太阳帆飞行器自适应极点配置控制方法研究  

Method of adaptive pole assignment control of spacecraft with solar sail

作　　者：邱锋[1,2] 杨星[1] 张莹[3] 

机构地区：[1]西北工业大学航天学院 [2]中国人民解放军96361部队 [3]西安卫星测控中心

出　　处：《现代电子技术》2014年第2期21-25,共5页Modern Electronics Technique

基　　金：航空科学基金(2012ZA53004);西北工业大学基础研究基金(JC201206)资助

摘　　要：太阳帆航天器对执行机构有着特定的要求,在此基于控制杆和偏置动量反作用飞轮展开研究,就姿态控制系统的物理模型及太阳帆的姿态动力学模型进行分析。并针对此类模型,利用鲁棒极点配置方法设计自适应控制器及太阳帆航天器姿态控制系统,通过数值仿真研究姿态控制中的姿态纠偏。结果表明,采用自适应鲁棒极点配置控制方法的控制系统能够使飞行器能够较快实现大角度的姿态控制要求。The spacecraft with solar sail has specific requirements for its actuator. The control rod and bias momentum reac-tion flywheel are studied in this paper. Physical model of the attitude control system and attitude dynamics model of the solar sail are analyzed. As for this kind of model,the robust pole assignment method is used to design the adaptive controller and atti-tude control system of the spacecraft with solar sail. The attitude correction of attitude control system is studied by means of nu-merical simulation. The results show that the control system which adopts robust adaptive pole assignment control method can make the spacevehicle realize large angle attitude control.

关 键 词：飞轮 太阳帆 鲁棒极点配置 自适应控制 

分 类 号：TN911.34[电子电信—通信与信息系统]