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Designing, building, andtesting of a thermal protection systemfor a spacecraft which cannot be qualifiedusing standard methodology
This is a case study of the Thermal Protection System (TPS) currently in use on the Parker Solar Probe spacecraft, which over its seven year life it will experience surface temperatures in excess of 1400C. The traditional methodology for qualifying a space structure, using the old adage, "test what you fly and fly what you test" was simply not practical based on the selected materials, the size of the TPS, and a space environment characterized by its hard vacuumand hightemperatures. The approach to risk mitigation both in te ...
Schaefera, Edward; Congdon, Elizabeth; Conkey, Shelly;
Published by: Proceedings of the International Astronautical Congress, IAC Published on:
Carbon carbon composites; Materials; Testing; Parker Engineering