Orbit and attitude control of spacecraft formation flying  

作　　者：张治国 李俊峰 

机构地区：[1]School of Aerospace,Tsinghua University

出　　处：《Applied Mathematics and Mechanics(English Edition)》2008年第1期43-50,共8页应用数学和力学（英文版）

基　　金：Project supported by the National Natural Science Foundation of China(No.10672084);the Specialized Research Fund for Doctoral Program of Higher Education(No.20060003097)

摘　　要：Formation flying is a novel concept of distributing the functionality of large spacecraft among several smaller, less expensive, cooperative satellites. Some applications require that a controllable satellite keeps relative position and attitude to observe a specific surface of another satellite among the cluster. Specially, the target space vehicle is malfunctioning. The present paper focuses on the problem that how to control a chaser satellite to fly around an out-of-work target satellite closely in earth orbit and to track a specific surface. Relative attitude and first approximate relative orbital dynamics equations are presented. Control strategy is derived based on feedback linearization and Lyapunov theory of stability. Further, considering the uncertainty of inertia, an adaptive control method is developed to obtain the correct inertial ratio. The numerical simulation is given to verify the validity of proposed control scheme.Formation flying is a novel concept of distributing the functionality of large spacecraft among several smaller, less expensive, cooperative satellites. Some applications require that a controllable satellite keeps relative position and attitude to observe a specific surface of another satellite among the cluster. Specially, the target space vehicle is malfunctioning. The present paper focuses on the problem that how to control a chaser satellite to fly around an out-of-work target satellite closely in earth orbit and to track a specific surface. Relative attitude and first approximate relative orbital dynamics equations are presented. Control strategy is derived based on feedback linearization and Lyapunov theory of stability. Further, considering the uncertainty of inertia, an adaptive control method is developed to obtain the correct inertial ratio. The numerical simulation is given to verify the validity of proposed control scheme.

关 键 词：satellite formation flying ORBIT ATTITUDE dynamics and control 

分 类 号：V412.41[航空宇航科学与技术—航空宇航推进理论与工程]