The invention provides a satellite attitude control method and system for satellite-ground alignment. The method comprises the following steps: acquiring output information of a detector of a payload, wherein the output information comprises a light spot coordinate of landmark laser on the detector through an optical lens; calculating an effective load reference optical axis and an optical axis deflection angle of the landmark laser according to the output information; calculating a final satellite station vector according to the optical axis deflection angle, wherein the final satellite station vector is a unit vector pointing to the ground communication station from the center of mass of the satellite under a satellite body coordinate system; calculating and measuring an opposite station angle according to the final satellite station vector; obtaining a satellite platform attitude determination attitude angle and a satellite platform attitude determination angular velocity; and calculating a satellite three-axis control moment according to the station aligning angle, the satellite platform attitude determination attitude angle and the satellite platform attitude determination angular velocity, and controlling the satellite platform to move according to the satellite three-axis control moment. The output information of the detector of the effective load is used as the input information of the control system of the satellite platform, a coarse tracking system can be omitted, and the system is simplified.

    本发明提供了一种用于星地对准的卫星姿态控制方法、系统。方法包括:获取有效载荷的探测器的输出信息,输出信息包括地标激光通过光学镜头在探测器上的光点坐标;根据输出信息计算有效载荷基准光轴与地标激光的光轴偏角;根据光轴偏角计算最终星站矢量,最终星站矢量为卫星本体坐标系下由卫星质心指向地面通信站的单位矢量;根据最终星站矢量计算测量对站角;获取卫星平台定姿姿态角和卫星平台定姿角速度;根据对站角、卫星平台定姿姿态角和卫星平台定姿角速度计算卫星三轴控制力矩,根据卫星三轴控制力矩控制卫星平台运动。本发明利用有效载荷的探测器的输出信息作为卫星平台的控制系统的输入信息,可以省去粗跟踪系统,使得系统简化。


    Access

    Download


    Export, share and cite



    Title :

    Satellite attitude control method and system for satellite-ground alignment


    Additional title:

    用于星地对准的卫星姿态控制方法、系统


    Contributors:
    CHEN TING (author) / WANG ZUN (author) / WU HUIYING (author) / CHANG LIANG (author) / YI SHAN (author) / SHAO SHUAI (author) / WANG MENG (author)

    Publication date :

    2023-09-15


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS




    SATELLITE POSITION/ATTITUDE CONTROL SYSTEM, AND SATELLITE POSITION/ATTITUDE CONTROL METHOD

    NODA ATSUSHI / SHIRASAWA YOJI / SHIGETO SHUHEI et al. | European Patent Office | 2020

    Free access

    Satellite attitude control method

    ZHAO YITAO / ZHANG NAN / LI BO et al. | European Patent Office | 2021

    Free access

    Artificial satellite, attitude control system, and attitude control method

    KITAMURA KENJI / SHIMA TAKEYA / YAMADA KATSUHIKO | European Patent Office | 2021

    Free access

    ARTIFICIAL SATELLITE, ATTITUDE CONTROL SYSTEM, AND ATTITUDE CONTROL METHOD

    KITAMURA KENJI / SHIMA TAKEYA / YAMADA KATSUHIKO | European Patent Office | 2019

    Free access