[en] The size of small Unmanned Air Vehicles (UAVs) makes them susceptible to gusts, hence
an evaluation of their aeroelastic performance is a necessary requirement. With advances
in materials, new aircraft are ever lighter and more flexible, both in the span-wise and
chord-wise direction. An experiment is set up to evaluate the aeroelastic performance of a
2D chord-wise aerofoil structure under gust loading, where the wing of a small Unmanned
Air Vehicle (UAV) is considered by coupling a Finite Element (FE) structural model with
a Doublet-Lattice Method (DLM) aerodynamic model; a new semi-analytical modelling
approach is also described. The flexible aerofoil structure is then optimised by means
of a genetic algorithm (GA) framework for the minimum weight, subject to aeroelastic
constraints of flutter, divergence and structural displacement.
Disciplines :
Aerospace & aeronautics engineering
Author, co-author :
Vio, Gareth A.; University of Sydney > School of Aerospace, Mechanical and Mechatronic Engineering
Worotynska, Jagoda; University of Sydney > School of Aerospace, Mechanical and Mechatronic Engineering
Berci, Marco; University of Leeds > School of Mechanical Engineering
Dimitriadis, Grigorios ; Université de Liège - ULiège > Département d'aérospatiale et mécanique > Interactions Fluide-Structure - Aérodynamique expérimentale
Language :
English
Title :
Initial Investigation of Chordwise Flexible Flat Aerofoil
Publication date :
25 April 2012
Event name :
53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
Event organizer :
American Institute of Aeronautics and Astronautics
Event place :
Honolulu, Hawaii, United States
Event date :
from 23-04-2012 to 26-04-2012
Audience :
International
Main work title :
Proceedings of the 53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
