The fabrication and testing of a prototype deployable radiator system is described. Vapor compression with a conventional aircraft compressor yielded a net heat rejection effect at high environments while returning low temperature (10 F and 35 F) conditioned fluid to the payload thermal control system. The system is compatible with shuttle orbiter payloads, free flying experiment modules launched from the shuttle, or by another launch vehicle. (Author)


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    Title :

    Development of a Self Contained Heat Rejection Module, Phase 2 and 3


    Contributors:

    Publication date :

    1976


    Size :

    248 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





    Self-contained heat rejection module for future spacecraft

    Fleming, M. / Williams, J. / Baskett, J. | Tema Archive | 1975


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