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Aerospace
Special Issues
Active Flutter Suppression and Gust Load Alleviation
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Active Flutter Suppression and Gust Load Alleviation

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

Deadline for manuscript submissions: 30 May 2024 | Viewed by 3911

Special Issue Editors

Prof. Dr. Pablo García-Fogeda

E-Mail Website
Guest Editor
Departamento de Vehículos Aeroespaciales, Universidad Politécnica de Madrid, 28040 Madrid, Spain
Interests: aeroelasticity; fluid–structure interaction; harmonics; unsteady aerodynamics
Dr. Félix Arévalo Lozano

E-Mail Website
Guest Editor
Structural Dynamics and Aeroelasticity Dept., Airbus Defence & Space, 28906 Getafe, Spain
Interests: aeroelasticity; fluid–structure interaction; computational fluid dynamics; dynamic loads; impact loads
Dr. Pablo Salgado Sánchez

E-Mail Website
Guest Editor
E-USOC, Center for Computational Simulation, Departamento de Aeronaves y Vehículos Espaciales, Universidad Politécnica de Madrid, 28040 Madrid, Spain
Interests: computational fluid dynamics; fluid–structure interaction; vibrations; flow control; microgravity

Special Issue Information

Dear Colleagues,

Lighter and higher-aspect-ratio wings are currently being developed with the objective of fuel consumption reduction. This will result in less-stable aircraft configurations from the aeroelastic point of view. To counteract these effects, active flutter suppression (AFS) systems need to be implemented, and have shown to be an effective method to reduce or avoid flutter problems. When AFS is included from the beginning of the aircraft design process, more efficient airframes can result.

These aircrafts are also more vulnerable to loads caused by maneuvers and gusts. Gust load alleviation (GLA) systems improve the overall efficiency of the aircraft by reducing wing weight and decreasing the wing loads during maneuvers and airflow turbulence, thus increasing the importance of the GLA design. Thereby, GLA can extend the safety margins of the flight envelope and provides better flying qualities.

When nonlinearities are present, as in the transonic flow regime, free-play of the control surface, flow separation or large geometrical deformations, the optimum control law for AFS or GLA can even be hindered. This area of research is certainly a challenge because often only linear systems are considered for AFS and/or GLA.

The dynamics of actuators, sensors and controllers is also a relevant issue for AFS and GLA. Time delays are present when digital controllers and hydraulic actuators are used. It is essential to understand and to account for their effects in order to ensure that the airplane is stabilized or the loads are reduced through the action of the AFS or GLA and not the opposite.

This Special Issue focuses on the design principles for AFS and GLA concepts in linear and nonlinear systems, including the influence of sensors and actuators in the control loop. 

Prof. Dr. Pablo García-Fogeda
Dr. Pablo Salgado Sánchez
Dr. Félix Arévalo Lozano
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

  • flutter suppression
  • aeroservoelasticity
  • control laws
  • gust load alleviation
  • unsteady aerodynamics
  • dynamics of actuators and sensors

Published Papers (3 papers)

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Research

23 pages, 1041 KiB  
Article
Active Flutter Suppression of a Wing Section in the Subsonic, Sonic and Supersonic Regimes by the H∞ Control Method
by Álvaro Muñoz and Pablo García-Fogeda
Aerospace 2024, 11(3), 198; https://doi.org/10.3390/aerospace11030198 - 29 Feb 2024
Viewed by 969
Abstract
This paper compares various procedures for determining the optimal control law for a wing section in compressible flow. The flow regime includes subsonic, sonic and supersonic flows. For the evolution of the system in the Laplace plane, the present method makes use of [...] Read more.
This paper compares various procedures for determining the optimal control law for a wing section in compressible flow. The flow regime includes subsonic, sonic and supersonic flows. For the evolution of the system in the Laplace plane, the present method makes use of the exact unsteady aerodynamic forces in this plane once the control law is established. This is a great advantage over other results previously published, where the unsteady aerodynamics in the Laplace plane are merely approximations of the curve-fitted values in the frequency domain (imaginary axis). A comparison of different control techniques like pole placement, LQR and H-infinity control demonstrates that the H-infinity controller is the optimal choice, exhibiting an H-infinity norm approximately two orders of magnitude lower than the LQR case. Furthermore, the H-infinity controller demonstrates lower pole values than those of the pole placement and LQR compensator, showing the advantage of the H-infinity controller in terms of economic efficiency. Full article
(This article belongs to the Special Issue Active Flutter Suppression and Gust Load Alleviation)
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22 pages, 7963 KiB  
Article
Adaptive Feed-Forward Control for Gust Load Alleviation on a Flying-Wing Model Using Multiple Control Surfaces
by Liqi Zhang and Yonghui Zhao
Aerospace 2023, 10(12), 981; https://doi.org/10.3390/aerospace10120981 - 22 Nov 2023
Cited by 1 | Viewed by 979
Abstract
Based on measured gust information, a multi-input multi-output (MIMO) adaptive feed-forward control scheme for gust load alleviation (GLA) on a semi-span flying-wing aircraft using multiple control surfaces is proposed. In order to remedy weight drift and biased estimation problems that are commonly encountered [...] Read more.
Based on measured gust information, a multi-input multi-output (MIMO) adaptive feed-forward control scheme for gust load alleviation (GLA) on a semi-span flying-wing aircraft using multiple control surfaces is proposed. In order to remedy weight drift and biased estimation problems that are commonly encountered in adaptive control, the circular leaky LMS (CLLMS) algorithm is employed, which utilizes gust measurement information, filtered reference signals, and error signals to update controller parameters online. The results demonstrate that good load reductions are achieved in both continuous and discrete gust environments. For instance, the designed GLA control system leads to an 80.72% reduction in the root-mean-square (RMS) values of wing-root bending moment in the Dryden gust environment and a 77.59% reduction of its maximum value in the 1-cos discrete gust condition. Based on the limited power of the actuator and the limited authority for control surface deflections when integrating GLA into the flight control system, a weight-updating algorithm with deflection angle and rate constraints on control surfaces is proposed. The simulation results show that the strict constraints on control surface deflections will degrade the GLA performance. Finally, the influence of the partial jamming fault of actuators on GLA performance is studied. It is found that good GLA performance can be preserved despite the degraded performance during the initial stage of the actuator jamming fault. This is due to the robustness brought about by multiple control surfaces and the adaptability of the control algorithm. Full article
(This article belongs to the Special Issue Active Flutter Suppression and Gust Load Alleviation)
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24 pages, 11155 KiB  
Article
Development of an Active Wingtip for Aeroelastic Control
by Francesco Toffol and Sergio Ricci
Aerospace 2023, 10(8), 693; https://doi.org/10.3390/aerospace10080693 - 04 Aug 2023
Viewed by 1247
Abstract
This paper presents the design of an innovative wingtip device actively actuated to control the aeroelastic loads, with a focus on the gust load alleviation. It summarizes the work carried out in the Clean Sky 2 AIRGREEN2 project, where the device was developed [...] Read more.
This paper presents the design of an innovative wingtip device actively actuated to control the aeroelastic loads, with a focus on the gust load alleviation. It summarizes the work carried out in the Clean Sky 2 AIRGREEN2 project, where the device was developed from scratch and reached a relevant technology readiness level with the full-scale prototype manufacturing and testing, compulsory to obtain the permit to fly. This paper describes the overall design of the devices, covering the structure, the aero-servo-elasticity characteristics of the whole aircraft, the actuation system design, the scaled wind tunnel testing, and the full-scale structural qualification tests. The paper proves how the development of a new item involves several disciplines simultaneously, remarking on the importance of an integrated approach to the new generation aircraft design. Full article
(This article belongs to the Special Issue Active Flutter Suppression and Gust Load Alleviation)
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