摘要
研究了具有模型参数不确定和受空间环境干扰影响的挠性航天器姿态大角度快速机动快速稳定控制问题,设计了一种受细胞膜放电模型启发的鲁棒姿态控制器。综合考虑挠性航天器的强非线性和强耦合特性,设计了对模型参数和环境干扰具有鲁棒性的姿态机动控制器。为了减小机动中姿态突变激发的挠性附件振动,基于细胞膜放电的动力学模型设计了一种改进的鲁棒控制器。当参数不确定范围和干扰有界时,所提鲁棒控制器可使闭环系统的解最终一致有界。最后,分析了控制器参数对姿态控制性能及所需能量的影响。数值仿真验证了所提鲁棒控制器用于姿态机动控制可以得到良好的效果。
Under model parametric uncertainties and external disturbances in space,this study investigates attitude maneuvering control for large angle rapid maneuvering and fast stable of flexible spacecraft.A cell membrane discharge model enlightened robust attitude maneuvering control law is designed.To cope with the existing model parametric uncertainties and external disturbances,a robust attitude maneuvering controller is proposed based on the nonlinear and coupled characteristics of flexible spacecraft.The problem of jump of attitude which will excite the elastic vibration mode during large angle maneuver of flexible spacecraft is studied.By using dynamics model of cell membrane discharge,an improved robust attitude maneuvering controller is proposed.When the errors of model parametric uncertainties and external disturbances are bounded,it is proved that the closed-loop system is uniformly ultimately bounded.Finally,by using the control parameters properly,the control performance can be improved and the control energy can be reduced.The simulation results demonstrate the effectiveness of the proposed robust controller.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2013年第2期222-230,共9页
Journal of Astronautics
基金
国家自然科学基金(60975075
61074023)
关键词
挠性航天器
姿态控制
非线性系统
鲁棒控制
快速机动
Flexible spacecraft
Attitude control
Nonlinear system
Robust control
Rapid maneuvering
