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Master thesis and internship[BR]- Master's Thesis : Aeroelastic modelling of the Sonaca 200[BR]- Internship (linked to master's thesis)

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Rulliere, Hadrien ULiège
Promotor(s) : Dimitriadis, Grigorios ULiège
Date of defense : 7-Sep-2020/9-Sep-2020 • Permalink : http://hdl.handle.net/2268.2/10272
Details
Title : Master thesis and internship[BR]- Master's Thesis : Aeroelastic modelling of the Sonaca 200[BR]- Internship (linked to master's thesis)
Translated title : [fr] Modélisation aéroélastique du Sonaca 200
Author : Rulliere, Hadrien ULiège
Date of defense  : 7-Sep-2020/9-Sep-2020
Advisor(s) : Dimitriadis, Grigorios ULiège
Committee's member(s) : Andrianne, Thomas ULiège
Menghdel, Carl 
Dewandel, Carl 
Noels, Ludovic ULiège
Language : English
Number of pages : 70
Keywords : [en] Aeroelasticity
[en] Vortex Lattice Method
[en] Finite Elements
[en] Flutter analysis
[en] Thin structures theory
Discipline(s) : Engineering, computing & technology > Aerospace & aeronautics engineering
Funders : Sonaca Aircraft
Target public : Researchers
Professionals of domain
Student
Institution(s) : Université de Liège, Liège, Belgique
Degree: Master en ingénieur civil en aérospatiale, à finalité spécialisée en "aerospace engineering"
Faculty: Master thesis of the Faculté des Sciences appliquées

Abstract

[en] The present work concerns flutter analysis of the Sonaca 200, more precisely extension of
the aeroelastic model to the full airplane. It fits in the continuation of two master theses
that studied aeroelastic behavior of the main wing. The studied configuration corresponds
to the prototype state of the airplane in 2018, without fuel nor luggage and with fixed
control surfaces. An analytical approach relying on Megson aircraft structures theory [1]
is here implemented to provide structural models for the rear fuselage and the empennage
that are suited for flutter analysis. The different components are then assembled using
elastic connections to create a full finite element model of the aircraft. Numerical modal
analysis is performed on this latter and the resulting eigenmodes are compared with
experimental data from ground vibration testing for validation. In parallel, an aeroelastic
model of the Sonaca 200 utilizing the vortex lattice theory [2][3] is developed in Matlab
based on the work of Dimitriadis. It manages aerodynamic efforts on the structure with
use of vortex ring elements and relies on modal analysis data to solve the aeroelastic
equation of motion. The algorithm is first tested with experimental modes and provides
a satifactory degree of comparison with reference aeroelastic solutions computed by the
Leichtwerk company. Outputs of the finite element model are subsequently injected in
the program to observe the differences in terms of aeroelastic solutions. The results seem
encouraging but highlight sensitivity of the Vortex Lattice Method to modal parameters
of the system. It would thus be beneficial to investigate ways of improving accuracy of
the finite element model for it to be appropriate in practice. Part of this improvement
may come from determination of the real boundary conditions with the ground. Besides,
implementing movable control surface in the finite element model would allow to test
critical configurations of the airplane where actual flutter might appear.


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Author

  • Rulliere, Hadrien ULiège Université de Liège > Master ingé. civ. aérospat., à fin.

Promotor(s)

Committee's member(s)

  • Andrianne, Thomas ULiège Université de Liège - ULiège > Département d'aérospatiale et mécanique > Interactions Fluide-Structure - Aérodynamique expérimentale
    ORBi View his publications on ORBi
  • Menghdel, Carl Sonaca Aircraft
  • Dewandel, Carl Sonaca Aircraft
  • Noels, Ludovic ULiège Université de Liège - ULiège > Département d'aérospatiale et mécanique > Computational & Multiscale Mechanics of Materials (CM3)
    ORBi View his publications on ORBi
  • Total number of views 47
  • Total number of downloads 108










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