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Approximate output regulation of non-minimum phase hypersonic flight vehicle

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Abstract

To circumvent the non-minimum phase behavior in a hypersonic flight vehicle, an asymptotic flight tracking controller is investigated in this work. When the elevator is the only control surface available for the altitude dynamics, the hypersonic vehicle model exhibits unstable zero dynamics, preventing the application of standard inversion-based control techniques. The standard output regulation theory is utilized to design a nonlinear controller, achieving asymptotic tracking of velocity and altitude in a sinusoidal maneuver case with longitudinal acceleration and deceleration. Moreover, a three-layer neural network-based approximation method is presented to solve the center manifold equation for the output regulation problem. Finally, numerical simulations in MATLAB/Simulation Environment illustrate that the proposed controller is effective in providing favorable tracking performance and resisting unstable zero dynamics.

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Authors and Affiliations

  1. School of Electrical and Electronic Engineering, Tianjin Key Laboratory for Control Theory and Applications in Complicated Systems, Tianjin University of Technology, Tianjin, 300384, China

    Yuehui Ji

  2. Tianjin Institute of Metrological Supervision and Testing (TIMST), Tianjin, 300192, China

    Hailiang Zhou

  3. School of Electrical Engineering and Automation, Tianjin University, Tianjin, 300072, China

    Qun Zong

Authors
  1. Yuehui Ji
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  2. Hailiang Zhou
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  3. Qun Zong
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Corresponding author

Correspondence to Yuehui Ji.

Additional information

This research was partially supported by National Natural Science Foundation of China (Grant Nos. 61603274 and 61673294).

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Ji, Y., Zhou, H. & Zong, Q. Approximate output regulation of non-minimum phase hypersonic flight vehicle. Nonlinear Dyn 91, 2715–2724 (2018). https://doi.org/10.1007/s11071-017-4041-9

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