The invention provides a whole-satellite dynamic characteristic prediction method for an expandable structure during in-orbit expansion. The whole-satellite dynamic characteristic prediction method comprises the following steps: establishing a whole-satellite flexible dynamic equation and a flexible multi-body dynamic equation set in an expansion process of the expandable structure; carrying out one-step numerical integration on the flexible multi-body dynamics equation set; according to the integral result, the hinge which is unfolded in place or reaches preset clamping stagnation in the expandable structure is replaced by six-degree-of-freedom force element connection, the clamped hinge and the corresponding connecting part are locked, and a semi-locking and semi-unfolding mixed multi-body dynamic structure dynamic model is established; through modal analysis, rigid body modals are eliminated, and a deployable structure dynamic model is obtained; on the basis of the deployable structure dynamic model and the whole satellite flexible dynamic equation, obtaining a semi-locking dynamic model and a semi-unfolding dynamic model during the on-orbit unfolding period of the satellite; therefore, the problems of whole-satellite attitude stable control input and unfolding fault handling and whole-satellite model handling caused by the fact that the satellite-borne deployable structure is unfolded and locked at the same time during the on-orbit unfolding period can be solved.

    本发明提供了一种可展开结构在轨展开期间的整星动力学特性预示方法,通过建立整星柔性动力学方程和可展开结构展开过程的柔性多体动力学方程组;对柔性多体动力学方程组进行一步数值积分;根据积分结果,将可展开结构中展开到位或到达预设卡滞为止的铰链替换为六自由度力元连接,将卡滞的铰链与对应的连接部件锁定,并建立半锁定和半展开混合的多体动力学结构动力学模型;通过模态分析,消除刚体模态,得到可展开结构动力学模型;基于可展开结构动力学模型和整星柔性动力学方程,得到卫星在轨展开期间的半锁定和半展开动力学模型;如此,本发明能够解决星载可展开结构在轨展开期间边展开边锁定带来的全星姿态稳定控制输入和展开故障处置整星模型处置问题。


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    Title :

    Method for predicting whole-satellite dynamic characteristics of deployable structure during on-orbit deployment


    Additional title:

    可展开结构在轨展开期间的整星动力学特性预示方法


    Contributors:
    DONG FUXIANG (author) / DENG MINGLE (author) / XU HONGYAN (author) / ZHOU ZHICHENG (author) / WANG MIN (author) / JIANG CHUNYANG (author)

    Publication date :

    2025-01-24


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    G16C / B64G Raumfahrt , COSMONAUTICS / G06F ELECTRIC DIGITAL DATA PROCESSING , Elektrische digitale Datenverarbeitung





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