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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    Title :

    Omnidirectional thrust coupling position keeping method for geosynchronous orbit satellite


    Additional title:

    一种地球同步轨道卫星全向推力耦合位置保持方法


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

    Publication date :

    2024-06-14


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS




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