A satellite includes a structural element that is deformable during a collision with a spatial object. The structural element includes a first side, a second side spaced apart from the first side to define an interior portion between the first side and the second side, and at least one material disposed within the interior portion. The first side includes a first material layer on which a payload element is disposed, and the second side includes a second material layer. The material disposed within the inner portion is designed to absorb energy during a collision process with each spatial object. The first layer, the second layer, and/or the material disposed within the interior portion are configured to capture one or more spatial objects upon collision with a satellite.

    一种卫星包括结构元件,所述结构元件在与空间物体碰撞期间可变形。所述结构元件包括第一侧、与第一侧间隔开以在第一侧与第二侧之间限定内部部分的第二侧、以及设置在内部部分内的至少一种材料。第一侧包括上面设置有有效载荷元件的第一材料层,并且第二侧包括第二材料层。设置在内部部分内的所述材料被设计成在与每个空间物体的碰撞过程期间的时间内吸收能量。第一层、第二层和/或设置在内部部分内的所述材料被配置成在与卫星碰撞时捕获一个或多个空间物体。


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    Title :

    Space debris capturing device and implementation method thereof


    Additional title:

    空间碎片捕获装置及其实施方法


    Contributors:

    Publication date :

    2024-08-23


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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