The invention discloses a spacecraft high-precision attitude control method based on sliding mode disturbance observation. The method comprises the following steps: determining an attitude angle error and an angular velocity error of a spacecraft; the PD controller determines the attitude control torque of the spacecraft system when interference is not considered according to the attitude angle error of the spacecraft and the angular velocity error of the spacecraft; determining the attitude control moment of the spacecraft system when the interference is considered by using the interference estimated value and not considering the attitude control moment of the spacecraft system when the interference is considered; the three-axis attitude angle of the spacecraft and the angular velocity of the spacecraft are determined through the total interference and the attitude control torque of the spacecraft system during interference, and then high-precision attitude control over the spacecraft is completed; and the interference observer determines an interference estimation value by using the three-axis attitude angle of the spacecraft and the angular velocity of the spacecraft, and after the interference estimation value is fed back, the interference estimation value is used for determining the attitude control torque of the spacecraft system when the interference is considered so as to realize closed-loop control.
一种基于滑模干扰观测的航天器高精度姿态控制方法,包括:确定航天器的姿态角误差、航天器的角速度误差;PD控制器根据航天器的姿态角误差、航天器的角速度误差,确定不考虑干扰时航天器系统的姿态控制力矩;利用干扰估计值、不考虑干扰时航天器系统的姿态控制力矩,确定考虑干扰时航天器系统的姿态控制力矩;利用总干扰、干扰时航天器系统的姿态控制力矩,确定航天器的三轴姿态角、航天器的角速度,进而完成航天器高精度姿态控制;干扰观测器利用航天器的三轴姿态角、航天器的角速度,确定干扰估计值,该干扰估计值反馈后,用于确定考虑干扰时航天器系统的姿态控制力矩,实现闭环控制。
Spacecraft high-precision attitude control method based on sliding mode disturbance observation
一种基于滑模干扰观测的航天器高精度姿态控制方法
2022-09-02
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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