The invention provides a flexible ball spacecraft inflation unfolding structure evaluation method, which can evaluate the rationality and reliability of the inflatable unfolding structure of the flexible ball spacecraft. The method relates to flexible ball spacecraft test conditions, installation bearing modes and flexible ball inflation unfolding process monitoring, the inflation unfolding function of the flexible ball spacecraft can be verified, and then the inflation unfolding structure of the flexible ball spacecraft is evaluated.

    本发明提供了一种柔性球航天器充气展开结构评估方法,能够评估柔性球航天器充气展开结构的合理性、可靠性。涉及柔性球航天器试验条件、安装承载方式以及柔性球充气展开过程监测,可以验证柔性球航天器的充气展开功能,进而对柔性球航天器充气展开结构进行评估。


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    Titel :

    Flexible ball spacecraft inflation unfolding structure evaluation method


    Weitere Titelangaben:

    一种柔性球航天器充气展开结构评估方法


    Beteiligte:
    WANG HU (Autor:in) / ZHANG KAIFENG (Autor:in) / LI LIN (Autor:in) / ZUO HUAPING (Autor:in) / CAO SHENGZHU (Autor:in) / LI XUELEI (Autor:in) / HAO HONG (Autor:in) / LUO SHUILIAN (Autor:in) / GAO HENGJIAO (Autor:in) / WANG ZHIMIN (Autor:in)

    Erscheinungsdatum :

    02.04.2021


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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