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为解决航天器姿态控制中考虑非主轴惯量不确定性和外干扰的问题,设计了滑模控制器组成的鲁棒控制系统来处理系统中的参数不确定性及外干扰项的影响,并在滑模控制器的到达运动控制律设计中引入一个滞后因子来减小系统所需的最大控制力矩,从而节省航天器的控制成本.仿真结果验证了所设计控制器的性能,同时验证了控制律中的符号函数对于抑制抖振现象,提高控制精度的作用.
In order to solve the problem of uncertainty and disturbance of non-spindle inertia in spacecraft attitude control, a robust control system composed of sliding mode controllers is designed to deal with the influence of parameter uncertainty and external disturbance in the system. A hysteresis factor is introduced into the sliding mode controller’s arrival control law design to reduce the maximum control torque required by the system, so as to save spacecraft’s control cost.The simulation results verify the performance of the designed controller and verify that the control law The symbol function in the suppression of chattering phenomenon and improve the control accuracy of the role.