A high-precision satellite attitude control method only controlled by a magnetic torquer comprises the following steps: firstly, calculating an expected control moment according to an attitude angle and an attitude angular velocity, and then calculating an expected control magnetic moment according to geomagnetic field information and the expected control moment; then, according to inertial angular velocity information, gravity gradient moment estimation and last-cycle theoretical control moment estimation are combined, filtering estimation is carried out on the satellite residual magnetic moment by using a formula provided by the invention, and finally, the estimated residual magnetic moment is deducted from the expected control magnetic moment, and the expected control magnetic moment is converted into magnetic torquer control voltage to be output.
一种仅使用磁力矩器控制的高精度卫星姿态控制方法,首先根据姿态角和姿态角速度计算期望控制力矩,再根据地磁场信息和期望控制力矩计算期望控制磁矩,然后根据惯性角速度信息结合重力梯度力矩估计和上周期理论控制力矩估计,使用本发明提供的公式对卫星剩磁矩进行滤波估计,最后将期望控制磁矩扣除估计的剩磁矩并转换为磁力矩器控制电压进行输出。
High-precision satellite attitude control method only using magnetic torquer for control
一种仅使用磁力矩器控制的高精度卫星姿态控制方法
2024-06-21
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
LEQG and Game Theoretic Satellite Attitude Control With Magnetic Torquer
British Library Conference Proceedings | 1997
|Attitude Control by Magnetic Torquer (AAS 09-169)
British Library Conference Proceedings | 2009
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