A major objective of the FP7 project named ReVuS (Reducing the Vulnerability of Space systems) is to define new shielding solutions to limit the effects of debris impact and to reduce the vulnerability of future low Earth orbit (LEO) satellites to small and mediumsized debris (typically 1 mm to 5 cm). The paper describes considerations on shielding strategy definition. The aim is to select new materials and shielding designs against hypervelocity impacts taking into account compatibility with space environment and design constraints (e. g. mass, accommodation). From the vulnerability analysis of two reference satellites, critical equipments and areas have been identified for the most critical size ranges of debris. Then, vulnerable configurations to be shielded have been listed. A process has been defined to select suitable protection features from a list of possible geometries and materials (e. g. aluminium meshes, aramid and ceramic layers, Quartz fibres, synthetic foams, corrugated layers, laminated aluminium with ceramic particles). Different solutions can be implemented as stuffing layers combining different materials to reduce high impact energy levels, to fragment further projectiles and to absorb debris before a non-desirable penetration into the inner spacecraft. Based on preliminary test results made on individual layers, the effectiveness of different combinations of protection layers has been assessed by analysis. Different solutions for identified critical equipment configurations will be tested in the frame of the project. An overview on the test plan is presented in this paper.
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