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-...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.展开更多
The improved structural filter combined with Positive Position Feedback(PPF) controller is investigated for high-precision attitude control of flexible spacecraft which consists of rigid central body and flexible appe...The improved structural filter combined with Positive Position Feedback(PPF) controller is investigated for high-precision attitude control of flexible spacecraft which consists of rigid central body and flexible appendages.PPF controller is adopted for high frequency vibration suppression,while the improved structural filter is used for suppression of low frequency vibration.After introducing PPF controller,the vibration frequencies are changed.In view of the frequency uncertainties,an improved structural filter is designed,and the stability study for the centralized control system is conducted.The simulation results show that the performance of spacecraft control system is improved,and the control inputs remain unchanged.展开更多
文摘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.
文摘The improved structural filter combined with Positive Position Feedback(PPF) controller is investigated for high-precision attitude control of flexible spacecraft which consists of rigid central body and flexible appendages.PPF controller is adopted for high frequency vibration suppression,while the improved structural filter is used for suppression of low frequency vibration.After introducing PPF controller,the vibration frequencies are changed.In view of the frequency uncertainties,an improved structural filter is designed,and the stability study for the centralized control system is conducted.The simulation results show that the performance of spacecraft control system is improved,and the control inputs remain unchanged.
