纯磁控微小卫星姿态控制研究  

Attitude Control of Micro-Satellite With Only Magnetic Actuators

作　　者：刘海颖[1] 王惠南[1] 程月华[2] 

机构地区：[1]南京航空航天大学自动化学院,南京210016 [2]南京航空航天大学高新院微小卫星中心

出　　处：《空间科学学报》2007年第5期425-429,共5页Chinese Journal of Space Science

基　　金：教育部博士点基金项目资助(20030287005)

摘　　要：针对微小卫星速率阻尼、姿态捕获及三轴稳定的不同姿态控制模式,设计了采用纯磁控的控制律.首先以轨道坐标系为参考建立卫星模型,然后在卫星能量分析和Lyapunov稳定方法基础上,应用B-dot控制进行速率阻尼,给出了全局稳定能量控制来进行姿态捕获和三轴稳定控制的新方法,同时根据线性化的卫星模型,设计了常系数LQG控制律.仿真结果表明,B-dot可以有效地进行速率阻尼,能量控制策略适用于大角度姿态捕获和三轴稳定,稳定控制时LQG与能量控制相比具有更高的精度,但稳定度略差.This paper researched on the attitude control of Micro-satellite using only magnetic torque for the different control modes including detumbling and attitude acquisition as well as threeaxis stabilization. The satellite model was established relative to orbit frame firstly, then based on the energy considerations and Lyapunov stability analysis methods, the B-dot controller for detumbling was presented, moreover, a new method using global energy control for attitude acquisition and three-axis attitude stabilization was given. At the same time based on the Linearizatlon of the satellite model, a constant gain LQG-controller was designed. Simulating result indicated that the B-dot controller can detumble the satellite＇s rate effectively; the global energy controller may be used in the large range of attitude capture and stabilization modes; while in small angle range the LQG controller has high precision but the stability properties is not so good compared to the energy controller.

关 键 词：微卫星 磁控 B-dot控制 能量控制 LQG控制 

分 类 号：V448.1[航空宇航科学与技术—飞行器设计]