The invention provides a full-frame type hollowed-out satellite configuration which comprises a satellite main structure, the satellite main structure comprises a structural part and a mechanism part, the structural part comprises a full-hollowed-out metal frame body with a cabin, and the full-hollowed-out metal frame body is formed by splicing a bottom plate, side plates and a top plate. The side plates and the top plate are all of a full-frame hollowed-out structure. The full-frame open-type hollow-out satellite structure has the beneficial effects that the full-frame open-type hollow-out structure is adopted, so that the weight ratio of the satellite structure is reduced to the maximum extent, and meanwhile, the satellite structure is easy to assemble.

    本发明提供了一种全框架式镂空卫星构型,包括卫星主结构,所述卫星主结构包括结构部分和机构部分,所述结构部分包括具有舱体的全镂空金属框架主体,所述全镂空金属框架主体由底板、侧板及顶板拼接而成,所述侧板与所述顶板均采用全框架镂空结构。本发明的有益效果是:采用的全框架开敞式镂空结构,最大化地降低了卫星结构重量占比,同时易于装配。


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    Titel :

    Full-frame type hollow satellite configuration


    Weitere Titelangaben:

    一种全框架式镂空卫星构型


    Beteiligte:
    GAO GE (Autor:in) / LIU XUEFENG (Autor:in) / HAN FEI (Autor:in) / TANG XINCHUN (Autor:in) / SUN RISI (Autor:in)

    Erscheinungsdatum :

    2022-12-20


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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