The invention belongs to the field of spacecraft control, and relates to a geosynchronous orbit satellite omnidirectional thrust coupling position keeping method. According to the method, a multi-pulse control scheme considering thrust coupling is adopted, and the method is suitable for the situation that north-south position protection and east-west position protection have the radial thrust coupling effect. The method comprises the processes of south-north bit-hold control quantity calculation, eccentricity rate control quantity calculation, radial thrust compensation, flat longitude drift rate control quantity iterative calculation, double-pulse control parameter calculation, three-pulse control parameter calculation and the like, and thrust coupling position holding combined control is achieved through bit-hold ignition moment optimization and control quantity iterative solution.

    本发明属于航天器控制领域,涉及一种地球同步轨道卫星全向推力耦合位置保持方法。本发明采用考虑推力耦合的多脉冲控制方案,适用于南北位保和东西位保具有径向推力耦合作用的情形。本发明包含南北位保控制量计算、偏心率控制量计算、径向推力补偿、平经度漂移率控制量迭代计算、双脉冲控制参数计算和三脉冲控制参数计算等过程,通过位保点火时刻优化和控制量迭代求解,实现了推力耦合位置保持联合控制。


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    Titel :

    Omnidirectional thrust coupling position keeping method for geosynchronous orbit satellite


    Weitere Titelangaben:

    一种地球同步轨道卫星全向推力耦合位置保持方法


    Beteiligte:
    SHI HENG (Autor:in) / LIU XIAOXIANG (Autor:in) / LIN BO (Autor:in) / LIU LEI (Autor:in) / HE GANG (Autor:in) / WANG KAI (Autor:in) / GUO JIANXIN (Autor:in) / CHANG JIANSONG (Autor:in) / WANG ZUOWEI (Autor:in) / WU PEIYA (Autor:in)

    Erscheinungsdatum :

    14.06.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS




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