带有可伸缩挠性附件航天器的姿态控制  

Attitude Control of Spacecraft with Deployable and Retractable Flexible Appendage

作　　者：沈少萍[1] 

机构地区：[1]厦门大学自动化系,厦门361005

出　　处：《系统仿真学报》2009年第8期2288-2291,共4页Journal of System Simulation

基　　金：973计划资助(2002CB312205);刚-柔-控耦合系统几何非线性动力学;控制及实验(10372015);国家自然基金重点项目(60034010);空间智能控制技术国家级重点实验室项目资助;厦门大学引进人才科研启动资助

摘　　要：根据特征模型的参数推算了系统实时的转动惯量,设计了基于转动惯量的黄金分割自适应控制器和逻辑微分控制器,将这两种控制器相结合对带有可伸缩挠性附件的刚体进行姿态控制,仿真结果与基于确知系统模型所设计的变系数PD控制器相比较,表明了该自适应方法控制一类时变系统的有效性。基于特征模型的自适应方法不需要知道系统具体的模型,具有很强的鲁棒性能,因此这种方法具有很重要的实际应用价值。Through the characteristic parameters, the system ＂s real-time moment of inertia was given. Then golden section adaptive control law and logic derivative control law both based on moment of inertia were designed, The two kind of control laws were combined to control the attitude of spacecraft and their simulation results were compared with the ones of PD control law which was designed based on the certainly-known system model. The results show that this adaptive control law is effective on one kind of time-variable system studied. This adaptive control method needn＇t know the model of system and its robustness is very strong, so it has very important engineering practical value.

关 键 词：特征模型 可伸缩挠性附件 黄金分割自适应控制器 转动惯量 

分 类 号：V448.223[航空宇航科学与技术—飞行器设计]