摘要
针对挠性卫星在飞行过程中存在参数不确定性、干扰(常值扰动和正弦扰动)及挠性附件的振动控制问题,提出了一类基于输出反馈控制系统的鲁棒设计方法,该设计仅利用姿态四元数输出信息,而无需角速度、挠性变形位移及其速率测量信息;同时,在控制中又引入积分环节用于减小常值干扰引起的稳态误差,并且控制器参数的选者并不依赖于系统参数,基于Lyapunov理论证明了所设计的控制器保证了姿态的稳定和模态振动的衰减;最后,将该方法应用于挠性卫星的姿态机动控制,仿真结果表明该控制器不仅对参数不确定性具有很好的鲁棒性,而且能够有效消除常值干扰和正弦干扰的影响,在完成姿态机动控制的同时,能够抑制挠性附件的结构振动,具有良好的过渡过程品质.
An angular velocity - free attitude control system is designed for an orbiting three - axis stabilized satellite with flexible appendages, which took into account parametric uncertainties and external disturbances （constant and periodic ones）. The designed controller, incorporates a low - pass linear filter, which is derived with- out explicit differentiation of attitude to synthesize angular velocity - like signals. Moreover, an integral feedback of the attitude was explicitly included to compensate the constant disturbances. The associated stability proof is constructive and accomplished by the development of a Lyapunov function candidate, which contains eross states and elastic vibration variables. The uniformly bounded stability of the closed - loop system is guaranteed and the elastic vibration is also passively reduced provided that the appropriate robustness conditions on the controller gains are satisfied. These conditions use partial knowledge of the parameters to describe the elastic dynamics. The closed -loop performance of the control solution derived here was evaluated extensively through numerical simulations.
出处
《动力学与控制学报》
2009年第4期379-384,共6页
Journal of Dynamics and Control
基金
国家自然科学基金(60774062)
高等学校博士学科点专项科研基金(20070213061)
教育部留学回国人员科研启动基金
黑龙江省留学回国人员科学基金(LC08C01)~~
关键词
挠性卫星
输出反馈控制
振动抑制
姿态控制
flexible satellite, output feedback control, vibration suppression, attitude control
