【摘要】 针对空间飞行器常带有大型挠性附件,而挠性附件的振动往往使控制系统性能变差的问题,提出了一种能有效抑制系统残留振动的姿态机动控制策略,即机动控制内环结合前置补偿结构.控制内环为由姿态控制执行机构(PWPF modulator)、控制器(PD controller)构成的挠性卫星姿态闭环系统,前置补偿器采用多模态输入成型器.内环用于保证主刚体的期望转动,输入成型器则用于抑制系统的残留振动.仿真结果表明:在卫星姿态满足期望指向的前提下,基于Pade′拟合设计的多模态成型器更短,对于系统的参数摄动也具有一定的鲁棒性.该控制策略改善了姿态机动控制系统的过渡过程.更多还原

【Abstract】 Considering the condition that modern spacecraft are always of large flexible appendages and the fact that the flexible vibration often degrades the control system performance,this paper employs a method that consists of a feedforward compensator and a feedback control loop to fulfill attitude maneuver rapidly with little residual vibration.Including a pulse-width pulse-frequency modulator and a proportional differential(PD) controller,the feedback control loop is designed to meet desired performance;the feed-forward compensator,a multi-mode input shaper based on Pade′approximation,is designed to eliminate whole system residual vibration.Simulation results show that the proposed multi-mode input shaper has shorter length and can provide robustness to parameter uncertainty.During maneuvers,the presented control strategy introduces less overshoots and shorter system response time.更多还原