基于直接自适应的挠性航天器姿态稳定控制  

Flexible Spacecraft Attitude stabilization Control Based on Direct Adaptive Algorithm

作　　者：刘敏[1] 徐世杰[1] 韩潮[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《中国空间科学技术》2012年第4期1-7,共7页Chinese Space Science and Technology

基　　金：国家自然科学基金(10872028)资助项目

摘　　要：针对挠性航天器姿态稳定控制,基于退步控制方法与直接自适应控制方法提出了一种自适应控制策略。首先将挠性航天器模型分解为运动学子系统和动力学子系统,并设计具有理想控制性能的参考模型;然后在姿态小角度的假设下,对满足近似严格正实性的姿态运动学子系统设计了直接自适应中间控制律;最后运用退步控制方法对航天器动力学子系统设计了姿态控制器,并证明了闭环系统的稳定性。理论分析和数值仿真结果表明该控制器对挠性航天器的姿态稳定控制是有效的。An adaptive control strategy based on backstepping control and direct adaptive control was proposed to resolve the flexible spacecraft attitude stabilization control problem. Firstly, the flexible spacecraft was divided into dynamics subsystem and kinematics subsystem, and an ideal reference model was designed. Secondly, under the assumption of small attitude angle, a direct adaptive intermediate control law was designed. Finally, the spacecraft attitude controller was designed by adopting the backstepping control method, and the stability of the close-loop control system was proved. Theoretical study and numerical simulation results validate the efficiency of the flexible spacecraft adaptive attitude stabilization controller.

关 键 词：姿态控制 直接自适应控制 退步控制 挠性航天器 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]