摘要
卫星编队飞行的相对轨道运动和姿态指向运动并不是彼此独立的,而是相互耦合的。利用几何学方法和编队卫星的相对位置与姿态指向的耦合关系推导了卫星编队飞行的姿态指向运动学和动力学方程。并运用指数趋近律滑模控制方法对系统进行耦合控制。仿真结果表明:耦合控制系统在不借助额外姿态测量信息的情况下可同时实现相对位置和姿态指向的精确控制。
The orbit and attitude of satellite formation flying are usually regarded as uncoupled systems. However, this is not true. In this paper, coupled kinematics and dynamics equations of relative position and attitude pointing of satellites formation flying are derived. A sliding mode control based on exponent reaching law is applied to the coupled system. The simulation results show that the coupled control system can simultaneously drive the relative position and attitude pointing to the desired states without the measurement information about the attitude angle.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2009年第3期1000-1005,1029,共7页
Journal of Astronautics
关键词
卫星编队飞行
相对轨道
姿态指向
耦合系统
滑模控制
Satellite formation flying
Relative orbit
Attitude pointing
Coupled system
Sliding mode control
