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

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Abstract

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.

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Authors and Affiliations

  1. School of Aeronautics and Astronautics, Dalian University of Technology, Dalian, 116024, China

    Shunan Wu & Shenghui Wen

  2. State Key Laboratory of Structural Analysis for Industrial Equipment, Dalian University of Technology, Dalian, 116024, China

    Shunan Wu

Authors
  1. Shunan Wu
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  2. Shenghui Wen
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Corresponding author

Correspondence to Shunan Wu.

Additional information

This work is supported by the National Natural Science Foundation of China (11502040), the Education Department of Liaoning Province (L2014030) and the Fundamental Research Funds for the Central Universities (DUT15LK31).

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Wu, S., Wen, S. Robust \(H_\infty \) output feedback control for attitude stabilization of a flexible spacecraft. Nonlinear Dyn 84, 405–412 (2016). https://doi.org/10.1007/s11071-016-2624-5

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  • DOI: https://doi.org/10.1007/s11071-016-2624-5

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