The invention provides a 2U cubesat configuration, which is characterized in that a satellite adopts a stack type design scheme in an available envelope space of a separation launching device, and comprises a deorbit sail (1), a main frame structure (2), an expansion type solar wing (5), a fixed type solar wing (4), a camera (14) and a UV expansion antenna (7). High-density integration of the 2U cubic satellites is achieved, the utilization efficiency of the internal space of the 2U cubic satellites is greatly improved, the internal space of the separation spring of the separation launching device is fully utilized, the universality is high, and the cost is low.

    本发明提供了一种2U立方星构型,在满足分离发射装置可用包络空间内,卫星采用堆栈式设计方案,包括离轨帆(1)、主框架结构(2)、展开式太阳翼(5)、固定式太阳翼(4)、相机(14)、UV展开天线(7)。本发明实现了2U立方星的高密度集成,大幅提高2U立方星内部空间利用效率,且充分利用了分离发射装置分离弹簧内部空间,通用性强,成本低。


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    Title :

    2U cubesat configuration


    Additional title:

    一种2U立方星构型


    Contributors:
    HU YONGQIANG (author) / HAN YIHONG (author) / LIU ZHIJIA (author) / LIU JIANG (author) / BAI ZHAOGUANG (author) / WANG CHONGYU (author)

    Publication date :

    2024-03-26


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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