摘要
空间飞行器姿态控制系统是一个MIMO非线性系统,其姿控执行机构通常由若干个脉冲工作状态的发动机组成。为减轻发动机质量,有时会选用发动机个数较少的布局方案,从而导致三通道控制力矩相关,引起附加的耦合问题(下称布局耦合问题)。针对这一问题,采取反馈线性化方法,直接以发动机推力作为控制输入,在最小范数的约束条件下,得到了姿态解耦控制,有效地解决了发动机布局耦合问题。仿真结果验证了该姿态解耦控制方法的正确性。
The spacecraft attitude control system is a MIMO system whose executor is generally composed of several thrusters working in pulse.In order to decrease the mass of thrusters,sometimes the layout with fewer thrusters is chosen,which results in the interrelationship among the three control torques,and the extra coupling(layout coupling problem) are introduced into the attitude control system.To solve this problem,the feedback linearization method is adopted taking the thruster forces as input directly in this...
出处
《现代防御技术》
北大核心
2008年第5期41-45,共5页
Modern Defence Technology
关键词
姿态控制
发动机
反馈线性化
布局耦合
解耦
attitude control
thrusters
feedback linearization
layout coupling
decoupling
