考虑太阳帆板指向的编队卫星相对姿态跟踪控制  

Relative Attitude Pointing Tracking Control of Satellite Formation Flying with Considering the Orientation of Solar Panel

作　　者：张治国[1] 李俊峰[1] 宝音贺西[1] 

机构地区：[1]清华大学航天航空学院,北京10084

出　　处：《宇航学报》2008年第1期202-207,共6页Journal of Astronautics

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

摘　　要：编队飞行一种应用是受控卫星对目标卫星跟飞或者绕飞,有效载荷指向目标卫星以执行各种任务。研究了太阳帆板固定的卫星姿态控制,在保证有效载荷始终指向目标卫星的前提下,使得太阳帆板尽可能朝向太阳。给出了太阳帆板法线与太阳光夹角最小的几何条件。采用四元数状态反馈的控制律实现了姿态跟踪,仿真结果检验了控制律有效性及太阳帆板朝向太阳的效果。In satellite formation flying,a controllable chaser satellite flies around a target satellite to carry out various missions.This paper treats the case of a chaser satellite powered by a unmovable plane solar array with a payload that needs to be pointed a target satellite at all times.The attitude control problem in this application is studied.A possible desired attitude of the chaser is determined,to make the solar panel face to the sun as much as possible,on the premise of that the payload points to the t...

关 键 词：卫星 编队飞行 姿态跟踪控制 太阳帆板指向 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]