The invention discloses an attitude and orbit coupling control method and an attitude and orbit coupling control system. The attitude and orbit coupling control method comprises the following steps: determining an orbit motion state; determining an attitude motion state; determining an attitude and orbit coupling motion state according to the orbit motion state and the attitude motion state; and obtaining a coupling motion relationship of attitude control and orbit control according to the attitude and orbit coupling motion state, and issuing a control instruction according to the coupling motion relationship. The method and the system have the technical effects of simplifying the system design, improving the system reliability and reducing the system risk.

    本申请公开了一种姿轨耦合控制方法及其系统,其中,姿轨耦合控制方法,包括:确定轨道运动状态;确定姿态运动状态;根据轨道运动状态和姿态运动状态确定姿轨耦合运动状态;根据姿轨耦合运动状态获取姿控轨控的耦合运动关系,并依据耦合运动关系下发控制指令。本申请具有简化系统设计、提高系统的可靠性和降低系统风险的技术效果。


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    Titel :

    Attitude and orbit coupling control method and attitude and orbit coupling control system


    Weitere Titelangaben:

    一种姿轨耦合控制方法及其系统


    Beteiligte:
    WU WEIPING (Autor:in) / MA YUHAI (Autor:in) / LIAN JIE (Autor:in) / ZHANG XIA (Autor:in) / YUAN CHUNGUI (Autor:in) / LIU KAI (Autor:in) / YANG YIQIANG (Autor:in)

    Erscheinungsdatum :

    10.04.2020


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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