The design, fabrication, development testing, and growth potential of an advanced design thermal control subsystem for the free flying P80-2 satellite is described. Free flying satellite applications can have large payload heat rejection requirements. For example, the P80-2 heat rejection requirement was in excess of 4 kilowatts. An inherent requirement for these vehicles is to incorporate a means for transferring heat from a source, frequently electronic components, to a sink, typically a space radiator. This heat transfer can be accomplished by a liquid coolant loop that is pumped and temperature controlled by a coolant pumping and conditioning assembly (CPCA) system. Major CPCA components typically include a long life space qualified pump, power inverter, thermal control valve, accumulator, and miscellaneous sensors.


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    Title :

    Thermal Control Subsystem for Free Flying Satellites


    Additional title:

    Sae Technical Papers


    Contributors:

    Conference:

    Intersociety Conference on Environmental Systems ; 1982



    Publication date :

    1982-02-01




    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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