Search for Articles:
Title / Keyword
Author / Affiliation / Email
Journal
Article Type
 
 
Advanced Search
 
Section
Special Issue
Volume
Issue
Number
Page
 
3.4
2.1
Journals
Aerospace
Special Issues
Structural Dynamics Modelling, Aeroelastic Analysis and Experimental Verification Methods for...
share announcement

Structural Dynamics Modelling, Aeroelastic Analysis and Experimental Verification Methods for Aircraft Systems

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

Deadline for manuscript submissions: 31 December 2025 | Viewed by 2087

Special Issue Editors

Dr. Weizhe Feng

E-Mail Website
Guest Editor
School of Mechanics and Aerospace Engineering Analysis, Dalian University of Technology, Dalian 116024, China
Interests: aircraft design; nonlinear dynamic modelling; aeroelastic and aeroservoelastic stability; elastic flight dynamic modelling; aeroelastic optimization; active aeroelastic control; boundary element and panel methods
Prof. Wei Qian

E-Mail Website
Guest Editor
School of Mechanics and Aerospace Engineering Analysis, Dalian University of Technology, Dalian 116024, China
Interests: structural dynamics; aeroelasticity; flutter; unsteady aerodynamics; static aeroelasticity; ground vibration test; wind tunnel tests; flight test
Dr. Rafic M. Ajaj

E-Mail Website
Guest Editor
Department of Aerospace Engineering, Khalifa University, Abu Dhabi 127788, United Arab Emirates
Interests: VTOL aircraft; morphing wings; aircraft/UAV design; flight loads and aeroelasticity; flight dynamics and control; adaptive structures and flexible materials
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

Structural dynamics and aeroelasticity are important problems in the design of aircraft. With the development of new aircraft, such as aircraft with high aspect ratios, morphing wings, eVTOLs, blended wing bodies, and hypersonic vehicles, there appear to be some complicated aeroelastic problems that need to be solved through the innovation of analyzing and experimental methods. These problems include lumped parameter nonlinearity, geometrical nonlinearity, time-varying systems, coupled flight dynamics and elasticity, propeller aeroelastic instability, gust response and alleviation, flow separation and buffeting, etc. Meanwhile, with the development of new paradigms of computational science, such as data-driven based modeling and digital twin techniques, the structural dynamics and aeroelasticity of aircraft confront great innovations in the areas of numerical modeling and experimental methods.

This Special Issue of Aerospace aims to report new developments in the fields of structural dynamic modeling, aeroelastic analyses, and experiment verification methods for aircraft systems. We cordially invite submissions of original research papers, reviews, and short communications that align with the theme of this Special Issue, including submissions on a broad spectrum of topics, including, but not limited to, the following:

  • The development of structural dynamic modeling and data-based model-updating methods;
  • The development of linear and nonlinear aeroelastic analysis methods；
  • The development of aerodynamic modeling and order reduction of unsteady aerodynamics；
  • Aeroservoelastic modeling and active aeroelastic control methods;
  • Coupled modeling of flight dynamics and aeroelasticity techniques;
  • Aeroelasticity-oriented structure and aerodynamic optimization;
  • Body-free flutter and its active or passive control methods；
  • Whirl flutter and its active or passive control methods；
  • New development of ground vibration test, wind tunnel test, and aeroelastic flight test techniques;
  • The development of new measurement methods and new support systems in wind tunnel tests;
  • Dry wind tunnel test technique based on the simulation of unsteady aerodynamics;
  • Development of data-driven virtual test system for aeroelasticity.

This Special Issue aims to collect and disseminate the latest research and advances in structural dynamics and aeroelasticity for aircrafts, which make a significant contribution to the field. You are also welcome to propose other topics in the field of this Special Issue.

Dr. Weizhe Feng
Prof. Wei Qian
Dr. Rafic M. Ajaj
Guest Editors

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 100 words) can be sent to the Editorial Office for announcement on this website.

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

  • structural dynamic modeling
  • structural dynamic optimization
  • aeroelastic stability
  • aeroservoelastic stability
  • computational aeroelasticity
  • ground vibration test
  • wind tunnel test
  • data-driven virtual test techniques

Benefits of Publishing in a Special Issue

  • Ease of navigation: Grouping papers by topic helps scholars navigate broad scope journals more efficiently.
  • Greater discoverability: Special Issues support the reach and impact of scientific research. Articles in Special Issues are more discoverable and cited more frequently.
  • Expansion of research network: Special Issues facilitate connections among authors, fostering scientific collaborations.
  • External promotion: Articles in Special Issues are often promoted through the journal's social media, increasing their visibility.
  • Reprint: MDPI Books provides the opportunity to republish successful Special Issues in book format, both online and in print.

Further information on MDPI's Special Issue policies can be found here.

Published Papers (4 papers)

Download All Papers
Order results
Result details
Show export options expand_more Show export options expand_less
Select all
Export citation of selected articles as:

Research

20 pages, 9770 KiB  
Article
Damage Evaluation of Typical Aircraft Panel Structure Subjected to High-Speed Fragments
by Yitao Wang, Teng Zhang, Hanzhe Zhang, Liying Ma, Yuting He and Antai Ren
Aerospace 2025, 12(4), 354; https://doi.org/10.3390/aerospace12040354 - 17 Apr 2025
Viewed by 250
Abstract
This study explores the damage behavior of typical titanium alloy aircraft panel structures under high-speed fragment impacts via ballistic experiments and FEM-SPH simulations. Using a ballistic gun and two-stage light gas gun, tests were conducted with spherical, rhombic, and rod-shaped fragments at 1100–2100 [...] Read more.
This study explores the damage behavior of typical titanium alloy aircraft panel structures under high-speed fragment impacts via ballistic experiments and FEM-SPH simulations. Using a ballistic gun and two-stage light gas gun, tests were conducted with spherical, rhombic, and rod-shaped fragments at 1100–2100 m/s to analyze damage morphology. The FEM-SPH method effectively modeled dynamic impacts, capturing primary penetration and debris cloud-induced secondary damage. Residual strength under tension was evaluated via multiple restart analysis, linking impact dynamics to post-damage mechanics. Experimental results revealed fragment-dependent damage modes: spherical fragments caused circular shear holes with conical/jet-like debris clouds; rhombic fragments induced irregular tearing and triangular perforations due to unstable flight; rod-shaped fragments produced elongated breaches with extensive plastic deformation in stringers. Numerical simulations accurately reproduced debris cloud diffusion and secondary effects like spallation. Residual strength analysis showed tensile capacity was governed by breach geometry and location: rhombic breaches (34.6 kN) had lower strength than circular/square ones (38.1–38.3 kN) due to tip stress concentration, while stringer-located damage increased ultimate load by 8–12% via structural redundancy. In conclusion, high-speed fragment impacts dominate shear/tensile tearing, with morphology dependent on fragment characteristics and impact conditions. Debris cloud-induced secondary damage must be considered in structural assessments. The FEM-SPH method is effective for complex damage simulation, while breach geometry and damage location are critical for residual strength. Stringer involvement enhances load-bearing capacity, highlighting component-level design importance for aircraft survivability. The study results and methodologies presented herein can serve as references for aircraft structural damage analysis, residual strength evaluation of battle-damaged structures, and survivability design. Full article
(This article belongs to the Special Issue Structural Dynamics Modelling, Aeroelastic Analysis and Experimental Verification Methods for Aircraft Systems)
►▼ Show Figures

Figure 1

14 pages, 11276 KiB  
Article
The Dynamic Response of Aluminum Alloy Plates Subjected to Multiple-Fragment Impacts Under Pre-Tensile Loading: A Numerical Study
by Yitao Wang, Teng Zhang, Hanzhe Zhang, Yuting He, Liying Ma and Antai Ren
Aerospace 2025, 12(4), 353; https://doi.org/10.3390/aerospace12040353 - 17 Apr 2025
Viewed by 251
Abstract
This study presents an innovative numerical investigation into the synergistic effects of pre-tensile loading and multi-fragment hypervelocity impacts on thin-walled 7075-T6 aluminum alloy structures, addressing a critical gap in aircraft survivability design under realistic combat conditions. Utilizing an advanced finite element framework with [...] Read more.
This study presents an innovative numerical investigation into the synergistic effects of pre-tensile loading and multi-fragment hypervelocity impacts on thin-walled 7075-T6 aluminum alloy structures, addressing a critical gap in aircraft survivability design under realistic combat conditions. Utilizing an advanced finite element framework with stress dynamic relaxation preloading, the established model was rigorously validated against experimental gas-gun impact data, achieving less than 11% deviation in residual velocity. Distinct from prior single-impact studies, our work pioneers a systematic multi-parameter analysis encompassing multiple pre-stress levels, circumferential/linear fragment distributions, velocity gradients, and geometries. The findings of this parametric study establish a linkage between dynamic penetration mechanics and operational airframe stresses, offering guidelines for damage-tolerant design optimization in aircraft structures. Full article
(This article belongs to the Special Issue Structural Dynamics Modelling, Aeroelastic Analysis and Experimental Verification Methods for Aircraft Systems)
►▼ Show Figures

Figure 1

28 pages, 7673 KiB  
Article
Modal Phase Study on Lift Enhancement of a Locally Flexible Membrane Airfoil Using Dynamic Mode Decomposition
by Wei Kang, Shilin Hu, Bingzhou Chen and Weigang Yao
Aerospace 2025, 12(4), 313; https://doi.org/10.3390/aerospace12040313 - 6 Apr 2025
Viewed by 236
Abstract
The dynamic mode decomposition serves as a useful tool for the coherent structure extraction of the complex flow fields with characteristic frequency identification, but the phase information of the flow modes is paid less attention to. In this study, phase information around the [...] Read more.
The dynamic mode decomposition serves as a useful tool for the coherent structure extraction of the complex flow fields with characteristic frequency identification, but the phase information of the flow modes is paid less attention to. In this study, phase information around the locally flexible membrane airfoil is quantitatively studied using dynamic mode decomposition (DMD) to unveil the physical mechanism of the lift improvement of the membrane airfoil. The flow over the airfoil at a low Reynolds number (Re = 5500) is computed parametrically across a range of angles of attack (AOA = 4°–14°) and membrane lengths (LM = 0.55c–0.70c) using a verified fluid–structure coupling framework. The lift enhancement is analyzed by the dynamic coherent patterns of the membrane airfoil flow fields, which are quantified by the DMD modal phase propagation. A downstream propagation pressure speed (DPP) on the upper surface is defined to quantify the propagation speed of the lagged maximal pressure in the flow separation zone. It is found that a faster DPP speed can induce more vortices. The correlation coefficient between the DPP speed and lift enhancement is above 0.85 at most cases, indicating the significant contribution of vortex evolution to aerodynamic performance. The DPP speed greatly impacts the retention time of dominant vortices on the upper surface, resulting in the lift enhancement. Full article
(This article belongs to the Special Issue Structural Dynamics Modelling, Aeroelastic Analysis and Experimental Verification Methods for Aircraft Systems)
►▼ Show Figures

Figure 1

23 pages, 3448 KiB  
Article
A Comparison of Modern Metaheuristics for Multi-Objective Optimization of Transonic Aeroelasticity in a Tow-Steered Composite Wing
by Kantinan Phuekpan, Rachata Khammee, Natee Panagant, Sujin Bureerat, Nantiwat Pholdee and Kittinan Wansasueb
Aerospace 2025, 12(2), 101; https://doi.org/10.3390/aerospace12020101 - 30 Jan 2025
Viewed by 845
Abstract
This study proposes a design procedure for the multi-objective aeroelastic optimization of a tow-steered composite wing structure that operates at transonic speed. The aerodynamic influence coefficient matrix is generated using the doublet lattice method, with the steady-state component further refined through high-fidelity computational [...] Read more.
This study proposes a design procedure for the multi-objective aeroelastic optimization of a tow-steered composite wing structure that operates at transonic speed. The aerodynamic influence coefficient matrix is generated using the doublet lattice method, with the steady-state component further refined through high-fidelity computational fluid dynamics (CFD) analysis to enhance accuracy in transonic conditions. Finite element analysis (FEA) is used to perform structural analysis. A multi-objective transonic aeroelastic optimization problem is formulated for the tow-steered composite wing structure, where the objective functions are designed for mass and critical speed, and the design constraints include structural and aeroelastic limits. A comparative analysis of eight state-of-the-art algorithms is conducted to evaluate their performance in solving this problem. Among them, the Multi-Objective Multi-Verse Optimization (MOMVO) algorithm stands out, demonstrating superior performance and achieving the best results in the aeroelastic optimization task. Full article
(This article belongs to the Special Issue Structural Dynamics Modelling, Aeroelastic Analysis and Experimental Verification Methods for Aircraft Systems)
►▼ Show Figures

Figure 1

Show export options expand_more Show export options expand_less
Select all
Export citation of selected articles as:
 
Displaying articles 1-4
Back to TopTop