The invention discloses an ultra-low orbit satellite high-precision attitude control system and method. The system comprises an attitude measurement sensitive module, an attitude controller and a control execution mechanism, wherein the attitude measurement sensitive module is used for measuring attitude information of a current satellite; the attitude controller is used for combining the attitude information of the current satellite and adopting a preset control strategy to solve the control quantity input of the control execution mechanism; and the control execution mechanism is used for generating torque influencing satellite attitude motion according to control quantity input so as to control the satellite attitude in a mode of alternately using reaction flywheel control and air injection control. Based on the propulsion system, the reaction flywheel and the magnetic torquer, the full-interval high-precision high-stability attitude control target for the ultra-low orbit satellite is realized.

    本发明公开了一种超低轨道卫星高精度姿态控制系统及方法,所述系统包括:姿态测量敏感模块、姿态控制器以及控制执行机构;其中,姿态测量敏感模块用于测量当前卫星的姿态信息;姿态控制器用于结合当前卫星的姿态信息,采用预设控制策略,解算出控制执行机构的控制量输入;控制执行机构用于根据控制量输入产生影响卫星姿态运动的力矩,以通过反作用飞轮控制与喷气控制交替使用的方式对卫星姿态进行控制。本发明基于推进系统、反作用飞轮及磁力矩器,实现了针对超低轨道卫星的全区间高精度高稳定度姿态控制目标。


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    Titel :

    Ultra-low orbit satellite high-precision attitude control system and method


    Weitere Titelangaben:

    一种超低轨道卫星高精度姿态控制系统及方法


    Beteiligte:
    WANG JUN (Autor:in) / CHANG LIANG (Autor:in) / ZHANG FEI (Autor:in) / WANG ZUN (Autor:in) / SHAO SHUAI (Autor:in)

    Erscheinungsdatum :

    15.09.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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