卫星编队飞行有限时间控制方法  

Finite-Time Control for Satellite Formation Flight

作　　者：胡敏[1] 曾国强[2] 

机构地区：[1]中国人民解放军装备学院,北京101416 [2]国防科技大学航天与材料工程学院,长沙410073

出　　处：《空间控制技术与应用》2012年第1期23-28,共6页Aerospace Control and Application

基　　金：国家高技术研究发展计划资助项目(2010AA7026053)

摘　　要：针对卫星编队飞行相对位置控制问题,提出了一种有限时间控制方法.首先,建立了编队卫星相对运动的非线性动力学方程.其次,设计了有限时间快速收敛的滑模面,提出了一种有限时间控制方法,该方法能保证闭环控制系统的全局稳定性和快速收敛性,并给出了理论证明.最后,将提出的方法应用于卫星编队飞行维持控制.仿真结果表明该方法在收敛时间和控制精度方面均优于传统线性滑模控制和终端滑模控制.A finite-time control scheme is proposed for satellites formation flight.Firstly,the nonlinear relative dynamics equation of formation flying satellites is established.Then,the sliding manifold with global fast convergence is designed,and a finite-time control technique is also presented,to guarantee global fast stability of the closed-loop system and fast convergence of the tracking errors.The theoretical proof of stability and convergence is given subsequently.Finally,formation keeping scenarios are carried out to validate the effectiveness and advantage of the finite-time control method.Simulation results show that the developed finite-time control technique has faster convergence time and better control accuracy than traditional linear and terminal sliding mode controls.

关 键 词：卫星编队飞行 有限时间控制 滑模控制 编队维持 

分 类 号：V448[航空宇航科学与技术—飞行器设计]