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Aeroelastic behaviour of a wing including geometric nonlinearities

Published online by Cambridge University Press:  27 January 2016

M. Y. Harmin  and
J. E. Cooper
M. Y. Harmin*
Affiliation:
University of Liverpool, Liverpool, UK
J. E. Cooper*
Affiliation:
University of Liverpool, Liverpool, UK
*
m.harmin@liverpool.ac.uk
j.e.cooper@liverpool.ac.uk
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Abstract

A procedure for developing efficient aeroelastic reduced order models (ROMs) for aerospace structures containing geometric nonlinearities is described. The structural modelling is based upon a combined modal/FE approach that describes the non-linear stiffening effects from results of non-linear static analyses for a range of prescribed inputs. Once the structural ROM has been defined, it is coupled to the rational fraction approximation of the doublet lattice aerodynamic model corresponding to the wing planform. The aeroelastic model can then be used to predict the dynamic aeroelastic behaviour of the defined structure. The methodology is demonstrated on the aeroelastic model of a flexible high aspect ratio wing with the static deflections, LCO behaviour and gust response being predicted.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 115 , Issue 1174 , December 2011 , pp. 767 - 777
Copyright
Copyright © Royal Aeronautical Society 2011 

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