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Predicting the response of low-aspect ratio, flexible aircraft

Published online by Cambridge University Press:  03 February 2016

L. Meirovitch ,
I. Tuzcu  and
W. D. McGrory
L. Meirovitch
Affiliation:
[email protected], Department of Engineering Science and Mechanics, Virginia Polytechnic Institute and State University, Blacksburg, VA, USA
I. Tuzcu
Affiliation:
Department of Mechanical Engineering, California State University, Sacramento, CA, USA
W. D. McGrory
Affiliation:
AeroSoft, Blacksburg, VA, USA
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Abstract

Accurate prediction of the response of low-aspect ratio, flexible aircraft requires correspondingly accurate modeling of the aircraft itself and of the aerodynamic forces, both respectable problems. Assuming that the wing can be modeled as a nonuniform plate, the discretisation process of choice is the finite element method (FEM), which demands a very large number of degrees of freedom for good accuracy. Moreover, accurate modeling of the aerodynamic forces acting on the aircraft suggests the use of computational fluid dynamics (CFD), which requires the use of an extremely large number of variables. On the other hand, feedback control design for the aircraft demands an aircraft model of relatively small order, so that the dimension of the FEM and CFD models must be reduced drastically. Based on physical considerations, reasonably accurate model reductions can be achieved, but a problem remains because the FEM and CFD grids are likely to differ from one another. It is shown in this paper how to achieve desirable model reductions for both the FEM and CFD and how to integrate the aerodynamic forces into the aircraft state equations. A numerical example demonstrates how the theory can be applied to the flight of a flexible aircraft. The analytical/computational approach developed here should permit parametric studies ultimately resulting in a reduction in the time required for aircraft design and flight testing.

Type
Research Article
Information
The Aeronautical Journal , Volume 113 , Issue 1142 , April 2009 , pp. 207 - 219
Copyright
Copyright © Royal Aeronautical Society 2009 

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