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.


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    Title :

    Electrically conductive materials for thermal isolation in spacecraft charging environments


    Contributors:
    Erikson, R. (author)


    Publication date :

    2001


    Size :

    11 Seiten, 14 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English





    AIAA-2001-1366 Electrically Conductive Materials for Thermal Isolation In Spacecraft Charging Environments

    Erikson, R. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2001



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