American Journal of Aerospace Engineering

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Hypersonic Glider Autopilot Using Adaptive Higher Order Sliding Mode Control with Impulsive Actions

Received: 28 August 2018    Accepted: 14 September 2018    Published: 25 October 2018
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Abstract

Hypersonic glider designs often exhibit limited control authority and poor transversal stability. Furthermore, the methods used for aerodynamic performance estimation at high flight altitudes and hypersonic speeds are inevitably inaccurate and uncertain. Hypersonic Glider performance could be severely degraded by using traditional control and autopilot techniques that rely on an accurate knowledge of the aerodynamic coefficients. A new autopilot and control approach, presented in this paper, is based on recently developed special Higher Order Sliding Mode Control (HOSMC) algorithms that are mostly based on relative degrees but not on the glider’s mathematical model. Specifically, this autopilot and control approach includes robust continuous aerodynamic control augmented by impulsive reaction control thrusters. Control gain-adaptation allows addressing the vehicle bounded uncertainties and perturbations without overestimating the control gains. The impulsive augmentation of the continuous Higher Order Sliding Mode control provides almost instantaneous convergence thereby mitigating the risk of control loss caused by sideslip angle departures due to poor transversal stability and small lateral control authority. While Higher Order Sliding Mode control algorithms are inherently insensitive to the matched uncertainties and disturbances, the observers embedded in the Continuous Higher Order Sliding Mode Control algorithms reduce the time response of the control compensation. Simulation of a representative hypersonic glider executing normal and bank-to-turn maneuvers and controlled by the studied algorithms demonstrate excellent performance in the presence of significant model uncertainties and perturbations.

DOI 10.11648/j.ajae.20180502.12
Published in American Journal of Aerospace Engineering (Volume 5, Issue 2, December 2018)
Page(s) 71-86
Creative Commons

This is an Open Access article, distributed under the terms of the Creative Commons Attribution 4.0 International License (http://creativecommons.org/licenses/by/4.0/), which permits unrestricted use, distribution and reproduction in any medium or format, provided the original work is properly cited.

Copyright

Copyright © The Author(s), 2024. Published by Science Publishing Group

Keywords

Hypersonic Gliders, Autopilots, Higher Order Sliding Mode Control

References
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Author Information
  • Aero Thermo Technology Inc., Huntsville, USA

  • Department of Electrical and Computer Engineering, University of Alabama in Huntsville, Huntsville, USA

  • Aero Thermo Technology Inc., Huntsville, USA

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  • APA Style

    Christian Tournes, Yuri Shtessel, Allen Spencer. (2018). Hypersonic Glider Autopilot Using Adaptive Higher Order Sliding Mode Control with Impulsive Actions. American Journal of Aerospace Engineering, 5(2), 71-86. https://doi.org/10.11648/j.ajae.20180502.12

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    ACS Style

    Christian Tournes; Yuri Shtessel; Allen Spencer. Hypersonic Glider Autopilot Using Adaptive Higher Order Sliding Mode Control with Impulsive Actions. Am. J. Aerosp. Eng. 2018, 5(2), 71-86. doi: 10.11648/j.ajae.20180502.12

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    AMA Style

    Christian Tournes, Yuri Shtessel, Allen Spencer. Hypersonic Glider Autopilot Using Adaptive Higher Order Sliding Mode Control with Impulsive Actions. Am J Aerosp Eng. 2018;5(2):71-86. doi: 10.11648/j.ajae.20180502.12

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  • @article{10.11648/j.ajae.20180502.12,
      author = {Christian Tournes and Yuri Shtessel and Allen Spencer},
      title = {Hypersonic Glider Autopilot Using Adaptive Higher Order Sliding Mode Control with Impulsive Actions},
      journal = {American Journal of Aerospace Engineering},
      volume = {5},
      number = {2},
      pages = {71-86},
      doi = {10.11648/j.ajae.20180502.12},
      url = {https://doi.org/10.11648/j.ajae.20180502.12},
      eprint = {https://download.sciencepg.com/pdf/10.11648.j.ajae.20180502.12},
      abstract = {Hypersonic glider designs often exhibit limited control authority and poor transversal stability. Furthermore, the methods used for aerodynamic performance estimation at high flight altitudes and hypersonic speeds are inevitably inaccurate and uncertain. Hypersonic Glider performance could be severely degraded by using traditional control and autopilot techniques that rely on an accurate knowledge of the aerodynamic coefficients. A new autopilot and control approach, presented in this paper, is based on recently developed special Higher Order Sliding Mode Control (HOSMC) algorithms that are mostly based on relative degrees but not on the glider’s mathematical model. Specifically, this autopilot and control approach includes robust continuous aerodynamic control augmented by impulsive reaction control thrusters. Control gain-adaptation allows addressing the vehicle bounded uncertainties and perturbations without overestimating the control gains. The impulsive augmentation of the continuous Higher Order Sliding Mode control provides almost instantaneous convergence thereby mitigating the risk of control loss caused by sideslip angle departures due to poor transversal stability and small lateral control authority. While Higher Order Sliding Mode control algorithms are inherently insensitive to the matched uncertainties and disturbances, the observers embedded in the Continuous Higher Order Sliding Mode Control algorithms reduce the time response of the control compensation. Simulation of a representative hypersonic glider executing normal and bank-to-turn maneuvers and controlled by the studied algorithms demonstrate excellent performance in the presence of significant model uncertainties and perturbations.},
     year = {2018}
    }
    

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  • TY  - JOUR
    T1  - Hypersonic Glider Autopilot Using Adaptive Higher Order Sliding Mode Control with Impulsive Actions
    AU  - Christian Tournes
    AU  - Yuri Shtessel
    AU  - Allen Spencer
    Y1  - 2018/10/25
    PY  - 2018
    N1  - https://doi.org/10.11648/j.ajae.20180502.12
    DO  - 10.11648/j.ajae.20180502.12
    T2  - American Journal of Aerospace Engineering
    JF  - American Journal of Aerospace Engineering
    JO  - American Journal of Aerospace Engineering
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    EP  - 86
    PB  - Science Publishing Group
    SN  - 2376-4821
    UR  - https://doi.org/10.11648/j.ajae.20180502.12
    AB  - Hypersonic glider designs often exhibit limited control authority and poor transversal stability. Furthermore, the methods used for aerodynamic performance estimation at high flight altitudes and hypersonic speeds are inevitably inaccurate and uncertain. Hypersonic Glider performance could be severely degraded by using traditional control and autopilot techniques that rely on an accurate knowledge of the aerodynamic coefficients. A new autopilot and control approach, presented in this paper, is based on recently developed special Higher Order Sliding Mode Control (HOSMC) algorithms that are mostly based on relative degrees but not on the glider’s mathematical model. Specifically, this autopilot and control approach includes robust continuous aerodynamic control augmented by impulsive reaction control thrusters. Control gain-adaptation allows addressing the vehicle bounded uncertainties and perturbations without overestimating the control gains. The impulsive augmentation of the continuous Higher Order Sliding Mode control provides almost instantaneous convergence thereby mitigating the risk of control loss caused by sideslip angle departures due to poor transversal stability and small lateral control authority. While Higher Order Sliding Mode control algorithms are inherently insensitive to the matched uncertainties and disturbances, the observers embedded in the Continuous Higher Order Sliding Mode Control algorithms reduce the time response of the control compensation. Simulation of a representative hypersonic glider executing normal and bank-to-turn maneuvers and controlled by the studied algorithms demonstrate excellent performance in the presence of significant model uncertainties and perturbations.
    VL  - 5
    IS  - 2
    ER  - 

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