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A Control Method for Thermal Structural Tests of Hypersonic Missile Aerodynamic Heating

Author

Listed:
  • Chao Lu

    (College of Electrical Engineering and Control Science, Nanjing Tech University, Nanjing 211899, China)

  • Guangming Zhang

    (College of Electrical Engineering and Control Science, Nanjing Tech University, Nanjing 211899, China)

  • Xiaodong Lv

    (College of Electrical Engineering and Control Science, Nanjing Tech University, Nanjing 211899, China)

Abstract

This paper presents an intelligent proportional-derivative adaptive global nonsingular fast-terminal sliding-mode control (IPDAGNFTSMC) for tracking temperature trajectories of a hypersonic missile in thermal structural tests. Firstly, the numerical analyses on a hypersonic missile’s aerodynamic heating are based on three different external flow fields via the finite element calculation, which provides the data basis for the thermal structural test of hypersonic vehicles; secondly, due to temperature trajectory differences of a hypersonic missile and the thermal inertia and nonlinear characteristics of quartz lamps in thermal structural test, IPDAGNFTSMC is proposed, consisting of three components: (i) the mathematical model of the thermal structural test is established and further replaced via an intelligent proportional-derivative with a nonlinear extended state observer (NESO) for online unknown disturbances observation; (ii) compared with the traditional sliding-mode control method, the AGNFTSMC method eliminates the reaching phase and the initial control state is trapped on the sliding-mode surface. Therefore, it can alleviate chattering phenomenon, accelerate the convergence rate of the sliding mode, and ensure that there is no singular problem in the entire control process; (iii) the adaptive law is designed to effectively solve problems of convergence stagnation and chattering phenomenon. The Lyapunov stability theory is used to prove the stability of the proposed IPDAGNFTSMC-NESO. Finally, the advantages of the designed control method are verified by experimental simulation and comparison.

Suggested Citation

  • Chao Lu & Guangming Zhang & Xiaodong Lv, 2025. "A Control Method for Thermal Structural Tests of Hypersonic Missile Aerodynamic Heating," Mathematics, MDPI, vol. 13(3), pages 1-22, January.
    • Handle: RePEc:gam:jmathe:v:13:y:2025:i:3:p:380-:d:1576242
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    References listed on IDEAS

    as
    1. Xiaodong Lv & Guangming Zhang & Mingxiang Zhu & Huimin Ouyang & Zhihan Shi & Zhiqing Bai & Igor V. Alexandrov, 2022. "Adaptive Neural Network Global Nonsingular Fast Terminal Sliding Mode Control for a Real Time Ground Simulation of Aerodynamic Heating Produced by Hypersonic Vehicles," Energies, MDPI, vol. 15(9), pages 1-25, April.
    2. Hongcheng Zhou & Dezhi Xu & Bin Jiang, 2015. "Model Free Command Filtered Backstepping Control for Marine Power Systems," Mathematical Problems in Engineering, Hindawi, vol. 2015, pages 1-8, October.
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