Sensor Data Fusion For Hazard Mapping And Piloting

International audienceAutonomous landing on Mars, Moon or asteroids may require a Hazard Detection and Avoidance (HDA) system on-board the lander. Past studies on HDA dealt with the use of camera or LiDARs separately to detect dangerous slopes, boulders and shadow areas. The present work, performed in the frame of an ESA TRP, proposes to use jointly a camera and a LiDAR to take advantage of each while mitigating their drawbacks, consequently improving the HDA performances. Various algorithmic solutions and sensor configurations are proposed and tested in the Mars and asteroid landing cases

Li-Ion Cots Cells for Low Temperature Mars Landers

This digest describes the work undertaken to develop a secondary Li-ion battery for use in European space exploration missions from Commercial off the Shelf (COTS) cells. The battery was required to operate at temperatures below −20°C and survive a freeze/thaw cycle. A previous paper [1] described the search for a suitable cell, and the initial data from the module life test. As the results from this testing were extremely promising, the project was extended to determine the module performance up to 720 Sols at −20°C. Very low temperature survivability tests were also performed on the selected cells with good results. Further work has therefore been carried out to determine the longer term effects following a freeze/thaw cycle. The final part of the project was to produce a performance model of the cells. Results from the simulations have been compared to test data for the selected cell type

Li-Ion Cots Cells for Low Temperature Mars Landers

This digest describes the work undertaken to develop a secondary Li-ion battery for use in European space exploration missions from Commercial off the Shelf (COTS) cells. The battery was required to operate at temperatures below −20°C and survive a freeze/thaw cycle. A previous paper [1] described the search for a suitable cell, and the initial data from the module life test. As the results from this testing were extremely promising, the project was extended to determine the module performance up to 720 Sols at −20°C. Very low temperature survivability tests were also performed on the selected cells with good results. Further work has therefore been carried out to determine the longer term effects following a freeze/thaw cycle. The final part of the project was to produce a performance model of the cells. Results from the simulations have been compared to test data for the selected cell type

An astrobiology payload complement for a Europa Penetrator

We report on the selection and design of an astrobiology payload for a Europa penetrator, which would impact at ~300m/s, and subsequently access a sub-surface sample, analysis it, and return the science data to an overflying orbiter. We aim for a very highly integrated package whose payload elements are limited to 2.2 kg before 50% maturity margin for elements with TRL<5, and a further 20% system margins are applied. This mass limit also has to include a sample acquisition mechanism. Selection of instruments requires that the astrobiology return is maximised with technology which is capable of flight readiness by the end of this decade. In the case of absence of astrobiological signatures the associated geophysical return is also assessed. Major drivers used in instrument selection and design are science capability within a penetrator context, and technology elements which include resources (mass, power, volume), maturity (heritage, TRL), ruggedness, contamination, radiation, planetary protection, mounting orientation, thermal, telemetry and commanding issue

Sensor Data Fusion For Hazard Mapping And Piloting

International audienceAutonomous landing on Mars, Moon or asteroids may require a Hazard Detection and Avoidance (HDA) system on-board the lander. Past studies on HDA dealt with the use of camera or LiDARs separately to detect dangerous slopes, boulders and shadow areas. The present work, performed in the frame of an ESA TRP, proposes to use jointly a camera and a LiDAR to take advantage of each while mitigating their drawbacks, consequently improving the HDA performances. Various algorithmic solutions and sensor configurations are proposed and tested in the Mars and asteroid landing cases

Small Mars Mission Architecture Study

While the vast majority of ESA’s funding for Mars exploration in the 2020s is planned to be invested in ExoMars and Mars Sample Return, there is an interest to assess the possibility of implementing a small mission to Mars in parallel with, or soon after, the completion of the MSR programme. A study was undertaken in the Concurrent Design Facility at ESA ESTEC to assess low-cost mission architectures for small satellite missions to Mars. Given strict programmatic constraints, the focus of the study was on a low-cost (<250MEuro Cost at Completion), short mission development schedule with a cost-driven spacecraft design and mission architecture. The study concluded that small, low-cost Mars missions are technically feasible for launch within the decade