航天器编队飞行多目标姿态快速跟踪鲁棒控制  

Robust Attitude Control for Rapid Multi-Target Tracking in Spacecraft Formation Flying

作　　者：袁长清[1] 李俊峰[1] 王天舒[1] 宝音贺西[1] 

机构地区：[1]清华大学航天航空学院,北京100084

出　　处：《应用数学和力学》2008年第2期169-180,共12页Applied Mathematics and Mechanics

基　　金：国家自然科学基金资助项目(10672084);高等学校博士学科点专项科研基金资助项目(20060003097)

摘　　要：研究了航天器编队飞行多目标姿态跟踪鲁棒控制问题.主航天器装有一个快速机动天线和一个星载相机.考虑相机对地面目标跟踪,同时考虑天线与从航天器通信的空间任务.通过引入角速度约束和姿态角约束,分别推导了相机和天线的参考姿态角、角速度和角加速度.提出期望逆系统的概念,将三维空间姿态跟踪问题转化为调节问题,简化了控制器的设计.考虑存在参数摄动和外部干扰力矩的情况,基于期望逆系统和滑模控制,设计了鲁棒姿态跟踪控制器,并利用Liapunov稳定性理论证明了控制系统的渐近稳定性.以两航天器编队飞行多目标跟踪为例进行数值仿真,结果表明所设计的控制器具有良好的鲁棒性和优越的跟踪性能.A robust attitude tracking control scheme for spacecraft formation flying is presented. The leader spacecraft with a rapid mobile antenna and a camera was modeled. While the camera is tracking the ground target, the antenna is tracking the follower spacecraft. By an angular velocity constraint and an angulax constraint, two methods were proposed to compute the reference attitude profiles of the camera and antenna, respectively. To simplify the control design problem, the desired inverse system （DIS）, which can convert the attitude tracking problem of 3D space into the regulator problem, was derived. Based on DIS and sliding mode control （SMC）, a robust attitude tracking controller was developed in the presence of mass parameter uncertainties and external disturbance. By Liapunov stability theory, the closed loop system stability can be achieved. The numerical simulations show that the proposed robust control scheme exhibits significant advantages for the multi-target attitude tracking of a two-spacecraft formation.

关 键 词：姿态控制 编队飞行 多体航天器 鲁棒控制 多目标跟踪 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]