航天器编队飞行多目标姿态跟踪终端滑模控制  

Terminal Sliding Mode Control for Multi-Target Attitude Tracking in Spacecraft Formation Flight

作　　者：袁长清[1] 李俊峰[2] 张威泰[3] 周昊[4] 

机构地区：[1]空军航空大学,长春130022 [2]清华大学航天航空学院,北京100084 [3]北京控制工程研究所,北京100190 [4]哈尔滨工业大学,哈尔滨150001

出　　处：《空间控制技术与应用》2010年第5期18-24,共7页Aerospace Control and Application

基　　金：国家自然科学基金(10902125)资助项目

摘　　要：研究航天器编队飞行多目标姿态跟踪控制问题.为避免姿态大范围跟踪可能出现的奇点,采用欧拉参数描述航天器姿态.基于终端滑模技术,设计多目标姿态跟踪终端滑模控制器,并应用Lyapunov稳定性理论和扩展的Lyapunov有限时间稳定性理论证明控制系统稳定性和有限时间收敛性.该控制器参数方便调整,易于实现.由于没有对复杂多体航天器动力学进行线性化处理,从而保证了姿态跟踪控制精度.仿真结果表明,存在惯量参数摄动和外部干扰力矩的情况下,所设计的多目标姿态跟踪控制器具有良好鲁棒性和优越的跟踪性能.The attitude multi-target tracking control problem of spacecraft formation flight is investigated in this paper. Euler parameters are introduced to describe the orientation of a spacecraft to avoide singularities in the kinematic equations. Based on terminal sliding modes control,a multi-target attitude tracking controller is developed. Using the Lyapunov stability theory and an extended Lyapunov description of finitetime stability,the closed loop system stability and the finite-time convergence can be proved. Since neither linearization nor decoupling is used to simplify the model,the control result is more accurate. Simulation results demonstrate the good tracking characteristics of the proposed control scheme during spacecraft inertia changes and in presence of external disturbances.

关 键 词：姿态控制 编队飞行 终端滑模 多目标跟踪 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]