The embodiment of the invention provides a satellite attitude control method and device and a satellite, and relates to the technical field of aerospace, and the satellite is provided with a first magnetic torquer mounted on an X axis, a second magnetic torquer mounted on a Y axis and a reaction wheel mounted on a Z axis. The method comprises the steps of obtaining an expected control moment based on an angular velocity error, an attitude angle error and a preset angular velocity threshold value of a satellite; according to the working state and the expected control torque of the reaction wheel, a first magnetic moment instruction of the first magnetic torquer and a second magnetic moment instruction of the second magnetic torquer are adjusted, and a control torque instruction of the reaction wheel is adjusted, so that the attitude of the satellite is controlled. By applying the technical scheme provided by the embodiment of the invention, the structural thickness of the satellite in the opposite direction can be reduced, and the satellite launching cost is reduced.
本申请实施例提供了一种卫星的姿态控制方法、装置及卫星,涉及航空航天技术领域,卫星上配置有在X轴上安装的第一磁力矩器、在Y轴上安装的第二磁力矩器和在Z轴上安装的反作用轮,上述方法包括:基于卫星的角速度误差、姿态角误差和预设角速度阈值,获得期望控制力矩;根据反作用轮的工作状态和期望控制力矩,调整第一磁力矩器的第一磁矩指令和第二磁力矩器的第二磁矩指令,以及调整反作用轮的控制力矩指令,以对卫星的姿态进行控制。应用本申请实施例提供的技术方案可以降低卫星沿对地方向的结构厚度,降低卫星发射成本。
Satellite attitude control method and device and satellite
一种卫星的姿态控制方法、装置及卫星
2023-11-10
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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