Robust \(H_\infty \) output feedback control for attitude stabilization of a

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• 作者：Shunan Wu ; Shenghui Wen
• 关键词：Flexible spacecraft ; Robust control ; Attitude dynamics ; Output feedback ; Stabilization
• 刊名：Nonlinear Dynamics
• 出版年：2016
• 出版时间：April 2016
• 年：2016
• 卷：84
• 期：1
• 页码：405-412
• 全文大小：641 KB
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• 作者单位：Shunan Wu (1) (2)
  Shenghui Wen (1)
  
  1. School of Aeronautics and Astronautics, Dalian University of Technology, Dalian, 116024, China
  2. State Key Laboratory of Structural Analysis for Industrial Equipment, Dalian University of Technology, Dalian, 116024, China
  
• 刊物类别：Engineering
• 刊物主题：Vibration, Dynamical Systems and Control
  Mechanics
  Mechanical Engineering
  Automotive and Aerospace Engineering and Traffic
  
• 出版者：Springer Netherlands
• ISSN：1573-269X

文摘

Current spacecraft is always equipped with large flexible appendages and payloads, and the high-precision attitude control is therefore a challenging problem. This paper addresses the robust \(H_{\infty }\) output feedback control to achieve attitude stabilization of a flexible spacecraft. The Lagrange-like model of attitude dynamics is firstly proposed. Then a LMI-based output feedback controller is designed in the presence of disturbances. The stability of closed-loop system is discussed by the Lyapunov method. To deal with the model uncertainties, the convex optimization algorithm is presented. Numerical simulations are finally provided to illustrate the performance of the proposed controllers.