磁控微小卫星速率阻尼和姿态捕获研究  

Detumbling Controller and Attitude Acquisition for Micro-satellite Based on Magnetic Torque

作　　者：刘海颖[1] 王惠南[1] 陈志明[1] 

机构地区：[1]南京航空航天大学自动化学院,南京210016

出　　处：《宇航学报》2007年第2期333-337,共5页Journal of Astronautics

基　　金：教育部博士点基金项目(20030287005)

摘　　要：针对非重力梯度稳定、偏置动量轮加三轴磁控的微小卫星初始姿态控制阶段,采用B-dot控制进行速率阻尼,设计了滑模控制律进行姿态捕获。除了磁控阻尼—捕获—动量轮起旋外,还首次提出了B-dot加动量轮常速起旋、磁控加动量轮姿态捕获的新方法。仿真结果表明,纯磁控的B-dot方法能有效得进行速率阻尼,滑模控制捕获姿态精度高、时间短;B-dot阻尼同时进行动量轮开环起旋,可以迅速使姿态稳定,滑模磁控律可以有效得对偏置动量卫星进行大角度姿态控制,尤其该新方法操作简捷,明显减少初态控制时间。For the micro-satellite that controlled by magnetic torque and pitch bias momentum, This paper used the B-dot controller to detumble the angular rate, then designed sliding mode controller to capture the attitude. Besides the usual sequence of Detumbling, acquisition and wheel start-up, this paper gives a new method for detumbe and attitude acquisition with the wheel working at the same time. Simulating result indicated the B-dot controller can detumble the satellite＇ rate effectively, and sliding mode control has higher precision as whell as shorter capture time. B-dot plus bias momentum controller may stabilize attitude quickly, and the sliding mode controller may control the attitude in large angles, especially the second method is simple and convenient that can reduce the consuming time evidently.

关 键 词：微小卫星 B-dot控制 滑模控制 速率阻尼 姿态捕获 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]