Flight Control (2nd Edition)

A special issue of Aerospace (ISSN 2226-4310). This special issue belongs to the section "Aeronautics".

Deadline for manuscript submissions: 31 December 2024 | Viewed by 816

Special Issue Editor


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Guest Editor
Division of Mechanics, Institute of Aeronautics and Applied Mechanics, Faculty of Power and Aeronautical Engineering, Warsaw University of Technology, 00-665 Warsaw, Poland
Interests: flight dynamics; aircraft system identification; optimization methods; modeling and simulation in MATLAB environment
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Special Issue Information

Dear Colleagues,

Flight control systems play a vital role in the advancement of modern aircraft, enabling the execution of intended maneuvers and enhancing overall aircraft capabilities. Their complex design necessitates a multidisciplinary approach, encompassing flight mechanics modeling, control theory, mathematical optimization, the analysis of complex aeronautical systems, compliance with aviation regulations, the consideration of pilot input, and various other factors. The integration of these components poses significant challenges and demands considerable time and effort. Consequently, flight control system design remains a dynamic field characterized by ongoing development and innovative breakthroughs. This Special Issue endeavors to showcase the latest progress in flight control design, encompassing such diverse areas as the following:

  • Aerodynamic parameter estimation and modelling;
  • Artificial intelligence and machine learning for aeronautics;
  • Autonomous aircraft and aeronautical systems;
  • Guidance, navigation, and control;
  • Flight tests and instrumentation;
  • Flexible and resilient control systems;
  • Modern flight mechanics;
  • Pilot in the loop modelling and simulation;
  • Risk-based oversight.

Dr. Piotr Lichota
Guest Editor

Manuscript Submission Information

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Keywords

  • adaptative control
  • autonomous systems
  • guidance, navigation, and control
  • neural networks and machine learning
  • flight dynamics
  • flight testing
  • pilot modelling and human–aircraft interaction
  • reconfigurable and fault-tolerant control
  • risk and safety management
  • system identification

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Published Papers (1 paper)

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Research

20 pages, 5077 KiB  
Article
Sliding Mode Flight Control Law Design Requirements for Oblique Wing Aircraft Based on Perturbation Theory
by Lixin Wang, Xun Sun, Hailiang Liu, Jingzhong Ma, Wenyuan Cheng, Shang Tai, Yun Zhu and Ting Yue
Aerospace 2024, 11(5), 366; https://0-doi-org.brum.beds.ac.uk/10.3390/aerospace11050366 - 6 May 2024
Viewed by 444
Abstract
Flight control law parameters should be designed to provide a sufficient stability margin for closed-loop aircraft while ensuring command tracking accuracy. The singular perturbation margin (SPM) and generalized gain margin (GGM), which are generalizations of the classical phase margin (PM) and gain margin [...] Read more.
Flight control law parameters should be designed to provide a sufficient stability margin for closed-loop aircraft while ensuring command tracking accuracy. The singular perturbation margin (SPM) and generalized gain margin (GGM), which are generalizations of the classical phase margin (PM) and gain margin (GM), respectively, from a linear time-invariant system to a nonlinear time-varying system, can be used to quantitatively characterize the maximum singular perturbation and regular perturbation allowed to maintain system stability. In this paper, the sliding mode flight control structure and the design parameters of the sliding mode control law are first introduced for an oblique wing aircraft (OWA), the SPM-gauge and GGM-gauge are added to this closed-loop aircraft model, and the analytical expressions of the SPM and GGM are derived with respect to the control law parameters. Second, the stability margin design requirements of closed-loop aircraft in flight control system design specifications are converted into limitations on the SPM and GGM to determine the value range of the flight control law parameters. Then, with the goal of reducing the sum of the approaching time and sliding time, the parameter value combination is selected within the control law parameter range that meets the stability margin requirements, thus forming a flight control law design method for OWA during the wing skewing process. Finally, the designed control law parameters are applied to a sample OWA, and the stability margin of closed-loop aircraft during the wing skewing process is verified. Full article
(This article belongs to the Special Issue Flight Control (2nd Edition))
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