A satellite platform modular thermal control device comprises a low temperature index thermal control module, a normal index thermal control module, a high temperature index thermal control module, a rail control thermal control module and a load thermal control module, wherein the low temperature index thermal control module is used for bearing an instrument which meets low temperature index requirements and is in thermal isolation connection with the rest thermal control modules; the normal index thermal control module is used for bearing an instrument which meets normal temperature index requirements; the high temperature index thermal control module is used for bearing an instrument which meets noncryogenic index requirements; the rail control thermal control module is used for bearing an instrument of a rail control subsystem and is in thermal isolation connection with the rest thermal control modules; the load thermal control module is used for bearing a load instrument and is in thermal isolation connection with the rest thermal control modules; an inner surface of a structural plate of each thermal control module is in thermal coupling with the corresponding instrument through thermal conduction filler; a corresponding thermal dissipation coating is pasted on an outer surface of each structural plate, thus a thermal dissipation channel is formed, so that thermal of the corresponding instrument in each thermal control module is transmitted to the corresponding structural plate, and then radiated to the outer space through the outer surface of the corresponding structural plate. By adopting the satellite platform modular thermal control device, thermal control flexibility and generality of a satellite platform are improved, the development cycle is shortened, and development costs are reduced.


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    Titel :

    Satellite platform modular thermal control device


    Beteiligte:
    ZHANG XIAOFENG (Autor:in) / YIN ZENGSHAN (Autor:in) / LIU HONG (Autor:in) / SHI RONGRONG (Autor:in) / HUANG JIN (Autor:in) / GAO YANG (Autor:in)

    Erscheinungsdatum :

    05.08.2015


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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