This paper compares four candidate material systems suitable for thermal isolation of instruments operating at cryogenic temperatures in spacecraft charging environments. These materials have thermal conductivity comparable to the G-10 fiber-glass formerly used for this role, but have sufficiently low electrical resistivity to ameliorate charge build-up in the orbital plasma environment. The nature of thermal and electrical conductivity is reviewed, with theoretical and practical material options. Extremely thin titanium sandwich construction, carbon-loaded fiberglass (Norplex NP511ESD), carbon-loaded polyetherimide (Ultem 7201), and carbon-loaded, glass-reinforced polyetherimide (RTP 2199) have been tested and prototype isolators fabricated. Materials, processes, tests and prototypes are discussed.
Electrically conductive materials for thermal isolation in spacecraft charging environments
2001
11 Seiten, 14 Quellen
Conference paper
English
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