动态滑模在航天器姿态控制中的应用  

Application of dynamic sliding mode in spacecraft attitude control

作　　者：罗宗樾 管萍[1] 戈新生[1] LUO Zongyue;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4期9-13,共5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：针对挠性航天器大角度姿态机动问题,采用动态滑模控制的方法设计了姿态机动控制律。首先,用挠性航天器三轴姿态角描述其姿态运动学方程,得到挠性航天器的系统模型;然后,通过对传统滑模控制中的切换函数进行微分得到新的切换函数,设计出挠性航天器的动态滑模控制律,并证明了其稳定性。最后的仿真结果表明,与传统滑模控制器相比,动态滑模不仅具有鲁棒性强、参数变化不敏感等优点,而且能有效地削弱抖振,抑制挠性附件振动,从而使挠性航天器的跟踪误差快速收敛到零,具有较好的控制性能。The dynamical sliding mode control method was used to design the attitude maneuver control law to solve the large angle attitude maneuver problem of flexible spacecraft.First,the three-axis attitude angle was used to describe the kinematics equation of flexible spacecraft.Then,the switching function of traditional sliding mode control was transformed into a new switching function through differential link,and the dynamical sliding mode control law of flexible spacecraft was designed.The stability of flexible spacecraft attitude control system was verified.The simulation results show that dynamical sliding mode control not only has the advantages of strong robustness and insensitivity to parameter change,but also can effectively weaken the chattering and suppress the vibration of flexible appendages,so that the flexible spacecraft tracking error can quickly converge to zero and satisfactory control performance is achieved.

关 键 词：航天器 挠性附件 姿态机动 动态滑模 振动抑制 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]