The invention provides a satellite temperature control method allowing rapid responding and multi-orbit adaption, wherein by adopting a heat pipe network, reinforcing contact thermal conduction, and spraying a high-emissivity thermal control coating inside a satellite to reinforce in-cabin thermal conduction and radiation heat exchange, a temperature field is distributed uniformly in a cabin; a whole satellite temperature level is adjusted by a compensative electric heater; a nightside of a side plate of the satellite is taken as a major heat dissipation face, the outer surface of the nightside is sprayed with a white paint, and all the other outer surfaces of the satellite body, except for the major heat dissipation face, are covered by multiple layers of thermal insulation assemblies; and components outside the satellite are sprayed with a white paint thermal control coating. A propelling cabin has independent design, wherein the entire outside of the cabin is covered by the multiple layers of the thermal insulation assemblies, a baseplate inside the cabin is covered by the multiple layers of the thermal insulation assemblies, and the propelling cabin is finally integrated with a platform cabin. By integral design of machinery, heat and electricity, the satellite temperature control method allowing the rapid responding and the multi-orbit adaption provided by the invention realizes thermal control requirements of the whole satellite under conditions of a sun-synchronous orbit and an inclined track by the temperature control method.


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    Title :

    Satellite temperature control method allowing rapid responding and multi-orbit adaption


    Contributors:
    ZHOU YAN GENG (author) / ZHAO JIZHE (author) / XIE LONG (author) / WU ZISHUAI (author)

    Publication date :

    2015-11-11


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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