The invention provides a spacecraft angular momentum control method and system, and the method comprises the steps: closing a momentum wheel to avoid the loss of momentum unloading in a first stage of orbit transfer, and enabling an on-satellite attitude chemical thruster to carry out the satellite attitude control and adjustment in the first stage of orbit transfer; in the second orbital transfer stage, the unloading amount is pre-judged in advance, momentum unloading is conducted according to the pre-judgment result and the vector adjustment range, and in the first orbital transfer stage, the electric thruster conducts satellite orbital transfer; and in the third orbital transfer stage, the momentum wheel is closed to avoid loss of momentum unloading, and in the third orbital transfer stage, the on-satellite attitude chemical thruster is made to conduct satellite attitude control and fixed-point capture control.

    本发明提供了一种航天器角动量控制方法及系统,包括:在轨道转移第一阶段中,关闭动量轮以规避动量卸载的损耗,其中在轨道转移第一阶段中,使星上姿态化学推力器进行卫星姿态控制和调整;在轨道转移第二阶段中,提前预判卸载量,根据预判结果和矢调调节范围进行动量卸载,其中在轨道转移第一阶段中,使电推力器进行卫星变轨;以及在轨道转移第三阶段中,关闭动量轮以规避动量卸载的损耗,其中在轨道转移第三阶段中,使星上姿态化学推力器进行卫星姿态控制和定点捕获控制。


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    Titel :

    Spacecraft angular momentum control method and system


    Weitere Titelangaben:

    航天器角动量控制方法及系统


    Beteiligte:
    JIANG GUOWEI (Autor:in) / LIN BAOJUN (Autor:in) / SHEN YUAN (Autor:in) / WU GUOQIANG (Autor:in)

    Erscheinungsdatum :

    02.09.2022


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS




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