document title / titre du document TRP W ORK PLAN ... - emits - ESA

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TRP Work Plan 2005-2007 Description of Activities TEC-SB/7935/dc 12/Feb/09 TRP Reference: 03/W35 Title: Martian dust simulation facility for solar cells The differences between the Mars environment and the orbital environment in which the solar cells are most commonly used require dedicated facilities to test both the solar cell and the photovoltaic assembly Coupons. The critical differences between the two environments having strong impacts in the solar cell and photovoltaic assembly testing are: - Solar intensity and spectrum modified by dust - Low temperature operation - Dust deposition on the solar array surface The Martian dust does not remain suspended in the atmosphere, but deposits out of the atmosphere onto any horizontal surfaces with a dust coverage rate of 0.3 % power loss per day. This is potentially the major lifetime limiting factor for a solar power system on any Mars mission longer than 100 sols. For this particular reason it is very important to upgrade and to modify existing test facilities that could allow the characterization and the qualification of the photovoltaic components under representative Martian dust conditions so as to timely match the needs of future Aurora missions on the surface of Mars. To achieve the above mentioned technical objective, the following activity is proposed: - Development of a Martian dust simulating facility for solar cells and coupons by modifying an already existing Wind Tunnel facility. This activity will be mainly devoted to the realization of an environmental test chamber aimed at blowing representative Mars dust over the samples in order to perform specified dust adhesion experiments. The activity will be based on a Mars Dust and Environment Specification to be provided by ESA. Special emphasis will be more particularly placed on the definition of the detailed composition of representative Martian dust particulates and of the environmental conditions to be reproduced under testing. This test specification will be elaborated in the currently running Aurora technology activity, titled Solar Array design and technology development for Mars exploration missions. Deliverables: Development of Martian dust simulating facility for solar cells/coupons by modifying an already existing Wind Tunnel facility (Mars dust particulate/environment study and consequent realization of an environmental test chamber). Current TRL: TRL1 Target TRL: TRL4-5 Application Need/Date: TRL5 in 2009 Application/Mission: Mars Exploration Contract Duration: 18 months SW Clause : - Dossier0 Ref.: T-7720 Consistency with Harmonisation Roadmap and Conclusions: Solar Generators & Solar Cells TRP Reference: 04/G15 Title: Precision landing GNC test facility To mitigate technical, schedule and cost associated with enabling GNC technologies of future planetary missions requiring safe precision landing, they have to be tested as much as possible on ground in a precision landing GNC test facility. The main objective of the activity is to develop a precision landing GNC test facility that will emulate real lander dynamics and test safe precision landing navigation, guidance and control technologies to the performance level required by future planetary landing vehicles. Starting from the outputs of the on-going activity on "Verification Strategy for Smart Lander", the activity will involve: (1) analysis and trade-offs of precision landing GNC test facility configurations, inc. test facility requirements definition; (2) mechanical and electrical detailed design of the selected baseline test facility configuration; (3) manufacturing, assembly, acceptance tests and test campaign definition, and (4) integration of smart lander technologies from on-going TRP activities and test campaign results analysis. Deliverables: Precision Landing GNC Test Facility; Documentations (technical data package, summary report and abstract), including precision landing test facility configuration trade-offs/analysis, detailed design, test results, GNC SW demonstrator, test plan/results. Current TRL: TRL2 Target TRL: TRL4-5 Application Need/Date: TR5 in 2008 Application/Mission: ExoMars, MSR Contract Duration: 24 months SW Clause : Operational SW Dossier0 Ref.: T-8071 Consistency with Harmonisation Roadmap and Conclusions: Page 75 of 227
TRP Work Plan 2005-2007 Description of Activities TEC-SB/7935/dc 12/Feb/09 TRP Reference: 04/G25 + T306-01ES Autonomous Rendez-vous GNC test facility + Integrated Multi-Range Rendezvous Title: Control System Building upon the heritage from ATV, the European reference rendezvous with manned targets in LEO, and ongoing technological developments applicable to rendezvous systems, the main objective of the study is to design and develop the 2nd generation of space autonomous rendezvous GNC systems applicable to a wide set of potential missions (rendezvous with cooperative, non cooperative and natural objects). Special emphasis is given on a vision-based solution for the rendezvous navigation system from target acquistion to terminal approach. Two image processing algorithms, namely Features Extraction and Object Recognition & Matching, will be developed, prototyped and tested. These algorithms will be implemented on the NPAL camera breaborad that has been developed vision-based soft landing applications. In order to support image processing validation in the overall navigation chain, PANGU will be extended in order to generate representative space scene. Guidance Expert and robust control techniques, that take into account the specificity of performing rendezvous in elliptical orbit, will be developed and tested via Monte Carlo simulations. Finally, the preliminary design of the Autonomous Mission Management (AMM) will rely on a multi-layer architecture based on a decision level (planner) in charge of the onboard operation management, an execution level in charge of the time line detailed definition and execution, and an independant safety protection level in charge of the collision avoidance. The planner will make use of the guidance expert system in charge of re-computing adequate trajectories that fulfil the current system constraints. The AMM design will be validated via computer simulations using an upgraded functional engineering simulator. Deliverables: SW/HW, test facility + documentation. Documentation (technical data package, summary report, abstract), including autonomous rendezvous & capture GNC test facility configuration trade-offs/analysis, detailed design, GNC SW demonstrator, test plan/results. Current TRL: TRL2 Target TRL: TRL4-5 Application Need/Date: Application/Mission: exploration missions e.g. MSR Contract Duration: 24 months SW Clause : Operational SW Dossier0 Ref.: T-8070 Consistency with Harmonisation Roadmap and Conclusions: TRP Reference: Autonomous Rendez-vous GNC test facility + Integrated Multi-Range Rendezvous Title: Control System The activity combines two sub-activities: 1. Autonomous Rendez-vous GNC test facility (04/G25): redez-vous/docking and capture operations are of primary importance for sample return missions as well as in-orbit servicing and inspection. On the other hand, to mitigate technical, schedule and cost associated with enabling GNC technologies of future planetary missions requiring rendezvous and sample capture, they have to be tested as much as possible on ground. The overall study objective is to take a major step towards a European capability for autonomous orbital rendezvous and docking. Starting from recent study results on lidar/vision-based GNC systems and heritage from ATV GNC development, the activity concerns (i) the adaptation or enhancement of existing mission and simulation tools, real-time avionics and dynamics test benches for the validation of a high integrity autonomous multi-range rendezvous & docking control system (HARVD); (ii) the rapid prototyping of the autonomous mission and vehicle management (AMM) software and fault detection, diagnosis and recovery (FDIR) software and the integration of the on-board HARVD S/W demonstrator; (iii) the testing of its real-time performance and autonomous operations and transition capabilities (terminal rendezvous phase) with hardware-in-the-loop (HIL) in a laboratory environment. 2. Integrated Multi-Range Rendezvous Control System (T306-01ES): The main objective of the study is to define, develop and breaboard a generic multi-mission rendezvous GNC system applicable to a whole set of potential missions (rendezvous with cooperative, non cooperative and natural objects). The generic GNC architecture (sensors, actuators, algorithms, avionics) will be defined for two mission scenarios: in-orbit servicing (Earth environment) and sample return (Mars environment). The autonomous navigation system will make use of recent technology breakthroughs in vision and imagin lidar. Absolute and relative attitude and position measurements, from RF sensor and optical camera or lidar sensor, will seamlessly be integrated using an iterated, extended Kalman filter. Robust guidance and control algorithms will be developed for rendezvous in circular and elliptical orbits . For maneuver planning, it is foreseen to use a Lambert planner at long range with genetic algorithm optimization of start and transfer times. A Simplex planner with path constraints will be used at close range. Finally, a breadboard of the on-board software of the integrated multi-range rendezvous control system, inc. mission management and FDIR functions, will be developed and real-time performance tests with electrically stimulated relative navigation sensors and simulated actuator units on the ESA generic avionics testbed. Deliverables: SW/HW, test facility + documentation. Documentation (technical data package, summary report, abstract), including autonomous rendezvous & capture GNC test facility configuration trade-offs/analysis, detailed design, GNC SW demonstrator, test plan/results. Current TRL: TRL2 Target TRL: TRL4-5 Application Need/Date: Page 76 of 227
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