Nonlinear Aeroelastic Simulation of a Full-Span Aircraft with Oscillating Control Surfaces
Publication: Journal of Aerospace Engineering
Volume 18, Issue 3
Abstract
In this paper, the transonic and low-supersonic aeroelastic behavior of the generic fighter model was investigated in the time domain. The simulation of flutter flight test using forced harmonic motion of control surfaces including inertial coupling effects was conducted at the various conditions. The detailed dynamic aeroelastic responses are computed using a coupled time-marching method based on the effective computational structural dynamic and computational fluid dynamics techniques. The nonlinear aerodynamic effects due to an existing shock wave on the lifting surfaces were considered using a transonic small disturbance equation. A modal model obtained by a free vibration analysis was used for the structural model. The relations between the computed flutter boundary and the simulation results of the responses using the harmonic motions of control surfaces at various conditions were investigated.
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Acknowledgments
This work was partially supported through funding from the National Research Laboratory Program and the research project from Korea Aerospace Industry (KAI). The writers would like to acknowledge their support.
References
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Information & Authors
Information
Published In
Journal of Aerospace Engineering
Volume 18 • Issue 3 • July 2005
Pages: 156 - 167
Copyright
© 2005 ASCE.
History
Received: Aug 1, 2002
Accepted: Sep 26, 2004
Published online: Jul 1, 2005
Published in print: Jul 2005
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