The invention discloses a multi-pulse high-precision autonomous position keeping control method for a geostationary orbit satellite, and the method comprises the steps: determining the average orbit element of the satellite according to the instantaneous orbit element of the satellite; determining in-plane and out-plane pulse control sequences of a satellite orbit according to the average orbit element of the satellite; determining the on-off logic of the thruster according to the in-plane and out-of-plane pulse control sequences of the satellite orbit; and controlling the on-off of the thruster according to the on-off logic of the thruster to realize the multi-pulse high-precision autonomous position keeping control of the geostationary orbit satellite. According to the method provided by the invention, the multi-pulse high-precision autonomous position keeping control of the geostationary orbit satellite is realized.

    本发明公开了一种地球静止轨道卫星多脉冲高精度自主位置保持控制方法,包括:根据卫星的瞬时轨道要素,确定卫星的平均轨道要素;根据卫星的平均轨道要素,确定卫星轨道面内与面外的脉冲控制序列;根据卫星轨道面内与面外的脉冲控制序列,确定推力器的开关机逻辑;根据推力器的开关机逻辑,控制推力器开关,实现地球静止轨道卫星多脉冲高精度自主位置保持控制。通过本发明所述的方法实现了地球静止轨道卫星多脉冲高精度自主位置保持控制。


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    Titel :

    Multi-pulse high-precision autonomous position keeping control method for geostationary orbit satellite


    Weitere Titelangaben:

    地球静止轨道卫星多脉冲高精度自主位置保持控制方法


    Beteiligte:
    WANG KAI (Autor:in) / TANG LIANG (Autor:in) / CHEN SHOULEI (Autor:in) / LIU YIWU (Autor:in) / WANG SHUO (Autor:in)

    Erscheinungsdatum :

    06.12.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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