ORBi: Vio Gareth A. - Initial Investigation of Chordwise Flexible Flat Aerofoil

Reference : Initial Investigation of Chordwise Flexible Flat Aerofoil


	Document type :	Scientific congresses and symposiums : Paper published in a book
	Discipline(s) :	Engineering, computing & technology : Aerospace & aeronautics engineering
	To cite this reference:	http://hdl.handle.net/2268/118533

Title :	Initial Investigation of Chordwise Flexible Flat Aerofoil
Language :	English
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 - ULg > Département d'aérospatiale et mécanique > Interactions Fluide-Structure - Aérodynamique expérimentale >]
Publication date :	25-Apr-2012
Main document title :	Proceedings of the 53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
Publisher :	AIAA
Pages :	AIAA 2012-1774
On invitation :	No
Audience :	International
Event name :	53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
Event date :	from 23-04-2012 to 26-04-2012
Event organizer :	American Institute of Aeronautics and Astronautics
Event place (city) :	Honolulu, Hawaii
Event country :	United States of America
Keywords :	[en] Wings ; Chordwise flexibility ; Aeroelasticity
Abstract :	[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.
Target :	Researchers ; Professionals
Permalink :	http://hdl.handle.net/2268/118533

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