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

Chao Lu, Guangming Zhang and Xiaodong Lv ()
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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

Mathematics, 2025, vol. 13, issue 3, 1-22

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.

Keywords: hypersonic missile; thermal structural test; sliding mode control (search for similar items in EconPapers)
JEL-codes: C (search for similar items in EconPapers)
Date: 2025
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