宇航学报 ›› 2015, Vol. 36 ›› Issue (2): 179-185.doi: 10.3873/j.issn.1000-1328.2015.02.008

• 制导、导航与控制 • 上一篇    下一篇

航天器椭圆轨道自主交会的鲁棒H∞控制

刘伟杰,谌颖   

  1. 1.北京控制工程研究所,北京100190;2. 空间智能控制技术重点实验室,北京100190
  • 收稿日期:2014-04-10 修回日期:2014-07-22 出版日期:2015-02-15 发布日期:2015-02-25
  • 基金资助:

    国家自然科学基金( 61074159)

Robust H∞ Control for Autonomous Elliptic Orbit Rendezvous of Spacecrafts

LIU Wei jie, CHEN Ying   

  1. 1. Beijing Institute of Control Engineering, Beijing 100190,China;
     2. Science and Technology on Space Intelligent Control Laboratory,Beijing 100190,China
  • Received:2014-04-10 Revised:2014-07-22 Online:2015-02-15 Published:2015-02-25

摘要:

提出了一种航天器椭圆轨道自主交会鲁棒控制律的设计方法。用LAWDEN方程描述椭圆轨道交会的动力学,并将方程中的时变参数单独归类建立空间交会的线性不确定性模型。然后基于线性矩阵不等式(LMI),在考虑外部扰动的情况下,采用H∞理论设计自主交会的鲁棒控制律。为了提高系统的瞬态性能,在LMI的基础上完成了控制器的二次D稳定性分析。本文设计的控制器采用线性定常增益,易于工程实现。仿真结果说明所设计的控制律能够实现椭圆轨道下航天器的自主交会。

关键词: 航天器, 椭圆轨道交会鲁棒控制, 二次D稳定性, 不确定性

Abstract:

A robust controller design method for spacecraft autonomous rendezvous in an elliptic orbit is developed. LAWDEN equation with time-varying parameters is used to model the elliptic orbit rendezvous dynamics and a linear model with uncertainties of elliptic orbit rendezvous is obtained by classifying the time-varying parameters. The H∞ theory is employed to design the robust control law for autonomous rendezvous based on linear matrix inequality (LMI) in the presence of disturbances, and quadratic D stablility analysis for the controller based on LMI is given to optimize the transient performances of the close-loop systems. The proposed controller is a constant-gain linear controller, and easy to implernent in engineering. Simulation results indicate that the controller can implement autonomous rendezvous in the elliptic orbit.

Key words: Spacecraft, Elliptic orbit rendezvous robust control, Quadratic D stability, Uncertainty

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