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author:

Xu, Zhouzhe (Xu, Zhouzhe.) [1] | Zhang, Hehong (Zhang, Hehong.) [2] (Scholars:张和洪) | Zhai, Chao (Zhai, Chao.) [3] | Qian, Qiumeng (Qian, Qiumeng.) [4] | Wu, Linfeng (Wu, Linfeng.) [5]

Indexed by:

EI

Abstract:

To address the strong decoupling between pressure and temperature variables in the intake environment simulation system (IESS) of altitude test facility, as well as the significant total disturbance caused by rapid transient tests, a novel fixed time sliding mode controller (FxTSMC) with a fixed time extended state observer (FxTESO) was designed, and thus, a fixed time active disturbance rejection compound decoupling control method (FxT-ADRCDC) was proposed. Specifically, a static decoupling method was adopted to decouple the IESS into two single-input, single-output systems, achieving independent control of intake temperature and pressure. In terms of total disturbance estimation and suppression, the FxTESO was utilized to rapidly and accurately estimate the states and total disturbances including dynamic coupling to deal with the strong disturbance, and then, a novel FxTSMC that can avoid singular problems and converge rapidly was proposed, the total disturbance was then compensated into the FxTSMC, obtaining the FxT-ADRCDC method. The Lyapunov function was designed to prove the fixed time stability of the closed-loop control system, obtaining the upper bound of the settling time, which does not depend on the initial conditions. Finally, the transient flight mission experiments on a high-confidence IESS platform were launched and the comparisons between the FxT-ADRCDC method and the linear active disturbance rejection decoupling control (LADRDC) method were carried out. The results show that the absolute integral error of intake pressure and temperature under the FxT-ADRCDC is, on average, reduced by approximately 70.3% and 70.7%, respectively, compared to the LADRDC method. Moreover, the valve swing satisfies the requirements for practical engineering. The proposed method effectively achieves high-quality decoupling control of intake pressure and temperature, and provides strong technical support for improving the system’s rapid and accurate dynamic modelling capabilities. © 2025 China Aerospace Science and Industry Corp. All rights reserved.

Keyword:

Closed loop control systems Disturbance rejection Linear control systems State estimation

Community:

  • [ 1 ] [Xu, Zhouzhe]College of Computer and Data Science, Fuzhou University, Fuzhou; 350108, China
  • [ 2 ] [Zhang, Hehong]College of Computer and Data Science, Fuzhou University, Fuzhou; 350108, China
  • [ 3 ] [Zhai, Chao]College of Automation, China University of Geosciences, Wuhan; 430074, China
  • [ 4 ] [Qian, Qiumeng]AECC Sichuan Gas Turbine Establishment, Mianyang; 621703, China
  • [ 5 ] [Qian, Qiumeng]College of Automation Science and Electrical Engineering, Beihang University, Beijing; 100191, China
  • [ 6 ] [Wu, Linfeng]College of Automation, China University of Geosciences, Wuhan; 430074, China

Reprint 's Address:

  • 张和洪

    [zhang, hehong]college of computer and data science, fuzhou university, fuzhou; 350108, china

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Source :

Journal of Propulsion Technology

ISSN: 1001-4055

Year: 2025

Issue: 2

Volume: 46

Cited Count:

WoS CC Cited Count:

SCOPUS Cited Count:

ESI Highly Cited Papers on the List: 0 Unfold All

WanFang Cited Count:

Chinese Cited Count:

30 Days PV: 0

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