挠性航天器的二阶滑模姿态机动控制  

The second-order sliding mode attitude maneuver control for flexible spacecraft

作　　者：吴希岩 管萍[1] 戈新生[1] WU Xiyan;GUAN Ping;GE Xinsheng(School of Automation,Beijing Information Science&Technology University,Beijing 100192,China)

机构地区：[1]北京信息科技大学自动化学院,北京100192

出　　处：《北京信息科技大学学报（自然科学版）》2021年第2期22-27,32,共7页Journal of Beijing Information Science and Technology University

基　　金：国家自然科学基金资助项目(11472058);国家自然科学基金重点资助项目(11732005)。

摘　　要：针对大角度姿态机动的挠性航天器,将二阶滑模控制应用于挠性航天器的姿态控制中。采用修正型罗德里格参数描述挠性航天器的运动学方程,设计了二阶滑模姿态机动控制器,并基于李雅普诺夫稳定性理论证明了整个控制系统的稳定性。利用姿态角误差和角速度误差构造滑模面,选取二阶滑模趋近律,得到二阶滑模控制律,提高了滑模变量的相对阶数。对所提出的挠性航天器的二阶滑模姿态机动控制系统进行了仿真研究。仿真结果表明,系统可有效抑制挠性附件的振动,对外界扰动和转动惯量不确定性具有较强的鲁棒性,并对姿态角指令有较好的跟踪性能。For the large angle attitude maneuver,the second-order sliding mode control is applied to attitude control system of flexible spacecraft.The modified Rodrigues parameters are used to describe the kinematics equation of flexible spacecraft and the second-order sliding mode attitude maneuver controller is designed.Based on Lyapunov stability theory,the stability of the whole control system is verified.A second-order sliding mode attitude maneuver control system for a flexible spacecraft is simulated.The simulation results show that the system can effectively suppress the vibration of flexible appendage,has strong robustness to external disturbance and inertia uncertainty,and has better tracking performance to attitude angle commands.

关 键 词：挠性航天器 姿态控制 二阶滑模 振动抑制 不确定性 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]