基于SGCMGs的挠性航天器预定时间滑模姿态机动控制  

Predefined-time sliding mode attitude maneuver control for SGCMGs-based flexible spacecraft

作　　者：王璐[1] 郭健 刘辽雪 Wang Lu;Guo Jian;Liu Liaoxue(School of Automation,Nanjing University of Science and Technology,Nanjing 210094,China)

机构地区：[1]南京理工大学自动化学院,江苏南京210094

出　　处：《南京理工大学学报》2024年第5期586-595,共10页Journal of Nanjing University of Science and Technology

基　　金：国家自然科学基金(62403242);江苏省自然科学基金(BK20241459);中央高校基本科研业务费专项资金(30924010932)。

摘　　要：针对挠性航天器中存在的外部时变干扰影响因素,提出了一种预定时间滑模姿态控制方法。设计自适应律估计未知干扰上界,并在控制器中对其进行补偿,以抑制外部干扰对系统的不利影响。同时,在挠性航天器姿态机动控制方案设计和稳定性分析过程中,引入对执行机构单框架控制力矩陀螺群(SGCMGs)动力学因素的分析,相对于已有方案更贴合实际应用。进一步地,该文采用Lyapunov理论证明了系统实际预定时间稳定。仿真结果可得,该文控制方案可使系统获得较高稳态精度,并可实现姿态快速机动。A predefined-time sliding mode attitude control method is proposed to address the external time-varying disturbance uncertainty in a flexible spacecraft system.An adaptive law is designed to estimate the unknown disturbance upper bound and the disturbance can be compensated to reduce the adverse effects of external disturbance on the system.Meanwhile,in the attitude maneuver control scheme design and stability analysis,the dynamics of the actuator single gimbaled control moment gyroscopes(SGCMGs)are analyzed,which is more practical in applications,compared to existing methods.Furthermore,the Lyapunov stability theory is applied to prove that the system is practical predefined-time stable.The simulation results show that the proposed control scheme can achieve high precision and accomplish rapid attitude maneuvering.

关 键 词：挠性航天器 预定时间控制 自适应控制 干扰不确定性 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]