The invention provides a high-integration satellite configuration suitable for multi-satellite formation flight, which comprises a satellite main structure, a solar cell array, a load, an inter-satellite communication unit and platform equipment, and is characterized in that the satellite main structure comprises structural components, the structural components are assembled into a hexahedral satellite body, the hexahedral satellite body is a satellite main body structure, and the solar cell array is arranged on the hexahedral satellite body; the solar cell array, the load, the inter-satellite communication unit and the platform device are respectively installed on the structural assembly. The invention has the beneficial effects that the satellite envelope size is effectively reduced, the long linear size distribution requirement of the load is met, the space design is compact, the integration degree is high, and the structural design is ingenious.

    本发明提供了一种适用于多星编队飞行的高集成度卫星构型,包括卫星主结构、太阳电池阵、载荷、星间通信单元及平台设备,所述卫星主结构包括结构组件,所述结构组件组装为六面体星体,所述六面体星体为卫星主体结构,所述太阳电池阵、载荷、星间通信单元及平台设备分别安装在所述结构组件上。本发明的有益效果是:有效降低了卫星包络尺寸,同时满足载荷的长线性尺寸分布要求,空间设计紧凑,集成度高,结构设计巧妙。


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    Titel :

    High-integration satellite configuration suitable for multi-satellite formation flight


    Weitere Titelangaben:

    一种适用于多星编队飞行的高集成度卫星构型


    Beteiligte:
    LIU XUEFENG (Autor:in) / GAO GE (Autor:in) / ZHUANG ZHIWEI (Autor:in) / YOON MU-HYUN (Autor:in) / ZHENG JING (Autor:in)

    Erscheinungsdatum :

    2024-03-01


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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