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Aerospace
Special Issues
Control of Hypersonic Morphing Flight Vehicles
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Control of Hypersonic Morphing Flight Vehicles

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

Deadline for manuscript submissions: 30 November 2026 | Viewed by 458

Special Issue Editor

Prof. Dr. Changzhu Wei

E-Mail Website
Guest Editor
School of Astronautics, Harbin Institute of Technology, Harbin 150001, China
Interests: aircraft control; advanced guidance and trajectory optimization; artificial intelligence theory and application

Special Issue Information

Dear Colleagues,

Morphing aircraft can rapidly alter their aerodynamic configuration, flight trajectory, and attack methods, making them one of the key directions for the innovative development of future-generation aircraft. They have the potential to reshape operational patterns of future warfare and establish a new paradigm for the intelligent application of morphing aircraft. Compared with traditional aircraft, morphing aircraft can adjust their structural configuration and flight state according to their environmental conditions, mission status, and operational objectives, thereby providing superior aerodynamic performance and manoeuvrability and significantly enhancing the aircraft's mission adaptability. This has attracted widespread attention from scholars and research institutions worldwide, establishing morphing aircraft as a cutting-edge research focus in advanced aircraft control technology.

To facilitate the exchange the latest research in advanced guidance and control for morphing aircraft, the editors of this Special Issue invite submissions addressing the challenges of guidance and control in these systems. The aim is to foster collaboration among researchers and to drive innovation in advanced guidance and control technologies for morphing aircraft.

Prof. Dr. Changzhu Wei
Guest Editor

Manuscript Submission Information

Manuscripts should be submitted online at www.mdpi.com by registering and logging in to this website. Once you are registered, click here to go to the submission form. Manuscripts can be submitted until the deadline. All submissions that pass pre-check are peer-reviewed. Accepted papers will be published continuously in the journal (as soon as accepted) and will be listed together on the special issue website. Research articles, review articles as well as short communications are invited. For planned papers, a title and short abstract (about 250 words) can be sent to the Editorial Office for assessment.

Submitted manuscripts should not have been published previously, nor be under consideration for publication elsewhere (except conference proceedings papers). All manuscripts are thoroughly refereed through a single-blind peer-review process. A guide for authors and other relevant information for submission of manuscripts is available on the Instructions for Authors page. Aerospace is an international peer-reviewed open access monthly journal published by MDPI.

Please visit the Instructions for Authors page before submitting a manuscript. The Article Processing Charge (APC) for publication in this open access journal is 2400 CHF (Swiss Francs). Submitted papers should be well formatted and use good English. Authors may use MDPI's English editing service prior to publication or during author revisions.

Keywords

  • modeling and flight performance analysis of morphing aircraft
  • trajectory optimization methods and deformation strategies for morphing aircraft
  • advanced guidance methods for morphing aircraft
  • advanced control methods for morphing aircraft
  • integrated design methods for guidance and control of morphing aircraft
  • intelligent control theory and methods for morphing aircraft
  • other guidance and control methods related to morphing aircraft

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Published Papers (1 paper)

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Research

33 pages, 5226 KB  
Article
Adaptive Augmented Anti-Disturbance Load Relief Controller Design and Stability Analysis
by Liang Zhang, Runyu Cai, Tianyou Lin, Xiaoyun Luo and Wutao Qin
Aerospace 2026, 13(5), 415; https://doi.org/10.3390/aerospace13050415 - 29 Apr 2026
Abstract
This paper proposes an adaptive augmented anti-disturbance load relief control scheme for a solid launch vehicle. It can effectively satisfy the composite control requirements including high-precision attitude control, resistance to elastic frequency deviations, sudden wind disturbances, and active load relief. Firstly, the dynamic [...] Read more.
This paper proposes an adaptive augmented anti-disturbance load relief control scheme for a solid launch vehicle. It can effectively satisfy the composite control requirements including high-precision attitude control, resistance to elastic frequency deviations, sudden wind disturbances, and active load relief. Firstly, the dynamic model of the elastic solid launch vehicle was established and subjected to small-perturbation linearization. Based on the state-space approach, the open-loop transfer function of the system was derived, and a basic PD controller with correction networks was presented. Subsequently, an adaptive augmented control law was designed to achieve adaptive variation in open-loop gain. Furthermore, a load relief control law was designed to address the launch vehicle’s need for load mitigation during the ascent phase through high-wind regions. Simultaneously, to further enhance disturbance rejection capability, a linear extended state observer was developed. Finally, frequency-domain methods and sinusoidal function analysis were applied to the four designed modules to evaluate the system’s stability margins, and the overall stability margin of the whole control system was calculated. Comprehensive time-domain simulation results and frequency-domain analysis examples demonstrate the effectiveness of the proposed method, which offers a novel solution for launch vehicle ascent control and facilitates meeting multi-constraint control requirements. Full article
(This article belongs to the Special Issue Control of Hypersonic Morphing Flight Vehicles)
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