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Aerospace
Special Issues
Flutter Phenomena – Modeling, Identification and Control
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Flutter Phenomena – Modeling, Identification and Control

A special issue of Aerospace (ISSN 2226-4310).

Deadline for manuscript submissions: closed (31 January 2022) | Viewed by 10341

Special Issue Editors

Dr. Manuel Pusch

E-Mail Website
Guest Editor
Institute of System Dynamics and Control, German Aerospace Center (DLR), Oberpfaffenhofen, Germany
Interests: modeling, control, and optimization of aeroelastic systems (multidisciplinary design optimization, reduced-order aeroservoelastic modeling, robust performance analysis and control design, control allocation, gust and maneuver load alleviation, flutter suppression)
Dr. Tamás Luspay

E-Mail Website
Guest Editor
Institute for Computer Science and Control, Budapest, Hungary
Interests: systems and control theory; linear parameter varying systems; analysis and reduction of large-scale dynamical systems; decomposition and decoupling of dynamical systems

Special Issue Information

Dear Colleagues,

In recent years, efforts to increase aircraft efficiency by reducing excess structural weights have led to the concept of high aspect ratio lightweight wings and more flexible airframes. Consequently, the coupling between structural dynamics and aerodynamics has become tighter, which poses new challenges in the design, modeling, and control of aircraft. The increased interaction between aerodynamics and structural dynamics often leads to undesired oscillations which may even become unstable at certain airspeeds, also known as aeroelastic flutter.

Recognizing the interdisciplinary nature of the flutter phenomena, researchers from various fields have investigated the problem, providing new insights and a better understanding. While these results are offering a solution for the flutter phenomena from a certain aspect, they also imply a tighter co-operation between the different research fields. Therefore, in order to efficiently solve the new challenge, a multidisciplinary approach is required.

This Special Issue on Flutter Phenomena aims to collect new research results and bring the various approaches together. Topics may include:

  • Modeling and prediction of the flutter phenomena;
  • Online and offline methods for identifying modal damping and other flutter parameters;
  • Active and passive flutter suppression;
  • Airframe design for flutter testing;
  • Flight test design and experimental results.

Submissions of state-of-the-art results on one or more aspects of the aeroelastic flutter phenomena are strongly encouraged.

Dr. Manuel Pusch
Dr. Tamás Luspay
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.

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

Published Papers (3 papers)

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Research

21 pages, 1659 KiB  
Article
Effect of Aerodynamic Damping Approximations on Aeroelastic Eigensensitivities
by Christoph Kaiser and David Quero
Aerospace 2022, 9(3), 127; https://doi.org/10.3390/aerospace9030127 - 1 Mar 2022
Cited by 2 | Viewed by 2859
Abstract
Aeroelastic sensitivities for the flutter solution are a crucial component of the multi-disciplinary optimization methods employed in modern aircraft design. This paper derives the aeroelastic sensitivities for different aerodynamic damping approximations—the p-k method, the g method and the generalized aeroelastic analysis [...] Read more.
Aeroelastic sensitivities for the flutter solution are a crucial component of the multi-disciplinary optimization methods employed in modern aircraft design. This paper derives the aeroelastic sensitivities for different aerodynamic damping approximations—the p-k method, the g method and the generalized aeroelastic analysis method—highlighting the influence of the employed aerodynamic approximation on the required derivatives. The derived formulation for the determination of aeroelastic sensitivities by means of a direct method is verified for the case of a two-degree-of-freedom typical section model, where analytical aeroelastic sensitivities can be analytically obtained. For this and for an additional model, namely the AGARD 445.6 weakened wing, the significant effect of the aerodynamic damping approximation on the aeroelastic sensitivities is shown. Full article
(This article belongs to the Special Issue Flutter Phenomena – Modeling, Identification and Control)
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18 pages, 11921 KiB  
Article
The Development of a Flight Test Platform to Study the Body Freedom Flutter of BWB Flying Wings
by Pengtao Shi, Feng Liu, Yingsong Gu and Zhichun Yang
Aerospace 2021, 8(12), 390; https://doi.org/10.3390/aerospace8120390 - 10 Dec 2021
Cited by 6 | Viewed by 3477
Abstract
A flight test platform is designed to conduct an experimental study on the body freedom flutter of a BWB flying wing, and a flight test is performed by using the proposed platform. A finite element model of structural dynamics is built, and unsteady [...] Read more.
A flight test platform is designed to conduct an experimental study on the body freedom flutter of a BWB flying wing, and a flight test is performed by using the proposed platform. A finite element model of structural dynamics is built, and unsteady aerodynamics and aeroelastic characteristics of the flying wing are analyzed by the doublet lattice method and g-method, respectively. Based on the foregoing analyses, a low-cost and low-risk flying-wing test platform is designed and manufactured. Then, the ground vibration test is implemented, and according to its results, the structural dynamics model is updated. The flight test campaign shows that the body freedom flutter occurs at low flight speed, which is consistent with the updated analytical result. Finally, an active flutter suppression controller is designed using a genetic algorithm for the developed flying wing for future tests, considering the gains and sensor location as design parameters. The open- and closed-loop analyses in time- and frequency-domain analyses demonstrate that the designed controller can improve the instability boundary of the closed-loop system effectively. Full article
(This article belongs to the Special Issue Flutter Phenomena – Modeling, Identification and Control)
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31 pages, 13467 KiB  
Article
Multimodal Estimation of Sine Dwell Vibrational Responses from Aeroelastic Flutter Flight Tests
by Sami Abou-Kebeh, Roberto Gil-Pita and Manuel Rosa-Zurera
Aerospace 2021, 8(11), 325; https://doi.org/10.3390/aerospace8110325 - 1 Nov 2021
Viewed by 2253
Abstract
Aircraft envelope expansion during new underwing stores installation is a challenging problem, mainly related to the aeroelastic flutter phenomenon. Aeroelastic models are usually very hard to model, and therefore flight tests are usually required to validate the aeroelastic model predictions, which given the [...] Read more.
Aircraft envelope expansion during new underwing stores installation is a challenging problem, mainly related to the aeroelastic flutter phenomenon. Aeroelastic models are usually very hard to model, and therefore flight tests are usually required to validate the aeroelastic model predictions, which given the catastrophic consequences of reaching the flutter point pose an important problem. This constraint favors using short time excitations like Sine Dwell to perform the flight tests, so that the aircraft stays close to the flutter point as little time as possible, but short time data implies a poor spectrum resolution and therefore leads to inaccurate and non repetitive results. The present paper will address the problem related to processing Sine Dwell signals from aeroelastic Flutter Flight Tests, characterized by very short data length (less than 5 s) and low frequency (less than 10 Hz) and used to identify the natural modes associated with the structure. In particular, a new robust technique, the PRESTO algorithm, will be presented and compared to a Matching Pursuit estimation based on Laplace Wavelet. Both techniques have demonstrated to be very accurate and robust procedures on very short time (Sine Dwell) signals, with the particularity that the Laplace Wavelet estimation has already been validated over F-18 real Flutter Flight Test data as described in different papers. However, the PRESTO algorithm improves the performance and accuracy of the Laplace Wavelet processing while keeping its robustness, both on real and simulated data. Full article
(This article belongs to the Special Issue Flutter Phenomena – Modeling, Identification and Control)
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