本发明提供了一种以载荷为中心的卫星平台协同控制方法,该方法包括:根据载荷平台在载荷平台坐标系下相对于载荷平台旋转坐标系的姿态偏差和姿态角速度偏差,以对磁悬浮关节进行指向控制;对磁悬浮关节的涡流传感器测量数据进行解算,得到磁悬浮关节的位移量,以对载荷平台和卫星平台的相对位置进行控制;根据载荷平台的期望控制力矩和期望控制力,确定不同安装位置的磁悬浮关节的输出控制力矩和输出控制力;根据姿态偏差计算得到卫星平台相对载荷平台的姿态误差;根据姿态偏差、姿态角速度偏差、位移量、输出控制力矩、输出控制力和姿态误差对卫星平台进行控制。本方案提高了载荷平台的控制精度和控制稳定度,进而提高了对卫星平台的控制稳定度。

    The invention provides a load-centered satellite platform cooperative control method, which comprises the following steps of: performing pointing control on a magnetic suspension joint according to attitude deviation and attitude angular velocity deviation of a load platform relative to a load platform rotating coordinate system under a load platform coordinate system; calculating the measurement data of the eddy current sensor of the magnetic suspension joint to obtain the displacement of the magnetic suspension joint so as to control the relative position of the load platform and the satellite platform; according to the expected control moment and the expected control force of the load platform, the output control moment and the output control force of the magnetic suspension joints at different installation positions are determined; calculating an attitude error of the satellite platform relative to the load platform according to the attitude deviation; and controlling the satellite platform according to the attitude deviation, the attitude angular velocity deviation, the displacement, the output control torque, the output control force and the attitude error. According to the scheme, the control precision and the control stability of the load platform are improved, and the control stability of the satellite platform is further improved.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    一种以载荷为中心的卫星平台协同控制方法


    Erscheinungsdatum :

    17.06.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS