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对于三轴角动量飞轮式卫星的姿态控制提出了一种鲁棒控制设计方法。针对挠性卫星中存在的未建模动态以及参数不确定性问题,基于H∞控制理论对姿态控制器进行了设计,通过选取合适的加权函数将姿态控制问题转化为标准H∞控制问题,进而获得所需控制器。并与PID控制器进行了仿真实验对比,仿真结果表明,对于系统中存在的干扰和参数不确定性,H∞控制具有良好的鲁棒稳定性与动态性能。
For the attitude control of three-axis angular momentum flywheel satellite, a robust control design method is proposed. In view of the unmodeled dynamics and parameter uncertainties existing in the flexible satellite, the attitude controller is designed based on the H∞ control theory, and the attitude control problem is transformed into the standard H∞ control problem by selecting the appropriate weighting function. Get the required controller. Compared with the PID controller, the simulation results show that the H∞ control has good robust stability and dynamic performance for the disturbance and parameter uncertainty existing in the system.