主动磁控微卫星姿态控制  

Attitude Control of Micro-satellite with Active Magnetic Control

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,江苏南京210016 [2]南京航空航天大学高新院微小卫星研究中心,江苏南京210016

出　　处：《应用科学学报》2007年第4期377-381,共5页Journal of Applied Sciences

基　　金：教育部博士点基金项目(20030287005)

摘　　要：采用偏置动量轮加磁力矩器作为控制方案的非重力梯度微卫星不同于通常的速率阻尼—姿态捕获—动量轮起旋控制模式.针对这一问题,该文提出了B-DOT磁控加动量轮常值起旋、主动磁控加常值动量轮进行姿态捕获和稳定控制的方法,设计了限制姿态反馈控制律进行捕获和稳定控制,以及LQG稳定控制律.采用磁场测量与磁控分时处理的策略,考虑测量误差和干扰力矩,以及不同偏置动量进行仿真.结果表明该方法使整个控制过程操作简捷,初态控制阶段时间显著减少,稳态阶段具有较高的控制精度和抗干扰能力.Different from the normal sequence consisting of attitude detumble, acquisition, and wheel speed-up, a method of attitude acquisition and stabilization for magnetic controlled micro-satellite is proposed, which uses B-dot controller, momentum wheel acceleration for detumble and active magnetic controller, and constant wheel. A limiting attitude feedback controller is designed for attitude capture and stabilization, and a LQG controller for attitude stabilization. Simulation is carried out using magnetic determination and control at different time. Measurement error, disturber moment and different bias momentum are considered. The result indicates that the method makes the control process simple and convenient, and can reduce initial control time with high control precision and robustness in stabilization.

关 键 词：微卫星 主动磁控 B-DOT控制 限制姿态反馈 LQG控制 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]