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研究了挠性航天器高精度姿态控制问题。考虑被控对象的非线性、外部干扰以及挠性结构和惯量参数不确定性,设计了直接自适应姿态控制律。通过对经典直接自适应控制中参数自适应律的改进,进一步提高了姿态控制系统性能。该控制系统不仅考虑了挠性结构和惯量参数不确定性,同时考虑了系统非线性特性及外部干扰,且参考模型阶数小于实际被控对象阶数,控制系统结构简单。仿真结果验证了其有效性。
The problem of high-precision attitude control of flexible spacecraft is studied. Considering the nonlinearity of the controlled object, the external disturbance and the uncertainty of the parameters of the flexible structure and inertia, a direct adaptive attitude control law is designed. Through the improvement of parameter adaptive law in classical direct adaptive control, the performance of attitude control system is further improved. The control system not only considers the uncertainties of the parameters of the flexible structure and inertia, but also considers the nonlinear characteristics of the system and external disturbances. The order of the reference model is smaller than the actual order of the controlled object. The control system has a simple structure. Simulation results verify its effectiveness.