8842
Consistency with Harmonisation TBD
Page 64 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
6 - Navigation
6 - Navigation
TRP Reference T604-301EE Activity Title 3-D Time-Dependent Modelling of Internal Charging in MEO and Model Validation Through Experiment Objectives The purpose of this activity is to create and validate a time-dependent 3-d internal charging code for application to the high electron flux environment of MEO navigation satellites Description Internal electrostatic charging of spacecraft dielectrics is a 3-dimensional phenomenon which depends on the transport of high energy electrons through spacecraft materials and the flow of electric charge and electric fields through the affected materials. Typically the materials in question are insulators such as cables, connectors and printed circuit boards. The result of the charging is electrostatic discharge within the spacecraft Faraday cage and close to electronic components and was the likely cause of several recent spacecraft anomalies. Internal charging is a serious hazard to spacecraft that pass through the electron-dominated outer radiation belt and MEO navigation satellites in particular pass repeatedly through the peak intensity region. As a result, these require careful design and high levels of analysis and protection. A preliminary study is generating limited 3-d modelling capability for internal charging using the GEANT-4 radiation transport code and elements of the SPIS spacecraft charging code. This first step will address the steady state case but will have limited capabilities for time-dependent solutions. For MEO navigation satellites, the steady state may never be reached in practice, due to the dynamic nature of enhancements of the belt and the extreme variations of flux along the orbit. It is proposed to extend the capability of this new tool to calculate time-dependent electric fields and currents. This will involve stabilisation of the time-stepping algorithm over a wide range of material conductivities and hence will need to handle different charging time-scales within the same simulation. Validation of the code will be required and this will be performed via experimental simulations in which dielectric structures are irradiated with high energy electrons and measurements of currents are performed. Deliverables Software Application/Need Date Navigation spacecraft in MEO (also applicable to GEO and Jovian missions), 2016 Duration (Months) 12 Estimated Current TRL Prototype Target TRL Beta Software Open Source SW Clause Reference to ESTER T-7887, T-8416, T-8688, T-7930, T-8777, T-8374, T-15, T-19, T-7637, T-8395 Code Consistency with Harmonisation TBD
TRP Reference T604-302EE Activity Title Exploitation of Giove In-Orbit Radiation Data for Environment Model and Effects Tools Update Objectives With this activity it is intended to use the experiences from GIOVE A and B to comprehensively update the methods and models used for definition of the radiation environment and the calculation of the resulting dose, internal charging and single event effects on components and systems, and to define margins. Data from all radiation monitoring, dosimetry and charging measurements, as well as experiences of the systems will be exploited. Description The Galileo precursor spacecraft, Giove-A and -B have been in service since 2005 and 2008 respectively and are still active. Both spacecraft carry radiation sensors which have been providing good quality radiation data, aimed primarily at improving the knowledge of the environment in this orbit. So far the observations have covered the declining phase of the solar cycle and solar minimum and they are current observing the rising phase which is expected to reach maximum in 2012 or 2013. Giove data already received are currently being used to validate a MEO radiation model designed for calculation of dose-related effects in the Galileo orbit. Because of the inclination of the Galileo orbit, the spacecraft pass through a range of L-shells from L=4 upwards, covering almost all the outer radiation belt to beyond the L-shell of geostationary orbit, 4 times per day. The Giove data will be used to improve on the standard L-shell dependent models that are used for dose effects (AE-8) and internal charging (Fluence Model for Internal Charging (FLUMIC)). Complementary data from the Standard Radiation Environment Monitor (SREM) on Integral, which crosses the radiation belt less frequently but with different inclination shall also be used. It has already been seen that FLUMIC is overly conservative for the Galileo orbit, and does not well describe the spectrum of severe enhancements there. AE-8 has under-predicted doses for the longer-lasting Giove-A mission so far. At the same time, the environment encountered by the missions has varied dramatically and in a way not captured in models - from a period of quasi-periodic increases linked to solar coronal holes, through an extended abnormally low flux period, to the exceptionally high flux event seen in April 2010. The output of the development will be improved dependence of energetic electron flux on location (L & lambda), and statistical models for the environment and the subsequent charging and dose effects. Deliverables Software Application/Need Date 2016 Duration (Months) 24 Estimated Current TRL Prototype Target TRL Beta Software Operational SW Clause Reference to ESTER T-7887, T-7930, T-8777, T-8374, T-9, T-10, T-15, T-19 S/W Radiation Environment Models, Monitors, Effects Tools and Test Methods (2009), Aims: 1/A2; 1/A9; 1/E1; Consistency with Harmonisation 3/A10
TRP Reference T606-301ET
Page 65 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Activity Title Navigation message Techniques and Concepts for fast Time To First Fix (TTFF) without Aiding Objectives This activity has the following objectives: 1. Analysis of Fast TTFF without terrestrial aiding 2. Analysis of RX-based techniques to improve TTFF 3. Analysis of Optimal Navigation Messages for Fast TTFF 4. Analysis of the benefits of a GEO-transmission 5. Analysis of the benefits of soft-combining techniques to improve the Navigation Message demodulation Description Today, the typical TTFF for a GPS-user or Galileo-user is 35 seconds for a Warm Start and more than 1 minute for a Cold Start. This is a major limitation for Mass Market Applications. The total TTFF can be written as the sum of TTFF_acq (the time required for acquisition and tracking of the signal), and TTFF_nav (the time required to receive and decode the full Navigation Message). As TTFF_nav constitutes the most significant part of the total TTFF, this activity shall aim at: 1. Extending the periods where reception of the Navigation Message is not required (i.e. no Cold Start required) 2. Minimizing the duration of the reception of the Navigation Message 3. Lowering the Navigation Message RX demodulation threshold, to enhance the Navigation Message reception under fading or shadowing propagation conditions Although the total TTFF can be improved by using aiding via terrestrial links (i.e. AGPS), a solution without aiding would be preferred, and only this one is targeted by this activity.
During its course, this study will cover the following subjects: 1. Techniques for RX-autonomous improved TTFF (i.e. without aiding, without improved Messages or signals) 2. Optimal Navigation Messages structure for Fast TTFF 3. Benefits of a GEO-transmission for Navigation Message distribution 4).Benefits of a satellite common message which can be soft combined by the receiver
Here below are listed examples of potential tasks:
A1. The propagation of ephemeris and/or almanac may be used to extend the validity time in the receiver. Although this concept has already been studied for GPS, the benefits when using Galileo (i.e. with better orbit and clock products) are still to be evaluated Furthermore the activity shall clarify which would be the future needs for satellite clock stability (and modelling) and user equipment clock stability (and modelling) perspective versus the different TTFF future targets A2. The Navigation Messages may be optimised to improve TTFF. For instance, the concept of multi-resolution Navigation Messages may be used: Orbit-parameters are split in a low- and high-resolution part, where the low-resolution part is broadcast frequently, leading to a fast TTFF (albeit with reduced initial positioning accuracy) A3. The use of a GEO for the transmission of Navigation Messages may be of interest, as the transmission by a GEO yields a very low Doppler, and the GEO may use a higher bit rate than used by GPS or Galileo (for the transmission of Navigation Messages) A4. Soft-combination at symbol level (before decoder) of equivalent parts of the navigation message. Preliminary studies have pointed out that that soft-combination at symbol level (before decoder) of equivalent parts of the Navigation Message can improve the demodulation threshold up to a factor of N, being N the number of parts combined. Deliverables Study Report 1. EGNOS V3 TUR 2. Galileo post-FOC TUR Application/Need Date 3. New Galileo signals 4. For bullets 2 and 3: Possible CS data content TRL5 by 2016 Duration (Months) 12 Estimated Current TRL 1 Target TRL 2
SW Clause N/A Reference to ESTER T-8380, T-8050, T-8035, T-8053, T-8055, T-8375
Consistency with Harmonisation TBD
TRP Reference T606-302ET Activity Title Development of Techniques for the calibration of Satellite-Sensor station Hardware biases in GNSS Objectives This study will develop techniques and algorithms for the off-line calibration of the GSS/satellite HW delays, affecting the code-phase and carrier-phase observables.
This activity will explore techniques for both relative and absolute calibration Description The GSS HW delays (with contributions which make them elevation and azimuth dependent) affecting the code-phase and carrier-phase observables, introduce very low frequency tracking errors (theoretical period, if tracking was continuous, equal to the satellite revisit time, which is 10 days for Galileo and 1 day for GPS) with amplitudes as high as 20 cm, which cannot be filtered efficiently by the Ground Segment Processing Facilities IPF, OSPF, MSF. These tracking errors play an important role on the performance of the above mentioned facilities, especially on the real-time integrity determination process at IPF level, and on the construction of the reference orbit and clock at MSF level. Analogously these tracking errors could play as well an important role on the performance of the EGNOS V3 processing facilities (CPF-PS, CPF-CS). The calibration of the GSS HW delays, affecting the code-phase and carrier-phase observables, can be achieved off-line, by different techniques and algorithms. Amongst these the following are envisaged: 1- Algorithms post-processing the code-phase and carrier-phase observables gathered by both a high gain antenna feeding a multi-frequency receiver, and a conventional GSS antenna. 2- Algorithms post-processing the residuals of a high performing orbit and clock determination algorithm, adequately tailored to the problem on hand
Page 66 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
(which would not be any more the orbit and clock determination), in terms of algorithms, configuration, and input data sets. 3- Others to be defined Under the (realistic) assumption of being the mentioned HW delays stable over time (1-2 cm variations over days) the calibration results would very likely be very accurate. These techniques and algorithms for calibration can be easily extended to the satellite HW delays. Amongst the contributions to the code-phase and carrier-phase hardware delays, it is found that the antenna is a relevant contributor, introducing an azimuth and elevation dependency. Therefore this activity will also explore different methods of antenna group delay measurements (e.g 3 antenna method, method by reflection with a metallic plane, etc..) under different potential test range configuration (e.g. near-field, far-field) to determine the most adequate and accurate one for the type of antenna to be tested. GSS hardware biases are particularly relevant when a station is used as reference by the system for GNSS System time scale (e.g. as in Galileo). The absolute calibration of these biases can be achieved with accuracy not much better than 1 nanosecond. (e.g. techniques developed in the frame of the Precise Time Facility in Galileo for absolute and real time monitoring of the delay by the injection of a simulated signal into the receiver). As the errors of these GSS calibration techniques imply a mismatch between different SIS channels in the order of a few decimetres, it is not possible to have a single clock set of parameters for a given satellite (these biases are lumped into the satellite clock solution by the precise orbit determination software).
During this study the following tasks will be performed: 1. To consolidate the input requirements (to be provided in the SoW) for the targeted calibration accuracy 2. To analyze different techniques and algorithms for GSS code-phase and carrier-phase HW delays calibration 3. To analyze different techniques for the calibration of the code-phase and carrier-phase HW delays (azimuth and elevation dependent) induced by the GSS antenna 4. To analyze different techniques and algorithms for S/C code-phase and carrier-phase HW delays calibration 5. To analyze different techniques for the calibration of the code-phase and carrier-phase HW delays (azimuth and elevation dependent) induced by the S/C antenna 6. To further develop the definition of the most promising techniques and algorithms out of 2) to 5) set of analyses 7. To perform a preliminary evaluation, based on real data, of the developed calibration techniques and algorithms, in particular for a: - Galileo GSS including antenna contribution - Galileo Satellite including antenna contribution - EGNOS RIMS including antenna contribution 8.To analyze the most adequate models (compromise between model number of parameters and model accuracy) for broadcasting the S/C code-phase and carrier-phase HW delays calibration results Deliverables Study Report 1. EGNOS V3, so that these techniques can be applied for the calibration of the GPS S/Cs (and EGNOS V3 RIMS) 2. Galileo post-FOC evolutions, so that these techniques can be applied for the calibration of the upgraded/not-upgraded Galileo S/Cs (and upgraded/not-upgraded Galileo GSS) Application/Need Date 3. EGNOS V3 TUR (or equivalent) 4. Galileo post-FOC TUR development upgrades TRL5 by 2016 Duration (Months) 12 Estimated Current TRL 1 Target TRL 2
SW Clause N/A Reference to ESTER T-8050, T-8033, T-8035, T-8053, T-8055, T-8161, T-8373
Consistency with Harmonisation N/A
TRP Reference T606-303ET Activity Title Signal Processing Techniques for the Integrity of Navigation for Land Users Objectives This activity will be investigating the specific issue of the provision of integrity for terrestrial users by RX digital signal processing techniques. Future systems will have to support the growing demand for more complex services. In particular Navigation systems may likely provide integrity also for terrestrial users. Numerous integrity barriers can be developed at RX digital signal processing level Description Provision of integrity in harsh terrestrial environment is very difficult due to the increasing rate of failure induced by the local effects. Analysis of these events shall be performed together with the possible countermeasure and detection mechanism in order to minimise the integrity impact maximising service availability and continuity. Ground Integrity Channel as EGNOS and GALILEO will only cover the system events so usage of local solutions is mandatory to cope with the local threats. Several options can be considered, and amongst them, techniques based on Integrity Barriers at Digital Signal Processing level (IB-DSP). The activity will: 1. Analyze the impact of challenging user environmental conditions on the tracking loops 2. Analyze (function definition and performance) IB-DSP techniques against multipath 3. Analyze (function definition and performance) IB-DSP techniques against interference 4. Analyze (function definition and performance) IB-DSP techniques against false lock 5. Analyze (function definition and performance) IB-DSP techniques against non line of sight tracking 6. Analyze the IB-DSP error distributions (including over-bounding) in controlled realistic conditions 7. For information compare the IB-DSP techniques against conventional RAIM-like techniques Deliverables Study Report 1. EGNOS V3 RIMS 2. Galileo post-FOC GRC upgrades Application/Need Date 3. EGNOS V3 TUR (or equivalent) 4. Galileo post-FOC TUR development upgrades TRL5 by 2016 Duration (Months) 12 Estimated Current TRL 1 Target TRL 2
SW Clause N/A Reference to ESTER T-8376, T-8035, T-8053, T-8055
Page 67 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Consistency with Harmonisation TBD
TRP Reference T606-304ET Activity Title Techniques for Synthetic Beam-Former for reference GS sensor stations Objectives This activity intends to study the suitability of synthetic-beam-former techniques for multipath mitigation at the G/S reference sensor stations (e.g. GSS or RIMS) Description Multipath mitigation improvement, at the G/S reference sensor stations (GSS or RIMS), via an increase of the sophistication at either RX digital processing level or at SIS definition level, has demonstrated to be quite limited in real field scenarios, once a certain level of sophistication is surpassed. This is due to the specific characteristics of the dominant multipath at the G/S reference sensor stations, and due to the later code-phase and carrier-phase observables pre-processing functions at the G/S Processing Facilities.
However spatial filtering may significantly improve the multipath mitigation, but at the expense of a visible increase of the sensor station complexity, and a visible increase of the sensor station calibration needs. ESA is currently prototyping a GNSS reference sensor station, aided by Real Beam-Forming techniques (multiple physical antennas). Alternatively spatial filtering could be attempted by Synthetic-Beam-Forming techniques (single physical antenna but with movement), what may allow to diminish the complexity inherently associated to the Real-Beam-Forming techniques, although at the expense of a certain potential degradation of its tracking performances and a certain potential degradation of the sensor station reliability.
The lower complexity of the Synthetic-Beam-Forming techniques versus the Real-Beam-Forming techniques justifies a dedicated and thorough assessment. Note that besides apparent commonalities between Synthetic and Real Beam-Forming concepts (e.g. both enable spatial filtering) the techniques are very different and not interchangeable.
Following tasks will be performed during the course of this activity: 1. To study the synthetic beam-former techniques developed in the past for other applications 2. To consolidate the conceptual definition (to be provided in the SoW) of Synthetic Beam-Formers for G/S reference sensor stations (NSS-SBF), including performance analyses for code-phase and carrier-phase tracking and acquisition, as well as performance analyses on sensor station reliability. 3. To evaluate the performance with a reduced proof of concept demonstrator Deliverables Study Report, Breadboard 1. EGNOS V3 RIMS 2. Galileo post-FOC GRC upgrades Application/Need Date 3. EGNOS V3 TUR 4. Galileo post-FOC TUR development upgrades TRL5 by 2016 Duration (Months) 12 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-8376, T-8035, T-8053, T-8055
Consistency with Harmonisation TBD
TRP Reference T606-305ET Activity Title Techniques for Robust Carrier Phase Tracking (under High Dynamic/Strong Fading/Scintillation conditions) Objectives The objectives of this activity are the study, design and simulation of techniques for robust carrier phase tracking under high dynamic/strong fading/scintillation conditions. Description Carrier phase measurements are more precise than pseudorange measurements and are used for high precision services. The quality of the carrier phase measurements influences directly the Galileo/EGNOS Ground-Segment navigation and integrity algorithms output quality, as well as the GPS/Galileo professional and mass market user positioning accuracy. Unfortunately, phase tracking can be severely stressed under ionospheric scintillation (under severe scintillation, phase may change too fast for being tracked by the receiver). Moreover, cycle slips can occur when tracking is interrupted due to blockage of the signals, or when signal fading is too intense. New and promising techniques enhancing carrier-phase tracking robustness can be envisaged, amongst them: 1. Those based on the processing of multiple signals and frequencies (>2). 1.1.The correlation of the physical phenomena at different frequencies is known. 1.2. The dynamics of the scintillation imply specific spectral characteristics of the loop the tracking signals 2- Those based on open loop estimations (algorithms which require the calculation of a branch metric which embeds an implicit estimate of the unknown parameters based on a "sliding window" of observations) The proposed activity aims at identifying promising techniques that can allow robust carrier phase tracking under high dynamic/strong fading/scintillation conditions. This study includes the study, design, simulation and validation of these techniques Deliverables Study Report 1. EGNOS V3 RIMS 2. Galileo post-FOC GRC upgrades Application/Need Date 3. EGNOS V3 TUR 4. Galileo post-FOC TUR development upgrades TRL5 by 2016
Page 68 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Duration (Months) 12 Estimated Current TRL 1 Target TRL 2
SW Clause N/A Reference to ESTER T-8376, T-8033, T-8035, T-8053, T-8055
Consistency with Harmonisation N/A
TRP Reference T606-306ET Activity Title Interference Mitigation Based on Novel Signal Processing Cancellation and RF Front End Objectives With this study it is intended to define and evaluate digital processing techniques and algorithms for interference mitigation, derived from the NBIIC, PIWIC-TD and PIWIC-TFD concepts, as well as to evaluate techniques for interference mitigation at RF FE. Description Given that a navigation signal is weak when received by a GNSS receiver on earth it can be easily interfered by other signals. Field campaigns, performed up to now, at numerous locations, have shown that the level of interference in Galileo E5 and E6 could be, quite often, significantly higher than the typical level of interference in Galileo E1. In the frame of the ESA GSP activity Interference Information Systems (IIS) several concepts for interference mitigation were proposed and preliminary assessed from a theoretical and conceptual perspective; amongst them the following: 1. Narrow-Band Interference Identification and Cancellation (NBIIC) concept 2. Pulsed-Interference Wavelets-based Identification and Cancellation (PIWIC-TD) in time domain concept 3. Pulsed-Interference Wavelets-based Identification and Cancellation (PIWIC-TFD) in time & frequency domain concept The work to end with concrete techniques and algorithms (of feasible real time implementation) for a ground sensor station from the NBIIC, PIWIC-TD and PIWIC-TFD concepts is still to be carried out. Furthermore as the characteristics of the RF FE contribute visibly to the interference rejection capabilities, the activity will asses potential new designs/techniques for the RF FE.
The aims of this activity will be: 1. To develop a detailed definition of techniques and algorithms for a ground sensor station based on the: 1.1. NBIIC concept 1.2. PIWIC-TD concept 1.3. PIWIC-TFD concept 2. To investigate potential new design/techniques for the RF-FE 3. To evaluate, via analyses and simulations, the benefits of the developed techniques and algorithms (see 1) 4. To perform, in a real scenario, a proof of concept of the developed techniques and algorithms capabilities. Deliverables Study Report 1. EGNOS V3 RIMS 2. Galileo post-FOC GRC upgrades Application/Need Date 3. EGNOS V3 TUR TRL5 by 2016 Duration (Months) 12 Estimated Current TRL 1 Target TRL 2
SW Clause N/A Reference to ESTER T-8376, T-8035, T-8053, T-8055
Consistency with Harmonisation N/A
TRP Reference T606-307ET Activity Title Adaptive Tracking Techniques for Navigation Signals Objectives The purpose of this will study techniques controlling adaptively the receiver tracking parameters, and amongst them techniques enabling: 1. Time-varying loop bandwidth settings 2. Time-varying Phase-Lock-Loop (PLL)& "Frequency-Lock-Loop (FLL) aiding" 3. Time-varying integration period, etc Description Adaptive techniques are typically used in communications receiver to cope with changing environments (multipath, fading, interference, H/W stability) but usage in GNSS Rx has been quite seldom since Rx were meant to work in the open field. The use of adaptive techniques in GNSS, has been basically reduced to: 1. Automatic Gain Control (AGC) 2. Adaptive threshold-level interference detection 3. Kalman filtering (prototype level) However other adaptive techniques have not been studied significantly. The activity will: 1. Investigate and assess (theoretically and through simulations) the benefit of adaptive techniques for filtering & tracking and acquisition (e.g. LMS, RLS, AGLRT), including the control of the loops settings, the control of the aiding amongst the PLL and FLL loops, the control of the loops integration time 2. Investigate and assess (theoretically and through simulations) the gained robustness of the adaptive techniques against in the presence of external perturbations 3. Investigate and assess (theoretically and through simulations) the benefit of channel equalisation techniques to combat fast-fading channels Deliverables Study Report
Page 69 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
1. EGNOS V3 RIMS 2. Galileo post-FOC GRC upgrades Application/Need Date 3. EGNOS V3 TUR 4. Galileo post-FOC TUR development upgrades TRL5 by 2016 Duration (Months) 12 Estimated Current TRL 1 Target TRL 2
SW Clause N/A Reference to ESTER T-8376, T-8381, T-8035, T-8053, T-8055
Consistency with Harmonisation N/A
TRP Reference T606-308ET Activity Title Techniques for High Sensitivity GNSS Receivers Objectives The objective of this study will focus on techniques for code, phase and frequency tracking, compatible for very weak GNSS signals (e.g. indoor and urban canyon environments). Description Studies on high-sensitivity Rx have already focussed on weak-signal (e.g. indoor and urban canyon environments) acquisition and very narrowband tracking but topics like discriminator design for optimal weak-signal tracking, characterisation of tracking in the vicinity of loops' threshold, and transition from acquisition to tracking for weak-signals have not been addressed sufficiently and in need of a specific study in view of the interest on the GNSS performance in difficult environments.
Within the scope of the activity, it can be found (with emphasis on GALILEO): 1- The investigation on high-sensitivity tracking techniques and characterisation of its behaviour 2- The investigation on techniques to optimize the transition from acquisition to tracking in the vicinity of the tracking loop threshold 3- The proof of concept in a single-channel demonstrator Deliverables Study Report, Breadboard 1. EGNOS V3 RIMS benefits from this activity 2. Galileo post-FOC GRC upgrades benefits from this activity Application/Need Date 3. EGNOS V3 TUR benefits from this activity 4. Galileo post-FOC TUR development upgrades benefits from this activity TRL5 by 2016 Duration (Months) 12 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-8376, T-8035, T-8053, T-8055
Consistency with Harmonisation N/A
TRP Reference T607-301EE Activity Title High Fidelity Channel Modelling for GNSS Receiver Performance Characterization Objectives Aim of the activity is to study the impact of multipath characterization on GNSS sensor station, vehicular, pedestrian, aeronautical and maritime receivers performance, considering channel complexity and limitation in the description, receiver characteristics and Signal-In-Space (SIS) properties. Analysis, synthesis and integration of models and design and development of an emulation hardware tool able to support high fidelity channel models for RFCS is part of the activity. Early mitigation techniques based on the results of the analysis shall be investigated. Description
Page 70 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
The effects of propagation impairments, in particular multipath on GNSS receivers is well known, affecting availability, accuracy and continuity of service. Initial investigations on the possibility to reduce complexity of channel models for characterizing GNSS Rx in terms of tracking and/or PVT performance has been performed for example in the "GALILEO SIS TESTING" activity.
Although promising results have been seen for the characterization of the statistics of the Rx, still limitations exist in this model reduction for characterising punctual fails (e.g. false lock due to high delay). Moreover, it is clear that multipath modelling for GNSS receivers performance can be highly dependent on receivers' characteristics and Signal-In-Space (SIS) properties and this is not addressed in the "GALILEO SIS TESTING" activity. At the same time, techniques for further studying model reduction and adaptation to hardware emulators can be foreseen based for example on second order moment of the channel and SIS/receiver properties.
Therefore, the effects of channel modelling limits (like channel length, number of taps, channel memory, etc) shall be further investigated together with SIS and Rx characteristics (like effects of the bandwidth of the SIS and of the Rx) on Rx performance characterization (code and phase and data demodulation errors). In fact, the dependency between channel model reduction/adaptation and Rx performance characterization revealed even tighter when targeting strong reduction of the complexity of the model. The capabilities and limitations of channel simulation in existing Radio Frequency Constellation Simulators shall be analysed and adapted models shall be proposed accordingly. Furthermore, a channel emulation platform compatible with RFCS signal shall be designed and developed.
Content of the activity will be: - Analysis of the impact of multipath characterization on GNSS receivers (sensor station, vehicular, pedestrian, aeronautical and maritime). - Analysis of limitations of current RFCS regarding the simulation of high fidelity channel models for GNSS receivers for ensor stations, vehicular, pedestrian, aeronautical and maritime. - Development of hardware channel emulator to be interfaced with existing RFCS able to reproduce high fidelity channels. - Characterization of the SIS in terms of Rx tracking and/or PVT performance with the new models. - Testing of existing multipath mitigation techniques and development of new potential techniques Deliverables Engineering Model 1. EGNOS V3 RIMS 2. Galileo post-FOC GRC upgrades 3. EGNOS V3 TUR Application/Need Date 4. Galileo post-FOC TUR development upgrades 5. Galileo post-FOC signal upgrades TRL5 by 2016 Duration (Months) 15 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-8376, T-8035, T-8053, T-8055, T-8033, T-8810
Consistency with Harmonisation N/A
TRP Reference T607-302EE Activity Title On-board Navigation Antenna Architectures and Technologies for Pattern Flexibility and High EIRP Objectives The aim of this activity is to investigate and trade-off antenna architecture for GALILEO advanced navigation payload satisfying the new needs for higher EIRP and reconfigurability. The activity will address architecture selection, design and breadboard of critical components of a new generation of navigation antennas. Description Challenging performances at antenna level are expected to be required to meet the overall quality of service of the Galileo system evolution. Next generation navigation payloads will need to satisfy challenging EIRP requirements and possibly reconfigurability in power and coverage (real-time evolving due to orbit dynamic), multiple-beam and multiple-frequency operation. New antenna architectures (e.g. active antennas) will be required to meet those challenging requirements. Several antenna architectures will be trade-off during the activity and the design and technology development of a new generation of antennas will be addressed. In addition to EIRP requirement, analysis of other parameters critical for navigation systems, such as phase centre and group delay stability shall be considered in the trade-off for the proposed architectures. Based on antenna architecture optimisation the requirements for all antenna sub-systems shall be derived and the critical ones will be subjected to design, breadboarding and validation activities. Deliverables Breadboard Application/Need Date GALILEO Evolutions, TRL5 by 2016 Duration (Months) 18 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-8373
Consistency with Harmonisation TBD
TRP Reference T607-303EE Improved Modeling of Short and Long Term Characteristics of Ionospheric Disturbances During Active Years of the Solar Activity Title Cycle Objectives
Page 71 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
This activity has the objective of developing ionospheric models and adapt existing ones based on experimental data measured in activities during active periods of the solar cycle (e.g. MONITOR) able to: - reproduce the effects of the ionosphere in equatorial regions (temporal/spatial gradients and ionospheric scintillations) - reproduce small-scale effects such as TIDs or depletions and other disturbances - understand better the effects of geomagnetic storms in the ionosphere - adapt to changes in geomagnetic field and solar cycle - improve prediction and forecasting capabilities for ionospheric effects - understand the effects of such effects on GNSS systems Description Extensive measurements over solar maximum will be carried out during the MONITOR activity under the GNSS Evolutions Programme and other experiments from external organisations. They will be able to provide a better insight on several processes affecting GNSS performance and they will have a proper basis for improved modelling. Such activities does not focus on a deep analysis of specific effects and the actual modelling of effects currently not considerd on average models. Also long-term characteristics shall be characterised on statistical basis. Furthermore, ionospheric climatological models uses monthly median maps of M(3000) and foF2 for ionospheric electron density and other predictions and internal analysis has indicated that such maps must be adapted to changes of geomagnetic field and solar cycle variations. The activity covers the following tasks: - Review and select relevant data from internal and external activities for the detailed characterisation of ionospheric effects (in the long and short-term). - Analyse tha data and process to remove external error contributions for the understanding of ionospheric characteristics. Compare with external data and geophysical indices. - Develop models suitable to analyse effects on GNSS systems and users. - Select datasets that reproduce effects on given scenarios, able to verify the models. - Analyse the effects on GNSS performance of the studied effects. Deliverables Test Report, Study Report Application/Need Date Galileo v2, EGNOS v3, 2016 Duration (Months) 12 Estimated Current TRL Algorithm Target TRL Prototype
SW Clause N/A Reference to ESTER T-8033
Consistency with Harmonisation TBD
TRP Reference T610-301GN Activity Title Study of Techniques for Combination of Space Geodetic Observations in the Generation of Terrestrial Reference Frame Objectives This Activity aims to investigate algorithms needed to generate a stable and highly accurate terrestrial reference frame of the Earth for precise orbit determination and for consistent analysis of data from the ESA missions over several decades. Description This Activity aims to investigate algorithms needed to generate a stable and highly accurate terrestrial reference frame of the Earth for precise orbit determination and for consistent analysis of data from the ESA missions over several decades.
The International Terrestrial Reference Frame (ITRF) is a set of points with their 3-dimensional Cartesian coordinates and velocities which realize an ideal reference system, the International Terrestrial Reference System (ITRS).
Beyond the ongoing international activities related to the generation of ITRF by various groups in Europe, based on processing of GNSS, SLR and DORIS measurements to a number of GPS, (GLONASS), (Galileo) and Earth Observation satellites, new requirements include combination of all space geodesy techniques on the observation level and inclusion of geodetic VLBI and Lunar Laser Ranging (LLR) measurements. Only consistent processing of measurements from all space geodesy techniques and combination on the observation level will provide a terrestrial reference frame of highest stability and accuracy.
There is a clear need for a stable terrestrial reference frame of the Earth to support consistent analysis of Earth Observation missions over several decades. This is especially the case for precise orbit determination of altimetry missions over several decades and consistent monitoring of sea level rise, climate change, the gravity field of the Earth, processing of SAR interferometry data, etc. On the other hand, the Galileo navigation satellite system will require accurate orbits for precise positioning in space and on the ground. The same applies to potential fundamental physics missions in the framework of the ESA Cosmic Vision and various formation flying concepts. This is only feasible if the terrestrial reference frame of the Earth is of the utmost accuracy and takes into account measurements of all space geodesy techniques: VLBI, GNSS, SLR, DORIS and LLR, taken over several decades. Inclusion of VLBI and Lunar Laser Ranging in the data processing is required in order to consistently combine the terrestrial and the celestial reference frames of the Earth. VLBI is the only space geodesy technique that directly provides geometrical information of Earth orientation, the scale of the coordinate system and precise coordinates of the ground stations. At the same time, VLBI provides a link to the equatorial coordinates of extragalactic radio sources, realizing an ideal celestial reference system, the International Celestial Reference System (ICRS). On the other hand Lunar Laser Ranging is a dynamic space geodesy technique allowing long-term combination of Earth Orientation time series, estimation of Earth orientation parameters (EOP) like precession, nutation, polar motion and UT1, and their long term effects. One of the advantages of the LLR is the possibility for precise estimation of the Earth GM constant by determining the Sun/(Earth + Moon) mass ratio. In addition, only Lunar Laser Ranging can provide accurate Lunar ephemerides, required for planned ESA Lunar missions, including landing on the Lunar surface in 2018.
This Activity aims to study LLR and VLBI processing algorithms and the optimal combination of all space geodetic measurements in the generation of terrestrial and celestial reference frames. Several different approaches need to be studied in the generation of the terrestrial reference frame including combination of normal equations from different space geodesy techniques and combination on observation level. Deliverables Study Report Application/Need Date TRL5 by 2016 Duration (Months) 20 Estimated Current TRL 1 Target TRL 2
SW Clause N/A Reference to ESTER T-8833
Page 72 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Consistency with Harmonisation N/A
TRP Reference T612-301GS Activity Title Integration of Optical Cryoresonator Components in Dilution Refrigerators. Objectives This activity aims at the integration of all clock subsystems needed for a ground cryogenic resonator optical clock, developed as part of two previous TRP activities (T612-013GS and T616-016GS) . The clock will perform at a stability of 1E-14/sqrt(Tau) or better up to 10000 seconds. In addition, another objective of the study is to test the operation of the cryogenic resonator (or even new resonator types) with dilution refrigerators. With these devices, the stability performance of the optical cryo resonator is expected to improve even further. Description During this activity, all subsystems breadboarded as part of previous activities (e.g. clock laser, cryo-components) and those procured as COTS equipment shall be integrated and tested.
In addition, the cryo resonator shall be operated in a continuous cycle dilution refrigerator. These devices are commonly used for low-temperature physics experiments and allow to reach temperatures below 2 millikelvins with the best systems. At such low temperatures, thermal expansion of some resonators (e.g. Ultra Low Expansion glass) improves significantly. As a result new resonator types can be designed and tested, potentially leading to better thermal noise floors and drifts. Deliverables Breadboard Application/Need Date TRL5 by 2016 Duration (Months) 24 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-8381
Consistency with Harmonisation activities A2 and A3 of the Frequency & Time Generation - ground
Page 73 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
7 - Generic Technologies
7 - 01 - On-board Data Systems
TRP Reference T701-305ED Activity Title SpaceWire node interface IP core Objectives Development of an Intellectual Property (IP) core for a complete SpaceWire node interface Description The SpaceWire codec IP cores offered by ESA's IP core service are widely used many projects. Other important functions of a SpaceWire interface like time counter, configuration port and hardware support for protocols have still to be designed by the user. This work requires still in depth knowledge of the SpaceWire standard which is often not the focus of a scientist developing an instrument. The SpaceWire node interface IP core shall provide an easy access to SpaceWire where all mandatory features are implemented in a standard compliant way. This configurable SpaceWire node IP core shall integrate a number of existing IP cores like the SpaceWire coded, Remote Access Memory Protocol (RMAP) IP core and complement them by adding the configuration port zero, inter port routing, time counter, scheduled traffic control, SpaceWire-D and PnP protocol support. Parameters like the number of SpaceWire links, the level of support for the different protocols in hardware and the type of on chip interface shall be easily configurable for every instantiation of this IP core. This IP core shall be prototyped and validated using a demonstrator in FPGA technology. Deliverables VHDL IP core Application/Need Date All missions/ 2015 Duration (Months) 18 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-7800
Consistency with Harmonisation TBD
TRP Reference T701-306ED Activity Title SpaceWire-D detailed specification and prototyping Objectives Produce a detailed SpaceWire-D specification to handle the Deterministic Control and Data Delivery over SpaceWire Networks Description The SpaceWire-D protocol allows to pass information over a SpaceWire network in a deterministic way defining a traffic schedule over the asynchronous network. SpaceWire-D has been proposed and investigated in the SpaceNet contract by the University of Dundee. As the next step a detailed protocol specification shall be produced, that can serve a basis for standardisation under ECSS. Deliverables Technical Specification Application/Need Date All missions. Protocol available > 2015 Duration (Months) 12 Estimated Current TRL N/A Target TRL N/A
SW Clause N/A Reference to ESTER T-8382
Activity is a continuation of AIM B of the On Board Payload Data Processing Roadmap which is not included Consistency with Harmonisation in current Roadmap but will be in the next one.
TRP Reference T701-309ED Activity Title Future Digital busses spacecraft testbench reference architecture Objectives The general objective is to provide a reference testbench to prove ECSS-E-ST-50-15 (CAN+CANOpen) and new ECSS-E-ST-50-14 (Digital sensor busses) based avionic system, that collects good practices when implementing new bus based avionic systems. The main targets are: - Taking ECSS-E50-15 as input, to implement the full protocol service in a representative flight environment. - To develop a test suite and a demonstration scenario allowing the testing of the protocol implementation. The protocol will be validated using the Integrity Verification Package (IVP) for ECSS-E50-15 can bus available at ESTEC Avionics LAB. This exercise will give confidence about the level of maturity in the protocol specification and will bring to the Space community the possibility to have a first validated protocol implementation according to the standard. Description
Page 74 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
The system shall integrate a Spacecraft Control Unit, A Payload Control Unit, A Mass Memory, plus several Remote Terminal Units (RTUs) (IO-concentrator Electronic Control Unit (ECU)). Full dual redundant Controller Area Network (CAN) bus shall be implemented, with RS-485 and International Standards Organisation (ISO) physical layers. All type of protocol stacks shall be present, in software, with ESA Intellectual Property (IP) core, and with downsized IPs. The testbench will become an all-round tool for the development, testing and analysis of entire avionic networks and individual ECUs. It will support the users (ESA, Primes, unit manufacturers) during the entire development process, from planning to startup of entire distributed systems and their individual ECUs. Its versatile functions and configuration options are intended to be used by network designers, development engineers and test engineers at various stage of development process. Its open design and widespread use areas makes it well-suited for dissemination within industry to increase know how and capabilities. The prototyping shall be implemented targeting Reference Architecture System Testbed for Avionics (RASTA) which features a LEON-based processor and CAN interfaces and has to be fully developed in C and compliant with the flight software coding rules. Deliverables Testbench Prototype The testbench shall be used for the validation of CAN based C&C systems and spacecraft and ECSS-E-ST-50-15. It will also Application/Need Date be used in support of ECSS standardization of CAN (ECSS-E-ST-50-15) and Transducer/Sensor bus (ECSS-E-ST-50-14). Duration (Months) 18 Estimated Current TRL N/A Target TRL N/A
SW Clause N/A Reference to ESTER T-7800
O7 - Digital busses spacecraft Consistency with Harmonisation Testbench
TRP Reference T701-310ED Activity Title Development of new SystemC IP models and OCP-IP sockets Objectives Enrichment of the ESA SystemC-IP catalogue with the Transaction Level Models (TLM) of the RTL IP-cores used in the Next Generation Multi-Purpose Microprocessor System-On-Chip, enabling analysis of such architecture and providing an environment for software development and optimization. In a second phase, OCP (Open Core Protocol) sockets and SPIRIT-compliant XML metadata descriptions shall be developed for all the IP models of the catalogue in order to ease IP interconnection, facilitate their reuse and interoperability with other IP models. Description On-going activities at ESA on Hw/Sw codesign mainly involve the development of SystemC Intellectual Property (IP) models, with the aim of integrating them together, enabling the simulation of the Systems-on-Chip (SoCs) currently used in the space domain (e.g. the LEON2 and LEON3 SoCs). As new SoC architectures are being developed at ESA, there is the need to accordingly enrich and maintain the catalogue of SystemC IP-models. In particular having the models of the Next Generation Multi-Purpose Microprocessor (NGMP) would allow performing explorations on its the optimal configuration for a given application set, to eventually apply small enhancements to the architecture in a second design iteration. It would also provide a flexible simulator of the NGMP to enable software development even before the hardware prototype is ready. The second part of the activity consists of the development of Open Core Protocol (OCP)-IP sockets to be added to the already existing SystemC IP-models and to the ones being developed in this contract; in addition the description of the models and of the their interfaces using Structure for Packaging, Integrating and Re-using IP within Tool-flows (SPIRIT)-compliant XML metadata shall be given. Both OCP-IP interfaces and SPIRIT descriptions are in line with the recent evolutions of the ESA Register Transfer Level (RTL) IP-core catalogue, enabling a coherent use of the models from the preliminary design phases down to hardware implementation. The activity can be divided into the following tasks: 1)Analysis of the specification and of the RTL simulation models of the Input/Output Memory Management Unit (IO/MMU), L2 cache, Memory Scrubber, and MultiProcessor-Interrupt Controller IP-cores part of the NGMP architecture. 2)Analysis and study of the modelling techniques based on the SystemC and Transaction Level Modelling (TLM) standards using the related OSCI SystemC and TLM libraries. 3)Implementation of the Transaction Level models of the IP-cores at point 1) using the OSCI SystemC and TLM libraries. 4)Study of the OCP-IP standard sockets, of the SPIRIT-compliant XML metadata, and of how they can be applied to our catalogue. 5)Development of the sockets and the XML metatada studied at 4), enhancing with them ESA SystemC IP-models catalogue. 6)Verification of the created models by using the RTL simulation models as reference for both timing and behaviour. The following outputs shall be produced: a)SystemC models of the following IP-cores: IO/MMU, L2 cache, Memory Scrubber, and MultiProcessor-Interrupt Controller. b)OCP-IP sockets for all the SystemC IP models of our catalogue, including the ones produced at point 1) c)SPIRIT-compliant XML descriptions of all the SystemC IP models of our catalogue, including the ones produced at point 1) Deliverables SystemC IP-models The output of this activity will be used to study and optimize the second iteration of the Next Generation Multipurpose Application/Need Date Microprocessor and the other SoCs (System on Chip). Duration (Months) 12 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-7796, T-7799
This activity is a follow-up on activity N1 from the Avionics Embedded Systems proposed in June 2010 ( not Consistency with Harmonisation yet endorsed by IPC)
TRP Reference T701-317ED Activity Title Microcontroller for embedded space applications: Specification and design verification Objectives The objective of the activity is to define and consolidate a detailed set of requirements for the implementation of the next generation of microcontroller device for low-end space applications and to design and develop prototypes to be validated in a laboratory environment.
Page 75 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Description As pointed out during the round table on Microprocessors for Space Applications (ADCSS09) the need for a reduced cost and highly integrated microcontroller for low-end space applications is strong. The obsolescence of the 80c51 is creating a hole not filled by the available high-end microcontrollers like the AT7913E.
This type of applications implies a reduced component price, a small and easy to be assembled low pin-count package (not BGA) and (monolithic) integration of essential system components (e.g. memory as RAM and (EE)PROM, serial I/Fs, GPIO's, PWM, ADC etc.) and a low power consumption. A key point is that well known SW development and validation tools should be easily available.
The first phase of the activity will specify high-level requirements on the microcontroller from the user's perspective. Requirements coming from current and future projects shall be identified. Potential application areas are for example Motion Control, Sensor Wireless Networks, Power Distribution Systems, Sensors Acquisition.
This will serve as input for the second phase where a detailed trade-off will be performed and detailed implementation requirements will be written.
The third phase will consist in the design and development of the microcontroller. Prototypes will be developed and validated in a laboratory environment. Deliverables Prototype Requirements Application/Need Date 2012 Duration (Months) 18 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-7891, T-7799
Consistency with Harmonisation TBD
7 - 02 - Space System Software
TRP Reference T702-305SW Activity Title Model Based Software Development Lifecycle Objectives Define a Lifecycle and develop the supporting tools for a Model Based Software Development approach for the On-Board Real-Time Software Systems. Provide for automation of the lifecycle activities in the context of heterogeneous modelling environments through Domain Specific Language(s) and tool interoperability solutions. Description Increasing complexity of Software Systems necessitates the focus on system function and behaviour, abstracting from lower-level implementation details of the programming languages. Modelling languages start to find their way into the development process, from requirements specification and system-software co-engineering, up to operations, through development and verification. Use of models increases the level of specification formality and provides a possibility for model simulation and formal analysis to verify certain aspects of the system from the early lifecycle phases. In the later phases the models can be exploited for design verification, model-based testing, and implementation (code) generation from the design-level models. Model based approach will facilitate the links of the Software Development to the Systems Engineering and Hardware-Software Co-Design.
To allow the move from the traditional software lifecycle towards a model-centric lifecycle, several tools and concepts are still missing: 1) The traditional notion of testing code moves towards testing models. Testing both models and code is seen as detrimental to the return on investment of Model Based Software Engineering. Related questions are the possibility to have model-in-the-loop validation, what is the meaning of a validation environment of a model (in particular when the model is used to subcontract software development). 2) All the tools necessary for the code management and verification (configuration management, concurrent development, metrication, verification, coverage, etc) need to be developed for models as they practically don't exist today. 3) Model Based Design must handle all the necessary elements and constraints needed throughout the full Lifecycle. The adequacy of the modelling language abstraction needs careful consideration. The auto-coding enables the automatic traceability from code to design and requirements. However some implementation issues need to be handled early in the lifecycle, shifting some aspects of Software Development to the Systems Engineering Process.
One of the main issues to be addressed is tool interoperability. It currently fragments the development process along the tool/formalism lines and prevents the effective integrated system-level analysis in the models context. A common Domain Specific Language (or limited set of languages to be selected in the activity as a support to the Harmonisation) will facilitate the resolution of the issues. Current open source initiatives such as TopCased, Opees, Specify etc shall be considered. A tool deployment and maintenance strategy shall be proposed. To automate the Model Based Lifecycle, and to keep the models consistent, the technologies of model transformation could be used, leading to translation or refinement of models within the lifecycle.
To enable the envisaged Model Based Software Lifecycle it shall be put in the context of/provide recommendations for future adaptations of existing processes and ECSS standards. It shall address the overall traceability of models (requirements to models, models to models and models to code), requirements management aspects (e.g. relationship to Doors, requirement numbering in models), model metrication (as compared to code metrication), and modelling guidelines (to optimize traceability and generated code). Deliverables Prototype Application/Need Date All projects/missions on board SW. SW operative > 2014-2015. Duration (Months) 24 Estimated Current TRL Algorithm Target TRL Prototype Open Source SW Clause Reference to ESTER T-7743, T-908, T-7660, T-7671, T-7662, T-7661, T-303, T-7667, T-7666, T-8414 Code
Page 76 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Harmo on board software 1st semester 2010 Consistency with Harmonisation Activities B6, B7, B8 of the Harmonisation Roadmap 2010 Derived from the ADCSS09 round table on model driven software engineering.
7 - 03 - Spacecraft Electrical Power
TRP Reference T703-301EP Activity Title High specifc energy Li cells based on high voltage materials Objectives The goals of the activity are: - Select high voltage cathode and suitable anode to form a cell - Characterise electrochemical system in button cells - Characterise high voltage cells with high specific energy (250Wh/kg)in 1 Ah cell - Test cells in a small battery (one string) Description To increase the specific energy (> 250Wh/kg), the cell voltage and/or cell capacity have to be increased. Many groups have been working on 5V cathodes (Several electrode materials could lead to high voltage cells). High capacity anode materials like Si composites are also interesting to increase energy. It can be combined with high voltage materials (5V materials like LiCoPO4 or spinels, doped LiMn2O4) to obtain a high specific energy cell. But 5V cathode leads to other issues like stability of the electrolytes at such high potential. Some ways to preserve the electrolytes from side reactions exist (use of additives, coating). This activity will focus on high voltage Lithium cells with high specific energy (250 Wh/kg or more). Stability of the electrochemical system against cycling, temperature, rate will be studied. Once a stable electrochemical system had been characterised and its suitability for space applications shown (by 2014), a space version of the cell will have to be developed and qualified (by 2017/2018). Deliverables Breadboard Application/Need Date All missions - 2017/2018 Duration (Months) 24 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-7810
Consistency with Harmonisation TBD
TRP Reference T703-302EP Activity Title Next Generation Solar Cells With 33% Target Efficiency Objectives Development of cost-efficient multi-junction solar cells based on semiconductor materials best suited for optimum utilization of the extraterrestrial sun light in combination with substrate release processes allowing for ultra-thin, light-weight solar cells with a very high power/mass ratio. This is essential in order to maintain European competitiveness and independence. Description The present triple junction technology is at its limit does not allow for efficiencies >30%. There are several new technical approaches to initially achieve efficiencies around 32% and in a next step 35%. For the time being all these approaches are equally promising.
There are two routes of development: • By an IMM (inverted metamorphic) growth approach. This solar cell type will be by design an ultra-thin cell requiring that a commercially attractive approach is found to arrive at a 20 micron cell. • The evolution of the classic cell build-up resulting in a solar cell of either the standard thickness (90micron – 150micron) or use an equivalent approach like for the IMM cell to arrive at an ultra-thin product (choice will be made on SG subsystem cost)
It is essential both developments are treated equally. Even if the classic cell build-up takes the lead and become a product first, in the long term the IMM technology might be required to arrive at higher efficiencies in the future. In case Europe would put all IMM development on hold, Europe might not be able to stay in the race for a commercially viable product in the future. All related patents will be in non European hands, and even if this would not be the case Europe will be confronted with a very costly recovery situation and ITAR regulations. Europe will technically not catch up with the competitors and thus will fall behind in competitiveness. So far only the Europe and US are global players in the space solar cell market, but at that time China will have entered this market segment as well.
The approach is to combine separate activities of the more classic approach and the IMM cell development to a single activity with two milestones at which it will be decided which technology has a better chance to become a commercial product first and what are the optimum development steps and technologies to focus on.
The individual structure optimization for the classic and IMM cells have to run in parallel: - Milestone 1, selection of most promising technology based on results from theoretical assessment (mainly technical risk, cost, schedule) and trial epitaxy - Milestone 2, successful refinement of processes for one technology with the possibility to switch back to alternative development route in case of unsuccessful progress.
Page 77 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Since the IMM cell requires an ultra-thin (UT) approach (20micron cell) one criteria will be the confidence in the UT technology to arrive on time with a commercially viable technical solution. The confidence in achieving the targeted initial efficiency of 32% within a predefined timescale is a further requirement for deciding on one or the other cell type. A third and also very important decision criteria is the potential of the technology/concepts to arrive in the future at efficiencies in the 35 % range. Deliverables Breadboard Application/Need Date all/TRL 6 in 2015 Duration (Months) 36 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-8812, T-8813
This activity covers and is enveloped by activities B4&B9 of the Solar Cells and Solar generators roadmap to Consistency with Harmonisation 100% and partially covers activities B7 and B10. Recent significant worldwide evolution in solar cell development required restructuring of European solar Cell development roadmap.
TRP Reference T703-306EP Activity Title Development of quantum well solar cells Objectives Fine-tuning and optimisation of multi-quantum well (MQW) solar cells especially towards EOL performance. Description In a first ESA funded TRP activity (Co. 21497) the potential benefit of incorporating multi-quantum well (MQW) into triple-junction solar cells has been successfully demonstrated. However, the design is not yet optimised. In a follow-on activity Co. 23027 (also funded under TRP budget) the optimum design shall be identified both by experiment and modelling where still fundamental understanding of the changes caused by incorporating MQW into a semiconductor structure has to be gained. This activity is then focussing on the fine-tuning of the structure also with respect to the possible trade-off between efficiency increase and radiation hardness. Deliverables Breadboard Application/Need Date All missions, >2017 Duration (Months) 18 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-8813
Consistency with Harmonisation This activity is fully enveloped by Activity B7 of the Solar Cells and Solar generators roadmap
7 - 04 - Spacecraft Environment & Effects
TRP Reference T704-301EE Activity Title Multi-scale high accuracy engineering tools for single event effects analysis in modern technologies Objectives Development and validation of key simulation capabilities for methods for modelling emerging categories of SEE in state-of-the-art micro- and nano-electronics. Actions to replace current methods and tools for SEE analysis that were established in the 1980s, and are inadequate for complex modern devices, will be executed and where possible coordinated and harmonised within Europe and elsewhere. Developments and complementary activities will be comprehensively evaluated and validated analytically and experimentally in accelerator facilities with appropriate test items. Result will be the establishment of new consistent computational tools fit for the purpose. Description Although Single Event Effects (SEE) have been known for many years to be a major source of anomalies in spacecraft, problems are multiplying because of technology evolution and the inability of analysis techniques to keep pace. New mechanisms in SEE generation are emerging, and "classical" analysis algorithms and software (such as CREME-96) are becoming rapidly outdated due to their major simplifications in the physics and in the treatment of the sensitive "bit" geometry. Expected growth in micro-and nano-scale electronics leads to the need to develop new techniques, with the added challenge to deploy them in project and industrial radiation harness assurance processes, as discussed in harmonisation. This activity will develop new algorithms and modelling methods for detailed description of charge injection by low-energy and secondary particle transport in semiconductor materials. Where necessary, processes including charge collection in deep-sub-micron devices, electron-hole pair transport in dynamic electric fields, the effects of nuclear interactions in overlayers and interconnects, and non-homogenous, complex sensitive volume geometries and sensitivities will be treated. Since the priorities will be to ensure usability in industrial and Agency software tools for SEE rate and risk analysis, and to ensure provision of necessary engineering interfaces, careful analysis of the RHA context of the tool(s) will be made to ensure cost-effective production of the necessary input parameters and data via testing, or other means. Inter-comparisons and validation will be made with embryonic next generation SEE tools (MUSCA, DESMICREX, CREME-MC, GEMAT) and with experiment. Deliverables Software Application/Need Date All ESA projects using modern microelectronic devices Duration (Months) 24 Estimated Current TRL Algorithm Target TRL Beta Software
Page 78 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Open Source SW Clause Reference to ESTER T-7888, T-8777, T-19, T-7935 Code Consistency with Harmonisation Radiation Environment Models, Monitors, Effects Tools and Test Methods: Aims 3/A4; 3/A13; 3/B13
TRP Reference T704-302EE Activity Title Improvement of energetic solar heavy ion environment models Objectives Relativistic solar protons and ions are responsible for single event and cumulated effect on all orbits. Current models have strong limitations especially regarding ion composition and energy spectra, and accessibility to low altitude, as identified by industry in harmonisation. This activity will use recent data to improve models and so address these limitations. Description Establish a reference ion data set and improve the Solar Energetic Particle Environment Modelling (SEPEM) model to include better prediction of ion composition and energy spectra, and transport across the geomagnetic field. This will include the ingestion of new data sets, the quality control and cleaning of the data (de-spiking, gap filling, saturation compensation, etc.), the interpolation to required energy values and augmentation with LET (Si, GaAs) values. A reference data set will be established along with a reference solar ion event list to allow custom Single Event Effects (SEE) analyses to be efficiently performed with adapted SEPEM tools. Deliverables Software Application/Need Date >2014 Duration (Months) 24 Estimated Current TRL Algorithm Target TRL Beta Software Operational SW Clause Reference to ESTER T-8416, T-15, T-8624 S/W consistent with harmonisation roadmap "Radiation models, monitoring, effects and test methods", in Aims Consistency with Harmonisation emphasised by industry & Eurospace as well as agencies: 1/C4; 1/D7; 1/E1; 1/E2; 1/E4; 2/A4; 2/B13
7 - 05 - Space System Control
TRP Reference T705-301EC Activity Title Estimation and Filtering techniques for space applications: Beyond the Kalman Filter Objectives The objective of this activity is to make advances in the application of innovative Estimation and Filtering Techniques for Space System Navigation. Most widely used algorithm in current industry for the purpose of Navigation is the Extended Kalman filter (EKF). The inherent shortcomings in using the EKF comes from the fundamental assumptions on the Gaussian distribution of the of random variables, time invariance and ergodicity of the random process that tolerate only mild nonlinearities. In time varying and highly nonlinear cases the EKF based navigation filters introduces large errors in the true posterior mean and covariance leading to poor performance and sometimes even to the divergence of the filter.
The objective of this activity is to investigate estimation techniques that can overcome the shortcoming in the EKF assumptions and take into account robustness issues. Candidate techniques as, Particle filtering, Unscented Kalman Filter, Nonlinear Optimal filters with Radial bases, H_inifinity based and variations thereof shall be investigated on their merits. Up to now, techniques such as mixtures of Gaussian, polynomial or particle filtering have been disregarded for space applications due mainly to their high CPU load. With the emergence of new processors, it is worth re-addressing the benefits of such approach for space applications ; approaches such as mix of Gaussians are also known to be more robust to initial uncertainties and non-linearities (both at dynamics and measurement levels) and could potentially overcome some limitations encountered in recent activities such as NPAL/PLGTF(non-linearities & anisotropy of measurement errors), or HARVD (initialization of EKF for detection due to very high initial uncertainties on canister position). Further application such as Hybrid Vision based Integrated Navigation applications that cover Space transportation, Rover, Entry Descent & Landing, rendezvous systems shall be studied. Description The activity shall review current estimation techniques employed in space industry and make a analysis in the face of improvement, new demands and functionalities related to space applications in the view of high accuracy control demands ranging from science missions, exploration and vision based control to space transportation guidance navigation and control applications.
The study shall execute the robust and high performance estimation and filtering techniques for accurate state reconstruction for hybrid integrated navigation purposes including vision based hybridisation. Integrated navigation systems are based on the fusion of observations from for example GPS (often noisy), Inertial Measurement Units (IMU), and other available sensors such as from vision and other measurement sources such as radars, lidars, laser altimeters, doppler-velocimeter. Typical absolute navigation problems (based on IMU + vision and/or altimeter and/or lidar) for landing require the "matching" with digital elevation maps (DEM) introducing non-linearities. Therefore it is important first to perform a survey of most important new theoretical developments in estimation and filtering in the view of nonlinearity, time varying effects and uncertainties is to be presented. The various candidate techniques are compared on the basis of metrics that address indicators necessary in the whole design process up to implementation.
Page 79 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
The survey resulting in candidate algorithms is then mapped onto the hybrid navigation needs for GNC space applications.
From the mapping a set of space applications benchmarks covering robust and high performance estimation needs shall be developed.
A comparative investigation shall be executed to reveal the impact on the performance, the added implications with respect to implementation and the design process. Such an activity shall also address, as part of the trade-offs, the especially investigation on CPU load of the filters for a future flight implementation.
The most promising selected estimation algorithms shall be coded and tested using simple yardstick applications.
After maturation a number of hybrid navigation test cases shall be executed for - vision based rover (slower estimation) - vision based entry descent and landing (fast estimation) - a launcher and re-entry vehicle application (fast application) - Rendezvous scenario could be also an interesting test case (slow). - the choice of the reference scenarios (among "slow" and "fast") shall be part of the activity (to be agreed by ESA)
Using developed metrics a synthesis is performed on the performance of the various hybrid navigation and estimation benchmarks. Deliverables Software Space transportation GNC/ Science / Application/Need Date Exploration and Robotic / Vision based EDL and precision landing Duration (Months) 24 Estimated Current TRL Target TRL Prototype
SW Clause N/A Reference to ESTER T-8384, T-7817
Consistency with Harmonisation TBD
TRP Reference T705-302EC Activity Title Mitigation of wheel friction torque instabilities Objectives Reduce / remove the impact of wheel friction torque instabilities on the spacecraft pointing and stability
Improved wheel performance for demanding missions Description Missions require more and more stringent stability performances, for which the performances of the reaction wheels become drivers.
A recurrent issue is the wheel friction instability, resulting in fast variations of the wheel response, which adversely affects the pointing stability.
This activity will: - examine the little understood effects of the lubrication system and environment on the stability and consistency of the delivered torque - characterise the impact of wheel instabilities on the pointing and stability - investigate solutions (at AOCS level, at wheel level, at system level, at HW or SW levels) - assess the system impact Deliverables Study Report Application/Need Date All missions. TRL5>2013 Duration (Months) 6 Estimated Current TRL 3 Target TRL 4
SW Clause N/A Reference to ESTER T-8336
Consistency with Harmonisation AOCS Sensors & Actuators 2009 - Reaction Wheels Aim A2
TRP Reference T705-303EC Activity Title Detailed FDI analysis of AOCS mode Objectives Conduct a formal FDI architecture analysis for AOCS mode and especially for safe mode and deorbitation mode. Description
Page 80 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
The activity will focus on two specific modes which are under review for general or legal purposes: safe mode and deorbitation mode. In order to maximize commonality and reuse across all future platforms, a generic safe mode appears an interesting option combining magnetic actuators and the propulsion system. It performs similarly on any orbit with any spacecraft, making the most of the advantages of both technologies. However it introduces extra complexity compared to all-magnetic safe modes. Strict observation of the 25-year deorbit deadline by new developments will require detailed understanding (and mitigation) of the failure cases which might prevent a given spacecraft from achieving the required orbit modification at the end of life. By conducting a thorough, multi-level Fault Detection and Isolation (FDI) analysis (at the equipment, function and mission levels), we can : -determine how to maximize the probability of successful deorbiting while minimizing the extra cost of adding redundancy to existing AOCS architectures or of an independent deorbit "package". -prove that the safe mode does not represent an increased risk, while it simplifies development, validation, and operations. The TRP will develop a generic multi-level FDI analysis approach for early design phases (phase 0/A) which would allow easy trade-off between various system architectures. Deliverables Study Report Application/Need Date 2015 Duration (Months) 12 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-8077
Consistency with Harmonisation TBD
TRP Reference T705-307EC Activity Title Nonlinear Propagation of Uncertainties in Space Dynamics based on Taylor Differential Algebra Objectives The objective of the activity is the implementation of a software framework that uses Taylor Differential Algebra (DA) as the main computational engine and that exploits its potentials in the field of uncertainty propagation in a generic dynamical system. This technology has enormous potential and its application is not limited to the space sector. Description Uncertainties in space trajectories are usually propagated by full nonlinear Monte Carlo simulations or by linear propagation methods. In Monte Carlo simulations, random samples are generated from the statistical distributions assumed for the uncertainties. Then, a pointwise integration of the full nonlinear dynamics is performed for each sample, followed by a statistical analysis of the results. This method is computationally intensive as it usually requires a large number of samples and pointwise integrations for the statistics to converge. Moreover, the Monte Carlo simulations need to be repeated for different initial distributions and do not provide the user with useful analytical information. In the linear approach, the covariance matrix of the initial state is propagated along the trajectory using the state transition matrix calculated by linearizing the nonlinear dynamics around the mean trajectory. This simplification makes this method less computationally intensive, but has a negative impact on accuracy for highly nonlinear systems and/or long propagation time intervals. Furthermore, this method assumes the uncertainties to be Gaussian.
The activity will consist in : 1) Review state-of-the-art and develop an European module based on Taylor Differential Algebra (DA) for application to space problems such as: high order expansion of ODE flow, Monte-Carlo simulations, solution of two point boundary value problems, uncertainty propagation, and robust design. 2) Verify and validate the efficiency of the method by computing arbitrary high order expansions of multivariable functions. This step is essential to the implementation of a DA integrator that will enable the use of DA for several space applications. 3) Implement a software framework for the propagation of uncertainty in a generic dynamical system based on Taylor DA 4) Verify and validate the efficiency of the library by applying it to a set of space-related test problems, e.g., determination of the debris footprint of a destructive re-entry, determination of the injection accuracy of a launcher, and study of a close encounter with a Near Earth Object. Deliverables Study report + software Application/Need Date All ESA missions: Monte Carlo analysis and uncertainty propagation are common to all ESA missions. Duration (Months) 12 Estimated Current TRL Target TRL Prototype
SW Clause N/A Reference to ESTER T-7817
Consistency with Harmonisation N/A
TRP Reference T705-309EC Activity Title Innovative autonomous navigation techniques Objectives Autonomous navigation techniques, more especially optical or vision-based ones, are enabling technologies for interplanetary missions that include challenging features like an autonomous detection and insertion, a high accuracy insertion, (possibly multiple) gravity assist or fly-by maneuvers, around the target body are required. Effective autonomous navigation strategies can also significantly decrease the operations cost and delta-V required for interplanetary missions and possibly low thrust orbital transfer (Earth, L2,...). The main purpose of this activity is to increase the maturity of these techniques starting from the work done previously in Europe for the Agency (AutoNav, Don Quijote, Marco Polo) as well as to expand them in order to address the complexity required by new missions like Laplace for which there is a need to performed accurate maneuvers closer to the swing-by point. Description
Page 81 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Building up on the results and achievements of the AutoNav activity and on the work done for the Don Quijote and Marco Polo studies, the present activity will increase further the TRL of optical, autonomous, interplanetary navigation. The activity shall focus on the robust design of a vision-based autonomous GNC and autonomous mission-planner, including autonomous guidance. The techniques developed will be applied to vision-based navigation, more especially in the case where successive flybys are required within short time intervals (like in Laplace). The effort will target the improvement of the end-to-end accuracy performance e.g. through the optimization of the navigation strategy based on optical beacons and planetary limbs, the use multi-head sensors to reduce thermo-elastic distortion, the possibility of multiple windowing with APS star-tracker, and the possibility to consider other beacons than optical ones. The autonomous navigation function will be integrated with the guidance function and both will be applied in particular to the mission planning of a gravity-assist mission. Innovative solutions at algorithmic and hardware levels will be investigated in order to improve the performance and reliability of the techniques proposed. Deliverables Study report and simulations Application/Need Date Exploration missions >>2015 Duration (Months) 15 Estimated Current TRL 3 Target TRL 4
SW Clause N/A Reference to ESTER T-8817
Consistency with Harmonisation TBD
7 - 06 - RF Payload and Systems
TRP Reference T706-302ET Activity Title Millilab frame contract 2011-2013 Objectives The present procurement aims to set up a contractual framework for the utilisation of the services and facilities of MilliLab in support of ESA technology programmes. Description MilliLab was established in 1995 as a joint institute between Technical Research Centre of Finland (VTT) and Technical University of Helsinki (TKK). Its main task is to establish and maintain a state-of-the-art measurement and characterisation facility for mm-wave components, circuits, and systems, and to make these services available to European companies and institutes. Deliverables Test services Application/Need Date -- Duration (Months) 3 Estimated Current TRL N/A Target TRL N/A
SW Clause N/A Reference to ESTER T-7829
Consistency with Harmonisation N/A
TRP Reference T706-303ET Activity Title Techniques for GNSS navigation at High Orbits (GEO/GTO/HEO) Objectives Study and development of the techniques (signal processing and navigation processing) for GNSS (GPS and Galileo) navigation at GEO/HEO/GTO and higher orbits. The selected techniques will be demonstrated in lab conditions by a suitable hardware/software Proof-of-Concept equipment. Description Recently, the feasibility of using GPS receivers for high orbits has been demonstrated. However, this feasibility study has also shown some significant short comings. The most important one being the low sensitivity (around 30 dBHz) of the current state-of-the-art receivers. This has lead to a lack of usable satellites (only between 2 to 5) for PVT computation and the need to use orbit propagators during long time windows. This translates into a degradation of the navigation performance especially after manoeuvres.
The techniques proposed under this activity are based on the ones being used on the Earth for GNSS indoor navigation, mainly by using high sensitivity signal processing algorithms and by using aiding data from other sensors (for example long coherent integration using FFT techniques, ultra-tight coupling kalman filter, vector tracking). Demonstration will be done in the lab environments using the ESA GNSS RF signal simulator.
This activity is a continuation of the feasibility study performed in the last year concerning the use of GNSS receivers for high orbits (see reference below). And the indoor positioning activities (DINGPOS) that developed high sensitivity receiver techniques for urban environments (see reference below). The techniques developed in DINGPOS demonstrated the possibility to track very weak GNSS signals at C/No of 10-15 dBHz, i.e. 30 dBs below the nominal values. These techniques are very interesting for GNSS navigation at high orbits and it is expected that the navigation performance will improve dramatically by applying them (the number of usable satellites is expected to raise to 4 to 7). Deliverables Technical Notes and Proof-of-Concept HW/SW Navigation for GEO/HEO/GTO and beyond (Lunar transfer). Telecom (AOCS), Earth Observation (from GEO) and Application/Need Date Exploration (Moon) > 2015. Duration (Months) 18 Estimated Current TRL 1 Target TRL 3
Page 82 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
SW Clause N/A Reference to ESTER T-7719, T-36
Consistency with Harmonisation Activity D07 in the roadmap: "On board radio navigation receivers", TEC-ETN/2007.65 Issue 2.2.
TRP Reference T706-304ET Activity Title Novel investigations in Multipactor effect in ferrites and dielectrics used in high power RF space hardware Objectives The aim of this activity to investigate and evaluate the Multipactor behaviour of non-metals used in high power RF hardware such as cables, connectors, filters, isolators, splitters, etc ... and develop a data base with secondary emission properties of this materials. Additionally, the study shall investigate the Multipactor behaviour between mixed surfaces (dielectric-metal) Description The European space industry and ESA programs lack information on RF breakdown (Multipactor) when ferrites and dielectrics are used. Present threshold margins calcuations considering these materials as “worst case metals” which, in many cases, leads to an extremely conservative safety margin with the subsequent development and qualification delta cost to industry. The study shall start with a comprehensive review of theoretical and test-data available in the literature on dielectrics and ferrites, which are used in microwave hardware such as circulators, filters, cables, connectors, amplifiers, etc … A short time and a long time characterisation of Multipactor susceptibility shall be carried out and the corresponding charts for industry reference shall be produced Frequency bands and gaps shall be carefully chosen to provide enough information to produce the susceptibility curves. A number of representative dielectric and ferrite loaded waveguide (parallel plate) test samples shall be built and tested using different surface combinations: metal-dielectric, metal-ferrite, metal A- metal B and ferrite-dielectric. Ceramic materials shall also be investigated and a data base on secondary emission created considering the subsequent aging effect. Deliverables Study Report, Test data Application/Need Date All missions, >2013 Duration (Months) 24 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-7829
Consistency with Harmonisation TBD
7 - 07 - Electromagnetic Technologies and Techniques
TRP Reference T707-303EE Activity Title Alternative approaches to radiated susceptibility testing at unit level Objectives The objective of the activity is to assess the repeatability and harmonization of set ups of different standard for radiated susceptibility testing at equipment level. This is to elaborate on alternative testing techniques to reproduce the same effects as the radiated susceptibility test. Description Radiated susceptibility (RS) standard test procedures foresee to radiate the units and their interconnecting cables by assigned radio-frequency (RF) field levels, and to monitor equipment operation in order to detect possible degradation of performance. The whole procedure is rather expensive (test site), time-consuming and inherently not-suited for low-frequency (LF) testing, due to typical limitations of anechoic chambers and antennas. Some non-space standards (e.g. RTCA DO-160F) already foresee RF susceptibility verifications by limiting the RS test to the frequency range 100 MHz - 18 GHz, while covering the lower frequency range, 100 kHz - 400 MHz, via bulk current injection (BCI). Some studies have also assessed the possibility of using cross-talking in place of RS testing. A rigorous assessment of the correlation and limitations of alternative testing techniques has not been carried out yet, which makes difficult adopting them in a conservative sector such as space, though the potential benefit does exist. The proposed, consistent with ESA EMC Technical Dossier, aims at providing such an assessment. It will in particular cover the following aspects: - theoretical study of the equivalence between E-field-to-wire coupling and at least two alternative test methods (e.g. BCI, EM clamp, crosstalk) - assess limitations and establish conditions of equivalence for bundles of cables in the frequency range 100 kHz - 1 GHz. - develop test procedure which can be implemented by industry with standard EMC instrumentation - verification by measurements. Deliverables Study Report Application/Need Date All Spacecraft, >2013 Duration (Months) 24 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-50, T-53
Consistency with Harmonisation N/A
TRP Reference T707-304EE Page 83 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Activity Title Multi-Magnetometer Methods for Magnetic Dipole Modelling Objectives Use of multiple magnetometers to reduce test time and to improve accuracy for magnetic cleanliness programmes. Description Background: The magnetic cleanliness of past or present programmes for Science and Earth Observation has been extensively based on multiple dipole modelling at unit level using so-called Mobile Coil Facilities (MCF) and at system level e.g. in the Magnetic Field Simulation Facility (German: Magnetfeldsimulationsanlage, MFSA) of IABG. These facilities use a small number of magnetometers and employ rotational measurements to obtain a magnetic signature around a unit under test. Disturbances of the ambient field during the test can require several repetitions. The rotation could be replaced by an increased number of fixed magnetometers. This could increase reproducibility and reduce measurement uncertainty while considerably reducing test time and operator expertise.
Activity: 1) Study possible multi-magnetometer setups, which reduce measurement time below 1 s to allow obtaining a "snap-shot" of the magnetic signature for a unit. Focus on optimum number of magnetometers and optimal locations for minimum uncertainty and maximum reproducibility of results. This includes consideration of combining individual magnetometers to gradiometer configurations. 2) Develop new software or adapt existing programs to solve the discrete inverse problem of finding the minimum number of magnetic sources able to cause the measured magnetic signature within an allowed uncertainty margin. 3) Build prototype facility for proof-of-concept, including a. hardware facility with magnetometers and/or gradiometers and mechanical unit support, b. automatic data acquisition system, c. modelling software based on 2) and report generator. 4) Verify with known magnetic sources like arrangements of dipole magnets, quadrupole sources and current-fed coils. Deliverables Study Report, Software, Prototype Application/Need Date Industrial competitiveness (All Spacecraft) / 2015 Duration (Months) 24 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-8822
Consistency with Harmonisation TBD
TRP Reference T707-305EE Activity Title Uncertainty Budgets for Magnetic Dipole Models Objectives Development of methods and tools for uncertainty budgets of equivalent magnetic dipole models used during development of missions with magnetic cleanliness requirements. Aim is to improve correlation with final system-level tests or mission performance, and to allow identification of critical equipment items. Description In past and present programmes for Science and Earth Observation magnetic cleanliness control during development is based on equivalent magnetic dipole models. Such models are derived from tests at unit level by fitting the field of equivalent magnetic dipoles to the measured magnetic field. The least-squares residuals describe the goodness of fit, but show only weak correlation to the real measurement uncertainty. A comprehensive assessment to identify sources of uncertainties and to quantify them is not available today. Since a system level model involves a large number of units and measurement uncertainties add up, this can cause disagreements with final system-level tests despite all efforts - as on Cluster - or with actual mission performance. The proposed activity, consistent with EMC Technical Dossier, and focusing on uncertainty budgets for equivalent magnetic dipole models, will not only bring agreement of models with final tests and mission performance but also will identify equipment with a critical uncertainty contribution already during development prior to integration.
Activity: 1) Study the current test facilities and test procedures to identify sources of uncertainties and to select appropriate statistical methods. 2) Quantify identified uncertainties by sufficiently large test series on a representative group of equipment items. 3) Combine the quantified uncertainties from different sources and derive a total uncertainty using analytical statistical methods. 4) Develop a software tool to establish an uncertainty budget and to calculate the total uncertainty. 5) Validate the software tool by independent analytical calculation. 6) Verify the total uncertainty by sufficiently large test series on a second group of representative equipment items different from the group in 2). Deliverables Software Application/Need Date All Spacecraft / 2013 Duration (Months) 18 Estimated Current TRL Algorithm Target TRL Beta Software
SW Clause N/A Reference to ESTER T-8822
Consistency with Harmonisation N/A
TRP Reference T707-306EE Activity Title ESD test method for spacecraft equipment
Page 84 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Objectives The objective of this activity is to develop a new Electrostatic Discharge (ESD) test method for space equipment with increased reproducibility and optimized cost and time efficiency based on easily accessible equipment. In addition, such a new method should be acceptable for use on flight equipment, which is not allowed at present because of the risk of latent failure. Description Two types of ESD test methods are used to qualify spacecraft equipment. The first type is derived from the IEC 61000-4-2 involves a device known as ESD gun and is mostly meant to test the immunity of equipment to human ESD. The second type was developed in the 80s by CNES and is mostly used in telecommunications industries. It is based on discharging a capacitor through a spark gap into a piece of wire tightly coupled over 20cm to one of the harness bundles of the equipment under test. The first method has shown non reproducible results and has sometimes resulted in nonconformances difficult to process. In addition, because the discharge location is undefined and poorly controlled, this has the risk of causing latent failure, which as a consequence can make the qualification problematic when the proto-flight approach is followed. The second method involves a 6kV spark gap that is actually difficult to procure, as it is an ITAR component, and would not be available in most EMC test houses.
Activity: 1) Review of the level, shape and frequency content of ESD transients indirectly coupled on a cable bundle as a result of an ESD in space (with emphasis on Medium Earth Orbit environment). 2) Review of both generators and transducers commercially available allowing to inject the defined ESD transient on a cable bundle. 3) Assembly and characterisation of the test set-up; comparison with the results given by the test method specified in the ISO and ECSS standards. 4) Investigation of the latent failure mechanisms, based on literature review and component testing. 5) Assessment of the risk of latent failure for the defined method. Deliverables Study Report, test equipment and test procedure Application/Need Date All Spacecraft, > 2015 Duration (Months) 24 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-7765, T-53
Consistency with Harmonisation TBD
TRP Reference T707-307EE Activity Title Phaseless Near Field Antenna Measurements Objectives Demonstate with critical evaluation a phaseless Near Field (NF) measurement Description Conventional Near Field measurements require coherent signal detection. This becomes increasingly difficult at sub-mm wave frequencies but it is also applicable to systems without dedicated test-ports or systems with inaccessible internal Local Oscillator (LO) sources. Efforts have been made to perform phaseless Near Field measurements (any geometry). However, further investigations in terms of accuracy and dynamic range in comparison to conventional coherent Near Field measurements are required. This study will start with the definition of test requirements for future missions at millimetre and sub-millimetre waves. A survey of the state-of-the-art of phase-less antenna measurements will then be carried out. The best approach to meet the priority requirements will be identified, simulated and validated by test. Deliverables Study Report Sub-mm wave missions, e.g. PREMIER, EJSM/Laplace; CoreH2O Application/Need Date Testing of (active) systems with internal (inaccessible) sources Duration (Months) 12 Estimated Current TRL 1 Target TRL 2
SW Clause N/A Reference to ESTER T-52
Consistency with Harmonisation No
TRP Reference T707-309EE Activity Title Ultralight reflector mesh material for very large reflector antennas Objectives To realise reliable ultralight mesh material (< 50 gram/m^2) for large reflector antennas, supported by accurate modelling and sample testing. Description
Page 85 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
The objective is the realisation of mesh material of superior Electromagnetic Quality, commensurate with space environmental requirements, to provide highly accurate antenna reflector performances for various reflector applications in various frequency domains (from UHF up to Ka band) for large-sized reflector antennas. Such mesh technology is an enabling technology with its very low mass (<50 gr/m^2). With its flexibility and properties it allows folding and a very compact stowage volume. The main objective of the activity deals with mesh realisation and modelling (EM) and its availability, manufacturing and its control and processes for realisation needed, thus securing the potential for a European source independent of other sources outside Europe. Demonstration samples with proper EM characterisation and verification for space environmental factors are part of the work to consolidate relevant EM models. Cross sectorial aspects and spin-off scenarios are to be included, with material and processes to be described. Deliverables Breadboard -1- telecommunication large reflector antennas, enabling technology -2- earth observation larger sized reflector antennasin lower band (Biomass, DesdiNY, SMAP, Cardwheel passive antennas, Application/Need Date other) -3- Enabling other reflector antennas with low stowage to deployed volume constraints. -4- Wearable antennas Duration (Months) 18 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-8798, T-8399, T-7832, T-8821, T-7855, T-7917
This activity is within the scope of AIM D of the Reflector Antennas for Telecommunications roadmap. Consistency with Harmonisation However, the proposition of new activities within this AIM to THAG was delayed.
7 - 08 - System Design & Verification
TRP Reference T708-301SW Activity Title Automated testing using ECSS-E-70-32 Test and Operations procedure language Objectives The ECSS-E-70-32A test and operations procedure language standard was published in 2006 and there is still no system fully compliant with this standard and fully adequate for being used in both AIT and Operations. The objective of this activity is to perform all pre-requisite work that is required for ensuring a successful development. Description A few systems have been prototyped/developed based on updating existing facilities but full compliance with the standard is still not achieved.
The objective of this activity is to perform all pre-requisite work that is required for ensuring a successful development of a new generation of test and operations automated procedure language and related preparation and execution environment, based and fully compliant with ECSS-E-70-32, guaranteeing: - full adequacy to AIT and operations automation needs including configuration for domain specific issues, - long-term maintainability as required by long-term missions, - adherence to ECSS-E-70-31 (monitoring and control data definition) and ECSS-E-70-32 abstractions as required in order to support extensive procedure validation and verification campaigns, operations support and components stability and evolution, etc.
The work to be performed will consist in: -identifying and specifying the components of an overall procedure preparation and execution systems including interactions with the space system monitoring and control database software; -identifying and specifying the domain specific needs and where needed, additions to , i.e. tailoring, the standard; -developing standard parsers/compilers for ECSS-E-70-32 procedures and producing feasibility reports for full compliance to the standard. Deliverables Prototype Application/Need Date All missions Duration (Months) 24 Estimated Current TRL Algorithm Target TRL Prototype Open Source SW Clause Reference to ESTER T-7557 Code The activity was not yet in the current roadmap, but in the frame of harmonisation activities has been Consistency with Harmonisation identified as useful and necessary extension from previous activities
TRP Reference T708-303TC Activity Title Calibration and Verification of micro vibration test facilities Objectives Validate the performance of various micro vibration test facilities traceable to accredited standards Description
Page 86 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Micro vibration test facilties are used to measure the dynamic characteristics of spacecraft elements in order to evaluate disturbances induced by their operation. The calibration of such facilities is challenging since a controlled six degrees of freedom, low level excitation needs to be induced on the measurement platform of the facility. This study shall - collect functional and performance requirements to be applied in order to simulate micro vibration environments representing typical specimen - identify the gaps in COTS available technology - design and develop a concept for a calibration and verification device meeting the performance requirements and able to be applied on various test facilities - investigate and compile verification and calibration procedures needed to achieve traceability to accredited standards - build a prototype to demonstrate the validity of the proposed concept and to validate the generated procedures Deliverables Prototype Application/Need Date 2012 Duration (Months) 12 Estimated Current TRL 2 Target TRL 4 Open Source SW Clause Reference to ESTER T-678, T-8336, T-1013, T-555, T-8384 Code Consistency with Harmonisation N/A
TRP Reference T708-315TC Activity Title Development of a vacuum compatible rotative dynamic seal for cryogenic liquids. Objectives For thermal vacuum testing, thermal shrouds are flushed continuously with Liquid Nitrogen. For sun simulation or any other test set-up requiring spacecraft motion (e.g. deformation or infrared measurements) those shrouds are placed onto a motion system. As a result those shrouds need to rotate with respect to their fixed supply, limiting the motion range. To overcome this limitations and to drastically reduce the design space needed, it is proposed to develop a rotative joint to be used under thermal vacuum conditions. Description The state of art of available rotatable nitrogen supplies for thermal vacuum testing is based on hose spirals. The limited allowable bending radius of the hoses, especially when they are pressurized, do not allow a compact and multi-turn solution. Therefore a new compact multi-turn rotatable Nitrogen joint shall be developed and the prototype shall be qualified under thermal vacuum conditions. Deliverables Prototype The application relates to thermal balance test facilities where a motion simulator is fitted with liquid nitrogen cooled shrouds Application/Need Date like in the ESTEC Large Space Simulator. The application is needed immediately. Duration (Months) 8 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-543
Consistency with Harmonisation N/A
7 - 09 - Mission Operations and Ground Data Systems
TRP Reference T709-302GI Activity Title High Rate Telemetry Transfer Services Objectives To determine the approach for the processing of high rate telemetry, from the demodulated bit stream up to the delivery to the final User. Description
Page 87 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
The upcoming Earth Observation and L2 missions require processing of very high rate telemetry, in the range of 50 Mbps to 1 Gbps. For such rates, the technology available in the ESA ground segment to perform TM frames decoding, storage, filing and delivery to Users shall be assessed in this Study.
An assessment shall address: 1. the operational scenario of the upcoming high data rate missions 2. various options for data structures to be processed : demodulated bit stream, encoded frames, decoded frames, decoded frames with metadata, etc 3. architecture of the existing infrastructure, with the aim of optimizing its performances 4. survey of existing products and equipment (high density storage, applications for data filing and archiving, etc) 5. survey of existing protocol standards for delivery to Users (CCSDS SLE Services, File Transfer Services, etc...)
After completion of the survey, the Study shall produce a set of recommendations for the implementation the various elements building up the ground segment infrastructure and the relevant interfaces. A "Demonstrator" shall be produced, on the basis of the design recommendations from the previous phase of the Study. This Demonstrator shall contain all the (true or simulated) elements of the ground segment infrastructure . A set of test scenarios for the Demonstrator shall be produced. The tests shall be run, and the relevant results shall be recorded in the Test Report. Deliverables beta software Application/Need Date Earth Observation Missions and Lagrange Points Missions. TRL6 in 2013 (Sentinel 4 and 5, Earth Care, Earth Explorer). Duration (Months) 8 Estimated Current TRL Prototype Target TRL Beta Software Operational SW Clause Reference to ESTER T-8411 S/W Consistency with Harmonisation N/A
TRP Reference T709-303GI Advanced Ergonomics on HCI for Satellite M&C, Problem Analysis, Design&Planning Activities and Support for Critical Activity Title Operation Phases Objectives The objectives of this study would be - to examine the suitability of recent developments in ergonomics to improve the interaction of users with the ground segment systems. - Investigate the use of large high resolution touch displays to support operational and engineering activities. In particular, routine M&C, problem analysis (e.g. spacecraft anomalies), common design activities (e.g. software engineering) and support for critical operations. - Prototyping and installation of the proposed technologies (wall-mounted high-resolution touch display, large touch displays for operators, graphic pads This will improve the interaction of users with the ground segment systems Description Typically the human computer interface used on current operational systems consists of a three headed workstation with a keyboard and mouse. During mission critical phases the flight control team and associated support personnel (who are typically distributed throughout different rooms) wear headsets and communicate over voice loops. In the event that an issue arises that requires discussion a meeting is called. This entails that the meeting participants need to leave their workstations to attend the meeting.
The objective of this study is to investigate whether the ergonomics of the current Human–computer interaction (HCI) could be improved by the use of newer technologies, in particular touch screens, and also to investigate if the replacement of the current 3 screens with 1 or 2 larger screen would improve operability. In addition there are a number of technologies that could reduce the need for physical meetings for troubleshooting. For instance the use of videoconferencing and data conferencing software often includes tools that let the user mark up the electronic whiteboard (whiteboarding is the term used to describe the placement of shared files on an on-screen "shared notebook" or "whiteboard"). much as one would with a traditional wall-mounted board. This could be combined with the use of a graphics pad to ease the production of diagrams during any discussion. Output of the study would be a demonstrator o the the next generation operational console demonstrating the use of these and other appropriate technologies.
The big advantage of large, high-resolution displays is that related information can be displayed next to each other and so it is easy for the users to get a better overview of the complete situation. The display considered for this special activity should be wall mounted (and/or desk - table adapted) and have a size of around 2,50m x 1,20m to allow 2-3 people to work at the screen at the same time. The screen should support touch interaction so that users don't have to use separate devices like mouses or keyboards to interact with the screen.
Potential application scenarios are: 1) Problem investigation for spacecraft anomalies and ground station problems: In this case applications (like SCOS or GSMC), log files, diagrams, models, etc could be displayed at the same time and the user can move windows around to display related information next to each other. Additionally, it should be possible to use electronic post-its to attach notes to windows. 2) Design & Planning Activities: Requirements Engineering and architectural design of system can benefit from large high-resolution displays because all information can be displayed on a single screen and all the details can still be visible (e.g. in case of a large UML diagram). Furthermore, for agile development processes such a screen would be very useful for sprint planning meetings as user stories could be put on electronic cards and could be easily moved around to do the planning. There are probably also applications for operational planning like allocation of ground station passes to missions, mission planning, etc. Furthermore, the use of such displays for distributed design meetings should be investigated (e.g. for CDF studies). 3) Support for critical mission scenarios: Again, the advantage is that a huge amount of information can be displayed in a single display. Users are able to move windows containing these information around and should be able to attach notes to windows. Deliverables Demonstration, No H/W procurement foreseen Application/Need Date Flight control teams and other users of the ground segment Duration (Months) 18 Estimated Current TRL 2 Target TRL 4 Operational SW Clause Reference to ESTER T-8413 S/W Consistency with Harmonisation No
Page 88 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
TRP Reference T709-304GI Activity Title State-aware user actions recorder and replayer Objectives To identify the concept and prototype a demonstrator able to record and replay user actions over a complex combination of systems as well as recording the state-related information. Further processing and mining of the collected information would be used to support incident investigation and perform more accurate regression testing. Description The Ground Segment is a complex environment where different applications have to interact. Investigations of incidents are difficult and often require reviewing many different logs produced by the different applications as well as interviews with the actors. Due to this level of complexity, the validation of the ground segment often relies on simulation campaigns where the spacecraft operations procedures are exercised. These campaigns often find errors and problems that appear when the different applications interact together and would be difficult to identify during the validation of individual applications. During previous incident investigations the need for a system to deal with this complexity has become evident. Such a system shall be able to process the events taking place in an ordered and organised manner. As spacecraft operations are driven by the users, user actions are a key ingredient and need to be recorded. In addition to this, the system must be able to record the internal state of every application that makes up the Ground Segment and relate it to user actions. The system must also be able to process and present all the recorded information in a way that can be easily understood by the operators. The study will deal with the following tasks - Identify the key elements that can provide the application state. This may involved the identification of observability requirements that would need to be implemented as part of the software - Identify and evaluate methodologies to record user actions and relate them to the application state - Identify and evaluate approaches to process and present the information. - Propose and assess methodologies (such as data mining) that can support the operators in their analysis tasks - Identify the overall architecture of the system - prototype and validate the concepts Such a system as proposed would be used not just to support incident investigation. The definition of regression test plans will benefit from the information collected. The system must therefore be able to produce test execution flows that can be used later in regression testing campaigns (either for the whole ground system or for individual elements). Deliverables Prototype Application/Need Date Any combination of complex software systems (such as the ground segment)./2014 Duration (Months) 14 Estimated Current TRL Algorithm Target TRL Prototype Operational SW Clause Reference to ESTER T-7840 S/W Consistency with Harmonisation No
TRP Reference T709-305GI Activity Title Advanced Planning & Scheduling Technology Research Objectives Objective of this activity is to further prepare the technologies initially investigated and assessed in the GSP study Advanced Planning & Scheduling Initiative (APSI) Experimental Framework (based on advanced Computer Science concepts like Artificial Intelligence and Knowledge Engineering) to be ready for a future implementation in the OPS infrastructure by an investment activity. Description Currently mission planning systems are developed from scratch or by ad-hoc reuse from an existing mission planning system if the missions concerned have sufficient overlap in requirements. The development and validation of a typical mission planning system is a costly and time consuming process which currently represents a significant risk in the development of mission ground segments, due to the criticality and operational relevance of this subsystem. In order to address this, infrastructure development has recently started on a framework (EGOS MPSF) that can be used by missions as the basis on which their planning system can be build, by providing standard functionality that can be used as is, or extended as required to meet the missions requirement.
Extremely significant aspects of a planning system that are not fully addressed by this development are the planning engine together with a modelling language to support the representation of the mission planning process. The planning engine and the planning language provide the mechanisms to achieve the specified goals within the constraints imposed by the available resources.
The above aspects entail a significant level of complexity. No known implementation provides the level of sophistication and maturity imposed by the needs of the typical missions operated by ESOC. For this reason, in the past, whilst some aspects of rules and constraints and resource availability were configurable, most of the planning intelligence was still hard coded.
Starting from the recent GSP financed Advanced Planning and Scheduling Initiative (APSI), the study will further develop and consolidate the enabling technologies for advanced planning solutions in operational environments. The project will entail the following activities: - Definition of a planning modelling language that allows the specification of constraints, rules, objective functions, metrics, etc. and how these should be applied. - Design and development of planning and scheduling algorithms structured into a library - Study the mechanism of porting or transferring the study results (bullet 1 and 2) into the EGOS MPSF via plug-in interface (in preparation for future infrastructure implementation) - Validation of the implemented language and benchmarking of algorithms with ESA missions use cases
The expected results of this study are the following: - A Planning Modelling language to enable Advanced Modelling Capabilities by representing the different aspects of space planning, including domain representation and problem description. The language should be flexible enough to support the complex needs of planning multiple spacecraft and resources.
Page 89 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
- A Library of planning and scheduling algorithms. Its objective is to identify, implement, and integrate a library of generic planners and/or schedulers that can be (re-)used for solving P&S problems. - A demonstration of how example of the first two output could be exploited, as plug-in elements, by the EGOS MPSF Deliverables Prototype Application/Need Date ESOC Missions to be launched after 2014 Duration (Months) 24 Estimated Current TRL Algorithm Target TRL Prototype Operational SW Clause Reference to ESTER T-8410 S/W Consistency with Harmonisation No
TRP Reference T709-307GI Activity Title Annotation of spacecraft telemetry and exploitation by Web 2.0 like applications Objectives The objective is to prototype a system which allows engineers to easily annotate spacecraft data with a higher level of comments, questions, event tags, multimedia links etc. It should allow sophisticated search, allow users to easily share a personal view of the data with members of different groups and allow them to interact (if desired) as a community. Description More and more spacecraft are being operated in a fleet or "family" mode. This means a group of people share responsibility for operating more than one satellite simultaneously. There is little support from the control or offline analysis systems for this way of working. Every good engineer knows his data is the central pillar of his job. This is presently bare - any information the engineer may derive from this data is kept somewhere else or just forgotten. We must remember that negative results i.e. "I looked at this and it is OK, are sometimes just as important as positive ones. Negative results are often just forgotten. The first step to collaboration (and this means across time as well as across a group of people) is to allow engineers to annotate the data they are dealing with and then to keep this information with the data. In order to increase the usefulness of this process it is proposed to borrow from some concepts in Web 2.0 applications such as sophisticated search and collaborative features i.e. allow users to create their own view on the data and to share this with other users in dynamic groups Deliverables Prototype Application/Need Date All ESA missions from 2014 Duration (Months) 12 Estimated Current TRL N/A Target TRL Prototype Operational SW Clause Reference to ESTER T-7843 S/W Consistency with Harmonisation No
TRP Reference T709-308GI Activity Title Automatic Behaviour Detection and Interpretation from low Level Data Sets such as Telemetry Objectives Operations engineers monitor spacecraft health by either 1.Looking at the evolution of various telemetry parameters on graphs or 2.Being triggered by automatic detection of limit transitions
In the first case, engineers interpret the graphs, classify the behaviour and assess if it is according to expectations. Expert knowledge is needed to do this (without the expert, the data has no meaning) and this is not easily transferred or replicated at the moment. Spacecraft are also producing more and more telemetry parameters (up to 60,000) so it is becoming impossible for engineers to monitor the whole data set in this way. The engineers would have to spend all their time looking for behaviour changes rather than investigating them. Therefore a brutal selection process has to take place and the chances of missing something important are increased.
The second case (limit transition detection) is sufficient for signalling major anomalies but not for picking up more subtle behaviour changes or transients. Subtle changes or transients can often be signs of component aging or signal other effects that can be operationally useful, such as changes in performance or environment. Our present reliance on limit checks means small changes are missed and with increasing parameter numbers this will get worse.
The objective of this study is to solve these two problems with a system that can analyse historical telemetry and determine different behaviour classes for each parameter.
This will be used to automatically signal new behaviour. The engineer can then decide on the operational significance of the difference. This system will then be expanded to one in which the engineers can teach the system whether these differences signal interesting and not interesting behaviour i.e. knowledge transfer. This can then be used to automatically annotate historical data or suggest behaviour modes for recently ingested telemetry.
The system will use three stages: data preparation, correlation and classification. Each stage will build on research work already performed at ESOC in this area, especially the underlying principles surrounding the Dr MUST development. DrMUST can already perform pattern matching and perform correlation analysis. An added value of this activity would be to expand DrMUST's capabilities to automatically monitor the behaviours found by DrMUST and when they happen synthesise their meaning.
The project will entail the following activities: - Elicitation and formalization of User Requirements of an Automatic Behaviour Detection and Interpretation (ABDI) system - Identification, evaluation and selection of enabling technologies for ABDI
Page 90 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
- Spiral prototyping implementation & evaluation on ESA provided Use Cases - Requirements Consolidation, Assessment and Follow-on Description There is already a large body of academic research on finding unusual sequences in time series. These all work by classifying past behaviours and so can be directly used. Search algorithms combined with pre-processing and correlation techniques will be brought to bear on the control centre problem. The system will be developed and tested using housekeeping data stored at ESOC for real missions.
In the first phase only the housekeeping data itself will be used and the system will require an absolute minimum of pre-knowledge regarding the spacecraft itself or help from the engineers. The objective is to produce a system which can detect "never seen before" spacecraft behaviour automatically. It will be plug and play i.e. it can be applied to a new dataset without the need for re-training.
In the second phase, engineers will be asked to feed back into the system declaring specific behaviours normal or anomalous and so they can be classed in the future. This concept allows engineers to teach a system what data behaviours characterize certain spacecraft status. This way, from this point onwards, engineers do not need to re-interpret this behaviour from the data again. The system would provide them with this interpretation [from data to information] so that they can decide if the spacecraft is behaving according to expectations. In addition, has the advantage of letting engineers from other missions know what a certain spacecraft is doing even if they are not familiar with which parameter evolutions characterize specific spacecraft behaviours.
The expected results of this study are the following:
- Consolidated set of User Requirements for ABDI system - TN on Enabling technology assessment - Validated set of algorithms - Pre-operational prototypes for extended operational validation - Final report with assessment and follow-on Deliverables Prototype Application/Need Date Missions in the 2014 - 2020 period Duration (Months) 18 Estimated Current TRL N/A Target TRL Prototype Operational SW Clause Reference to ESTER T-95 S/W Consistency with Harmonisation N/A
7 - 10 - Flight Dynamics and GNSS
TRP Reference T710-302GN Activity Title GNSS Service for the Onboard Real-Time Precise Orbit Determination Objectives This Activity aims to develop capability in the onboard real-time high precision orbit determination using GNSS. Description A need for the high-precision onboard orbit determination of near Earth orbiting satellites based on GNSS data has been clearly identified. Achievable accuracies for different scenarios shall be studied, and there is a clear potential for decimetre or even sub-decimetre accuracy in real time, especially when combined with a service for dissemination of real-time high-precision GNSS data which the Navigation Support Office can provide.
Based on the precise GNSS satellite orbit and clock parameters, the LEO orbit can be estimated directly onboard the satellite and with an accuracy level required by the most of the LEO missions.
Beyond the ongoing developments and activities related to ultra-rapid and real-time estimation of the GNSS satellite orbit and clock parameters, this activity requires development of a dedicated software and a service for the real-time onboard precise orbit determination of LEO satellites and dissemination of the real-time GNSS products to LEO orbit.
Deliverables Study Report Application/Need Date 2012 Duration (Months) 24 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-8831
Consistency with Harmonisation No
7 - 11 - Space Debris
Page 91 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
TRP Reference T711-301GR Activity Title Streak detection and astrometric reduction Objectives This study shall formulate and discuss suitable approaches for the detection and astrometric reduction of linear and curved streaks for challenging ground-based and space-based observation strategies, and shall develop and evaluate prototype software implementations. Description Detection and astrometric reduction of streaks is required by the Space Debris Office to provide space debris-related services, such as the improvement and validation of space debris environment models through the acquisition of optical observations of objects in high altitudes. Streak detection and astrometric reduction may also become relevant in the scope of SSA, in particular for the processing of optical observations acquired to build-up and maintain a catalogue of orbital elements, or for processing observations of NEOs. To meet the objectives, 3 tasks shall be performed: 1) Review of known theoretical approaches for streak detection, and review of potential implementations existing so far 2) Formulation and evaluation of candidate algorithms 3) Prototype implementation, performance demonstration and test If the study is successful, i.e. if an algorithm for streak detection and astrometric reduction of low-SNR objects in optical observations to objects in Earth orbits can be found, and a prototype implementation of this algorithm has proven the feasibility for the application to observations of objects in lower altitudes or to space-based optical observations, a dedicated test campaign shall be initiated using either modified existing optical sensors or by then newly available optical survey and tracking means, both operating according to the currently developed optical observation strategies. This test campaign shall be co-ordinated with the SSA Program in order to further study the contribution of the obtained data to SSA tasks. The test campaign may be introduced by ESA to the Inter-Agency Space Debris Coordination Committee (IADC), which would open the contribution of a new class of measurements to the internationally co-ordinated efforts to better understand and model the space debris environment around Earth. Deliverables Prototype Application/Need Date SD services for all missions, TRL6 for 2013 Duration (Months) 12 Estimated Current TRL Algorithm Target TRL Prototype Operational SW Clause Reference to ESTER T-1093 S/W Consistency with Harmonisation N/A
TRP Reference T711-302GR Improvements of space object observation strategies and processing techniques through using silicon-based hybrid CMOS Activity Title detectors Objectives Collection of information and in-depth analysis of commercially available hybrid CMOS detector technology, in particular in terms of benefits for ground-based and space-based optical observation strategies in the visible wavelengths. Special focus shall be on simulating image processing and orbit determination according to already proposed ground-based and space-based survey-only observation strategies that were found challenging using CCD detector technology. Description The goal of this study is to 1) Collect information on this new sensor technology and to carefully assess the accessibility for European customers. After that commercially available sensors shall be analysed in-depth, in particular for optical observations of earth satellites in the visible wavelengths. 2) Analyse how the already applied (and for SSA the proposed) optical observation strategies may benefit from the availability of hybrid sensor technology. This analysis shall cover both, ground-based and space-based observations (observation scenarios as, for example, proposed by Ref 1-4) and address sensitivity limits and coverage of a given reference population of objects in orbit. Special attention shall be paid to survey-only observation strategies that were always found to suffer from existing sensor duty cycles heavily, and to the implementation of "fences" covering regimes of faster moving objects, such as MEO. Covering orbital regimes with "fences" leads to only an often insufficient number of single object detections, even for telescopes with reasonably large field-of-view diameters. The fence dimension had to be kept to a minimal width, lowering the performance of the observation strategy. The analysis shall also include simulations on the gain or losses in orbit determination accuracy that may result from changes in the pixel scale, astrometric accuracy and epoch registration accuracy by a simulation of the identified improved observation strategies. The Space Debris Office requires improvements of optical observation techniques for its space debris-related services, such as the improvement and validation of space debris environment models. Improvements in observation techniques, as well as new observation capabilities, may allow observing other orbital regimes or so-far inaccessible classes of objects by optical means. Additionally, the preliminary SSA sensor architecture shall be considered in this activity, as for SSA optical means are foreseen for observing objects in high altitudes, and for observing NEOs. Deliverables Study Report Application/Need Date SD services for all missions, TRL 6 for 2013 Duration (Months) 12 Estimated Current TRL 1 Target TRL 2
SW Clause N/A Reference to ESTER T-1093
Consistency with Harmonisation N/A
7 - 12 - Ground Station System & Networking
Page 92 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
TRP Reference T712-301GS Activity Title Next generation very low noise cryogenic amplifiers in K/Ka (26-34 Ghz) band Objectives The main objective of the activity is to develop new transistor technology in order to decrease the receiver noise in K/Ka band. Description Lagrange point and deep space mission in K/Ka band will require high data rate and optimised G/T. The thermal noise of the current cryogenic receiver is limited to 20K with the current InP technology. The use of new material such as InAs will allow to increase the indium content in the transistor channel and increase the electron mobility. The increase of the electron mobility will improve the gain and the noise of the device at high frequency. The study shall cover the following aspects: - establish the suitability of emerging new materials, such as InAs, InAlAs and others - select the best material suited for the manufacturing low noise cryogenic transistors - produce experimental batches of such transistors - produce some breadboards of cryocooled LNAs, to assess the obtainable performance Deliverables Prototype > 2016 Application/Need Date Future scientific and exploration missions (downlink) Interoperability with NASA, JAXA, Russia, China Duration (Months) 24 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-1263, T-7656
Consistency with Harmonisation N/A
TRP Reference T712-302GS Activity Title Ka-Band 100 W Solid State Power Amplifier (SSPA) Objectives The objective of this study is to develop a solid state amplifier suitable for Ka-band (34.3-34.7 GHz) uplink from ESTRACK Deep Space stations. This amplifier will be either used as stand alone or as a building block for reaching higher Equivalent isotropically radiated power (EIRP) levels. The design shall be cost efficient and provide higher reliability and lifetime than currently available vacuum tube solutions. Description Power amplifiers for Ka-band frequency range are either based on vacuum tubes (reaching several hundreds of W) or solid state technology (reaching few tens of W, in the telecom band). Missions like Bepi Colombo (Radio Science Experiment) and Juno have recently shown that a power amplifier in the range of 50-100 W, installed in ESTRACK Deep Space stations, could satisfy their needs of EIRP. Future missions will require higher Equivalent isotropically radiated power (EIRP) levels. However no SSPA exist on the market, reaching such power level today. Moreover, the time stability requirements coming from Radio Science applications are presently not met. In order to develop the proposed SSPA, the two following steps are foreseen: 1) Analyze the present status of materials and technologies for High RF power amplification and combination available at Ka Band. 2) Develop a Ka Band High power amplifier of 100 Watts. The design shall be of high reliability and cost efficient on production and maintenance. Particular attention shall be given to thermal and material aspects, device physics and selection, verification and testing of ESA specific needs (e.g. high stability). Concerning device selection, European (i.e. ITAR free) suppliers will be identified. Deliverables Breadboard > 2016
Application/Need Date Future scientific and exploration missions (uplink) Radio science experiments Interoperability with NASA, China Duration (Months) 18 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-1264, T-8838
Consistency with Harmonisation TBD
TRP Reference T712-303GS Activity Title Coupled enhanced Turbo codes demodulator and decoder Objectives The goal of this study will be to identify and evaluate possible algorithms to allow ESA telemetry receivers to operate and acquire in the areas of extremely low symbol to noise ratio (Es/No), below - 9 dB, as well as at higher signal levels. This is required by planned and future scientific/exploration missions using Turbo coding. An additional goal of this activity would be to improve the BER/FER performance of the Turbo decoding algorithms, especially in the error floor region, by two orders of magnitude. Moreover, from preliminary investigations, a slight improvement in the waterfall area could also be achieved. This would bring the performance of the Turbo decoder in the same region as the LDPC. One algorithm will be selected after thorough Matlab simulation and a breadboard of a receiver implementing that algorithm will be produced, allowing a complete characterisation of its performance.
Page 93 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Description Turbo codes, to be used by Bepi-Colombo, EXOMARS and future planetary missions for its telemetry, require the receiver to be able to lock to a signal with an extremely low symbol to noise ratio (Es/No), because these families of codes are able to work at low EbNo, and also because coding rates of down to 1/4 and 1/6 will be used. In Bepi-Colombo and EXOMARS, being the data rate requirements quite high and the Es/No very low, the signal at the input of the demodulator will be very weak. Using standard demodulation techniques will not work at this low Es/No, because there is a significant difficulty to have a reliable lock indication, even after correct acquisition. For instance, the current ESTRACK standard demodulator (IFMS) reaches reliable lock indication down to -2 dB of Es/No. Since the error-correction codes operate at very low symbol signal-to-noise ratios (Es/No as low as -8dB), there is the need for synchronization schemes e.g. carrier, subcarrier, symbol, etc. that operate efficiently in this scenario, so that loop lock can be detected reliably. Some studies [1] & [2] have been made on techniques for joint demodulation and decoding , but its applicability to the Turbo codes and the modulation schemes used in ECSS standard, has not been assessed.
Moreover Turbo codes' performance strongly depends on Eb/N0. In particular, two different regions of interest can be clearly identified; the waterfall area and the error floor area. The first area corresponds to low-medium and medium Eb/N0 values. In this region, the slope is very steep, almost vertical; as a consequence, a very small increment in Eb/N0 causes a big reduction on BER/FER (BER (Bit Error Rate) - FER (Frame Error Rate)) values. The second region though, corresponds to high Eb/N0 values. Here the slope is flatter and even a big increment on Eb/N0 provides a very limited improvement on BER/FER. The algorithm to be studied would improve the behaviour of the turbo decoder in the error floor region by two orders of magnitude, so that they can be used in a wider range of missions together with a slight improvement in the waterfall region. This would bring the performance of the Turbo decoder in the same region as the low-density parity-check (LDPC) decoders. It is expected that the operational region in Bepi-Colombo and EXOMARS would be in the floor area, making this development extremely useful.
The possibility to extend the study algorithm to LDPC decoders domain will also be analysed.
The study will be split in 6 activities: 1- Consolidation of requirements for a coupled receiver-decoder and enhanced Turbo decoder 2- Investigation on suitable algorithms and architectures 3.a- Simulation and selection of one algorithm and architecture for the coupled decoder and modulator. 3.b - Simulation of enhanced Turbo decoder and comparison with current approach 4- Run simulations in VHDL code and compare with C/MatLab results. 5- Incorporate the FPGA design in an commercial standard FPGA platform to produce a breadboard of the CODEC and the enhanced Turbo decoder 6- Validation of breadboard with respect to the initial requirements.
[1] J. Hamkins and D. Divsalar. Coupled receiver-decoders for low rate turbo codes. in Proc. IEEE Int. Symp. Inf. Theory (ISIT), Jun 2003. P. 381 [2] M.K. Simon et al. Information-reduced carrier synchronisation of BPSK and QPSK using soft decision feedback. In Proc 44th Allerton Con. Comm. Contr. Comput. Sept. 2006. Deliverables Breadboard > 2014 Application/Need Date All ESA scientific missions using turbo codes (L2, planetary, exploration). Interoperability with USA, Japan, Russia. Duration (Months) 18 Estimated Current TRL 1 Target TRL 3 Operational SW Clause Reference to ESTER T-1227 S/W Consistency with Harmonisation N/A
TRP Reference T712-304GS Breadboard of simultaneous ranging and high rate telemetry transmission for band-efficient suppressed carrier modulation Activity Title schemes Objectives The objective of this activity is to be able to transmit high data rate suppressed carrier telemetry while performing pseudo-noise ranging, which is currently not possible e.g. for GAIA. The loss in performance is expected to be negligible, thus higher efficiently in satellite operations can be achieved. Moreover, simplification in satellite transponder is achieved (no need of remanent carrier mode) Description CCSDS is preparing simultaneous transmission of high rate telemetry and ranging signals. Up to now, this is not possible and therefore, transponders for this kind of missions have two modes of operations, one for high rate suppressed carrier telemetry (TM) and one for lower rate TM transmitted with ranging and a residual carrier whenever ranging is to be performed. Since the latter has a very poor bandwidth efficiency, two new modes are considered at CCSDS to allow for simultaneous transmission of high rate TM and ranging signals: 1. Gaussian Minimum Shift Keying (GMSK) telemetry with the ranging signal added as a small delta phase. 2. Unbalanced Quadrature Phase-Shift Keying (UQPSK) with the TM on the I-channel and the ranging (with less power) on the Q-channel. The goal of this TRP activity is suggested to be in two steps. First step, implement an end-to-end system simulator (f.i. in Matlab) with simultaneous telemetry and ranging based on the CCSDS proposal to modulate the ranging onto the GMSK/UQPSK telemetry signal. With this simulator the overall system performance can be evaluated. Second step: build up a hardware demonstrator (breadboard) to further analyse the system performance and identify possible problems with the suggested schemes and their implementation into operational hardware, possibly into COTS elements. Deliverables Breadboard >2016 Application/Need Date L2 Missions, Exploration missions Duration (Months) 14 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-1227
Consistency with Harmonisation Activity B5 of the TT&C Transponders and Payload Data Transmitters Roadmap
Page 94 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
7 - 13 - Automation , Telepresence & Robotics
TRP Reference T713-301MM Activity Title Real-time Dynamic Library for Space Robot Control Objectives Development of a software library to support dynamic-aware control of space robots. The library shall allow to address in real-time change of dynamic parameters, change of kinematics chain, multiple contacts. Description Dynamics aware control is being increasingly used in industrial robotics, where the traditional control schemes could not cope with the ever increasing speeds required by industrial automation. In space, dynamics aware control will allow to cope with the typical problems a robotic servicer may experience when operating on free-floating spacecrafts. The activity shall: 1) evaluate state-of-the-art in the subject of RT Dynamics for robot control 2) define requirements for the library 3) perform architectural design and define demonstration scenarios 4) detail-design and coding of the library 5) test and demonstration
Deliverables Software Application/Need Date Satellite servicing missions, Advanced robot systems on ISS, >2016 Duration (Months) 24 Estimated Current TRL 1 Target TRL 3 Operational SW Clause Reference to ESTER T-939, T-4, T-871, T-3, T-8938 S/W Consistency with Harmonisation Activity A5 from the Automation and Robotics roadmap
7 - 14 - Life & Physical Sciences
TRP Reference T714-301MM Activity Title Low mass/power high leak tightness flow controller Objectives Improvement and development of miniaturised valves actuator assemblies for instrumentation and s/c systems Description Small valves are needed in instruments and subsystems handling gas flows. This is of particular importance for low resource and long duration missions (small satellites, long duration interplanetary missions) where leak budgets have an immediate effect on instrument/system mass. Small commercial valves with are already available but reach at this time leakage rates of about 10^-5cc/s He or less. Lower leak rates at lower mass and actuation power are required, maintaining high reliability for instance to meet stringent engineering requirements for currently planned missions This will become even more stringent for long duration missions. Deliverables Engineering Model Application/Need Date 2011 Duration (Months) 12 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-8906
Consistency with Harmonisation N/A
TRP Reference T714-302MM Activity Title Experimental evaluation of Contamination contact transfer Objectives Contamination transport from mechanical components and structures to scientific samples in exploration experiments is not yet well understood. Investigations are needed to characterise the transport mechanisms as a function of materials, surface properties, chemical and physical and eventually biological properties of contaminants.
Page 95 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Description Contamination transfer can be influenced by many parameters. Contaminants can be transported by several mechanisms, like outgassing, offgassing, contact, saltation etc. To validate complex models and to quantify effective transfer rates, experimental validation of these models is necessary. For this it is proposed to conduct experiments in a well defined environment with well characterised sample and surface properties, geometries etc. and to devise mitigation strategies by proposing e.g. appropriate engineering measures to limit the contamination transfer. Deliverables Study Report Application/Need Date 2011/2012 Duration (Months) 15 Estimated Current TRL N/A Target TRL N/A
SW Clause N/A Reference to ESTER T-8637, T-8392, T-8907, T-8946
Consistency with Harmonisation N/A
7 - 15 - Mechanisms & Tribology
TRP Reference T715-301MS Activity Title ESTL R&D frame contract 2011-2013 Objectives The subject of the present proposal is the funding of the 2011-2013 R&D part of the continuation of the ESTL activities during the period 2011-2015. Description The objective is to engage in theoretical analysis, experimental investigations and long and short-term testing in the field of tribology of mechanisms for use in a space environment. Deliverables Test services Application/Need Date -- Duration (Months) 36 Estimated Current TRL N/A Target TRL N/A
SW Clause N/A Reference to ESTER T-7846
Consistency with Harmonisation N/A
TRP Reference T715-302MS Activity Title Surface Treatment prior to Tribo-Coating Objectives The adhesion of tribological dry coatings to the substrate material is an essential parameter which determines to a large degree their lifetime capability. It is currently not clear what would be the optimum preconditioning of the surfaces. Target tribological coatings comprise e.g. sputtered MoS2 or ion plated Lead, or spray bonded poly-tetrafluoroethylene (PTFE). The surface preconditioning shall be investigated for the most commonly used substrate material alloys of Stainless Steel, Aluminium, and Titanium. The use and optimisation of intermediate non-metallic layers for Aluminium and Titanium alloys (e.g. Keronite, Hard-Anodizing, TiB2, CoBlast...) shall be investigated as well within this activity. Part of this activity shall also be to find the best suitable adhesion test procedure. Description A family of substrate materials shall be determined which has the highest use in space mechanisms. The preconditioning for Steel shall investigate treatments like passivation, activation, cleaning, electro polishing, or hardening, or a combination of these. The preconditioning for Aluminium and Titanium alloys shall investigate the different anodic or galvanic coatings available for space use, with an focus on the optimisation of hard and non-metallic coatings for Titanium alloys (density increase and porosity reduction of Keronite, for example). Available coating and test facilities at the ESA testhouses ESTL/ESR in the UK and AIT in Austria shall be used. Deliverables Study Report Application/Need Date all missions requiring mechanisms with dry lubrication. Duration (Months) 18 Estimated Current TRL 3 Target TRL 4
SW Clause N/A Reference to ESTER T-7846
Consistency with Harmonisation N/A
TRP Reference T715-303MS Activity Title Development of European lubricants for space mechanisms Objectives
Page 96 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
The objective of this activity is to develop, manufacture, characterise and validate European lubricants suitable for space mechanisms. Description European manufacturers of space mechanisms are highly reliant on space-approved fluids which are sourced outside Europe. In particular, cyclopentane oils - such as Nye 2001a - are routinely used in European spacecraft but are manufactured solely in the USA. As such, any political/economic action preventing their export, even if only of a temporary nature, could have important consequences on the ability of ESA-member states to produce fluid-lubricated mechanisms for space applications.
Previously ESTL surveyed European-sourced fluid lubricants with potential for use in space mechanism applications (ESA-ESTL-TM-0021) and no European equivalent of Nye 2001a (a multiply alkylated cyclopentane oil) was identified.
Therefore, the purpose of the proposed activity will be to develop an European synthetic hydrocarbon oil suitable for use in space applications. This oil will have to have the ability to be formulated as a space compatible grease.
The intended activity will consist of the following tasks: -Preparation of requirements specification, -Review and survey of relevant chemical compounds, materials, technologies and facilities, -Trade-off and definition of the candidate oils, -Definition of manufacturing specifications, processes and procedures, -Formulation of the most promising candidates, -Evaluation of rheological and tribological properties, -In-situ testing of the selected oils,
At least 4 different oil formulations shall be fully developed and tested.
Should the developed oil(s) be found acceptable for space mechanisms, then a follow on activity will consist of formulation a space compatible grease. Deliverables Study Report All future mechanisms with long life / high duty cycle requirements Application/Need Date > 2014 Duration (Months) 12 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-7846
Consistent with SADM harmonisation 2008 Consistency with Harmonisation Activity HRM_F03
7 - 16 - Optics
TRP Reference T716-301MM Activity Title Feasibility of Diffraction Gratings on Freeform surfaces Objectives The objective of the activity is the study and experimental verification of the feasibility of gratings machined on freeform surfaces. Description Gratings are frequently used in optical instruments, e.g. spectrometers. Various production methods are available like etching using a hologram and ruling on high precision latches. Most techniques are typically used for a more or less symmetrical shape of the surface with the grating lines, like flat, cylindrical or spherical surfaces. The aim of the activity is to evaluate the feasibility of cost effective techniques for gratings not only limited to symmetrical surface shapes but also to be implanted on so called freeform surfaces. Furthermore there is a growing need to accurately specify the shape of the lines (or grooves) in order to optimize the efficiency and wavelength positioning of the diffracted light. A possible solution could imply the use of high accuracy single point diamond turning machines. Alternative solutions could be based on holographic techniques. The availability for designers of this freeform grating production technique enables a more compact design of optical configurations and may reduce the number of components in a design, resulting in lower weights and costs of optical instruments. For the proposed optimisation a study needs to be conducted with theoretical and experimental investigations. The study shall include a survey of different manufacturing techniques. A baseline method shall be identified based on at least the following criteria: - Possibility to use freeform surfaces as grating substrates - Possibility to generate arbitrary groove curves - Costs and reliability of the manufacturing process - Grating straylight - Grating efficiency After selection, the proposed technique shall be used to produce a grating prototype. Deliverables Study report, Grating prototype Application/Need Date Earth observation, planetary exploration, astronomy > 2013 Duration (Months) 12 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-8444, T-8442
Page 97 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Consistency with Harmonisation No
TRP Reference T716-302MM Activity Title High-precision manufacturing of optical thin-films by Atomic Layer Deposition Objectives The objective of this activity is to investigate the advantages and limitations of the Atomic Layer Deposition technology for the deposition of optical thin-films for anti-reflection filters, spectral filters and optically absorbing filters. Description Manufacturing of optical filters with often stringent requirements is by no means a standard technology. Often, spectral and/or transmission requirements are difficult to meet involving a selection process to ensure that at least some filters out of one or several deposition batches fulfil the requirements. Atomic Layer Deposition is a new deposition method that allows to deposit thin-films with a unprecedented thickness accuracy of single atomic layers. Thickness control during the coating process is one of the precursors to ensure a faithful reproduction of the coating design. Combined with a reliable control of the optical properties of the coating layers this technology could significantly improve the performance of the produced coatings and the yield of the manufacturing process. This activity shall investigate the benefits of this new deposition process, study the reliability of the coating process, assess the reproduction of the coating design and determine the coating properties with respect to environment (adhesion, thermal and humidity). Deliverables Demonstrator Application/Need Date Optical filters in all optical missions (science, EO) TRL 5 by 2015 Duration (Months) 24 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-7760, T-8444
activities B07, B08, B09 and B10 of the Technologies for Optical Passive Instruments - Strable and Consistency with Harmonisation Lighweight Structures, Mirrors - roadmap
7 - 17 - Optoelectronics
TRP Reference T717-301MM Activity Title CMOS APS operation optimisation Objectives Optimisation and validation of CMOS APS control, read-out and on chip-functionality. Description This activity forms a part of the wider strategic programme to develop and stabilise European capability in providing high-performance and practical Complementary Metal-Oxide-Semiconductor (CMOS) Active Pixel Sensors (APS) detectors for space and related applications. CMOS APS detectors can be designed to operate in a wide variety of ways while the CMOS process allows the integration of increasing levels of on-chip functionality. The aim of this activity is to consolidate the operational and on-chip design functionality and develop the building blocks necessary for the construction of practical CMOS APS devices that can be matched to a wide variety of mission applications. This activity will be combined with equivalent activities in SD1 and SD2. Deliverables Breadboard Application/Need Date TRL 5 by 2015 Duration (Months) 24 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-8173, T-8757, T-7886
Consistency with Harmonisation TBD
TRP Reference T717-302MM Activity Title CMOS APS Pixel Design Optimisation Objectives Consolidation, design and validation of different CMOS APS pixel structures suitable for applications in Earth observation, astronomy, planetary science. Description This activity forms a part of the wider strategic programme to develop and stabilise European capability in providing high-performance and practical Complementary Metal-Oxide-Semiconductor (CMOS) Active Pixel Sensors (APS) detectors for space and related applications. In particular, it is recognised that a one size does not fit all and this activity aims to produce and characterise optimised pixel structures tailored to different operational requirements. This activity will be combined with equivalent activities in SD1 and SD2.
Page 98 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Deliverables Breadboard Application/Need Date TRL 5 by 2015 Duration (Months) 24 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-8173, T-8757, T-7886
Consistency with Harmonisation TBD
7 - 18 - Aerothermodynamics
TRP Reference T718-304MP Activity Title Uncertainty-Quantification Methodologies Applied to Aerothermodynamics Objectives Development of a methodology to assess objective confidence levels in quantitative information obtained from numerical predictions in aerothermodynamics Description The design of the heat shield of spacecraft heavily relies on the use of sophisticated physical-chemical models and numerical methods. It remains difficult to provide objective confidence levels in quantitative information obtained from numerical predictions. The complexity arises from the amount of uncertainties related to the inputs for such a complicated system. The quantification of the influence of uncertain parameters on the physical systems, also referred to as Uncertainty Quantification (UQ), is a major issue in order to properly predict the system response to random inputs. The three basic ingredients for predictive science,: - physical-chemical models - computational methods - experimental data must be integrated by means of state-of-the-art UQ tools. These tools will be applied to the rebuilding of the gas-surface interaction study in the VKI Plasmatron facility and to the study of radiation in the expansion tube. Deliverables Study Report Application/Need Date TRL 5 by 2017 Duration (Months) 18 Estimated Current TRL 1 Target TRL 2
SW Clause N/A Reference to ESTER T-8091
Consistency with Harmonisation activities A12, A13, A14, B06, B25, B31 and C01 of the aerothermodynamics tools roadmap
TRP Reference T718-305MP Activity Title Comparison of deorbiting technologies Objectives Identification of trade offs on system level of alternative deorbiting technologies compared with conventional technologies Description Since the number of space debris is increasing rapidly, increasing the probability of collisions with e.g. satellites, a safe and controllable technology to deorbit any kind of spacecraft will be crucial for the future. The advantages of innovative deorbiting systems as e.g. solar sails for satellites at high orbits or inflatable structures for lower orbits to increase drag shall be investigated with its impact on system level regarding performance of the overall system. The innovative systems shall be compared with classical ones (based on de-orbit propulsion systems). Deliverables Study Report Application/Need Date TRL 5 by 2017 Duration (Months) 18 Estimated Current TRL 1 Target TRL 2
SW Clause N/A Reference to ESTER T-1101, T-1105, T-7905
activities AA12, B05, B06, B12 and B30 Consistency with Harmonisation of the aerothermodynamics tools roadmap
TRP Reference T718-306MP Activity Title 3D radiative transfer code development Objectives
Page 99 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
To develop and validate three-dimensional engineering codes resolving radiative transfer problems, for the prediction of radiative fluxes around an entry vehicle or a payload/launcher element. Description A code shall be developed, offering different options for the resolution of radiative transfer problems encountered when a plasma emits radiation heating an entry probe, or when a rocket exhaust plume thermal radiation impinges on a launcher payload. Two options shall be offered: quick assessment or detailed analyses. The code shall be interfaced with Computational Fluid Dynamics (CFD) codes and spectral codes or databases. Deliverables Models, databases, technical notes, software Planetary Exploration Missions and Earth atmospheric entries, SW Operational by 2015-2018 Application/Need Date Launchers, SW operational by 2015-2020 Duration (Months) 24 Estimated Current TRL Algorithm Target TRL Prototype Operational SW Clause Reference to ESTER T-7904, T-8142 SW Consistency with Harmonisation activities A18, B04, B10, B12, B18 and B19 of the Aerothermodynamic tools roadmap
TRP Reference T718-307MP Activity Title Miniaturization of Electron Beam Fluorescence for hypersonic-flow in-flight characterisation. Objectives Enhancement of a flight model for Electron Beam Fluorescence (EBF) to perform local, non intrusive, steady and unsteady measurements of density, vibrational and rotational temperatures and velocity in low density hypersonic flows. Description Spectroscopic techniques are useful non-invasive techniques to probe high-speed flows characteristic of atmospheric (re)entry and that can provide important information regarding the evolution of the physical-chemical processes. At the moment, spectroscopic techniques are mainly applied in high-enthalpy wind tunnels. Of course their use directly in a flight environment is highly desirable because it will facilitate the validation of computational fluid dynamics solvers when applied directly to a spacecraft in a flight situation instead of simple geometrical models placed in wind tunnels. The present activity focuses on the enhancement and miniaturisation of an Electron Beam Fluorescence for future in flight applications. Deliverables Breadboard Application/Need Date TRL5 >2015 Duration (Months) 24 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-8094
Consistency with Harmonisation activities B14, B15, B16, B18, B21, B24, B25, B26, B27 and B28 of aerothermodynamics tools roadmap
TRP Reference T718-308MP Activity Title Catalogue of European materials and performance for heat shield applications Objectives To provide a catalogue of the existing European heat shield materials, defining the current performance envelope and extending the envelope where feasible. Description The study shall provide a catalogue of the main high temperature materials for heat shields based on the current state of the art in Europe, including Ablative technologies, Ceramic technologies and Ultra High Temperature Ceramics. It will take full advantage of existing knowledge in France, Germany and Italy amongst others.
Currently Ablative technologies are usually preferred for very high flux applications. The aim for ablative materials is to document current performance and the state of the art with respect to manufacturing capabilities in Europe.
Ceramic materials have traditionally been associated with re-usable heat shields and are therefore regularly associated with lower heat fluxes. With respect to ceramics the aim is to document the extensive knowledge gained on ESA and National programmes and to document the performance beyond the re-usable limits, where ceramics are known to maintain good performance.
Ultra High Temperature Ceramic (UHTC) materials offer a lot of potential for local applications with very high heat fluxes and for control surfaces. With respect to UHTC materials the aim is again to document the current performance envelope and the current status with respect to manufacturing techniques and TRL.
In all cases sample tests may be employed to extend the envelope and to increase the TRL for different heat shield applications, which would allow them to be considered for future missions such as Manned Capsules, Skip entry, Hypersonic Transport Aircraft, Aerocapture and Planetary Entry. Deliverables Study report & Sample test campaign Application/Need Date End 2012 Duration (Months) 12 Estimated Current TRL N/A Target TRL N/A
SW Clause N/A Reference to ESTER T-865, T-7878, T-7879, T-8273
Page 100 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Consistency with Harmonisation activities B01, B15, B19, B25 and B26 of the aerothermodynamics tools roadmap
7 - 19 - Propulsion
TRP Reference T719-302MP Activity Title Assessment of the use of non-intrusive diagnostics for Electric Propulsion testing (performance and qualification) Objectives The objective of the study is to assess, design and build a breadboard model of the non intrusive diagnostic and test it with an EPL thruster Description The underlying objective for electric propulsion (EP) terrestrial testing is to evaluate the performance which can be achieved in space to the accuracy required for the application. The required performance may be a direct function of the performance commanded such as thrust or specific impulse; alternatively it may be a function of equipment design such as exhaust plume shape and content. EP thrusters, their exhaust plume and their interactions with spacecraft are usually investigated through a combination of measurements and modelling. Far field measurements are usually performed by means of intrusive diagnostics. However, intrusive techniques affect the properties of the plasma under test and the interpretation of results can be sometimes questionable. This situation can get worse in case of near field measurements or even measurements performed in the interior of the thrusters. Thus non-intrusive diagnostics become an important tool to understand the local plasma properties or its interactions with parts of the thruster itself (discharge channel, etc..) in all high heat flux plasma environments. Erosion and/or contamination of some of the thruster parts can considerably decrease the lifetime of the EP devices.
This activity aims at assessing the use of a high spatial resolution and non-intrusive diagnostic technique to be used during the characterisation of an EP thruster during its performance and qualification phases. A review of the techniques and problematic issues as well as a state of the art shall be included. The diagnostic shall be designed and a Breadboard Model shall be built. An experimental characterisation in a space representative environment shall be performed with a Hall effect thruster and/or gridded ion Engine and/or HEMP thruster with the diagnostic technique. Deliverables Breadboard EP thruster testing (qualification and performances). Increase of lifetime of EP thruster Application/Need Date Need: horizon 2014 Duration (Months) 18 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-7766, T-1013, T-8119, T-8262
Consistency with Harmonisation TBD
TRP Reference T719-303MP Activity Title Rapid Manufacturing as a Key Enabler for Enhanced Monopropellant Catalyst Bed Design Objectives The ultimate goals are to: -Provide an enhanced monopropellant catalyst bed design through use of rapid manufacturing techniques. -Achieve cost reduction and thruster performance increase that provides a clear advantage for European suppliers.
The specific objectives of this proposal are to: -Define specific requirements for a catalyst bed with improved performance. -Research and identify suitable rapid manufacturing techniques and their limitations. -Identify the necessary complimentary conventional manufacturing techniques. -Develop preliminary catalyst bed design options based on results of the tasks above. -Critically analyse and down-select design options. -Manufacture a breadboard catalyst bed and perform preliminary development tests. Description Catalyst beds are used in monopropellant thrusters to induce reaction and rapid disassociation of the propellant in the combustion chamber. An effective catalyst bed must allow contact of a maximum portion of the propellant molecules with the catalyst material, while limiting the pressure drop across the catalyst bed. Typically, catalyst beds incorporate a structure with a large surface area to volume ratio and have catalytic elements dispersed and adhered across the surface. Current designs often use porous pellets or spheres packed into the thruster chamber. Other designs are comprised of a grid of channels (e.g. honeycomb) with the surface area enhanced through application of a slurry to the internal walls.
In both design options it is difficult to ensure a uniform and consistent catalyst structure and uniform distribution of the catalytic elements onto the surfaces of this structure. It is also difficult to maintain a low pressure drop. Use of Rapid Manufacturing could enable design options that are not available with current manufacturing techniques. A key advantage of Rapid Manufacturing is the ability to repeat the production of complex internal structures in a single process. Further, conventional manufacturing techniques can be used to compliment the Rapid Manufacturing process when needed. This would result in a lower cost, better performing catalyst bed for monopropellant thrusters. Deliverables Breadboard Application/Need Date 1N to 400N mono-propellant thrusters for spacecraft Duration (Months) 12 Estimated Current TRL 1 Target TRL 3
Page 101 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
SW Clause N/A Reference to ESTER T-867
Consistency with Harmonisation Harmonisation roadmap is from 2008
TRP Reference T719-304MP Activity Title Qualification of the AEPD system as a standard on-ground tool for electric propulsion thrusters Objectives The objective of this study is to demonstrate the complete capabilities of the AEPD system to be used as a standard tool for EP thrusters on-ground characterisation. Description The proposed project is based on the Advanced Electric Propulsion Diagnostic (AEPD) system recently developed within ESA/ESTEC contract N# 20461/06/NL/CP. The AEPD system consists of a high precision five-axis positioning system and currently 5 diagnostic tools (telemicroscope, triangular laser head, pyrometer, Faraday probe, energy-selective mass spectrometer). The capabilities of the AEPD system were demonstrated in two vacuum facilities of different sizes and with two different types of thrusters (GIE - RIT 22 - and HET - PPS1350 or SPT100 -. However the tests revealed critical issues of the test setup: - telemicroscope, triangular laser head and pyrometer are placed in a vacuum sealed housing at atmospheric pressure inside. The housings make the diagnostic head quite large and the use of normal pressure inside the housing bears some vacuum failure risks in case of damage to the housing's viewports or the housing itself. - the portfolio of diagnostic tools should be enlarged. - further tests are needed in order to define a standard tool for EP thruster characterisation. In consequence of the critical issues the diagnostic system shall be improved and qualified as a standard tool for EP thruster characterisation. In this activity, the following tasks are proposed": - in order to minimise the interaction between the diagnostic tools and thruster, as well as to minimise the risk of vacuum failure, telemicroscope and pyrometer shall be tested for in-vacuum operation; - additional tools such as thermocamera, differential thrust balance, retarding potential analyser, calorimetric probe shall be included; The APED shall be tested in different test facilities with two different thrusters in order to address chamber effects and diagnostic suitability's for different thruster types. Deliverables Study Report Application/Need Date EP thruster on-ground qualification; Standardisation for EP need date: around 2015 Duration (Months) 24 Estimated Current TRL 3 Target TRL 4
SW Clause N/A Reference to ESTER T-7766, T-1013, T-1073, T-8119
The proposed project refers to the Harmonisation Technical dossier related to Electric propulsion Consistency with Harmonisation technologies where Standardisation of test facilites and procedures is defined as one of the aims (activity G1)
TRP Reference T719-305MP Development and Test of a plasma Bridge Neutralizer based on Radio-Frequency Ionization for Electric Propulsion Activity Title Applications Objectives The objective is to develop a cathode-less neutralizer for EP thrusters to overcome lifetime issues and handling problems present with existing neutralisers. Description
Page 102 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
North-South station keeping, orbit raising, deep space missions and formation flying of two or more spacecrafts are domain of electric propulsion (EP). Development of neutralizing element - a necessary thruster system compaonent- with high life time, low power consumption and high reliability is the same challenge like the thruster development itself. Having a neutralizing element is mandatory. During ion thruster operation, poisitve ions are extracted from plasma on different principles dependant on the thruster type. Thereby a positive space charge is formed around the thruster, and the thruster body respectively the satellite becomes negatively charged. to encure proper operation of the thruster and to reduce the risk damage of satellite components by energetic ions the leaving positive charges have to be compensated by provided by a neutralizer system. Several types of neutralizer have been developed in the past such as hot cathode neutralizers, plasma bridge neutralizers with hot cathode or hollow cathode and bipolar grid system switches. Neutralizers with a hot or a hollor cathose are known to have a limited lifetime and/or reliability.
A cathodeless radio-frequency (RF) neutraliser would overcome most of the lifetime and handling problems. Indeed no external heating is necessary, nor hot parts like tungstem filaments or sensitive inserts. No component is sensitive to ambient gases and the design is robust. Because of the large operation time, the low maintenance effort and low beam impurity a cathode-less RF neutralizer would be an interesting alternative to frequently used hot-filament or hollow cathode neutralizers.
In previous research and development activities the capabilities of RF-neutralizer have been demonstrated. A generic design of an Elegant Breadboard (EBB) RF- neutralizer (current up to 1.8 A) has demonstrated its performance and readiness for the next step toward an engineering model together with a well defined thruster system (RIT-22). Studies dealing with the functionality and the RF-neutralizer lifetime were completed. However optimisation of the concept towards higher efficiency is mandatory. Moreover no test under environmental conditions embedded in a complete electric propulsion system was performed.
This activity aims at developping a breadboard model of the neutralizer capable to withstand meachnical loads during a launch and capable to operate under typical space conditions. Analytical models shall be eleborated. Experimental activities to validate the models shall be performed with and without a dedicated thruster. Deliverables Breadboard North-South station keeping, interplanetary mission Application/Need Date Horizon: 2015 Duration (Months) 18 Estimated Current TRL 2 Target TRL 4 Operational SW Clause Reference to ESTER T-1013 S/W Consistency with Harmonisation TBD
TRP Reference T719-306MP Activity Title High Voltage Single Stage Hall Effect Thruster Objectives In the frame of this activity, a prototype 5-kW thruster based on the PPS®X000 will be optimized for high-voltage operation, manufactured, and tested. The objective of this activity would be to validate by test the design optimization approach, and, very importantly, permit the first assessment of the combined impacts of this design and operating regime at high voltage on discharge channel erosion. Description Extensive on-going research work since 2003 has shown that Hall-effect thrusters can allow steady-state operation at specific impulses of at least 3000 seconds. Such devices can also be throttled to maintain a thrust per unit power about twice as large as that of ion engines. This capability has typically been evoked for future communications satellites where both orbit topping and station keeping would be done electrically. High-voltage HETs, however, can also be of prime interest for space exploration probes.
The large body of available test data shows that this flexibility in operating range comes at the cost of a drop in efficiency, typically at voltages above 500 V, or an Isp near 2500 s. This is because current designs and scaling laws have been derived from thrusters optimized for operating near 300 V. The criteria for design optimization at high voltage, however, are understood and a preliminary design is available at Snecma.
In the frame of this activity, a prototype 5-kW thruster based on the PPS®X000 will be optimized for high-voltage operation, manufactured, and tested. The preliminary design is already available, and it has been based on a high-power HET because large-scale HETs possess the following important features for this activity: 1) large thermal margins; 2) large magnetization margins; 3) large lifetime potential; 4) large operational domain. In addition, the PPS®X000 possesses a body of reference test data, including erosion assessments, over more than 2000 hrs of operation. The available optimized design for high voltage was also prepared with the objective of minimizing the hardware modifications to achieve an optimized design for a peak efficiency closer to 3000 s of Isp.
The proposed activity will be split into two main phases:
-The first phase will be to achieve detailed design of the thruster parts to be modified, based on the existing preliminary design. A technical note will describe the physics of the HET optimization for high-voltage operation, and the justification for the design choices. The modified parts will be manufactured and assembled on the modified (optimized) thruster design. -The second phase will consist first in a performance demonstration and characterization test, in order to compare predicted performance to experimental performance. The goal will be to demonstrate the effectiveness of the technological solutions implemented in the prototype. Second, the lifetime capability of the device will be assessed through a partial life demonstration test (for example 500 hours, non-cycled) at high voltage on the prototype. The results of this specific test will help understand and predict thruster erosion processes at high voltage, and will allow tuning of existing life prediction tools. The above two phases of this activity can be performed in, respectively, 8 and 4 months: Phase 1 :Detailed design of the modified parts and PPS®X000 upgrade Phase 2 :Performance demonstration and characterization test, followed by limited endurance
Deliverables Prototype
Page 103 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Geostationary satellites (present and future) for NS station keeping, and propulsively demanding (large-ΔV) space Application/Need Date exploration missions. Current Need Duration (Months) 12 Estimated Current TRL 3 Target TRL 4
SW Clause N/A Reference to ESTER T-7758
Consistency with Harmonisation This study is in line with the harmonisation dossier on Electric Propulsion (activity C1)
7 - 20 - Structures & Pyrotechnics
TRP Reference T720-301MS Activity Title Large Apertures Based on Ultrastable Membranes (LABUM) Objectives Demonstration of the suitability of thermo-elastically stable membranes and shell-membranes for the generation of large apertures in the range of 5 to 50 m. Demonstration of the backing structure construction principle, based on modularity, scalability and the minimum interaction between reflecting face and backing structure. The main applications can be large RF reflectors to be used in radio-astronomy missions, mobile telecommunications and earth-observation payloads from GEO, HEO, LEO and L2 orbits. The objective is to demonstrate their feasibility in relation to the dimensional stability requirements for each application, paying due attention to the relevant environment and the manufacturing aspects. Description Membranes and shell-membranes, preserving a minimum of bending stiffness and constructed with thermo-elastically stable materials, offer the possibility of generating large apertures with minimal mass. A relevant feature is the absence of pre-tension in a deployed configuration, as opposed to metal-mesh reflectors, which reduces sensitivity to instability and imperfections. The use of recent developments in Carbon Fibre fabrics embedded in elastic resin systems, such as silicones, offer the possibility to control the thermo-elastic behaviour, the foldability into small packages and the elastic energy storage for deployment. The open question is the robustness of the concepts to harsh environmental conditions and materials and processes imperfections. This activity shall develop a mid-size demonstrator (5 m aperture) and run a thermal vacuum test with simulation of sun and shadow for the generation of the worst possible thermal cases with gradients. The design phase shall include details of the backing structure, but only a simplified one will be manufactured for the demonstrator. Breadboading will be necessary to support design of the backing structure folding principle, as well as its modularity and/or scalability. Meanwhile the shell of the demonstrator shall be representative of a flight article. Deliverables Demonstrator The main applications are large RF reflectors to be used in telecommunications, radio-astronomy and earth-observation payloads. Mainly mobile communications and data relay require this kind of apertures with a strong market demand. The outcome of a market analysis performed in ESTEC has shown that about 10 antennas per year of more than 4 m, up to 25 m projected aperture, will be required worldwide in the coming 10 years. These reflectors of more than 4 m are not available in Application/Need Date Europe, meanwhile the US, Japan and Russia are already operating antennas of up to 22 m. This represents a clear technological dependency resulting from lack of telecom market understanding, planning and funding in the European context. In order to correct this situation and not incur in patent restrictions, this technology proposed can represent a new concept worth investigating and a technological breakthrough, enabling many applications. Duration (Months) 18 Estimated Current TRL 3 Target TRL 4
SW Clause N/A Reference to ESTER T-555, T-617, T-353, T-8399, T-7917, T-543
This activity is within the scope of AIM D of the Reflector Antennas for Telecommunications roadmap. Consistency with Harmonisation However, the proposition of new activities within this AIM to THAG was delayed.
TRP Reference T720-302MS Activity Title Methodology for microvibration management at system level Objectives The objective of this activity is to define a methodology aiming at defining and validating the microvibration environment at system level early in the project development Description The activity aims at defining: - system level performance requirement definition and associated maximum allowable disturbance amplitude - budget techniques to allocate disturbance specification to noisy sources (top to bottom interface requirements derivation method) - system and subsystems verification techniques of the microvibration performance by analysis and/or tests (incl. noise source characterization, system microvibration test...) - need for active/passive isolation system in case of identified problem
This global system methodology should be implemented in the time frame of a S/C project and should address the microvibration problem as early as possible in the design phase. Deliverables Study Report
Page 104 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
This activity, together with the TRP T719-083MC (TRP 2008-2010), will define a general framework to be used at project Application/Need Date level to address during the design loop the microvibration performance. This will thus avoid discovering late some performance issues (e.g. pointing, image acquisition…) that necessitate usually costly solutions. Duration (Months) 18 Estimated Current TRL 3 Target TRL 5
SW Clause N/A Reference to ESTER T-8792, T-8954
Consistency with Harmonisation TBD
TRP Reference T720-303MS Activity Title CFRP Grid structures for dimensionally stable structures Objectives Investigate feasibility and advantages of CFRP grid structures for dimensionally stable structures. Design, manufacture and test a dimensionally stable grid structure and trade-off with existing technologies Description CFRP grid structures have been proven to be highly efficient load bearing structures for launcher applications. Some lightweight deployable space structures also resemble grid structures. However, these have low strength and stiffness. In this project the use of grid structure technology for dimensionally stable structures which need to have adequate strength and stiffness shall be explored. The technology shall be demonstrated by: -designing and analyzing a dimensionally stable structure, -sample testing -manufacturing and testing a demonstrator structure. Deliverables Technical reports, technology samples, demonstrator Application/Need Date Earth Observation, Science /2013 Duration (Months) 18 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-5296
the activity is consistent with the Technology Subdomain 16-B/20, Technology for Passive Optical Consistency with Harmonisation Instruments - Mirrors, Stable and Lightweight Structures- Harmonisation Dossier but was not proposed in the Harmonisation roadmap at the time.
TRP Reference T720-304MS Activity Title SAFE (Shock Attenuator For Equipment) Objectives To develop and qualify an isolation system compatible of existing interfaces Description Compatibility problem with respect to shock environment is often discovered too late (i.e. when S/C design is frozen, and hardware is already manufactured). Any design modification at this stage of the development would have a dramatic impact on the project. Some viscoelastic isolation systems for equipment are widely available, however non of them can be implemented on a spacecraft if the compatibility problem is evidenced late in the development. Indeed the commercial isolation systems require a specific mounting condition. The objective is to develop and qualify an isolation system compatible of existing interfaces (existing hole in the equipment flange, existing threaded hole on spacecraft wall). The isolation system should be versatile, and should be designed for several loads and attenuation targets. Deliverables Prototype Some viscoelastic isolation systems for equipment are widely available, however none of them can be implemented on a spacecraft if the compatibility problem is evidenced late in the development. Indeed the commercial isolation systems require Application/Need Date a specific mounting condition. There is a gap between S/C needs and available solutions: The need from a spacecraft is a versatile isolation system which can be implemented as a curative solution, without modifying the existing interfaces. Duration (Months) 12 Estimated Current TRL 2 Target TRL 5
SW Clause N/A Reference to ESTER T-8286
Consistency with Harmonisation N/A
TRP Reference T720-305MS Activity Title Shock Release system classification Objectives
Page 105 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
To develop a standardised (but representative) test set-up for identification of shock signature of release systems. The test setup shall have a standardised plate with a standardised I/F, bolt, boundary conditions, sensor positions and pretension load. Description Experience shows that shock specifications for release systems provided by suppliers rely on different test methods and test setups. As a consequence the specified SRS are not comparable and compliance statements given in proposal phases can still impose some risk. The selection of the release system thus strongly depends on individual experience and heritage. The objective is the definition of a standardised test setup for release systems, are the generation of a shock test database which includes most used releases systems (pyro and non-pyro). This database will be complementary to the already existing one generated by the ESA/CNES pyro laboratory. Deliverables Test bench The development of a standardised test set-up and the generation of an extensive shock database will be beneficial for the Application/Need Date selection of a release systems and beneficial for new developments of release systems. Duration (Months) 12 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-562
Consistency with Harmonisation N/A
7 - 21 - Thermal
TRP Reference T721-301MT Activity Title Multiple-evaporator multiple-reservoir Loop Heat Pipe Objectives To design, manufacture and test a LHP having as a minimum two evaporators and two reservoirs as an alternative to two separate LHPs working in parallel Description The STENTOR six-evaporator LHP system, which was successfully qualified on-ground has, as opposed to the current proposed activity, a common reservoir. Indeed, all six reservoir wicks are collocated and connected to each other. Consequently, these six reservoirs behave as one unique reservoir from thermal and hydraulic point of view. In the frame of this activity, the two (or more) reservoirs shall not be collocated and shall be of a relatively large distance from each other, which reflect the potential accommodation of the two (or more) evaporator-reservoir blocks on-board a spacecraft. Past US and Russian experiments on this type of two LHPs have shown that one of the reservoirs tended to be completely filled in and other one(s) empty. An innovative method shall consequently be investigated in order to solve this flow distribution issue between the reservoirs. In addition, specific design shall be investigated such that one evaporator failure does not propagate to other evaporator(s). Deliverables Engineering Model Application/Need Date 2015 Duration (Months) 24 Estimated Current TRL 3 Target TRL 4
SW Clause N/A Reference to ESTER T-7874
Consistency with Harmonisation TBD
TRP Reference T721-302MT Activity Title Advanced Solver Technology for Thermal and ECLSS Simulation Objectives The objective of the activity is to develop advanced solver technology within EcosimPro that will be necessary of the next generation of large and complex model for ECLSS, thermal, propulsion and power system simulation. Description
Page 106 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
EcosimPro is a powerful simulation tool capable of modelling any kind of dynamic system represented by differential-algebraic equations (DAE) or ordinary-differential equations (ODE) and discrete events. Originally developed under ESA contract for the simulation of Environmental Control and Life Support Systems (ECLSS), it is now a commercially available tool with a worldwide user base.
More recently EcosimPro has become the agency's standard tool for the simulation of propulsion systems through the development of the European Space Propulsion Simulation System (ESPSS) libraries. This has led to a surge in the use of EcosimPro in industry and also the use of models that are much more computationally demanding. EcosimPro is also starting to be used heavily with the TEC-EP division internally in ESA for power systems simulation.
Although the EcosimPro has been continually developed over the years, the core solver, DASSL, dates back to the early 1980's. Whilst the solver has so far proven to be exceptionally robust and efficient, the use of extremely large models, as are produced by the ESPSS propulsion libraries, has highlighted the possibility to further develop these solvers with more modern technology. Such development would benefit the whole user base of EcosimPro including users from the domains of thermal, propulsion, power systems, operations and ECLSS.
Examples of some of the technology of interest are: - Use of the next generation of DASSL solvers which are better suited to large systems. - Parallel computing with EcosimPro. This would enable large models to be split up and run in parallel on multiple processors. - Use of completely different solver technologies e.g. those based on Bond graph theory. - Development of better optimisation algorithms that can be used for parametric studies.
The proposed activity would investigate different options to improve the solver technology within EcosimPro and determine which are most suitable given the requirements of future models. The expected deliverables from the activity are a prototype version of EcosimPro containing advanced new solver technology. The added value of the new technology will be demonstrated using several test models that are characteristic in terms of size and complexity of those that are likely to be use in the future for thermal, propulsion and power system simulation. Deliverables Software Application/Need Date 2013 Duration (Months) 15 Estimated Current TRL Algorithm Target TRL Prototype
SW Clause N/A Reference to ESTER T-7882
Consistency with Harmonisation N/A
TRP Reference T721-304MT Activity Title Passive by-pass valve for single and two phase mechanical pumped fluid loops Objectives To develop a passive by-pass valve for a mechanical pumped fluid loops. Description Mechanical pumped fluid loops are used to collect waste heat from internal components and reject it to the external environment via a radiator. If the internal power dissipation decreases below a certain level, the pumps will need to be stopped in order to maintain the internal temperature above the operating limits. However, this may create large gradients within the spacecraft. Therefore, if a by-pass valve would be used to cut the fluid flow to the radiator, the fluid loop will be used to equilibrate the internal temperature by distributing the internal power dissipations. Under an Artes8 activity, an active by-pass valve was developed. However the valve is large and it requires additional control electronics. Deliverables Prototype The valve would be used on Telecom Spacecrafts as well as on exploration missions where miniature mechanical pumps are Application/Need Date used Duration (Months) 24 Estimated Current TRL 1 Target TRL 4
SW Clause N/A Reference to ESTER T-8437
Consistency with Harmonisation Mechanical Pumped fluid loop systems
TRP Reference T721-305MT Activity Title Non-centrifugal pump for Mechanical Pump Driven Loops Objectives To find an alternative for centrifugal pumps currently used for single-phase and two-phase Mechanical Pump Driven Loop Description Currently mechanical pumps which have been developed for space use are centrifugal pumps. They have been used for both single-phase and two-phase Mechanical Driven Loops. For a two-phase MPDL where relatively high pressure rise is specified and relatively low flow rates are required compared to single-phase MPDL, non centrifugal design such as gear pump is a preferred solution in terms of specific speed and achievable efficiency. In addition, while the flow characteristics of centrifugal pumps vary according to the loop restriction and impeller geometry, the gear pumps provide an almost constant volume flow characteristics in relation to the pressure rise. The goal of the activity to design a gear pump, compatible with long lifetime requirement for space missions, which will be integrated within a two-phase MPDL which will be used either for large telecommunication platform (large power) or exploration landers/rovers (low power). The development will also encompass single-phase fluid loops requirements. Deliverables Engineering Model
Page 107 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Application/Need Date 2014 Duration (Months) 30 Estimated Current TRL 3 Target TRL 4
SW Clause N/A Reference to ESTER T-8437
Consistency with Harmonisation Two Phase Heat Transport System Harmonisation S1 2009 - AIMS C6
TRP Reference T721-306MT Activity Title Applying CNT for thermal interfiller performance enhancement and high-performance thermal straps Objectives To study and demonstrate methods to exploit carbon nanotube thermal conductivity in
1.a new thermal interfiller product for use on equipment footprints 2.thermal straps in a range of dimensions to be suitable for application both to support heat rejection from equipment on the outside and to reject heat from critical boards and components on the inside Description Carbon nanotubes (CNT) are known to have the potential to offer superior characteristics compared to other materials with respect to mechanical and electrical properties and it is also the case for thermal conductivity, which for pure CNT material has a value of 6000 W/mK (to be compared to 150 W/mK for aluminium and 200 W/mK for graphite in-plane thermal conductivity). The challenge with nanoparticles in general, including CNT, has been to achieve an even dispersion in the matrix material so that the high intrinsic thermal conductivity of the dispersed material results in a high overall thermal conductivity, even when percolation is reached. Recent research shows that earlier limitations are about to be overcome, with new methods to align the orientation of CNT additions by means of tailored distribution of the matrix material. The resulting fibres will have the ability to allow for much improved phonon motion and therefore have the potential to exhibit much increased thermal conductivity, which will form the basis for thermal straps. Methods also exist to produce uniformly oriented CNT forests, such as by Chemical Vapor Deposition (CVD), over sufficiently large areas so that a high-performance thermal interfiller is one of the other possible applications.
While heat pipe technology has lead to much improved means to spread dissipated heat over radiator panels of spacecraft, transfer of waste heat inside equipment from PCB to housing and from equipment baseplates to panels and heat pipes form a bottleneck for the thermal design. In order to support further miniaturization of onboard electronics and the related increase in power density and heat generation, improved means to transport heat from the inside to the outside of equipment will be required. Use of CNT technology offers the opportunity to drastically improve the performance of two essential tools for accommodating the required heat transport; a) thermal interfiller material for equipment mounting and heat pipe interfaces and b) thermal straps, either between boards and components inside equipment housings or from equipment to surrounding structures. The need date will be next generations of telecom and earth observation payloads and to be part of upcoming developments a need date of 2013 is suggested. Deliverables Study Report Application/Need Date Telecom/Science/Earth Observation, > 2013 Duration (Months) 18 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-8839
Consistency with Harmonisation N/A
7 - 22 - Environmental Control Life Support (ECLS) and In-Situ Resource
TRP Reference T722-301MM Activity Title Study of Countermaesures against bio-contamination of exobiology research spacecraft, manned vehicle and payloads. Objectives Identification of an adequate control programme and countermeasures, and validation of these strategies in ground facilities Description Exploration to virgin planets as well as manned space missions requires a high degree of biological cleanliness. This degree of cleanliness is only reachable if proper countermeasures are applied. Consequently it is very important to gain a better understanding of countermeasures against bio-contamination processes in a closed environment, either on flight hardware, clean room, or in a manned space vehicle. A systematic and scientifically-based approach is required to fulfil the needs of a correct assessment of the efficiency of the bio-contamination countermeasures. The ideal method should not only rely on empirical strategy but should be based as well on prediction of microbial contamination and to take proactive counter-measures.
Identification of an adequate control programme and countermeasures, and validation of these strategies in ground facilities. The milestones in this phase can be defined as: - Correct translation of bio-contamination understanding into a monitoring strategy with optimized sampling frequency and determination of preferred sampling locations. - Successful activation and implementation of countermeasures when the threshold levels of microorganism are exceeded. Deliverables Study Report
Page 108 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Application/Need Date As soon as possible (ATV, ISS payloads, ISS operation, Exomars) Duration (Months) 24 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-7762, T-7788, T-7789
Consistency with Harmonisation N/A
7 - 24 - Materials & Processes
TRP Reference T724-302QT Activity Title Metallic Materials Characterisation Objectives Continue metallic materials laboratory process and performance assessments. Description Within the framework of the European Space industry there is a continuous need to review the properties of existing materials and processes and characterise the performance of new materials and processes. This process is being driven by the mass, cost, performance and reliability requirements of missions as well as the environmental demands of many missions becoming more extreme. The Characterisation of Metallic Materials programme at ARC Seibersdorf is running since 1995. It is a continuous laboratory activity cofounded by corporate budgets and the TRP consisting of a serious small projects of typically less than 6 month. Deliverables Test Report Application/Need Date All missions Duration (Months) 36 Estimated Current TRL N/A Target TRL N/A
SW Clause N/A Reference to ESTER T-8843
Consistency with Harmonisation N/A
TRP Reference T724-303QT Activity Title Metal Matrix Composites (MMCs) as high performance metallic material Objectives To establish the limits of the materials commercially available with respect their processing. To derive design guidelines for using MMCs materials To characterise the corrosion behaviour of these alloys and define the suitable corrosion protection technologies. Description MMCs possess very attractive mechanical properties; in particular stifffness that can be twice that of conventional metals. To benefit from these materials, their ability to be processed for space hardware shall be established. Deliverables TN, test samples, test report Application/Need Date All missions Duration (Months) 18 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-8841
Consistency with Harmonisation N/A
TRP Reference T724-304QE Activity Title Nano-hybrid transparent materials Objectives Evaluation of materials functionalities reg. their radiation resistance Tailoring of material composition and processing techniques Focus on LEO applications, mainly UV/VUV and thermal cycling Description This study shall aim to develop a highly transparent (colourless or low solar absorbing with a high thermal emittance) hybrid material in combination with a high radiation resistance (Proton, electron, UV, VuV, X-ray etc.), good handling flexibility as well as being resistant to thermal cycling seen in space. This material shall be used as the first target application as a Second Surface Mirror (SSM) configuration and its performance shall supersede commonly used FEP SSMs. It is clear that a material development will only be successful after several iterations/improvements and that progress can only be achieved in a step by step approach.
Page 109 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Deliverables Study Report Application/Need Date EO, SCI missions, >2013 Duration (Months) 18 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-8390
Consistency with Harmonisation N/A
TRP Reference T724-305QE Activity Title Use of Nanocomposite reinforced Foams for Manufacture of Superlightweight Stiff Sandwich Panels Objectives Development of more complex designs with associated mass reductions. Develop structural elements for spacecraft and launcher systems Testing and verification of samples Description Composite panels consisting of an aluminium honeycomb and a carbon fibre reinforced skin (CFRP) have been successfully introduced into spacecraft structures now for well over a decade but what is the next step? Recent developments in nano-reinforcement have lead to the commercial use of these materials in polymeric foam structures to produce stiffer and stronger cores for use in articles such as squash racquets. The use of such materials, if realised, may offer significant advantages over conventional sandwich panels. These include: - Reduced weight - Increased stiffness - Reduced sandwich panel volume for equivalent mechanical performance - Possible profiled/contoured designs. - Possible tailoring/grading of properties such as conductivity, RF response etc. It is proposed that a programme of work be initiated to investigate different nanocomposite foams available in conjunction with suitable CFRP systems to manufacture sandwich panels. Selection of suitable systems should be on the basis of fulfilling the same criteria as conventional CFRP-aluminium honeycomb panels but utilising a nano-composite based foam core and either a conventional CFRP or a nano-reinforced CFRP skin. The objective of this investigation will be to develop a conventional panel utilising the new materials and demonstrating the improved performance levels obtained by testing with conventional mechanical techniques such as LBF (long beam flexural), insert and FWT (flatwise tension) tests. Deliverables Study report + test samples Application/Need Date All missions/ Immediately Duration (Months) 18 Estimated Current TRL 1 Target TRL 2
SW Clause N/A Reference to ESTER T-8840, T-8390, T-8289
Consistency with Harmonisation N/A
TRP Reference T724-306QT Activity Title Metallizing ceramic structures Objectives Deposit a metallic layer on the surface of a ceramic with strong bonding strength between the metal and the ceramic. Assessment of the reliability of the bond characteristics. Description Ceramic structures are often brittle and difficult to connect to. Complicated and bulky interfaces are required to distribute the loads adequately whilst maintaining the grip over a wide temperature range. A metallised layer on the surface of the ceramic would open alternative joining technologies to be employed such as brazing or friction stir welding Deliverables Breadboard Application/Need Date All missions Duration (Months) 24 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-8841
Consistency with Harmonisation N/A
TRP Reference T724-307QE Activity Title Advanced in-situ/real time on ground contamination monitoring; phase 1 Objectives Combined quantitative and qualitative real-time monitoring of molecular contamination. Currently only mass information can be acquired, chemical analysis needs to be done ex-situ, i.e. outside facilities and after post-degradation effects.
Page 110 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Description End to and technology development available on request Deliverables Prototype Application/Need Date 2013 Duration (Months) 24 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-8392
Consistency with Harmonisation N/A
7 - 26 - Spacecraft Avionic System
TRP Reference T701-303ED Activity Title Adoption of Electronic Data Sheets and Device Virtualisation for onboard devices Objectives The aim of this activity is to: * determine and/or verify the DVS (Device Virtualisation Service) device class interfaces for a range of representative, primarily, AOCS devices; * determine and/or verify the use of an EDS (Electronic Data Sheet) with the same representative devices; * demonstrate the use of the DVS in a flight-representative system. Description Devices used as part of the onboard data handling system are typically specified using paper documentation which must be used generate device drivers and device specific software. This results in repeat development and test for each project, even if the same device is utilised. In addition, devices intended to perform the same or similar function provide information in device specific ways thus hindering the reuse of application software which must be modified to the peculiarities of each device. This activity seeks to ease the generation of device specific drivers through the provision of electronic data sheets which offer the opportunity for auto, rather than manual coding. In addition, the activity proposes to demonstrate the provision of a standard interface to application software for a range of commonly used devices. The demonstration should include the use of the DVS device class interface and should further demonstrate the following two approaches: * Offline use of an EDS for autocoding; * Online use of an EDS for parameterisation. It may also be necessary to select and/or develop appropriate tools for the handling of EDSs. Deliverables Prototype Application/Need Date All missions. SW operative by 2015. Duration (Months) 12 Estimated Current TRL Algorithm Target TRL Beta Software Operational SW Clause Reference to ESTER T-8383 S/W Consistency with Harmonisation Activity J4 of the Avionics Embedded systems roadmap proposed in June 2010 (not yet endorsed by IPC)
TRP Reference T701-304ED Activity Title Deploying Plug and Play Avionics Objectives The aim of this activity is to demonstrate the use of plug-and-play avionics in a flight-representative command and control environment. Description The use of Plug-and-play in the onboard data handling system will improve system integration times and also support Failure Detection, Isolation and Recovery (FDIR) by offering the possibility to reconfigure the onboard subnetwork. As part of any onboard reconfiguration a number of parameters will need to be modified depending on the underlying subnetwork technology and capabilities. Such parameters include addressing, bandwidth allocation and routing tables. This activity will identify several use cases taking account the currently used onboard technology, Milbus, CANbus and SpaceWire. From this, a set of prototyping activities will be undertaken using existing Agency test-beds. Deliverables Prototype Application/Need Date All missions/2015 Duration (Months) 12 Estimated Current TRL 1 Target TRL 4
SW Clause N/A Reference to ESTER T-8383
Consistency with Harmonisation TBD
Page 111 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
TRP Reference T701-307ED Activity Title Network management and FDIR for SpaceWire networks Objectives Research and prototype methods for network management and FDIR in SpaceWire networks Description SpaceWire defines the links and the network as well as some higher level protocols. The users are free to define the network management and the Failure Detection Isolation and Recovery (FDIR) scheme adapted for their application. With the increasing spread of SpaceWire more users ask for recommendations how to perform network management and FDIR for their application. In this activity a set of typical use cases of SpaceWire networks shall be prototyped and recommendations for network management and FDIR shall be found. This should also take into account the different levels of required system availability and autonomy including network contained FDIR. Deliverables Study Report Application/Need Date All missions. Protocol available > 2015 Duration (Months) 18 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-7751, T-7821
Consistency with Harmonisation No
TRP Reference T701-312ED Activity Title Packet Utilisation Standard (PUS) library using SOIS services Objectives The objective is to develop a full implementation of a PUS software library building block mapped to the communication services provide by the Consultative Committee for Space Data System (CCSDS) Spacecraft Onboard Interface Services (SOIS) standards. A reference mission scenario will be provided under the Reference Architecture System Test-bed for Avionics (RASTA) so that the implemented building block is representatively tested. Description The prototype will be used to verify the new PUS standard in the context of standard onboard services being defined by CCSDS. The work will involve both ESOC and Estec test-beds in an end to end context. Deliverables Prototype Application/Need Date PUS is used by all ESA missions. The library is required following the next release of the ECSS PUS standard. Duration (Months) 12 Estimated Current TRL Algorithm Target TRL Prototype Operational SW Clause Reference to ESTER T-8383 S/W Consistency with Harmonisation TBD
TRP Reference T701-314ED Activity Title Standardization of Digital Interfaces for Sensors (Temperature, Pressure, Position, Velocity, Acceleration) Objectives The ECSS-E-50-14 defines analog interfaces, bi-level discrete interface and serial digital interface (16-bit). Considering the most recent sensor acquisition methodologies that are dominating the industrial world the space community should update the standard in order to include the recent and conceivable evolution of sensors acquisition systems. The major deliverable will be a technical specification to be provided as an input to the corresponding ECSS working group. Description Temperature Sensors (Thermistors and Thermocouple), Pressure sensors , Position Sensors ( Encoders, Resolvers, Contactless angular sensor based on Hall effect sensors), Accelerometers used in space applications have been acquired as analog signals up to now. A natural evolution is pushed by the need to increase the signal integrity and resolution of the transmitted signals and by the availability of miniaturised ASIC-sensors able to locally include the sensor biasing and signal conditioning/processing functionalities. Maintaining in any case a low power consumption requires the definition of standards for digital transmission of sensor data in a S/C, which represents the focus of the present activity. Deliverables Study Report Application/Need Date Future Spacecrafts. Standard implementable>2014 Duration (Months) 12 Estimated Current TRL N/A Target TRL N/A
SW Clause N/A Reference to ESTER T-7885, T-452
Consistency with Harmonisation activity C4 of the Avionics Embedded Systems roadmap proposed in June 2010 (not yet endorsed by IPC)
TRP Reference T701-315ED
Page 112 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Activity Title FDIR Validation Test-Bed Objectives This activity will build a configurable Test Bed to validate Failure Detection Isolation and Recovery (FDIR) concepts and implementations for spacecraft Avionics data systems. As an important result of this activity a report containing recommendations and suggestion in advance of an ECSS standard for a correct design and implementation of FDIR concepts ( for the part that affects the Avionics Data system) Description Starting from the already available Reference Architecture System Testbed for Avionics (RASTA) system and pushed by recent anomaly events, the aim is to have a real HW test-bed where the conceived or implemented FDIR concepts can be validated. The currently available RASTA system has to be upgraded mainly in order to: - to implement redundancies (needed to test FDIR concepts) - to improve its configurability/functionality features At the same time the opportunity will be taken to take account of the latest processor modules (e.g. LEON 3, SCOC?). The upgrade will also provide the reference platform for all applicable building block activities. Reconfiguration Mechanisms, correct use of Safe Guard Memory, fault coverage, BIT are only some of the topics that the availability of a real Test Bed can allow to investigate and validate Deliverables Test Bed, Study Report Application/Need Date All spacecrafts > 2014 Duration (Months) 12 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-7751, T-7671, T-7803, T-7821
Consistency with Harmonisation Activity O6 of the Avionics Embedded Systems roadmap proposed in June 2010 (not yet endorsed by THAG)
TRP Reference T702-301SW Activity Title FDIR Development and V&V Process Objectives Develop Failure Detection Isolation and Recovery (FDIR) Development and Verification and Validation (V&V) Process, coordinated with the System and Software Development Processes. Develop corresponding FDIR Development Environment implementing the Process and allowing for the approach coherent with System and Software Engineering. Description Currently employed approaches to FDIR development are poorly phased with regard to the main Software Development activities. They have tendency of starting late, awaiting for the system Failure Mode Effects and Criticality Analysis (FMECA) data. If functional FMECA is sometimes available, its update into the physical FMECA is seldom ready for software development. FDIR definition is not adequately synchronised with the nominal Software System behaviour. Traditional approaches to testing are often inadequate for FDIR due to large amount of possible combinations of the monitored events, limited system observability, and difficulties in recreating the necessary conditions. Dedicated FDIR Development Processes, and Verification methods, applicable to and harmonised within the European Space Industry, are required for the coordinated approach to FDIR development, effective project planning and control, and proper achievement of FDIR operational objectives. The FDIR Development Process resulting from this activity shall take into account the lessons learnt with regard to FDIR development from the current operational projects. It shall provide the FDIR Development Environment implementing the Process and allowing for the approach coherent with the System and Software Engineering. Set of methods and tools shall be developed for formal FDIR specification and analysis for correctness, consistency, FDIR operational effectiveness, and effect on the overall System Dependability. System-level FDIR V&V shall be addressed. This activity shall leverage results of the ESA COMPASS project and developed Integrated Tool-set. Deliverables Prototype Application/Need Date FDIR Development and V&V, all missions. Prototype SW > 2013. Duration (Months) 36 Estimated Current TRL Algorithm Target TRL Prototype Open Source SW Clause Reference to ESTER T-7743, T-908, T-7660, T-7671, T-7661, T-303, T-7667, T-8414, T-8603 Code Consistency with Harmonisation Activity H3 of the Harmonisation Roadmap 2010 for Avionics Embedded Systems 1st semester 2010
TRP Reference T702-303SW Activity Title System-Hardware-Software co-engineering Objectives The activity investigates a model based and automated process going from system (avionics) models to software and microelectronic models.
Description
Page 113 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Using the avionics architectural language, the system model should be able to express microelectronic blocs as well as hardware components and software elements. The interface between hardware, software and microelectronic will be defined. The model should contain parameters allowing to verify some particular properties related to the hw-sw co-design, e.g. for the performance. This would allow some tools to decide on the best implementation, and to initialize the software and the microelectronics models from the avionics model.
The activity will include: - Analyse of the process leading from a complete avionics model towards software and microelectronics models and hardware components. - selection of the most appropriate languages to express the various models, - investigation of potential model transformation to initialize the software and microelectronic models from the avionics model, - investigation of techniques and tools to use the models and their parameters to drive the microelectronic or software implementation decision. Deliverables Prototype Application/Need Date All missions/2013 Duration (Months) 18 Estimated Current TRL Algorithm Target TRL Prototype
SW Clause N/A Reference to ESTER T-7662
Consistency with Harmonisation TBD
TRP Reference T702-306SW Activity Title Avionics Architecture Modelling Language Objectives The activity aims to define a space profile for an existing commercial avionics modelling language Description The model based software engineering consists in expressing the software functional requirements with models. In order to get the requirements right as early as possible, system-software co-engineering is necessary, in this case avionics-software co-engineering, where the software functional models are placed consistently into an avionics model. The avionics model represents the physical architecture on which the software will run (deployment view). It allows to define some key parameters which enters into the definition of system functional and performance properties such as end-to-end response time, accuracy etc. These properties can then be mapped onto the software models and verified at software level by model checking. The avionics architecture model represents roughly a set of boxes (computing nodes such as computers or IMA partitions) connected with busses, plus parameters characterising the avionics elements and used by the software deployment and software verification tools: name of processor, throughput, bandwidth of bus, etc. This model is one essential element contributing to the on-board software reference architecture and supported by the component based approach. The main example of an avionics architectural language is AADL (SAE standard initiated by Honeywell). The main example of the parameters that could be attached to it are the one described in the MAST tool, a schedulability analyzer for distributed system (University of Cantabria). They configure various scheduling policies such as cyclic, pre-emptive, IMA, distributed, etc.
The activity includes the definition of a space profile for an existing commercial avionics modelling language - derive the (space specific) requirements for an avionics architecture modelling language - select a commercial tool based on the derived requirements for the language - demonstrate the validity of the tool by means of a pilot application Deliverables Study report and models/software Application/Need Date All projects/missions on board SW. Prototype by end 2012. Duration (Months) 12 Estimated Current TRL Algorithm Target TRL Prototype
SW Clause N/A Reference to ESTER T-7743, T-908, T-7660, T-7662
European Space Technology Harmonization Roadmap meeting presentation - Avionics Embedded Systems v2.0 1st semester 2010 Consistency with Harmonisation Activity SD7A - A8 Aim A: Reference Architectures
TRP Reference T702-307SW Activity Title Catalogue of system and software properties Objectives The activity aims at investigating exhaustively the system properties that are associated to the avionics and software of a spacecraft. This include for example the modes management and their transition, the end-to-end response time of specific behaviours, performance properties, dependability properties, etc. Description
Page 114 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
The software development is shorter and shorter. A way to reduce the software life cycle is to replace tests (which happen at the end of the cycle) by verification of design (which happen earlier and can both track and avoid errors and can minimize the test effort). Design correctness is checked by verifying that the design fullfills a set of properties. An example is the real-time property that every task of the software complete before its deadline. The objective is to push this principle even earlier in the software life cycle, at the level of software requirements, when the system is also architectured, so in the phase of system-software co-engineering. Software properties must be derived from system properties. For example, an end-to-end system response time will result into a software schedulabity property. A system availability property will result into software FDIR mechanisms that must have a particular behaviour. A system performance property may result in a software numerical accuracy property. The objective of the activity is : 1) to know better (and more exhaustively) what the system properties are 2) to make the link between the system properties and the software properties 3) to understand which verification technique (generally formal methods or model checking methods) are best suited to verify the properties 4) ultimately to be able to focus the future R&D investment on only the needed verification techniques.
Following the ADCSS round table on Formal method, it appeared that the use of formal method was appropriate to verify system and software properties. However, it was difficult to select which formal methods should be picked up and industrialized, because it was not clear the kind of system properties that were more frequently used.
The activity includes: - Taxonomy of system and software properties to verify throughout the development life cycle (from early stages up to implementation) - selection of the appropriate formal methods to be used for the verification of system and software properties - small demonstration of the use of the selected methods, - R&D plan for formal methods industrialisation and/or integration in the architectural models. Deliverables Study report and models/software Application: All on board SW projects/missions Application/Need Date Need date: end 2012 Duration (Months) 12 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-908, T-7660, T-7662, T-7661
European Space Technology Harmonization Roadmap meeting presentation - Avionics Embedded Systems v2.0 1st semester 2010 Consistency with Harmonisation Activity SD7 M4 Aim M: System Software Co-engineering
TRP Reference T702-309SW Activity Title IMA-SP System design toolkit Objectives The activity shall refine the processes, methods (including model based design), roles and tools for the effective deployment of the IMA-SP approach to spacecraft avionics Description The Integrated Modular Avionics for Space (IMA-SP) concept introduces the role of System Architect to the spacecraft avionics domain. The System Architect has the key responsibility for negotiating the avionics resource allocation with the hosted application suppliers and then performing a system-level verification to ensure that the configured system is capable to host the applications and meet the system requirements. The allocation of the platform resources is an iterative process between the Architect and the application suppliers. It requires an extensive system toolbox to ensure that the Architect can correctly specify the allocation of resources for a particular partition in such a manner that the application supplier can design and develop their software in isolation to the remainder of the system components, yet the tool workflow must be sufficiently flexible to accommodate changes due to requirement modifications, requests for more resource allocations (e.g. CPU time, IO bandwidth), etc. Consequently, the system toolbox must be able to define, model and specify for each partition the I/O characteristics of the Time and Space Partitioning (TSP) system such as bandwith, latency, availability, and establishing hard real-time constraints for critical data, while ensuring the schedulability of the overall system. The system toolbox must be compatible with the avionics modelling language defined in other activities.
The activity shall therefore cover the following tasks: 1. Refine the existing understanding of the IMA-SP roles and processes and identify methods to improve the efficiency of the IMA-SP concept. Produce a set of guidelines documenting how to apply the roles and processes to the space domain. 2. Tools shall be developed to enable the System Architect to model the system in order to perform system design and allocate and optimise the use of the available resources, including the CPU time and I/O for each partition. The avionics architectural language shall be considered as input to the activity
The outputs from these tasks shall be installed and demonstrated within the ESTEC Avionics Lab Deliverables Software Impacts next generation of avionics for Telecoms, Earth Observation, Rovers, constellation, swarm, formation flying, Application/Need Date Navigation missions; also applicable for next generation avionics for Launchers Need date: 2013 to support future R&D work and system studies (see role of System Architect) Duration (Months) 18 Estimated Current TRL Prototype Target TRL Beta Software Open Source SW Clause Reference to ESTER T-1561, T-7751, T-7671, T-8414, T-8157, T-5224, T-8598 Code Avionics roadmap 1st semester 2010 Consistency with Harmonisation Activity D2
Page 115 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
TRP Reference T702-310SW Activity Title Security building blocks for flight software applications Objectives This study shall analyse existing spacecraft systems to identify critical applications that can be integrated together on to a common computing platform (possibly the central OBC) to reduce the number of on-board modules. Description In existing spacecraft avionics security critical applications responsible for ensuring the integrity of the mission are embedded within dedicated hardware modules to ensure that failures of common avionics and software do not cause a failure within the critical unit. With the development of secure partitioned avionics, it is now possible to migrate critical applications from their dedicated hardware modules into common computing nodes that could support multiple critical applications. This study shall analyse existing spacecraft systems to identify critical applications that can be integrated together on to a common computing platform (possibly the central OBC) to reduce the number of on-board modules. In addition, the migration of functionality from hardware into the software shall allow the update of these applications while in-flight. Deliverables Study Report Impacts next generation of avionics for dual-use missions: Telecoms, Earth Observation, Rovers, constellation, swarm, formation flying, Navigation missions, potential application to Human Space Flight (secure European restricted computing Application/Need Date nodes and data in collaborative programmes with other international partners, e.g. ISS) Need date: 2014 in order for outputs to be feed directly into future R&D activities Duration (Months) 12 Estimated Current TRL 1 Target TRL 2
SW Clause N/A Reference to ESTER T-7671, T-8414, T-8157, T-7803, T-5224, T-8598
Consistency with Harmonisation Activity K7 of the Avionics Embedded System proposed in June 2010 (not yet endorsed by IPC)
TRP Reference T705-304EC Activity Title AOCS SpW test bench preparation Objectives The SAVOIR AOCS interface working group recognised Spacewire as an important interface standard but raised a number of questions with respect to the system aspects of basing an AOCS on it (e.g. FDIR, redundancy etc). This activity will pave the way towards future avionics testing by the conceptual design of an AOCS architecture based on SpW. Description The activity will first analyse the impact of Spacewire on the sensors and actuators electrical, communication and functional interfaces. Main types of sensor and actuators shall be addressed (star trackers, sun sensors, gyros, reaction wheels, etc). Timing/synchronisation aspects will be analysed both for on-board control (delay, jitter) and for ground monitoring (TM time stamps). A representative mission will be proposed (e.g. Earth Observation in LEO) for which a preliminary design of AOCS based on Spacewire bus will be performed. The performance of main AOCS control loops performance will be analysed and checked by simulations. On Board SW will be prototyped for at least one representative AOCS Mode and basic FDIR mechanisms will also be developed and tested. Recommendations will be issued. Deliverables Study Report Application/Need Date 2013 Duration (Months) 24 Estimated Current TRL Algorithm Target TRL Prototype
SW Clause N/A Reference to ESTER T-7671
Consistency with Harmonisation Avionics Embedded Systems Activity O3
TRP Reference T705-305EC Activity Title RS-422 protocol standard for AOCS equipments Objectives Development and validation of an ESA standard for RS-422 based data communication implementation between AOCS equipment (star tracker, earth sensor, sun sensor, magnetorquer and reaction wheel) and the Data Handling system (be it AOCS Interface Unit, Remote Terminal or Command and Data Management Unit). This shall be a UART based implementation building on the current electrical standard and including the adoption or adaptation of a currently existing protocol layer but stopping short of TM/TC or data standardisation. The end goal should be to propose an update/ addition to the ECSS-E50-15 (Discrete interface standard) and will allow much easier implementation of RS-422 based equipment's from different suppliers on the s/c. Description The activity should cover an initial equipment interface survey, the development/adaptation of the protocol, the refinement and clarification of the interface options, definition of the UART implementation and demonstration of the interface with real equipment. Deliverables Study Report Application/Need Date 2012 Duration (Months) 9 Estimated Current TRL 1 Target TRL 2
SW Clause N/A Reference to ESTER T-7671
Consistency with Harmonisation Avionics Embedded Systems:Activity C2.
Page 116 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
TRP Reference T709-301GI Activity Title SM&C Services implementation for a PUS/SOIS based spacecraft Objectives A new standard (Spacecraft Monitoring and Control, SM&C) specifying the monitoring and control services to be offered by space systems is being defined within Consultative Committee for Space Data Systems (CCSDS). The standard is based on a technology and communication protocols independent implementation. In addition, the CCSDS Spacecraft Onboard Interface Services (CCSDS SOIS) family of standards will specify the on-board interfaces and services. All current and future ESA missions will however be designed in accordance with the Packet Utilisation Standard (PUS), which defines the ground-to-space interface to access the on-board monitoring and control services. The natural question is whether these three standards can be made compatible and how. A possible approach is to adopt the definition of the SM&C services in the ground interfaces between the monitoring and control kernel (the SM&C service provider) and the ancillary monitoring and control applications consuming these services (e.g. requesting the execution of a given action, receiving alerts in case of anomalies detected by the monitoring service, etc.). This activity will look into the feasibility of such an approach by prototyping an SM&C service provider for a PUS/SOIS based spacecraft. Description This study proposal addresses the issue of compatibility between the CCSDS SM&C and SOIS standards and the ECSS PUS standard. Each of these standards bring an added value and represent a useful reference for the definition and implementation of Monitoring and Control (M&C) kernels on ground. However, they are unfortunately defined independently from each other and show significant overlaps (especially between SM&C and PUS) and/or contradictions. As stated above, the SM&C philosophy is not to rely on any specific implementation and not even to address the split of responsibility between the controlling entity (ground) and the controlled entity (the spacecraft) in the monitoring and control activities. The PUS philosophy is entirely the opposite i.e. it defines exactly the ground/space interfaces enabling access to the M&C services provided by the controlled system (the spacecraft). In spite of these fundamental differences, the two standards can however be reconciled. The aim of this study is to examine the feasibility of mapping the SM&C services onto the PUS/SOIS based on-board implementation. A prototype will be developed which will be verified end-to-end by means of the (OPS) ground segment and (TEC) space segment test-beds. Deliverables Prototype Application/Need Date TRL 6 2013 Duration (Months) 15 Estimated Current TRL 2 Target TRL 5 Operational SW Clause Reference to ESTER T-8410 S/W Consistency with Harmonisation TBD
TRP Reference T709-306GI Activity Title File based Operations Objectives This study shall enable a consolidation of the reference architecture supporting the adoption of File based Operations for future ESA missions. Recently, an end-to-end concept has been elaborated, enabling the native exchange of files (in addition to packets) between the on-board and the ground applications. The adoption of File based Operations requires the support of additional data management services, both on the space and ground segment side. This activity will prototype a 'File enabled' ground segment and enable an end-to-end verification of the proposed implementation for a spacecraft supporting CCSDS File Delivery Protocol (CFDP), SOIS based File Storage/Management services and PUS services according to the revised version of this standard. The validation of this prototype will first be achieved by means of a light space segment simulator (enabling the demonstration of the concept and of its expected benefits) and eventually be end-to-end verified by interfacing with the space segment test bed managed by TEC-E. Description This activity will prototype the ground S/W enabling the adoption of the operational concept identified by the ESOC Working Group about File based Operations. Interactions with the ongoing revision of the Packet Utilisation Standard (PUS) are envisaged, as it is expected that the new standard will include the capability to manage and use files from within the space segment application layer and to expose these capabilities to ground by means of PUS services. The following phases are therefore foreseen:
A - Consolidation of the operational concept and collaboration with the PUS revision Working Group to identify the exact definition of the file based services
B - Definition of the reference architecture for ground data systems enabling the support of File based Operations
C - Implementation of a prototype demonstrating the concept and its expected benefits
D - End-to-end validation of the ground/space interactions using the OPS-E test-bed (supporting CFDP, and the file related SOIS services). Deliverables Prototype Application/Need Date All future ESA missions, 2013 TRL 5 Duration (Months) 18 Estimated Current TRL 3 Target TRL 5 Operational SW Clause Reference to ESTER T-98 S/W Activities B1, B2 and B3 of Avionics Embedded System roadmap proposed in June 2010 (to be endorsed by Consistency with Harmonisation IPC in Q1 2011)
Page 117 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
TRP Reference T710-301GF Activity Title Autonomous S/C manoeuvres Objectives The acrtivity aims to setup a ground flight dynamics system to evaluate autonomous S/C manoeuvres and payloads operations to maximise observation. Description Setup of a ground flight dynamics system to evaluate autonomous S/C manoeuvres and payloads operations to maximise observation. With increasing autonomy of both exploration and earth observations S/C the task of flight dynamics ground operations is shifting from classical commanding and execution to preparation of GNC inputs before and assessment of the autonomously executed S/C manoeuvres after the manoeuvre. The required tools can only be implemented in close cooperation with the experts for the onboard GNC systems. Vice versa the design and implementation of the relevant GNC onboard systems require a close interaction with the operations experts to ensure safe operations and to maximise the payload data return.
- Design and prototyping of flight dynamics system elements for: - Preparation of autonomous manoeuvres: Modelling the onboard GNC input and validating the settings. - Following the execution if possible, this is strongly depending on the S/C itself and the mission scenario. - Definition and assessment of performance parameters. Deliverables Software Application/Need Date 2012 Duration (Months) 24 Estimated Current TRL Prototype Target TRL Beta Software Operational SW Clause Reference to ESTER T-8828 S/W Consistency with Harmonisation N/A
TRP Reference T705-308EC Activity Title RDV and Docking 3D camera technology trade-off and BB demonstration Objectives Investigation of 3D camera technology for RDV docking and proximity operations. Such sensor has a very low maturity level but has a strong potential to drastically simplify GNC sensor suite and associated algorithms in critical phases. Description RDV, Docking and Proximity operations cameras all have a common set of requirements and represent one of the most demanding applications from a technological viewpoint (lifetime, accuracy, range and update rate). The applications listed generally need different resolutions, update rates and illumination types and give different outputs. The core technology (detector), once selected, will be the same and one technical challenge is to design a single piece of hardware that can be reconfigured in terms of internal operation, timings and image processing via software and internal h/w switching (e.g. different processing path in the FPGA/ ASIC) to be able to fullfil multiple roles during one mission. The activity will include an initial feasibility study defining the achievable performances and selecting the best technology. The requirements for each application will be consolidated. Breadboard demonstration and test of a basic 3D camera system will be performed, and recommendations for future work will be issued. Deliverables Breadboard Application/Need Date Future landers, rovers and RDV missions Duration (Months) 18 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-7817
Consistency with Harmonisation TBD
7 - 27 - End to End System Design Processes
TRP Reference T708-302QQ Activity Title System Level Integrated Failure Analysis Objectives Safety in complex systems can only be achieved through proper management structure and processes, system (hardware, software, human) hazard analyses, requirements modelling and analysis for completeness, system modelling, special SW design techniques, safety testing and verification and operational feedback. The current TRP activity focus is not on all these "ingredients" contributing to system safety but on a fraction of it. Namely, the proposed TRP activity aims to develop and demonstrate the benefits of an innovative failure analysis methodology for safety and dependability assurance on ESA projects, which supports: -dynamic and interactive failure modelling of complex technical systems ("dynamic complexity" induced failures), -modelling of human errors in spacecraft operations (human induced failures), -systematic modelling of organizational failures with dependability & safety consequences ("dependability & safety culture" induced failures), and allows the integration of modelling at various levels of system architecture for future ESA missions.
Page 118 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Description The current dependability & safety analysis methods as used on ESA projects such as Failure mode, effects, and criticality analysis (FMECA) and hazard analysis are limited as they do not model: -dynamic and interactive failures of hardware, software, human in increasingly complex technical systems, which have to be designed to be tolerant to such failures. In highly complex space systems, there can be system intrinsic feared events due to complex interaction. Such as: tight coupling and high interdependencies, which become intellectually unmanageable for an analyst due to e.g. the absence of randomness, logic problems in firmware/software algorithms, complex time dependences, rapid processes, unplanned and dysfunctional interactions (difficult to plan, understand, anticipate and control). -human error scenarios while the technical system and operation regime need to be designed to be tolerant to human errors. -errors or flaws in the organization and associated processes which can contribute to or directly cause technical failures as well as render operational failure recovery processes ineffective, such that consequences occur with impact on safety & mission success.
Such failures need to be analyzed and modelled to reduce the associated technical risks, but no suitable analysis method exists.
The TRP activity will develop these needed innovative system safety & dependability failure analysis methods, which shall allow integration of modelling at various levels of system architecture and address: -a dependability and safety analysis method capable to predict and model dynamic and interactive failures of hardware, software, human in highly complex technical systems, which will support hazard and failure reduction for highly complex space systems, -a human dependability analysis method based on the adaptation and experience from other industrial domains such as e.g. aviation, nuclear power/chemical plant operations and transportation, which will support human error control on ground and in space, and -an organizational failure analysis method capable to predict and model scenarios with organizational failure causes and consequences impacting safety & mission success.
The activity will focus in the definition and assessment of innovative safety & dependability failure analysis methods, in the application of the selected method(s) to Agency selected space system / space system of system cases, assessment of the potential benefits and identification of the context in which such methods could be applied (e.g. Phase 0, A, B, C/D). Deliverables Study Report Application/Need Date One of a kind missions, typically science missions / 2013 Duration (Months) 15 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-8845
Consistency with Harmonisation N/A
TRP Reference T708-304GD Activity Title Improvement of functional validation by analysis of operational problems Objectives The current approach to system and in particular Onboard Software (OBSW) validation is not able to find all possible problems. Some critical problems have been discovered only in the operational phase.
The objective of this study is to improve this process by making a detailed review of in flight incidents with the objective to identify alternative means to test the system. Description Based on recent operational experiences of ESA missions in-orbit problems with the OBSW shall be analysed. The objective of this analysis is: - to understand why the problem has not been identified in the different steps of the verification and validation activities leading up to the launch - to understand at what moment in the development and testing of the system this could have been detected - to analyse if there is a systematic issue with these problems - what process improvements would be necessary to increase the probability to discover these problems at the earliest moment Deliverables Study Report Application/Need Date All future missions would benefit. Duration (Months) 12 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-1561, T-303, T-7667
Consistency with Harmonisation No
TRP Reference T708-305SW Activity Title Formal approach to Space System Data Modelling Objectives
Page 119 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
To implement the concept of global conceptual modelling introduced within the ECSS-E-TM-10-23A Engineering Database technical memorandum, within the Monitoring and Control Data Modelling 2009/2010 TRP (i.e. contract reference 22080/08/NL/ST), formal means to specify conceptual models have been assessed and a prototype of a modelling tool, called FAMOUS for "FAct based Modelling Unifying System" has been developed. During this preliminary work, several issues have been identified that need further analysis and development prior to initiate the production of the FAMOUS operational tool. These issues are related to the need of extending the capability offered by the modelling language to also: - support the conceptual specification of the life cycle of the data, - support the conceptual specification of derived data, i.e. data that can be produced by combination of existing data.
For this purpose, a review of the capabilities offered by the "state of the art" research and development activities related to logic (e.g. ISO/IEC 24707) and other ontology's modelling methods (e.g. OWL2, RDF, SPARQL) and related tools (e.g. Protégé) will be performed to ensure the completeness (i.e. versus ECSS-E-TM_10-23A needs) and quality of the proposed solution.
Such capability, being developed (with reuse where adequate), will be integrated within FAMOUS and adapted to the needs of the different data modelling techniques supported by the tool. Description Developing space systems implies complex activities involving many parties who are widely distributed in location and time. Such development requires efficient and effective information exchange during the complete lifecycle of the space system. This can only be achieved by realizing semantic interoperability between all involved parties.
Within the 22080/08/NL/ST TRP contract, a first step has been performed in assessing how to solve the interoperability issue. Reusing the work performed by research institutes, the FAMOUS modelling tool has been prototyped implementing formal means to develop database systems according to a 3-level (i.e. conceptual, logical and physical) hierarchy of data models. Focusing on formalizing the development of database systems, this initial contract has addressed the methods and techniques related to relational databases and data exchange using XML. This new activity will first focus on: • assessing other methods and techniques used in the space business in order to support the modelling of any related database systems (i.e. other than relational, for example, hierarchical databases, object oriented databases), • augmenting the capability of the FAMOUS modelling methodology to cover the specific needs of specific methods and techniques, • offering a common modelling approach for any type of space system database.
Solving the issues of formalizing the development of space system databases is not sufficient. To enable interoperability, addditional work is required. As introduced in ECSS-E-TM-10-23, there is a need to address the semantic compatibility of the different conceptual models that constitutes the “System”, this is done by developing the ECSS-E-TM-10-23 global conceptual modelling concept, i.e. means to model at global level, i.e. serving the full space system community, the space system conceptual data, i.e standardizing this conceptual model for reuse at any lower level.
The new activity will also address these issues including: • the means to capture at conceptual level the different views that information may take (i.e. views that depend on the user needs) and to put into relations these different views, i.e. formalizing at conceptual level a language for specifying the transformation between these different views; • the means to automate the production of data transformation routines at physical level (i.e. transformation routines that are required when exchanging data between database systems). Taking into account the needs for data quality prior to operational use, the new activity will also address the modelling issues related to the life cycle of the data, i.e. formalizing at conceptual level a language for specifying this life cycle and producing at physical level, means to qualify the data when inside the local databases and during data exchange. The output of this new activity will consist of a second version of the FAMOUS modelling tool that includes all findings, thereby bringing it to a state where it can be used within a realistic environment, for verifying the adequacy of the ECSS-E-TM-10-23 global modelling concept and refining the functional needs for such an operational system, validating the adequacy of this overall modelling scenario to be used for enabling systems interoperability. Deliverables Prototype Immediately, for enhancing production of space system database software and allows production of (global) engineering Application/Need Date databases as of ECSS-E-TM-10-23. Duration (Months) 12 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-7863
Consistency with Harmonisation N/A
TRP Reference T708-306SW Activity Title System Functional Simulations in the Concurrent Design Process Objectives 1) Identification, feasibility analysis and integration of domain specific Simulation Tools and Simulation Models into a System Functional and Performance Simulations Infrastructure and instantiation of a System Concept Simulator. Specification of requirements of the Infrastructure and the System Concept Simulator are based on experiences, needs and use cases of the Concurrent Design Process.
2) Integration of the System Concept Simulator and corresponding processes with system databases and the Open Concurrent Design Server (OCDS).
3) Specification and development of a User Interface to the identified Infrastructure and the System Concept Simulator in favour of the System Engineer and his processes, and the a concurrent engineering study team in general. This includes visualisation of simulation results.
4) To investigate the feasibility and benefits of the System Concept Simulator as an output of the Concurrent Design Process (next to the currently existing Excel and OCDS-based parametric model), to serve as an input for the next phases. Description In the CDF context, different domain engineers (propulsion, power, etc) use different domain specific tools (Matlab/Simulink, STK, EcosimPro, Catia, etc) in support of domain-specific analysis. However, these domain engineers currently do not have the possibility to run these models in full system or mission context.
Page 120 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Also on system and mission level, the system engineer is often faced with analysis and verification questions regarding: -Design and Operational Constraints -Science Opportunity / Timelines -Ad hoc Dedicated / Specialised Issues
In addition quick turn-around 3D visualisation of the concept configuration of a mission with orbit trajectory, spacecraft attitude, pointing, kinematics and relevant celestial bodies is a much needed and very effective means of communication and clarification for the whole Concurrent Design Team.
In order to support both the concurrent design team and the system engineer of the concurrent design study, a System Functional and Performance Simulation Infrastructure that can be instantiated into a System Concept Simulator shall be developed. This System Concept Simulator can be composed of a combination of Simulation Tools and Simulation Models. These Simulation Models can originate from a system/mission library of models or can be the result of domain specific modelling (using the domain specific modelling tools). This System Concept Simulator can be considered as an output of the concurrent design study next to the current set of outputs, to be directly available at the start of the next phases.
Over the recent years enabling technologies (Simulation Model Portability standards and compatible simulation kernels) have been developed that allow for the porting Simulation Models from various modelling tools into an overall System Concept Simulator. E.g. by using SimVis in an architecture as depicted below, the Simulation Engineer is capable of composing a System Concept Simulator enabling functional verification and performance analysis on System and Mission level.
Currently however, the User Interface to this System Concept Simulator, very much needs specific Simulation Models and Software Engineering knowledge in order to execute and alter the simulation runs and analysis. By means of adding a System Engineering Layer as part of the System Functional and Performance Simulations Infrastructure the System Concept Simulator can be made accessible to every engineer.
In cases where it is not possible to directly port Simulation Models into the System Concept Simulator, integration of the Simulation Tools (rather than the Simulation Model) is proposed. By making smart combinations and configurations (even a-causal approaches) it is possible to integrate the tools and the overall System Concept Simulator into the OCDS environment, allowing early functional and performance modelling.
In order to preserve consistency with the design model, the exchange of the Simulation Models and corresponding parameterisation has to follow the OCDS process. Similarly, simulation results and analysis results and the feedback to the domain specific engineer also have to follow the OCDS and the concurrent engineering processes. Deliverables Software Application/Need Date 2013 Duration (Months) 18 Estimated Current TRL Prototype Target TRL Beta Software Operational SW Clause Reference to ESTER T-7834 S/W Consistency with Harmonisation No
TRP Reference T708-307SW Activity Title System Verification throughout the life-cycle Objectives Develop methods and define supporting tools for system requirements verification along the life-cycle. Formalisation of the process shall be specified, link to the relevant system data model established and a required supporting infrastructure be demonstrated Description After an analysis of the existing processes in industry, the relevant standards in the field (such as ECSS-E-ST-10-02) the activity shall provide a formalisation of the verification process, an identification of the required data description (based on system engineering datamodel) and specify a suitable informatics infrastructure to support this process.
This includes the need to formalise the process to generate a VCD-equivalent, enable the traceability of all engineering, design and testing information to facilitate the formal closure of requirements.
Starting from properly defined requirements, verification constraints can be derived, observables defined, and links to existing design, analysis and / or simulation definitions be established. This process needs to be set up at phase B, allowing a continuous monitoring of verification status of system requirements. Possibilities of early testing based on (virtual) models and the inclusion of the relevant information shall also be addressed.
Boundary constraints to be taken into account include in particular customer / supplier interfaces (such as between the Agency and system integrators, and between system integrators and lower-level suppliers). Transparency and confidentiality issues shall be taken into account. Deliverables Prototype Application/Need Date All ESA programmes, 2014 Duration (Months) 15 Estimated Current TRL Algorithm Target TRL Prototype Open Source SW Clause Reference to ESTER T-7863, T-1073 Code Consistency with Harmonisation TBD
TRP Reference T708-308GI Activity Title Standardised M&C interfaces for ground equipment
Page 121 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Objectives The main objective of this study is to verify the applicability to the mission operations involving ground stations equipment of the Monitoring and Control (M&C) interfaces defined by the Harmonisation project for the EGSE equipment. The existence of common interfaces/services supporting the monitoring and control of pre- and post-launch ground equipment would progressively enable the adoption of harmonised concepts, standards and implementations across mission phases. Description The M&C interfaces specified as part of the harmonisation project have been designed taking into account the pre-launch scenarios involving the operations of ground support equipment. Its applicability to the mission operations of ground station equipment will be explored as part of this activity, with the objective to consolidate the outputs of the Harmonisation project and to promote the adoption of common solutions across mission phases. Deliverables Prototype Application/Need Date ESOC Common Monitoring and Control Platform, European Common Ground System Core (EGCS-C), 2014 Duration (Months) 15 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-7292, T-1238
Consistency with Harmonisation TBD
TRP Reference T708-310SY Activity Title Integration of early system modelling into the concurrent design process Objectives To establish a coherent set of open standards for the integration and interoperability of early functional modelling at system level into Phase 0 / A / B concurrent engineering Description In concurrent design centres throughout Europe there is a need to improve the early integrated system modelling capabilities, in particular to have the capability to efficiently create and run executable simulators that represent the system structure (decompositions, shape, interfaces) and behaviour (functions, mission trajectory, attitude & pointing, moving parts, discipline-specific phenomena). The simulation environment should allow to integrate discipline-specific simulation models, e.g. for mission analysis, configuration (including simple kinematics), GNC, AOCS, power, thermal, propulsion, aero-thermo-dynamics. This is part of the trend to move from a document-centric to a model-centric approach to system engineering, labelled as Model Based Systems Engineering (MBSE) by INCOSE. Some elements for the environment are already available but they mainly exist of tool-specific point-to-point solutions. The concepts and approaches defined in the following ECSS parts shall be taken into account: -E-TM-10-20 Product data exchange; -E-TM-10-21 Modelling and simulation; -E-TM-10-23 Space system data repository; -E-TM-10-25 Engineering design model data exchange; -E-TM-40-07 Simulation model portability (SMP). In addition the following standards shall be taken into account: -OMG Systems Modelling Language (SysML) -X3D from Web3D (http://www.web3d.org/x3d/) -XSD, XML -Webservice support: WSDL, SOAP, JSON, RESTful http -ISO 10303 Exchange of product model data (STEP) -STEP-NRF and STEP-TAS -PDF / U3D (for final delivery / presentation purposes) The simulation environment shall interface with the Open Concurrent Design Server (OCDS) environment for concurrent design facilities. OCDS is the first implementation of E-TM-10-25, and will gradually replace use of the existing Excel based IDM (Integrated Design Model) in the ESTEC CDF and other concurrent design centres in Europe from mid-2010 onwards. As a target it shall become possible to exchange data between the following applications: OCDS/Excel, STK, Matlab/Simulink, Catia (limited to simple phase 0/A models), SimVis, EcosimPro, TCDT, MagicDraw SysML. Findings and recommendations from the following TRP activities shall be explicitly taken into account: -Virtual Spacecraft Design (VSD): completion expected early 2011; -Next Generation Requirements Engineering: completion expected mid 2011. Given the use of Eclipse, the Eclipse Modelling Framework (EMF) / Ecore and the Model Driven Architecture (MDA) approaches to (software) model transformation and code generation in VSD, it is likely that also these should be taken into account.
Outputs: -List of open standards for integration and interoperability of system and discipline-specific models into an overall executable system model framework. -Handbook with guidelines on how to use these standards to achieve early integrated executable simulators. -Data mapping specifications and prototype data adapters for a selected subset of engineering support tools used in concurrent design centres. -Final report, including recommendations for merge of ECSS E-TM-10-25 and E-TM-10-23 into one "Space system data repository" standard. Deliverables Prototype Application/Need Date 2011-Q4 Duration (Months) 9 Estimated Current TRL N/A Target TRL N/A
SW Clause N/A Reference to ESTER T-1073
Current System modelling and simulation tools roadmap does not extend beyond 2010. This activity is Consistency with Harmonisation continuation of A1 and B1 of the roadmap.
Page 122 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
TRP Reference T708-311EE Activity Title Interoperability for Space Environment Analysis Tools Objectives Improve the interoperability of space environment and effects tools by consistent data management among the tools Description Improve the interoperability of GEANT4, SPIS and ESABASE2 as well as other industry space environment and effects tools, and provide for their integration in space system end-to-end design. Particular attention will be given to those tools which need a detailed geometrical model of the system. The activity will consolidate and further extend the recently developed STEP-SPE protocol, updating it in line with the latest STEP-TAS protocol and creating a truely open source version. STEP-SPE and GDML interfaces will be implemented/consolidated in ESABASE2 and other selected industrial space environment software. A data hub base on STEP-SPE will be developed for use by space environment software in line with similar developments in the thermal domain (TASVerter). Deliverables Software Application/Need Date 2011 Duration (Months) 18 Estimated Current TRL Prototype Target TRL Software Release Open Source SW Clause Reference to ESTER T-7765, T-7594 Code Consistency with Harmonisation Consistent with harmonisation "Radiation Effects Tools" aims C10 (data exchange), C11 (user interfaces).
TRP Reference T708-312MS Activity Title Efficient Multi-Disciplinary product data exchange for Space System design and development Objectives This activity has three objectives: 1. Establishing a complete "chart" with all Space Engineering disciplines and their specific requirements for computer interpretable product data. This shall be based on the Spacecraft design and development process and the discipline specific design and analysis/verification tools. 2. Defining the best procedures for the product data exchange for the process and tools identified under 1, based on available standards. 3. Identifying the limitations, current shortcomings and necessary further developments to improve the use of computer interpretable product data resulting from parts 1. and 2. Description The 3D design tools (Computer Aided Design - CAD) provide a powerful tool to establish a physical representation of a product (Spacecraft or sub-system thereof). Various domains (Mechanical, Thermal, Aerodymanical, Optical, Attitude Control, Antenna Design, Functional verification, etc). require some level of representation of the 3D CAD model. It is highly inefficient to model a 3D representation of a Spacecraft or sub-system again and again in different tools. Re-use of a "central" 3D representation of the design will improve use, reduce time and errors and improves traceability of data. In the last decades many have made an effort to provide definitions and tools. In the last decades many have made an effort to provide definitions and tools. For the exchange of computer interpretable data from this 3D model to the different domains tools. In the ECSS standards, specifically ECSS-E-10-07 (Product Data Exchange), a reference can be found for the methods and tools for this data exchange. E-10-07 refers to the ISO 10303 standard for product data exchange (also referred to as STEP). This provides a way to exchange product data via a neutral (modelling tool independent) format. However, different tools require different data and level of detail for the design-analysis-verification in their discipline of application. In order to improve the use of product data between disciplines (and even between industry and ESA), clear requirements of which part of a model is required for which particular data exchange for which application. Deliverables Study Report Application/Need Date Immediately Duration (Months) 10 Estimated Current TRL N/A Target TRL N/A
SW Clause N/A Reference to ESTER T-7594
Consistency with Harmonisation N/A
TRP Reference T708-316IR Activity Title Analysis of S/C qualification sequence & environmental testing Objectives On the base of practical experience and anomalies reported, either on-ground or in-flight, this study shall analyze and evaluate the effectiveness of current environmental testing and recommend optimized procedures Description
Page 123 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Environmental testing is a vital part of S/C qualification procedures. However, there are many debates on the value and interest of environmental testing: at equipment level, in particular for recurrent models; at system level for acoustic testing, thermal vacuum testing, random testing. There is a lack of exploitation of development and in-flight data of European satellites, including those developed for commercial market, for ESA, or national agencies. The sharing of this exploitation should be of benefit for all European S/C. It could be used for decision making and to substantiate or evaluate the interest of performing such tests, giving the significant impact on costs and planning. This activity shall exploit at least the data of ESA S/C and launchers that have been launched since 1995. Inclusion of non ESA projects is an asset.
Work to be performed includes: 1. Analysis of the test plans for equipment, nominal and recurrent, 2. Analysis of anomalies detected during the tests: type of anomaly,( design error, workmanship). 3. Link with type of test and when in the sequence,( number of cycles, temperature range, level of load for example). 4. Analysis of subsystem and satellite/launcher tests performed. - Type of anomalies detected,( design, integration, workmanship, interface problems) during what kind of test. - For anomalies: what was seen at s/s system or equipment level .
From this analysis, conclusion should be made in terms of usefulness of tests to detect flaws: severity of the test, type of anomaly, characteristic of equipment,… Furthermore, a link between efficiency of the testing and the development philosophy should be established: low cost, proto flight model, no engineering model,…full ECSS rules, … Deliverables Recommendations on Environmental Testing Application/Need Date 2014 Duration (Months) 24 Estimated Current TRL N/A Target TRL N/A
SW Clause N/A Reference to ESTER
Consistency with Harmonisation TBD
TRP Reference T708-309EE Activity Title Parametric electromagnetic models Objectives To implement an open system for antenna design, antenna interactions and Electromagnetic Compatibility (EMC) problems, based on the parametric combination of simple fast and accurate slow models, also in combination with measurements, suitable for payload and system simulations and verification. Description Rather sophisticated electromagnetic models are required for accurate performance prediction in Phase B and C/D, for both antenna development and for payload and system level simulations with regards to antenna interactions and EMC. Current approaches to the problem, based on the exchange of large performance data files are quite rigid and inefficient as they make iteration and what-if analysis rather cumbersome. Furthermore the longstanding issue of reconditioning of spacecraft CAD models to the need of electromagnetic simulation has a strong impact on the quality and reliability of results. Parametric techniques to model antenna performances with sufficient accuracy for use in payload and system simulators have been recently developed and applied, among others, to antenna synthesis problems and can be exploited to ease the combination of fast high-level models, offering complete support to parametric analysis, fast iteration and what-if analysis, with slow accurate ones offering very reliable performance predictions. At the same time the accuracy and speed of detailed simulations can be improved by implementing CAD re-conditioning facilities. These need to be based on electromagnetic ground to ensure their effectiveness and, at the same, time exploit advance computational geometry algorithm to ensure robustness and generality. The advantage of a computational-geometry-based approach has been shown over the past decade by several developments funded by the Agency in the area of high-frequency scattering analysis for Antenna interactions (ESTEC C.No. 15771/01/NL/LvH and 18802/04/NL/JD). A prototype high-level modelling antenna tool aimed at Phase0/A studies has shown the feasibility of such combination of high-level models and low-level tools (ESTEC C.No. 21961/08/NL/ST) on a limited scale, using simplified versions of the low-level tool adequate for feasibility studies and without considering their chaining into complex computational procedures as required for detailed analyses. Furthermore there is today a good selection of platforms offering the basic services required to effectively combine models with different level of accuracy and speed, for instance the Agency Open Simulation Framework. Finally, the evolution of computing platforms and of optimisation algorithms makes it possible to incorporate into such system a service to allow full scale configuration optimisation. The collection of tools to be addressed shall guarantee a full coverage of main stream space missions and comply with modelling needs across the whole development cycle, from early sizing activities to flight acceptance. The objective of the activity is to deliver a proof-of-concept demonstrator based as far as possible on existing tools and open to future extensions. Deliverables Prototype Application/Need Date All missions / 2014 Duration (Months) 24 Estimated Current TRL Algorithm Target TRL Prototype
SW Clause N/A Reference to ESTER T-8396, T-7863, T-7594
Consistency with Harmonisation No
7 - 28 - Electronic Components
TRP Reference T701-316ED
Page 124 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Activity Title Dynamic Latchup protection chip for COTS components Objectives Development of a stand alone chip that is able to shut down the component and holds it powered-down for a preset time. Phase 1 Definition of requirements and scenario of potential usages, Architectural design Phase 2 Detailed Design, Breadboarding, Cost estimation and supplier identification for ASIC/Hybrid solution Phase 3 ASIC/Hybrid development Phase 4 ASIC/HYbrid implementation & Qualification Description The use of Commercial Off the Shelf (COTS) components is and will always be an option to achieve space system performances that cannot be achieved with available space qualified components. For such components that are not latchup proof by design the use of protection circuitry is essential. In this activity, a highly reliable analogue or mixed signal protection chip shall be designed which provides the following functions: - protection of the COTS target chip from damaging effects of a latchup - possibility for programming (hardwired) maximum currents in a wide range daisy chaining of such chips for protection / concurrent switch-off of multiple supply voltages signalling the occurrence of latchup to a monitoring chip/ processor via a simple interface (interrupt line) automated recovery after a programmable time, or controlled recovery via an enable input connected to a monitoring chip / processor (pin programmable) control of external components for supply currents higher than those that the chip can sustain in standalone mode.
The chip shall be developed, prototyped and tested under realistic conditions (radiation, load, latchup) for a range of latchup-capable target chips. Deliverables Prototype Application will be immediate as Latch Up (LU) sensitive components are already used but the new device will considerably Application/Need Date simplify the design of the protection electronics. Duration (Months) 18 Estimated Current TRL 2 Target TRL 5
SW Clause N/A Reference to ESTER T-697, T-8658, T-7800, T-8845, T-8064
Consistency with Harmonisation TBD
TRP Reference T723-301QE Activity Title Utilisation of a Heavy and Light Ion Facility at UCL for Component Radiation Studies Objectives To utilise, improve and maintain the capabilities of the UCL Heavy Ion (HI) and Light Ion (LI) irradiation test facility for the purpose of characterising Single Event Effects (SEE) in Electrical, Electronic and Electromechanical (EEE) components for flight on ESA missions and missions developed by European industry. Description This activity concerns execution of regular irradiation test campaigns on Electrical, Electronic and Electromechanical (EEE) components for flight on ESA and European space missions. Up to 360 hours per year of beam time is available free of charge on a priority basis for ESA. Additionally, a minimum of 500 hours per year is available for ESA sub-contractors, research institutes and other interested users at preferential hourly rates. The agency provides the facility with a detailed work programme of the test campaigns. Subsequently, the facility performs test campaign scheduling (in agreement with the Agency). Deliverables Beam time, operation report Application/Need Date 3 years, from January 2011 to December 2013 Duration (Months) 36 Estimated Current TRL N/A Target TRL N/A
SW Clause N/A Reference to ESTER T-7888
Consistency with Harmonisation TBD
TRP Reference T723-302QE Activity Title Utilisation of the High Energy Heavy Ion Test Facility at JYFL for Component Radiation Studies Objectives To utilise, improve and maintain the capabilities of the RADEF High Energy Heavy Ion (HI) irradiation test facility for the purpose of characterising Single Event Effects (SEE) in EEE components for flight on ESA missions and missions developed by European industry. Description This activity concerns execution of regular irradiation test campaigns on EEE components for flight on ESA and European space missions. Up to 240 hours per year of beam time is available free of charge on a priority basis for ESA. Additionally a minimum of 500 hours per year is available for ESA sub-contractors, research institutes and other interested users at preferential hourly rates. The agency provides the facility with a detailed work programme of the test campaigns. Subsequently, the facility performs test campaign scheduling (in agreement with the Agency). Deliverables Beam time, operation report Application/Need Date 3 years, from January 2011 to December 2013, 120kEuros per year (360kEuros total) Duration (Months) 36 Estimated Current TRL N/A Target TRL N/A
SW Clause N/A Reference to ESTER T-7888
Page 125 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Consistency with Harmonisation TBD
TRP Reference T723-303QE Activity Title Utilisation of the Proton Irradiation Facility at PSI for Component Radiation Studies Objectives To utilise, improve and maintain the capabilities of the PSI High Energy Proton irradiation test facility for the purpose of characterising Single Event Effects (SEE) and Displacement Damage (DD) effects in Electrical, Electronic and Electromechanical (EEE) components for flight on ESA missions and missions developed by European industry. Description This activity concerns execution of regular irradiation test campaigns on EEE components for flight on ESA and European space missions. Up to 240 hours per year of beam time is available free of charge on a priority basis for ESA. Additionally, a minimum of 500 hours per year is available for ESA sub-contractors, research institutes and other interested users at preferential hourly rates. The agency provides the facility with a detailed work programme of the test campaigns. Subsequently, the facility performs test campaign scheduling (in agreement with the Agency). Deliverables Beam time, operation reports Application/Need Date 3 years, from January 2011 to December 2013, 120kEuros per year (360kEuros total) Duration (Months) 36 Estimated Current TRL N/A Target TRL N/A
SW Clause N/A Reference to ESTER T-7888
Consistency with Harmonisation TBD
TRP Reference T723-304QT Activity Title 16-bit ADC Objectives Today there is no solution in Europe for high speed AFE (analogue front end) to process and digitalize Complementary metal-oxide-semiconductor (CMOS) output signal. The objective of this activity is to design, manufacture and test a high speed and high resolution encoder for CMOS detector meeting EO requirements with the following characteristics: 16 bits 10-20 Mpps Description The main tasks will be: -design -Foundry -Test of performances with existing CMOS detectors -Radiation tests Deliverables Breadboard Application/Need Date EO, SCI, Exploration missions Duration (Months) 24 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-720, T-7886
Consistency with Harmonisation TBD
TRP Reference T723-305QT Activity Title Evaluation and characterisation of a harmonised mixed signal ASIC flow Objectives Evaluate and characterise a common harmonised flow for the design, evaluation and qualification of mixed signal application-specific integrated circuit (ASICs) with the list of preferable foundries and assembly & test houses for mixed signal ASICs based on space user needs and applications from the preceding ECI-3 proposed activity. Description
Page 126 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Currently design, evaluation and qualification is tied to the practices of the individual design companies and/or foundries, with detrimental effects to cost, time and project risk exposure to a single source. Infineon, AMS, IHP, AMIS/ON Semiconductor, ST Microelectronics, UMC and XFAB have been used to produce mixed-signal ASICs for space with each following a different approach to design, evaluation and qualification. It is considered that a common harmonised flow for the design, evaluation and qualification of mixed signal ASICs will reduce development at the design stage by reuse/portability of IPs on different processes with tools like Bindkey, Sifix and Anaconda, reduce single source dependency on manufacturers, packaging and test-houses and reduce cost by drawing on qualification heritage. This common harmonised flow needs to be identified from the different processes and applications and ultimately lead to a "qualified" process or foundry and "qualified" assembly & test house.
This activity, also included in the CTB Silicon Dossier, shall evaluate and characterise the mentioned common harmonised flow. The coordination will be quite complex due to the large number of companies involved, as the design, wafer processing, packaging and test may be performed by separate companies. The approach shall look to complete evaluations of the design house, wafer fab, assembly and test house including audits of each. Following these evaluations an evaluation test programme shall be defined and executed (electrical characteristics, mechanical stress, environmental stress, endurance, radiation and construction analysis) shall be performed. Deliverables ETP Completion TAS intends to use this technology in several types of applications such as interfacing with RF equipment, Telenetry/Telecommands (TM/TC) functions in payloads and platforms, and particularly in earth observation for interfacing Application/Need Date with Charge Coupled Device (CCD) detectors. Depending on capabilities it might also be used in Power Control & Distribution Units (PCDUs). Astrium intends to use mixed signal asic for interface applications, TM/TC functions and for integration of discrete low/ medium complexity of analogue & digital functions today. Need date is 2011. Duration (Months) 24 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-8448, T-7795
Consistency with Harmonisation To be included in the next Microelectronics roadmap (2011)
TRP Reference T723-306QE Radiation Characterisation of GaAs MESFETs in support of European Radiation Hardness Assurance Standard and Activity Title Irradiation Test Guideline Objectives The objective of this activity is to perform a heavy ion irradiation characterisation on a large number of GaAs MESFET devices from different manufacturers and technologies to improve the radiation hardness assurance process and irradiation test guidelines, to identify technologies sensitive to radiation, and to derive Safe Operating Areas for these technologies. Additionally, this activity aims at sampling a range of other GaAs RF devices to identify their SEE susceptibility. Description Recent irradiation tests on Gallium Arsenide (GaAs) Metal-Semiconductor Field-Effect-Transistors (MESFET) show that GaAs MESFETs can be susceptible to destructive single event effects (SEE). Susceptibility has been observed in RF application conditions and static bias condition with high drain voltage. The correlation of the susceptibility in RF application conditions and influence of static bias condition is not fully understood. This issue needs to be investigated in support of development of ECSS radiation hardness assurance standard and ESCC SEE irradiation test guideline. A representative selection of GaAs MESFETs devices (and sample GaAs RF devices) from different manufacturers and technologies shall be selected and procured for irradiation characterisation. A Heavy Ion radiation test plan shall be defined and implemented to : 1.identify technology dependence of SEE sensitivity 2.obtain correlation between DC and RF testing (worst case test condition) 3.better define Safe Operating Area 4.improve GaAs RF component related Radiation Hardness Assurance procedures
The results will be used to update the ECSS Radiation Hardness Assurance standard and ESCC 25100 SEE irradiation test guideline/method. Deliverables Study Report Application/Need Date Q2-2012 Duration (Months) 12 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-7888
Consistency with Harmonisation activity F3 of Radiation Testing and Facilities Roadmap
TRP Reference T723-307QT Activity Title Development of a monolithic pulse-width-modulated (PWM)IC. Objectives Develop and evaluate a standard Pulse Width Modulator (PWM) integrated circuit (IC). Such a device shall withstand without degradation a total dose level of at least 100krads and shall not be latch-up sensitive in the usual space radiation environment. In order to avoid the risk of ITAR issues, the development shall be performed using a fully European design house and foundry. Description
Page 127 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
DC/DC converters destined for space applications have in the past presented serious problems to the designer. Regarding specifically the control aspects of the DC/DC converter, many of the problems are derived from the fact that the IC controllers used were not initially conceived for space-borne products. In general, they are up-screened MIL-quality parts with limited radiation test data, intended for low total doses that barely justify their use. In addition these devices show dose rate dependency and high variation. Also, these non-European products appear and disappear from the catalogue and are exposed to obsolescence without notice and control.
The activity, consistent also with the CTB (Component Technology Board) Silicon Dossier shall consist of conducting a technology and market study in order to firstly understand if the PWM controller answers to a big enough market to become a standard in the vast majority of DC-DC converters for space applications and secondly if the development and the recurrent costs remain competitive. A technology feasibility assessment shall be performed to assess the existing manufacturing capability for the production of a radiation hardened PWM controller, to identify the most promising technologies and lines of products that shall best suit the space application constraints in terms of performance and radiation tolerance. Any radiation data already obtained for the selected device type(s), if any, shall be shared with the Agency.
The Pulse Width Modulator (PWM) specification shall be developed during the course of this activity, while the design, manufacture and characterisation of PWM prototypes shall lead to the definition of a draft PWM controller specification. Deliverables Prototype All types of space applications are considered, including Earth Observation, Science, Telecoms & Navigation. Need date is Application/Need Date 2011. Duration (Months) 24 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-8448
activity C1 (Development of a European Supply Controller) in the Power Management and Distribution Consistency with Harmonisation harmonised roadmap
TRP Reference T723-308QT Activity Title Validation and experimental verification of ESA MEMS qualification methodology Objectives A Micro-Electro-Mechanical Systems (MEMS) qualification methodology has been drafted in the frame of a previous Portuguese Task Force activity. The draft methodology is available today but requires further reviews by the European MEMS community and additional experimental validation. These are the two major objectives of this proposal. Today the methodology has established more than 20 classes of MEMS and subsequent qualification has been defined for each class. Description MEMS are technology is becoming more and more important, and their use in space is very promising. However, they because of their potential diversity and specificity they will require the developemnt of new verification methodologies. More specifically, MEMS qualification standard procedures is required. The subject has been discussed in the frame of the CTB (Component Technology Board), e.g. ref to the MNT - miniaturization - dossier, as well as in a number of harmonisation dossiers. The proposed activity will focus on 5 major steps: Task 1: review of the existing draft Micro-Electro-Mechanical Systems (MEMS) qualification methodology by European research institutes, critical assessment of the failure mode and associated Failure Modes and Effects Analysis (FMEA)defined in the previous contract. Task 2: refinement of the draft methodology, simplification (reduction of the number of MEMS classes) and definition of the experimental validation testing for Task 3 Task 3 Manufacturing of adequate test vehicles for the experimental verification Task 4 Experimental testing, the major test qualification plan should be carried out to validate their efficiency and adequacy Task 5 Finalisation, preparation of the final ESA MEMS qualification methodology for further processing at ECSS or/and ESCC level. Deliverables Study Report Immediate, for the moment MEMS qualification for project level; are being done on a case by case basis (ex S3 gyro) but Application/Need Date standardisation is rapidly required Duration (Months) 20 Estimated Current TRL N/A Target TRL N/A T-7753, T-8335, T-8448, T-857, T-8722, T-8776, T-8803, T-7819, T-7818, T-7747, SW Clause N/A Reference to ESTER T-7830, T-7832, T-7861, T-8444, T-8057, T-7746 Consistency with Harmonisation N/A
TRP Reference T723-309QT Activity Title Prototyping and characterization of 1200V, Schottky SiC shottky diode Objectives Development, prototyping and characterization of 1200V SiC Schottky diode for Travelling WaveTube Amplifier (TWTA) application
Description The study will be focused on the developing of 5A 1200V Silicon Carbide (SiC) Schottky diode in hermetic package with the main goal to characterize the performances of the devices in terms of switching capability, reliability of the technology and main characterization of static and dynamic parameters as a function of temperatures as well as to characterize the thermal impedance and resistance of the proposed package solution. The device will also be characterized the tolerance of the device to Total Ionizing Dose (TID) and proton fluence in order to evaluate their potential future application in space missions. The goal is having a device whose electrical characteristics are enveloping the performances of the devices already available on the market:
Page 128 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
- Zero Reverse Recovery Current - Zero Forward Recovery Voltage - Temperature independent switching behaviour - Low figure of merit QC/IF where QC is the total capacitive charge (goal is QC<20nC) - Package in TO-257 or LCC style As one of the main feature of SiC compound is the high thermal conductivity (around twice the Si one) the maximum operating junction temperature and consequently the maximum power density is expected higher with respect the Si devices. The reliability of the developed diodes should as well be assessed in this study establishing a limit for the junction temperature for reliable operation as well as the thermal properties of the package At the present stage, the SiC Schottky devices have been already commercialized for mainly automotive market, but the developing and evaluation of an hermetic 1200V SiC Schottky diodes would be appealing for TWTA and other space voltage space application due to the demonstrated performances of the devices on the market.
The study will be organized with the following work structure: -Phase 1: critical analysis of the technical requirements, compliance matrix of goal values for the main key parameters -Phase 2: trade-off analysis of the main design structure and topology with relevant simulation -Phase 3: manufacturing processes definition and main trade-off analysis, first issue of draft Process Identification Document (PID), first run in foundry -Phase 4: Electrical characterization and stability verification of first run in foundry and analysis of the results -Phase 5: Review of the manufacturing processes implementing any corrective actions come from the previous phase, second issue of PID and second run in foundry -Phase 6: Definition of the electrical and thermal resistance/impedance characterization, reliability assessment and radiation test program. For the overall test program the sample size should be at least 100 devices. -Phase 7: critical analysis of test results. Reliability analysis and identification of future activities needed to qualification of the device, analysis of manufacturing cost and forecast of yield. Deliverables Test Report For any TWTA and high voltage application. The availability of qualified product for space application can be foreseen in 2 Application/Need Date years, starting with this study. Duration (Months) 18 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-259
Consistency with Harmonisation N/A
TRP Reference T723-310QE Device simulation of the single-event-burnout (SEB) and gate rupture (SEGR) in Si Power MOSFETs in support of European Activity Title Radiation Hardness Assurance Standard and Irradiation Test Guidelines Objectives To support recommendations for the RHA test methodologies and to update ESCC25100 SEE Radiation Test Guideline with simulations of the power Metal–Oxide–Semiconductor Field-Effect transistor (MOSFET) SEB and SEGR response to heavy ion irradiation Description This activity concerns the simulation of destructive events, SEB and SEGR, in power MOSFETs under heavy ion irradiation. Modelling of the underlying physical mechanisms will be implemented and developed in a device code. Several types of power MOSFETs, representatives of typical commercial devices, of different nominal voltage, will be simulated. The effects of the ion species and energy will be studied and compared with experimental results from the literature. The determination of worst-case conditions, not necessarily the same for SEB and SEGR, will support the European Radiation Hardness Assurance Standard and Irradiation Test Guideline. Deliverables Study Report Application/Need Date January 2011 Duration (Months) 18 Estimated Current TRL 3 Target TRL 5
SW Clause N/A Reference to ESTER T-7888
Consistency with Harmonisation TBD
TRP Reference T723-311QT Activity Title Development of Semi-Conductive Layer Insulation Cables Objectives Design and develop a Semi-conductive Layer Insulation Cables taking into consideration space environments. Description
Page 129 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Electrostatic charging and discharges phenomena represent a well-known issue of currently available cables by affecting data signal integrity or high voltage cable reliability.
In order to avoid such issues, new cable construction shall be defined, by considering a semi-conductive layer which will allow evacuation of charges. This technique may lead improvement of cable properties of the cable: -protection of the electrical components sensitive to tension or current spikes -improvement of the high and very high voltage cables lifetime -preservation of the electrical signal's quality in case of signal cables or coaxial cables.
A technology survey and a trade off shall be carried out in order to determine the techniques and materials able to meet the electrical and physical requirements as well as the mass constraints of space application. Selected solution and application domain will be described through detail specification, Process Identification Document. Characterization of the cables shall be performed and an evaluation test plan proposed in order to determine physical margin of the product and the associated failure modes. A synthesis shall provide guidelines and utilization recommendation regarding to the evaluation results. The subject of the proposed activity will also be included in the 2011 CTB (Component Technology Board) Passives Dossier. Deliverables Survey, PID, specification, Test report, samples Application/Need Date Earth Observation, Telecommunication, Generic Purpose / 2013 Duration (Months) 24 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-7890, T-8659
Consistency with Harmonisation N/A
TRP Reference T723-312QT Activity Title Manufacturing and preliminary space assessment of a new multi-channel silicon photodiode for optical encoders. Objectives The main goal of this activity is to accomplish the manufacturing and the assembly of a batch and the completion of a preliminary space assessment program on a new reference of photodiode for optical encoder purposes. Silicon photodiodes arrays are suitable components for the new architectures of the future European optical encoders, manufactured by Codechamp. They may assure an higher degree of hardening versus radiations and improve the performances of the system, providing more flexibility. Description The current 22 bits encoder generation uses custom 8 channel Phototransistors initially supplied by the US company Micropac. Other typologies of receivers are necessary to achieve a higher level of robustness, a higher degree of hardening versus radiations and to improve the performances of the system. Silicon photodiodes arrays are suitable components to achieve these improvements and are suitable for the new architectures of the future European optical encoders.
The CNES carried out in 2007 and in 2008 with Adveotec a first R&D activity on photodiodes. Several references of commercial photodiode matrixes revealed a good hardness versus radiations and ageing. In particular, Centronic was retained as a major candidate for the development and manufacturing of a new source of custom photodiode matrix, including a pre amplifier stage, for optical encoders.
The CNES is currently running a second activity with Centronic and Adveotec. The contract concerns mainly two tasks: -A short radiation preliminary evaluation program on some samples manufactured with an implant process. The objective is to raise as soon as possible potential issues related to the implant process that could affect the reliability of the devices for a space mission. -The objective is to design a new source of 8 channel photodiodes for optical encoders. CNES and ESA agreed that from September 2010, ESA will be involved as observer to follow this CNES activity
The main goal of this TRP activity is a follow-up of the preliminary work from the CNES activity and consists to accomplish the manufacturing and the assembly of a batch and perform a preliminary space assessment program on the new reference of the photodiode.
In summary the activity has the following goals: - Foundry - Assembly - Preliminary radiation and ageing tests Deliverables Breadboard Application/Need Date optical encoders (earth observation satellites, telecom, scientific mission etc.) Duration (Months) 18 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-8587, T-7889
Consistency with Harmonisation TBD
TRP Reference T723-314QE Activity Title Part to part and lot to lot variability study of TID effects in bipolar linear devices Objectives To minimize the risk of using non hardened bipolar linear devices in space systems by defining adequate radiation design margins and policies for radiation lot testing for high Total Ionizing Dose (TID) missions (ie. GEO and Laplace)
Page 130 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Description Non hardened bipolar linear devices are used in space systems. These devices are among the most sensitive to TID. They also exhibit large part to part and lot to lot variability in sensitivities. Radiation lot testing offers the highest radiation hardness assurance for these devices. However, in most space program TID radiation lot testing is waived based on historical data. Policies vary between main aerospace contractors about historical data quality and radiation design margin (RDM) requirements to compensate the use of less representative data. In this study 5 lots of 8 part types of linear devices most commonly used in space systems will be tested to TID. Part to part and lot to lot variability will be analyzed. Minimum RDM and lot testing requirements will be derived from the analysis. Radiation Hardness Assurance (RHA) requirements will be updated accordingly. Deliverables Study Report Application/Need Date 2013 Duration (Months) 18 Estimated Current TRL N/A Target TRL N/A
SW Clause N/A Reference to ESTER T-7888
Consistency with Harmonisation TBD
TRP Reference T723-316QT Activity Title Characterization of SiC JFET commercially available devices Objectives Characterization of medium voltage SiC JFET normally ON available on the market for generic power switching function in space power distribution and control function and motor driver Description The study will be focused in assessing and characterize performances, stability, reliability and radiation tolerance of SiC junction gate field-effect transistor (JFET) normally -ON medium voltage and medium power with the main goal to characterize the performances of the devices in terms of switching capability, stability of the technology and main characterization of static and dynamic parameters as a function of temperatures as well as to characterize the technology in radiation environment in order to evaluate their potential future application in space missions. The study will have the goal to screen out the devices actually on the market in order to assess the more promising technology for a future qualification for space application. The candidates under evaluation should be selected among the off the shelf available US and European suppliers and as prototypes or engineering model as well (in this case as well Normally-OFF JFET would be of interest for this study). They should be packaged in a suitable way that allow easy and safe handling and that can allow the full characterization in temperature of the devices. The main features of SiC base material (high energy gap, high electric field breakdown in combination with reasonably high electron mobility and high thermal conductivity) led to the following expected and in some cases already proven capabilities for power application: low on-state voltage, low recovery charge, fast turn-on and turn-off, high blocking voltage, higher reliable operating junction temperature, high power density. At the present stage, the SiC JFET devices are at the beginning of commercialization in US, but there is an increasing diffused interest in realizing high performance SiC JFET that shows a better switching capability. The minimization of switching loss would in any case compensate the complication of the circuitry due to the normally-ON status of a JFET. At this purpose the devices should be selected with |VF|< 15V in order that they can be used with the standard Mosfet gate driver circuitry. The study will be organized with the following work structure: -Phase 1: critical analysis of the technical requirements, definitions of goal values for the main key parameters, and selection of candidates under test -Phase 2: Definition of test program -Phase 3: Performances of Constructional analysis and issue of a technology dossier for each typology under test -Phase 6: Performances of the test program. -Phase 7: critical analysis of test results. Identification of the more promising candidates future activities needed to make suitable the device for space application, analysis of cost up to the industrialization Deliverables Study Report Due to the generic application field, any mission could benefit of the expected improved switching capabilities of the device under development in this study. The availability on the market could be reasonably expected in 4 years time starting now Application/Need Date with this prototype development. At our best knowledge this will be the first systematic study inclusive radiation characterization of SiC JFET for possible future space applications. Duration (Months) 18 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-7934, T-496
Consistency with Harmonisation N/A
TRP Reference T723-317QT Activity Title Enabling of embedded RF MEMS microwave Integrated Circuit Process Objectives In this activity it is proposed to support the establishment of a Monolithic Microwave Integrated Circuits (MMIC) process with RF embedded RF MEMS switches capabilities. The Micro-Electro-Mechanical System (MEMS) is directly implanted on the MMIC, this allows to remove the RF switch in from the MMIC and reduce weight and size as well as increase the reliability of the circuit by adding additional redundancy Description
Page 131 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
The proposed activity stems from the CTB WG (Component Technology Board working group). It is is listed in CTB MNT WG (on mimiaturization) as well as in the CTB microwave CTB WG active component dossier, and it is also in line with an ESA/IPC(2009)147 information note. The major tasks to be carried out are: Task 1 will be dedicated to the process review, today processes are under evolution in terms of MEMS integration both for SiGe and GaAs microwave ICs. The necessary additional process development will be identified . Task 2 will address process development, the various processing steps (sacrificial layer removal, metal contact deposition, etc) necessary to the implantation of RF MEMS within a monolithic die will be implemented and validated. Task 3 will allow embedded RF MEMS MMICs to be prototyped. Task 4 will be dedicated too testing and early reliability assessment to put the ground for a future ESCC evaluation to be carried out under ECI or GSTP in a couple of years. Deliverables Prototype Telecom, Earth observation science for the application , LNA, flexible payloads, RF antennae, application will be immediate Application/Need Date as soon as a reliable technology Duration (Months) 24 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-8448, T-8803, T-7830, T-7832, T-7746
Consistency with Harmonisation N/A
TRP Reference T723-318QT Activity Title Investigation of microwave devices using diamond as a semiconductor material Objectives To investigate the use of diamond as a semiconductor for fabrication of high performance microwave power transistors. Description A program of work shall be initiated to assess the feasibility of fabricating advanced microwave devices using diamond as a semiconductor material. Diamond is considered as the ultimate crystal for electronic devices. Some European initiatives are already running (e.g. Element6 (UK)) to develop microwave transistors on diamond where it is projected that single transistors could be capable of delivering over 100Watts of output power at X-band frequencies. If achievable, such devices would allow Travelling Wave Tube amplifiers (TWTA) to be replaced by semiconductor based SSPAs for frequencies ranging from L-band to Ka-band and revolutionise RF payload sub-systems. Also, since diamond is an excellent thermal conductor with a very large bandgap (5.5ev for diamond versus 3.4ev for GaN) then the potential for high temperature operation and improved radiation hardness is even better than for Silicon Carbide (SiC) or Gallium Nitride (GaN) based devices. The proposed activity has already been included in the Microwave CTB (Component Technology Board) Dossier roadmap and has been endorsed.
The work shall initially encompass a literature review to identify current state of art for diamond based microwave devices and the fabrication approaches used. Based upon this information the contractor shall investigate appropriate material doping and processing strategies supported by the use of physics based modelling tools to predict and refine theoretical electrical performance. This shall be followed by undertaking preliminary transistor fabrication trials using optical gate lithography for low cost. The initial target performance would be to demonstrate 100W of output power in L-band using optical gate lithography. Measured electrical performance shall be compared with theoretical predictions and the device strategy optimized. Deliverables Simulation data, epitaxy material samples Generic need for improved RF payload Solid State Power Amplifiers (SSPA) on all platforms, Application/Need Date electronics required to operate in harsh environments (e.g Solar Orbiter, 2017) Duration (Months) 24 Estimated Current TRL 1 Target TRL 2
SW Clause N/A Reference to ESTER T-8196, T-8234, T-8448, T-283, T-7737
Consistency with Harmonisation N/A
TRP Reference T723-319QT Activity Title Development and evaluation of chips film capacitor for space application Objectives
The main objective of this activity is to evaluate this chip seldhealing capacitors for space applications. Description Film capacitors are widely used in space project for their light weight and self-healing property that make them one of the most robust components. The main draw back of these components is their relatively big volume and the fact that they are only mounted by hand soldering. New developments lead now to the possibility to have this type of technology available as chips capacitors. This will reduce the volume and allow a pick and place mounting keeping the self healing property. In a first step, based on commercial product, a first evaluation will be performed to assess the potential weakness of these parts then the manufacturer will propose improvements (choice of packaging, terminal materials, design modification) to meet the requirements of space projects. A second evaluation will then be performed to verify the validity of the new product. Deliverables Prototype Application/Need Date Component space qualification. Duration (Months) 18 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-7890
Page 132 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Consistency with Harmonisation N/A
7 - 30 - Deep Sub Micron Development
TRP Reference T701-301ED Activity Title High density European Rad-Hard SRAM-based FPGA: Abound-Logic-based first validated prototypes Objectives The objective is to develop the first high capacity European Radiation Hardened By Design (RHBD) reprogrammable Field Programmable Gate Array (FPGA) using a newly validated innovative FPGA architecture from Abound Logic, France. It aims to ultimately complement the European offering and challenge the current US supply, to be by 2014/2015 in a position to replace US origin parts from Actel RTAX4000 and beyond as well as the Rad-tolerant Xilinx Virtex 4 rad-tolerant series and to be competitive with the soon-to-appear Rad-Hard Virtex-5 series. Description New satellite designs entail more and more complex functionalities implemented in Field Programmable Gate Arrays (FPGA). Although Europe is far behind the US in the availability of powerful FPGAs, the first European reprogrammable radiation hard FPGAs offer the unique opportunity to develop new, larger capacity European ITAR-free FPGAs including the silicon parts, software & hardware development and programming tools to be able to cover the big gap. The new Abound Logic FPGA innovative architecture provides a mix of programmable logic, and math and memory hard blocks that enable the applications requirements. This new FPGA will offer roughly 2.5M ASIC equivalent gates and will advantageously compete with its US competitors and to overcome the existing FPGA technology gap.
The activity includes first an assessment on the application of rad-hard techniques to the current Abound Logic commercial Raptor FPGA followed by the development program according to the standard ECSS-Q-ST-60-02C that will enable to move to a rad-hard version of the Raptor design. It will be starting from the specification, functional and verification test plan, passing through the architectural and detail design phases; getting the final layout and finishing with the first samples (prototypes) including the functional validation. The rad-hard by design FPGA prototype will be based on an advanced deep sub micron Complementary Metal-Oxide-Semiconductor (CMOS) process, the ST Microelectronics 65nm CMOS process developed under ESA TRP funding. This activity will be complementing the FP7 granted proposal RAdiation Hardening by Design a Highly Integrated FPGA for Space (RAHSHIFFS), which includes a consortium of users that will be using the first prototypes and will be performing the radiation testing of the prototypes.
This activity is included in the overall Atmel plan to introduce a series, and not only one, of Abound Logic based RHBD FPGAs using STM 65nm CMOS technology and other potential funding, which will probably mean 3 different chip sizes and in a variety of packages. Deliverables FPGA prot., boards & ECSS-Q-ST-60-02C deliverables All types of space applications are considered applicable, including Earth Observation, Science, Launchers and Telecomms & Navigation. All the major European primes are candidates for using such FPGAs and have joined Atmel for EC FP7 and Application/Need Date Catrene proposals on this topic. But beyond large primes, these devices would be used by any company of any size when developing custom integrated circuits for space applications. This kind of FPGA is of utmost importance since it will be used in almost all equipments for commercial telecom, earth observation and scientific missions. TRL5 by 2014-2015. Duration (Months) 24 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-7802
Consistency with Harmonisation Activity D2.3 of the microelectronics roadmap
TRP Reference T701-302ED Activity Title Next Generation General Purpose Microprocessor (NGMP) Engineering Models Objectives Activity Objectives: - validation of the early NGMP (Next Generation General Purpose Microprocessor) prototypes manufactured in commercial ASIC technology - detailed design and manufacturing of NGMP EM (engineering model) in target space ASIC technology (65nm by STM) - functional and radiation validation of the NGMP EM Description The NGMP architectural design is currently under way in TRP contract 22279. Early prototypes shall be manufactured by the end of 2010 in commercial Application Specific Integrated Circuit (ASIC) technology (eASIC, UMC, TSMC 90nm).
The present activity starts with the functional validation of the early prototypes. With feedback from this validation and from other beta users, the NGMP design will be consolidated, and manufactured as an Engineering Model in the target space technology, the 65nm by STM, which is currently being developed under TRP and FP7 activities. The activity is set to conclude with extensive validation from functional and radiation point of view. ASIC engineering models, validation board(s), design databases and documentation according to ECSS-Q60-02, validation Deliverables software and test benches, validation reports. This microprocessor will be used in payloads with requirements of high processing power (up to 1000MIPS) or where present Application/Need Date state of the art for space (AT697-LEON2, 100MIPS) is not enough (e.g. Gaia like missions). Payloads entering Critical Design Review (CDR) in 2013 could start using the up-screened Engineering Models to validate in space. TRL5>2014. Duration (Months) 24 Estimated Current TRL 2 Target TRL 4
Page 133 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
SW Clause N/A Reference to ESTER T-7885, T-7891, T-7796, T-7800
Consistency with Harmonisation This corresponds to activities E2 and E3 of microelectronics Roadmap
TRP Reference T701-313ED Activity Title Deep Sub Micron 65nm rad hard library (Phase 2) Objectives This activity aims to complement and finalise the rad hard 65nm ASIC library design work undertaken in the Phase 1 TRP activity (KIPSAT). Two rad hard libraries shall be developed, a Metal Customizable one for low cost applications (pre-diffused) and a Standard Cell one for high performance applications (semi-custom / full-custom). Description The library has already been defined in the Phase 1 TRP activity (KIPSAT). The present activity proposes the design, prototyping and testing of Standard Cell and Metal Customizable libraries, representing in total ~ 300 cells. Simulations shall be performed to demonstrate the cells performances and cells radiation hardness. Ageing shall also be taken into account by considering 20 years operational lifetime. The libraries test vehicles shall be manufactured and evaluated according the ECSS test procedures (temperature, radiation). The libraries shall also propose memory generators. A CAD flow and design kit shall be proposed, validated and made available to the end users. Finally the libraries shall be delivered with all the views for timing analysis, synthesis, place & route, power analysis. A design kit user guide and library design book shall be delivered to end users. Deliverables Engineering Model Application/Need Date The DSM technology will be used for the future generation of microprocessors and FPGA for Space applications. Duration (Months) 24 Estimated Current TRL 3 Target TRL 6
SW Clause N/A Reference to ESTER T-7751, T-7795, T-7799, T-7800, T-36, T-8819
Consistency with Harmonisation activity A3 of Microelectronics
TRP Reference T702-302SW Activity Title Development Environment for Future Leon Multi-core. Objectives The objective of the activity is to prepare a complete software development environment for the future Leon multicore. It will be based as much as possible on existing elements that will be adapted if needed to the specific aspects of the multi-core. Description An ESA study is starting considering the system aspects of the use of the multi-core for our applications, and this study will define the final technical solutions. However, the trend seems to be towards the use of a hypervisor. If this is confirmed, there could be a convergence between the various hypervisors used for partitioning, for security and for multi-core. An environment for hypervisor could therefore be reused, which is the focus of the the proposed activity. The activity includes: 1) adaptation of compiler(s) 2) adaptation of debugger(s) 3) adaptation of operating system(s) 4) adaptation of the runtime(s) for Ada language 5) demonstrator on the multi-core 5) develop/extend some benchmark (e.g.: SPEC) Deliverables Software/Study reports Application/Need Date Next Generation Multi Purpose (NGMP) microprocessor. Beta SW > 2012-2013 Duration (Months) 18 Estimated Current TRL Prototype Target TRL Beta Software Open Source SW Clause Reference to ESTER T-8603 Code On board SW v3.1 DEVELOP C: Cross development Multi-core Activity C10 Consistency with Harmonisation Comments from the mapping meeting: The development of multi-core operating systems should be made in parallel with the multi-core hardware development (NGMP). It would have to be open source. It is a unique opportunity to harmonise one operating system for this new type of processor.
TRP Reference T702-304SW Activity Title Emulators of future NGMP multicore processors Objectives
Page 134 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
1) develop performant and representative emulators (in SW and/or HW) for future CPUs (NGMP Next Generation Multicore Processors) Intermediate objectives: 2) consolidate Just-In-Time(JIT)/Dynamic-Tranlation/Block-oriented simulators of CPUs and demonstrate their improved performance for software 3) Evolve FPGA-based hardware-in-the-loop emulators of Leon2/3 towards NGMP next generation multi core processors 4) Characterise the emulators of Leon2/3 and future processors against benchmarks 5)Use the concept of "software bus" of the on-board software reference architecture (which interface the application software to the basic software) in order to demonstrate its use for simulators of Basic Software to boost simulation speed beyond the performance of instruction set and JIT emulators 6) Define , in relation with the on-board software reference architecture, the internal interfaces of Software Validation Facilities and Operational simulators to enable hardware suppliers to supply models of their HW that can be re-used by all simulator-suppliers across missions and in all phases of a mission 7) disseminate knowledge and promote use of interface for hardware models, especially with hardware vendors 8) grow culture in hardware suppliers for the development of simulation models of their hardware by means of pilot projects Description Performance of European processors for space applications have been increasing over the years, from the ERC32 (25MHz, current missions) to the single-core Leon2/3 (100MHz, upcoming missions) to the next generation processor (multicore, Leon4, future missions). Simulators are needed throughout the software, spacecraft and operations development. Simulator performance needs to keep the pace with the processors. Instruction set simulators for the ERC32 could keep up with real-time simulation of the overall spacecraft. Simulators are being upgraded to cope with Leon2/3 using two techniques, hardware-in-the-loop emulation using FPGAs and just-in-time/dynamic-translation/block-oriented software simulation. HIL is operational for flight software and delivers sufficient performance for Leon2/3, while JIT simulators have not been fully demonstrated yet for flight/embedded software for Leon2/3. The next step towards NGMP multicore processors still needs to be taken.
Therefore JIT/dynamic-translation/block-oriented emulators for Leon2/3 need to be consolidated and characterised against benchmarks, while software and hardware emulators need to be upgraded and characterised for NGMP next generation multicore processors.
Other ways to boost performance is also to simulate the basic software or other layers (e.g. one from Spacecraft Onboard Interface Services (SOIS)) to have purely a functional simulator which can even run on the operating system of a workstation. This is made possible by the on-board software reference architecture that defines a software bus as the interface between the application and the execution platform. It is therefore possible to replace the on-board execution platform (NGMP based) by a conformant Linux based execution platform. This could enable functional validation of application software running over this simulation layer.
Also, to shorten development time of simulator developments (Software Validation Facilities, Functional Verification simulators, Operational Simulators) and to avoid that several simulator developers re-develop the same models of the same hardware in different fashions for different simulation platforms, common interfaces should be defined so that hardware suppliers can deliver a functional model of their hardware units along with the units. Deliverables Software/Breadboard/Study Report Application/Need Date All future ESA missions. Prototype SW > 2013. Duration (Months) 24 Estimated Current TRL Algorithm Target TRL Prototype Open Source SW Clause Reference to ESTER T-7743, T-908, T-7660, T-7665, T-303, T-8603 Code Consistency with Harmonisation activity C13 of On-Board Software Roadmap
TRP Reference T702-308SW Activity Title Schedulability analysis techniques and tools for cached and multicore processors Objectives The objectives are: 1) Extend the theory of schedulability analysis to multicore 2) Extend the theory of schedulability analysis to IMA/TSP systems and architectures identified within SW reference architectures 3) Produce an ECSS Handbook with guidelines/best practices 4) Guidelines to enable schedulability analysis of building blocks 5) Develop prototype or extend commercial tools to support the theories and WCET 6) Hardware requirements on the processors to support WCET measurement and schedulability analysis 7) Demonstrate application of WCET tool and schedulability theories in a representative context, possibly from in orbit mission software 8) Result dissemination to industries (e.g. preparation of training material) Description
Page 135 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Different aspects of schedulability analysis are involved in the software development process, as per ECSS: - schedulability analysis - Worst Case Execution Time (WCET) estimated and measured - CPU load estimated and measured
Each of them are supported by theory and tools but, though the theory is solid for non-cached processors, like the ERC32 and simple Digital Signal Processing (DSP), this has to be refined for complex and multicore architectures.
The commercial tools are only available for simple architectures and hardly used in spacecraft projects.
The activity should account for several aspects: a) Several architectures need to be supported (e.g. possibly by separate theories), e.g. cyclic scheduler, fixed priority-based pre-emptive scheduling and hierarchical scheduling in Integrated Modular Avionics/Time and Space Partitioning (IMA/TSP) architectures (scheduling at the partitions level, and within partitions). b) All phases of the software development need to be supported from PDR to AR, e.g. 1) the Schedulability theory and associated tools should be modular to support incremental levels of accuracy from CPU utilisation to full blown schedulability including, e.g. blocking times on shared resources, priority inversion avoidance protocols, system overheads and allowance for interrupt handlers. 2) WCET tools should be able to work from DDR to CDR on the Software Development Environment for unit/integration testing as well as on the Software Validation Facilities (SVF) for validation based on Software-in-the-loop or Hardware-in-the-loop c) All processors used in space need to be supported, non-cached/cached (e.g. ERC32/Leon), single/ multi-core (e.g. Leon/ next-generation), micro-controllers/ general-purpose/ DSP/ system-on-chip/ network-on-chip (Leon/61020/HBRISC), d) All operating-systems/run-time-environments used in space need to be supported, e.g. Ada, RTEMS, VxWorks, eCos, Java virtual machine Deliverables Software/Study reports Application: All on board SW projects/missions Application/Need Date Need date: 2013 Duration (Months) 24 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-7743, T-908, T-7660, T-7665, T-7662, T-7667, T-8414, T-8603
On Board SW v3.1 Harmo 1st semester 2010 Consistency with Harmonisation TEST D: Verification of Schedulability analysis Activity D5
7 - 31 - Miniaturisation
TRP Reference T703-304EP Activity Title Modular and miniaturised secondary power conversion and distribution based on Point of Load converters Objectives Feasibility demonstration and optimisation a secondary power distribution scheme based on Point of Load conversion, with the aim to consolidate the basic building blocks specifications allowing a optimised, yet flexible, recurrent design approach. Description The need of integrated Point of Load (PoL) conversion solution is linked with the appearance of advanced digital technologies, to be used in all ESA and non-ESA space programs. Note that PoL converters might become the only feasible/efficient power supply solution for all equipments provided with advanced digital technologies (memories, programmable gate arrays, processors, line drivers and receivers), due to the relevant static and dynamic accuracies and noise requirements over very low supply voltages (down to 1.8V or less, one notable example being the sub-micron 65nm technologies for which voltages as low as 1.2V are foreseen).
Additionally, point of load conversion architecture might allow quick and economic implementation of any secondary power distribution needs (within usual voltage and currents required for generic platform or payload users), with clear benefits on overall reliability.
The activity will study and optimise a secondary power distribution scheme based on Point of Load conversion, with the aim to consolidate the basic building blocks specifications allowing a optimised, yet flexible, recurrent design approach. The basic building blocks are: - Intermediate Bus Converters - IBCs - (to be adapted to usual main bus voltages and for a minimum set of power levels); - Latching Current Limiters - LCLs - (operative at Intermediate Bus level); - Point of Load - PoL - converters (to be finally produced in ASIC or anyhow in miniaturised form) - Voltage Clamp - VC - devices (very precise solid state devices acting like very precise power zeners - to be finally produced in ASIC or anyhow in miniaturised form).
The activity shall entail the development, manufacturing and test of a limited set of IBCs, LCLs, and VCs and the use of existing PoL converters to establish the minimum design rules to design with the given building blocks a generic secondary power management and distribution scheme. Deliverables Study Report Application/Need Date All missions/technologies. Duration (Months) 18 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-8614, T-8622, T-8623
See activities B8 of Power and Consistency with Harmonisation Management Dossier, 2nd semester 2008.
Page 136 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
TRP Reference T703-305EP Activity Title Miniaturised core element for Point of Load (PoL) conversion Objectives Design, development, manufacturing and test of a core for PoL converters to be used in a distributed power conversion scheme (Application Specific Integrated Circuit (ASIC), or advanced, low-cost and reliable hybrid technology). Note that the PoL converter core is the part of the DC/DC converter that do not contain the required magnetic elements and the input/output capacitance. Description The need of integrated PoL conversion solution is linked with the appearance of advanced digital technologies, to be used in all ESA and non-ESA space programs. Note that PoL converters might become the ONLY feasible/efficient power supply solution for all equipments provided with advanced digital technologies (memories, programmable gate arrays, processors, line drivers and receivers), due to the relevant static and dynamic accuracies and noise requirements over very low supply voltages (down to 1.8V or less, one notable example being the sub-micron 65nm technologies for which voltages as low as 1.2V are foreseen).
Additionally, point of load conversion architecture might allow quick and economic implementation of any secondary power distribution needs (within usual voltage and currents required for generic platform or payload users), with clear benefits on overall reliability.
The activity shall entail 1. the evaluation of the promising, in-house, available, reliability-proven technologies to realise a radiation hardened Point of Load (PoL) conversion core (note that technology qualification is excluded from the activity); 2. the selection and the robustness of the technology to meet space environment (especially Total Ionizing Dose (TiD) and Single Event Effects (SEE)); 3. the design, development, manufacturing and test of the core for PoL conversion.
The deliverables of the activity shall be:
- A prototype of the PoL converter core (in integrated form); - Preliminary analyses (application notes, Worst Case Analysis, Parts Stress Analysis, Failure Modes Effects and Criticality Analysis , Thermal and Mechanical analyses, Reliability analysis, Radiation analyses - TiD/SEE - ) for the final qualified product(s) - Technical specification to identify the application corners of the final product(s) - Evaluation and qualification plan for following qualification phase Deliverables Prototype Application/Need Date All missions/technologies. Duration (Months) 24 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-8614
Consistency with Harmonisation See activities B8 of Power and Management Dossier, 2nd semester 2008.
TRP Reference T705-306EC Activity Title Miniature MEMS based IMU feasibility demonstrator Objectives To demonstrate the feasibility, performances and achievable mass/power budgets for a miniaturised MEMS based IMU. Description Develop, build and test a single axis demonstrator of a MEMS based IMU. This will have a single multi-chip detector component combining rate sensor, accelerometer and front end electronics. The activity will trade the options of integrating the accelerometer and rate sensor on the same silicon against implementing them as individual but co-packaged dies. The Front End (FE) electronics needs will be defined to support both functions and a simplified interface to a central processing/ interfacing Application Specific Integrated Circuit (ASIC). The die size and FE performances will be assessed. The co-packaging issues will be addressed and an optimum package derived. A demonstrator of the integrated detector component including the rate sensor, accelerometer, FE ASIC function and packaging will be manufactured and tested. Deliverables Prototype Application/Need Date All future missions requiring low mass, low cost IMU/rate sensor functionality Duration (Months) 24 Estimated Current TRL 3 Target TRL 5
SW Clause N/A Reference to ESTER T-8254
Consistency with Harmonisation AOCS Sensor and Actuator harmonisation 2008, Gyros, Aim D, Activity D1
TRP Reference T706-301ET Activity Title Miniaturised and Low Power Communications Architectures for Small Platforms Objectives
Page 137 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
To reduce drastically the mass, size and power consumption of the communication systems to be adopted for future missions based on small platforms, e.g. nano-satellites, pico-satellites and small interplanetary missions, by means of miniaturisation and high levels of system integration. Description Reducing the mass, size and power consumption of the communications subsystem is a key issue when developing small platform satellites. Several scenarios have been identified who could benefit from this development, i.e. Low Earth Orbit (LEO), Geostationary Transfer Orbit (GTO) and planetary exploration missions.
This work will investigate existing and future techniques and technologies for miniaturisation of the communications subsystem by taking advantages of the latest work on new materials used in devices such as Gallium Nitride (GaN) Solid State Power Amplifiers (SSPA), low power Low Noise Amplifiers (LNA), Transceiver/Transponders and Digital Analogue Converters (DAC)/Analogue Digital Converters (ADC) as well as of integration techniques such as system on a chip and basic concepts of Software Defined Radio. The overall communications system architecture, from the data handling subsystem to the antenna output interface, shall be considered during the activity.
Transceiver/Transponder architectures and their interface to the data handling unit will be studied and a trade-off conducted to identify the optimum partition between the digital and analogue functions with the aim of achieving an optimal integration of the required subsystem components.
The proposed architecture will be assessed in term of mass, size, required power and costs. The work will also evaluate the impact of the miniaturisation on the quality of transmitted and received signals, e.g. the accuracy of frequency/phase recovery, EMC issues and interfaces to the antennas.
The work will be concluded with the implementation of a proof of concept demonstrator of the key areas of the miniaturised and integrated communications subsystem.
Design Drivers: a) Architecture analysis to define the optimum Digital, IF, RF and Antenna interfaces in order to provide miniaturisation and reduced power consumption whilst complying with the subsystem requirements b) Multi-mission suitability (considering different frequency bands of operation, UHF, S-band, X-band) c) Assess current technology which can be used to provide an integrated communications subsystem d) Identification of key areas where technology developments are required to meet the aims of the study such as higher efficiency amplifiers or high performance DACs/ADCs in order to increase the IF frequency after digitisation. e) Assess the miniaturised multifunction antenna technology and define the optimum interfacing strategy to provide omni-directional and directional coverage for a range of mission requirements (e.g. requirements for small size EO mission or Deep Space missions). Deliverables Breadboard Communication system miniaturisation as baselined by ESA mission studies such as NanoSat and MiniMEX. Application/Need Date 2016/17 for flight hardware. Duration (Months) 18 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-7824
Miniaturisation is an agreed design driver in the TT&C and PDT harmonisation Dossier and roadmap and Consistency with Harmonisation required for missions such as MiniMEX and nanosat
TRP Reference T707-301EE Activity Title Modular and customisable accommodation-friendly antenna system for satellite avionics Objectives To study and demonstrate a modular TT&C/TM-TC antenna system easily adapted to different mission and accommodation requirements, with minimal delta qualification. Description Multiple antennas are used for Telemetry, Tracking &Control (TT&C)/Telemetry-Telecommanding (TM-TC) sub-systems in most spacecrafts. However the individual off-the-shelf antennas typically used have a fixed radiation pattern which is seldom optimal for the mission requirements, often resulting in the need for design modification or compromises on performances. Recent activities on distributed antenna systems for small satellites (ESTEC C.No 22014/08/NL/ST & 22016/08/NL/ST) indicate the feasibility of a different approach based on the use of several smaller elements, possibly in groups, which performance is tuned using computer modelling. The lack of directivity of the individual elements allows for optimal configuration of the antenna system for both gain and polarisation, using electromagnetic modelling tools to predict the combined radiation of elements placed on free areas of the platform. Therefore a single design of the radiating elements, possibly incorporating limited tuning capabilities not affecting qualification, supports a complete range of solutions which performance is optimised to the mission using accurate prediction tools. The possibility to tune the elements and their combination, demonstrated on small spacecrafts, is expected to significantly improve coverage performances in the direction of the desired omni-directional gain pattern for spacecrafts of all sizes. In addition improvements are foreseen for both single or double circular polarisation operations, with the possibility to include linear polarisation for the Earth to Deep-Space link following the most recent developments regarding Agency Deep-Space Antennas. The activity encompasses, as a first step, the initial adaptation of the approach to medium and large platforms, with the demonstration of feasibility by analysis and the planning of the further demonstration steps, including manufacturing and testing. In particular it shall include the study of different antenna system layouts and of different elements to cover X-band operations and possibly UHF, Ku and Ka-band. As a second step, candidate antenna elements at X band will be designed in detail and their performance demonstrated by analysis, with validation on laboratory test pieces if necessary. The element performances will be used to consolidate the antenna system design for a few of satellite configurations. Finally a selected system configuration will be used to implement a proof-of-concept demonstrator which performances will be proven by combined use of testing on a satellite mock-up and accurate modelling. The activity shall deliver a consolidated design concept, incorporating performance tuning capabilities based on computer modelling of the installed performances, as well as the definition of the development path up to EQM identifying design refinement needs, manufacturing requirements and test plans. Deliverables Prototype Application/Need Date All missions / 2020 Duration (Months) 24 Estimated Current TRL 2 Target TRL 3
Page 138 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
SW Clause N/A Reference to ESTER T-8770
Consistency with Harmonisation N/A
TRP Reference T707-302EE Activity Title Scalable low-mass low-envelope high-to-very-high gain antenna Objectives To demonstrate a modular and scalable antenna concept, suitable for fixed and deployable configurations, characterised by low mass, simple manufacturing, low recurring cost providing high-gain to very-high-gain beams for avionics (telemetry, telecommand and data downlink) and payload enabling the reduction of satellite mass and size for Earth Observation, Exploration and Science missions. Description Effective planar antennas based on the holographic principle have been developed at X and Ka band. In particular the possibility to operate the antenna in dual polarisation for an isoflux shaped beam has been shown (ESTEC C.No 22802/09/NL/JD/al). A similar approach can be applied to provide a variety of beam shapes covering the 20-40dBi gain range at different frequency bands. E.g. spot-beam or shaped-beam antennas for deep-space links at X band and also at Ka-band.
The new antenna concept features a low-profile (no protruding feed/subreflector), low-mass (2-3 Kg/m^2), low-cost (printed technology) and a gain comparable to that of a standard high-gain dish of the same diameter or equivalent arrays. The antenna can also easily be designed to have a beam pointed off-axis, up to 30deg, allowing flat mounting of the antenna on the satellite panel in most cases and leading to conical scan capabilities with simple in-plane rotation of the antenna panel. Furthermore the holographic concept enables the implementation of large apertures (w.r.t. the size of the host platform) by deployment of several panels of which only the central one needs to be fed. Thus removing one of the major obstacles in the use of large apertures, i.e. the need of external feeding either via a space-wave or a Beam Forming Network (BFN). Different implementation strategies are also to be addressed, from the standard multi-layer printed technology to advanced processes like 3D manufacturing technologies, also taking into account mechanical and thermal aspects to achieve a full demonstration of the space-worthiness of the concept.
The activity encompasses two steps. First, the demonstration of feasibility by analysis, with the consolidation of the procedure for the synthesis of the antenna configuration and panel layout (pattern of metallic shapes on the dielectric layers). Second the development of an X-band proof-of-concept demonstrator using flight-representative technology to be also used for the validation of the design tools. The feasibility of elevation scanning will also be addressed during the activity. The development path up to EQM, identifying design refinement needs, manufacturing requirements and test plans will also be established to complete the outcome. Deliverables Prototype Application/Need Date Science, Robotic exploration and Earth Observation missions / 2020 Duration (Months) 18 Estimated Current TRL 2 Target TRL 3
SW Clause N/A Reference to ESTER T-8821
Consistency with Harmonisation N/A
TRP Reference T715-304MS Activity Title Polymer based tape-spring type, ultra-light actuator. Objectives To develop an integrated actuator /structure combining "hybrid" and "bi-stable" composite tape springs actuators for an innovative deployable ultra-light solar array structure. Description Tape springs actuators showing "bi-stable" effect, can be coiled in small volume when stowed and provide actuation for deployment and stiffness when fully stretched. "Bi-stable" effects are exploited in this type of actuators to provide geometrical "locking" and high stiffness when fully uncoiled. A layer of polymeric material, applied to such an actuator (herein called "hybrid" tape spring actuator) can maintain the tape spring actuator in its coiled state if at temperatures below the polymer glass transition temperature. By polymer heating, material softening and controlled self-deployment can be achieved. By integrating this tape spring actuator concept (both in its "hybrid" and basic "bi-stable" versions) together with thin photovoltaic assembly structures, ultra-light deployable solar arrays can be produced among other structures. The focus of this activity will be the development of such an actuator and the feasibility verification of an integrated solar array concept. Breadboarding of a representative sample of hybrid tape spring actuator (including non hybrid bi-stable components) and functional test in laboratory environment to verify the concept shall be included. A dummy solar array structure shall be included in the functional test to verify actuation performances. Deliverables Breadboard Application/Need Date All missions with deployable structures/2013 Duration (Months) 24 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-8854
Activity A3 from deplyable Boom Roadmap from 2003 Harmonisation. Note : this activity will be put in the 2nd Consistency with Harmonisation semester 2010 proposed roadmap under a different reference number.
Page 139 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
TRP Reference T721-303MT Activity Title Miniaturised Heat Switch Technology Objectives The objective is to develop a miniaturised heat switch capable of conducting 0.5 to 10W of waste heat to a radiator. The heat switch would be a passive mechanical device, which at a specified temperature, would make a thermal contact with a cold sink and reject the excess heat. Description Robotic exploration missions that are subject to long diurnal cycles, require the use heat switches to thermally decouple from the cold external environment in order to save energy. A heat switch based on the Loop Heat Pipe technology was developed in the frame of a TRP activity. The heat switch LHP was design to transport 10 to 50W of waste heat. However, when managing small power dissipation coming from RHUs or payloads, a dedicated LHP Heat switch is oversized and too complex for the application. The miniaturised heat switch would have a mass lower than 160g and would be installed in series between the radiator and the dissipative unit. This concept was successfully validated on board the JPL Mars Rover where mechanical heat switches were used for the thermal management of the battery. Deliverables Engineering Qualification Model Application/Need Date Robotic Exploration Mission/TRL5 by 2015 Duration (Months) 24 Estimated Current TRL 1 Target TRL 5
SW Clause N/A Reference to ESTER T-8922
Consistency with Harmonisation N/A
TRP Reference T723-313QT Activity Title Miniaturisation of Power/Coaxial Connectors Objectives Design and develop a power microminiature connector taking into consideration the space environment. Description The objective is to develop, characterize and evaluate a microminiature connector solution for applications requiring power or coaxial link. To address these applications, the only connectors available at the present are the D-SUB connectors. These connectors, developed in the 50s, are widely used in space applications as users take advantage of performances with large choice of contact types (signal, power and coaxial contacts in same arrangement) and easy integration due to removable contacts. However, the main drawbacks of D- SUB connectors are the weight and the size which are not compatible with the objectives of mass reduction and miniaturization.
During the 80s, a first step to miniaturization has been reached by developing micro-miniature connectors. Important progress has been reached recently by developing micro-miniature connectors with removable contacts. However, all these efforts will be worthwhile only if the offer of microD connectors is equivalent to Sub-D connectors, with respect to size reduction impact on performances.
Nevertheless, any other solution than the ones based on microminiature connectors, might be also considered if it presents advantages in terms of performance or utilization with respects to miniaturisation
A technology survey and a trade off shall be carried out in order to determine solution able to meet the electrical and physical requirements as well as the constraints of space applications. Selected solutions and application domains will be described through a detailed specification, Process Identification Document. Characterisation of the miniature power connector shall be performed and an evaluation test plan proposed in order to determine physical margin of the product and the associated failure modes. A synthesis shall provide guidelines and utilization recommendation regarding to the evaluation results. The subject of the proposed activity will also be included in the next CTB (Component Technology Board) Passives Dossier. Deliverables Survey, PID, Spec, test report, samples Application/Need Date Generic Purpose >2013 Duration (Months) 24 Estimated Current TRL 1 Target TRL 3
SW Clause N/A Reference to ESTER T-7890
Consistency with Harmonisation N/A
TRP Reference T723-315QT Activity Title RF MEMS switch technology for space application: Phase 1: Benchmarking and selection Objectives In line with an ESA/IPC(2009)147 information note, the objectives are to benchmark RF MEMS potential suppliers of today with a common standardized technical specification. RF MEMS switches will be produced in accordance to the spec and tested through a common test plan using similar equipment by the same operators. This will select the optimum RF MEMS Switch process for further reliability testing, test robustness and packaging in phase 2 (see other TRP proposal Id 1266) and prepare it for further space qualification (phase 3) via the GSTP programme.
Page 140 of 141 TRP Work Plan 2011-2013 ESA/IPC(2010)119 ANNEX II: Description of Preselected Activities
Description The proposed activity, in line with an ESA/IPC(2009)147 information note, will focus on the following 5 major steps: Task 1: Endorsement and validation of the draft specification already existing and to be used by all RF MEMS suppliers selected for further processing. Task 2: Selection/Confirmation of the RF MEMS Supplier Task 3: Processing of RF MEMS switch test vehicles for further testing. Processing time will be frozen and limited in duration. Definition and endorsement of the test plan to be used in Task 4 Task 4: Performance of the common test plan agreed in Task 3 by a common group, using the same equipment and same operators Task 5: Review and selection of the preferred technology for further consolidation during phase 2 Deliverables Prototype Telecom, Earth observation science for the application , LNA, flexible payloads, RF antennas, application will be immediate Application/Need Date as soon as a reliable technology become available Duration (Months) 18 Estimated Current TRL 1 Target TRL 2
SW Clause N/A Reference to ESTER T-8448, T-8776, T-8803, T-7830, T-7832, T-7746
Consistency with Harmonisation N/A
TRP Reference T723-320QT Activity Title Embedded passive component: a way to miniaturization Objectives Passive components like chip resistors, capacitors and inductors are used in huge number and have a large footprint on the PCB. This study proposes to evaluate embedded passive technologies. 2 types of technologies shall be used: - Specifically designed passive chip components embedded in a PCB. - Embedded layers in the PCB like a polymer ceramic dielectric layer for replacing capacitors
The use of these technologies may allow space savings on the PCB by placing passives devices inside the PCB reducing the size of board and hence equipment by reducing the distance between passive and active components (improvement of signal performance). Description Embedded passive devices such as resistors are a fast emerging technology and already widely used in commercial applications. This technology is driven by signal performance and miniaturization. The subject has been discussed in the frame of the CTB (Component Technology Board) and the activity has been approved by the CTB Passive components working group. The study shall encompass an initial survey of the existing solutions, an assessment of the various designs of embedded devices, their reliability in assembly and their ability to withstand the space environment. Deliverables Prototype Application/Need Date All type of application using chips, resistors and capacitors leading to board miniaturisation. Duration (Months) 24 Estimated Current TRL 2 Target TRL 4
SW Clause N/A Reference to ESTER T-7890, T-8385
Consistency with Harmonisation N/A
TRP Reference T724-301QT Activity Title High Density Interconnect Technology and Thermount replacement with assembled devices. Objectives To evaluate, within well-defined process parameters at least 1 PCB manufacturer and assembly company, the HDI technology in combination with low CTE laminate and assembled devices. Description High Density Interconnect (HDI) technology entails miniaturisation of Surface Mounted Device (SMD) pads, tracks and microvias, which is already available technology for commercial market. Space market currently only uses more conservative larger dimensions for PCB routing and components. HDI is strongly driven by the decreasing pitch due to miniaturisation of available components. Denser population of PCBs leads to mass reduction. Typical HDI components are ceramic and, therefore, require the use of a low Coefficient of Thermal Expansion (CTE) laminate, such as the obsolete Thermount. Reliability of assembly and smaller routing are issues to be evaluated. Design rules shall be evaluated and an evaluation programme shall be performed on bare boards followed by assembled boards. Deliverables Study Report Application/Need Date All missions. Duration (Months) 24 Estimated Current TRL 3 Target TRL 4
SW Clause N/A Reference to ESTER T-8385
Consistency with Harmonisation N/A
Page 141 of 141