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Applied Sciences
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Structural Dynamics and Aeroelasticity
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Structural Dynamics and Aeroelasticity

A topical collection in Applied Sciences (ISSN 2076-3417). This collection belongs to the section "Aerospace Science and Engineering".

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Editors

Prof. Dr. Sergio Ricci

E-Mail Website
Collection Editor
Department of Aerospace Science and Technology, Politecnico di Milano, Via La Masa 34, 20156 Milano, Italy
Interests: aeroelasticity and structural dynamics; aircraft conceptual and preliminary design; morphing aircraft; multi-disciplinary design optimization
Special Issues, Collections and Topics in MDPI journals
Prof. Paolo Mantegazza

E-Mail Website
Collection Editor
Retired, Department of Aerospace Science and Technology, Politecnico di Milano, 20156 Milano, Italy
Interests: applied aeroelasticity; dynamics of aerospace systems
Dr. Alessandro De Gaspari

E-Mail Website
Collection Editor
Department of Aerospace Science and Technology, Politecnico di Milano, 20156 Milano, Italy
Interests: multi-disciplinary optimization; morphing technologies; structural dynamics; finite-element modeling; compliant mechanisms; wind tunnel tests; aeroelasticity
Special Issues, Collections and Topics in MDPI journals
Prof. Dr. Jonathan E. Cooper

E-Mail Website
Collection Editor
Department of Aerospace Engineering, University of Bristol, Bristol BS8 1TR, UK
Interests: aeroelasticity; loads; structural dynamics; adaptive aircraft structures; aeroelastic optimization
Prof. Dr. Afzal Suleman

E-Mail Website
Collection Editor
Department of Mechanical Engineering, University of Victoria, Victoria, BC V8P 5C2, Canada
Interests: computational and experimental mechanics; multidisciplinary design optimization; fluid–structure interaction; active aeroelastic and morphing aircraft structures; aeronautics and space; ocean energy and technology
Prof. Hector Climent

E-Mail Website
Collection Editor
1. Department of Aerospace Engineering, Universidad Carlos III de Madrid, 28005 Madrid, Spain
2. Airbus Defence and Space, 28906 Madrid, Spain
Interests: aeroelasticity; aerodynamics

Topical Collection Information

Dear Colleagues,

Aeroelasticity is a well-known research field that investigates phenomena emerging due to the interaction between fluids and elastic bodies, and more precisely among aerodynamic, inertial and elastic forces. While the typical application of aeroelasticity is in the branch of aircraft engineering, aeroelastic issues are also of concern in civil engineering, such as slender buildings, suspension bridges and electric lines; transport engineering, such as cars and ships; or power engineering, such as compressors and turbines.

Aeroelastic phenomena have been relevant since the beginning of aeronautics, and over the years a complete set of analytical, numerical, and experimental methods have been proposed, validated, and included in the certification process.

New problems have recently been of great interest, namely those relating to aeroelastic interactions with active control systems installed on aircraft (e.g., those related to load-alleviation systems), giving rise to the aeroservoelasticity branch of study. Finally, the adoption of multi-disciplinary optimization frameworks able to take advantage of aeroelastic deformation, passively or actively, promises to enable the design of adaptive structures able to guarantee structural mass reduction and performance improvements.

This Topical Collection aims to support the international scientific community in the dissemination of knowledge on analytical, numerical, and experimental methodologies related to the structural dynamics of deformable bodies and their fluid–structure interactions.

Aeroelasticity requires a multi-disciplinary approach with a correct blend of numerical approaches and experimental validations, which are well connected with the purpose of this journal, which provides an advanced forum on all aspects of applied sciences. For this reason, in this Topical Collection we welcome original research articles and reviews regarding research areas including (but not limited to) the following:

  • Stability and response problems related to the fluid–structure interaction of flexible bodies;
  • Time-domain, linear and nonlinear aeroelasticity;
  • CFD-based aeroelasticity;
  • Dynamic loads;
  • Experimental techniques in aeroelasticity and structural dynamics;
  • Active aeroelastic control and aeroelasticity of adaptive/morphing structures;
  • Aeroelasticity of rotary wing aircraft;
  • Aeroelasticity and structural dynamics modelling and optimization.

We look forward to receiving your contributions.

Prof. Dr. Sergio Ricci
Prof. Paolo Mantegazza
Dr. Alessandro De Gaspari
Prof. Dr. Jonathan E. Cooper
Prof. Dr. Afzal Suleman
Prof. Hector Climent
Collection 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 collection 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. Applied Sciences is an international peer-reviewed open access semimonthly 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

  • aeroelasticity and structural dynamics
  • CFD-based aeroelasticity
  • active aeroelastic control
  • aeroelastic optimization
  • linear and nonlinear aeroelasticity
  • aerosevoelasticity

Published Papers (2 papers)

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2024

14 pages, 13161 KiB  
Article
A Study on the Surrogate-Based Optimization of Flexible Wings Considering a Flutter Constraint
by Alessandra Lunghitano, Frederico Afonso and Afzal Suleman
Appl. Sci. 2024, 14(6), 2384; https://doi.org/10.3390/app14062384 - 12 Mar 2024
Viewed by 561
Abstract
Accounting for aeroelastic phenomena, such as flutter, in the conceptual design phase is becoming more important as the trend toward increasing the wing aspect ratio forges ahead. However, this task is computationally expensive, especially when utilizing high-fidelity simulations and numerical optimization. Thus, the [...] Read more.
Accounting for aeroelastic phenomena, such as flutter, in the conceptual design phase is becoming more important as the trend toward increasing the wing aspect ratio forges ahead. However, this task is computationally expensive, especially when utilizing high-fidelity simulations and numerical optimization. Thus, the development of efficient computational strategies is necessary. With this goal in mind, this work proposes a surrogate-based optimization (SBO) methodology for wing design using a predefined machine learning model. For this purpose, a custom-made Python framework was built based on different open-source codes. The test subject was the classical Goland wing, parameterized to allow for SBO. The process consists of employing a Latin Hypercube Sampling plan and subsequently simulating the resulting wing on SHARPy to generate a dataset. A regression-based machine learning model is then used to build surrogate models for lift and drag coefficients, structural mass, and flutter speed. Finally, after validating the surrogate model, a multi-objective optimization problem aiming to maximize the lift-to-drag ratio and minimize the structural mass is solved through NSGA-II, considering a flutter constraint. This SBO methodology was successfully tested, reaching reductions of three orders of magnitude in the optimization computational time. Full article
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28 pages, 1228 KiB  
Article
Comparison of Unsteady Low- and Mid-Fidelity Propeller Aerodynamic Methods for Whirl Flutter Applications
by Christopher Koch, Nils Böhnisch, Hendrik Verdonck, Oliver Hach and Carsten Braun
Appl. Sci. 2024, 14(2), 850; https://doi.org/10.3390/app14020850 - 19 Jan 2024
Viewed by 1032
Abstract
Aircraft configurations with propellers have been drawing more attention in recent times, partly due to new propulsion concepts based on hydrogen fuel cells and electric motors. These configurations are prone to whirl flutter, which is an aeroelastic instability affecting airframes with elastically supported [...] Read more.
Aircraft configurations with propellers have been drawing more attention in recent times, partly due to new propulsion concepts based on hydrogen fuel cells and electric motors. These configurations are prone to whirl flutter, which is an aeroelastic instability affecting airframes with elastically supported propellers. It commonly needs to be mitigated already during the design phase of such configurations, requiring, among other things, unsteady aerodynamic transfer functions for the propeller. However, no comprehensive assessment of unsteady propeller aerodynamics for aeroelastic analysis is available in the literature. This paper provides a detailed comparison of nine different low- to mid-fidelity aerodynamic methods, demonstrating their impact on linear, unsteady aerodynamics, as well as whirl flutter stability prediction. Quasi-steady and unsteady methods for blade lift with or without coupling to blade element momentum theory are evaluated and compared to mid-fidelity potential flow solvers (UPM and DUST) and classical, derivative-based methods. Time-domain identification of frequency-domain transfer functions for the unsteady propeller hub loads is used to compare the different methods. Predictions of the minimum required pylon stiffness for stability show good agreement among the mid-fidelity methods. The differences in the stability predictions for the low-fidelity methods are higher. Most methods studied yield a more unstable system than classical, derivative-based whirl flutter analysis, indicating that the use of more sophisticated aerodynamic modeling techniques might be required for accurate whirl flutter prediction. Full article
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Figure 1

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