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Home > Thèses et HDR > Thèses en 2023

02/06/2023 - Hugo FOURNIER

by Arnaud Lelevé, Laurent Krähenbühl - published on , updated on


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Hugo FOURNIER has defended his PhD on June 2nd, 2023 at 09:00 AM.
Place : Amphitheater of the Library of INSA Lyon 1, 69100 Villeurbanne

Aeroelastic Reduced-Order Modeling and Active Control of Flexible Aircraft

Jury :
Rapporteurs :
- M. Daniel ALAZARD, Professeur des Universités, ISAE Supaero
- M. Marco LOVERA, Professore Ordinario, Politecnico di Milano

Examinateurs :
- Mme Isabelle QUEINNEC, Directrice de Recherche, LAAS CNRS
- Mme Emmanuelle VIDAL SALLE, Professeure des Universités, INSA Lyon
- M. Rafael PALACIOS, Full Professor, Impérial college London

Encadrement à Ampère:
- M. Minh Tu PHAM, Maître de Conférences HdR, directeur de thèse
- M. Laurent BAKO, Maître de Conférences HdR
- M. Paolo MASSIONI, Maître de Conférences HdR

Abstract :
This thesis deals with the aeroelastic modeling of an aircraft, and its active control. By using aircraft control surfaces appropriately, wind gusts and turbulence loads can be reduced. This reduces the mass of the structures responsible for maintaining the integrity of the aircraft, and therefore improves the performance of the overall design. The use of a lidar, a sensor allowing the measurement of the wind speed several tens of meters in front of the aircraft, is envisaged to improve the load reduction capacities. Additionally, future aircraft are expected to have slimmer and more flexible wings, which reduces drag but creates adverse aeroelastic effects. Flutter is an instability that can lead to destruction of the wing at high speed. It can be canceled or at least moved outside of the flight envelope through active control of the control surfaces.
These two techniques have been developed in the thesis by means of various controller design techniques, mainly based on robust H-infinity synthesis and its variants. Dedicated techniques to model the aeroelastic dynamics of the aircraft have been developed. Techniques have also been to obtain models of reduced order, with constraints on the poles. To do this, a methodology based directly on the aeroelastic frequency response of the aircraft is used, as opposed to conventional techniques based on equations combining aerodynamics and structural dynamics, which generally lead to high order models, unusable by modern controller synthesis techniques.

Keywords: Identification, aeroelasticity, flutter, H-infinity, robustness

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