The invention relates to a thermal control system for a mass-produced small satellite, the mass-produced small satellite comprises a frame composed of a structural plate and a plurality of heat source single machines assembled on the inner side of the structural plate, the heat source single machines are fixed with the structural plate, pre-embedded heat pipes are pre-embedded in the structural plate, the inner side surface of the structural plate is coated with a first thermal control coating, the outer side face of the structural plate is coated with a second thermal control coating, the outer side of the structural plate is wrapped with a thermal insulation material, the position of the second thermal control coating is matched with the position of the heat source single machine installed on the structural plate, a hollow window area is formed in the thermal insulation material, and the position of the window area is matched with the position of the heat source single machine installed on the structural plate. According to the thermal control system, the frame design composed of the structural plates is adopted, the isothermal property and the heat dissipation capacity of the small satellites can be achieved, meanwhile, rapid design in the batch production process is achieved, and the requirements for the weight and the temperature of the small satellites and rapid design, rapid assembly and integration in the batch production process are met.

    本发明涉及一种用于量产化小卫星的热控系统,量产化小卫星包括由结构板组成的框架以及装配在结构板内侧的多个热源单机,热源单机与结构板固定,结构板内预埋设预埋热管,且结构板的内侧面涂覆第一热控涂层,结构板的外侧面涂有第二热控涂层,结构板的外侧包裹隔热材料,且第二热控涂层的位置与安装在结构板上的热源单机的位置相匹配,隔热材料上开设镂空的窗口区,窗口区的位置与安装在结构板上的热源单机的位置相匹配。本发明的热控系统通过采用上述结构板组成的框架设计,可实现小卫星的等温性和散热能力,同时实现批产过程中的快速设计,满足小卫星重量、温度以及批量从生产过程中的快速设计、快速装配,集成化需求。


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    Titel :

    Thermal control system for mass-produced small satellite


    Weitere Titelangaben:

    一种用于量产化小卫星的热控系统


    Beteiligte:
    HU LANFANG (Autor:in) / ZHU YE (Autor:in) / CAO CAIXIA (Autor:in) / LIANG HONG (Autor:in) / YU HUIYI (Autor:in) / LIU TINGYU (Autor:in) / XU ZHENGJUN (Autor:in)

    Erscheinungsdatum :

    2021-11-02


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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