基于摄动模型的挠性航天器姿态控制系统设计

为了完成挠性航天器高精度姿态控制任务,首先采用摄动法分析了挠性航天器动力学方程,得到相应的0阶和1阶动力学系统.针对0阶非线性时不变系统,同时考虑到转动惯量不确定性和干扰,对已有的非线性直接自适应控制律进行改进,设计PI(Propor-tional-Integral)型参数自适应律,以提高姿态控制精度,同时给出了稳定性证明.针对1阶系统设计PI控制器及PPF(Positive Position Feedback)控制器,以有效抑制挠性结构振动.仿真结果表明,在采用摄动法对动力学方程分析的基础上设计姿态控制系统,可以有效完成挠性航天器高精度姿态控制任务.

Flexible spacecraft attitude control based on perturbation method analysis

In order to achieve flexible spacecraft high precision attitude control, using the perturbation method, the dynamic equations were divided into the zero order and first order systems. For the zero-order nonlinear time-invariant systems, taking into account the inertia uncertainty and disturbance, the nonlinear direct adaptive control law was improved, and the improvement of the gain adaptation law aimed at the higher precision. Also, the stability proof was given. For the first-order system, the proportional-integral(PI) controller and positive position feedback(PPF) controller were designed to suppression the vibration. The simulation shows that the perturbation analysis and the corresponding controller design can achieve the flexible spacecraft high precision attitude control.