Robust Aeroelastic Control of a Thin-Walled Wing Structure with Model Uncertainty
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Volume 25, Issue 2
Abstract
The robust vibration control and dynamic response analysis of an advanced aircraft wing structure are addressed in this paper. The wing structure is modeled as a thin-walled beam with fiber-reinforced composite materials featuring a circumferentially asymmetric stiffness (CAS) configuration that completely splits into two coupled groups of motion. The time-dependent external loads are considered with unsteady aerodynamics in an incompressible flow field. To demonstrate the robust characteristics of the sliding mode methods, both the conventional linear quadratic Gaussian (LQG) regulator and the proposed method are compared with respect to model uncertainty and external excitation. The numerical results demonstrate that the sliding mode control (SMC) on the basis of the sliding mode observer (SMO) is an efficient way to control the unstable dynamic response subjected to various external loads associated with model uncertainty.
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Acknowledgments
This work was supported by Basic Science Research Program through the National Research Foundation of Korea (2010-0001642) and by a Korea University Grant.
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Published In
Journal of Aerospace Engineering
Volume 25 • Issue 2 • April 2012
Pages: 320 - 333
Copyright
© 2012. American Society of Civil Engineers.
History
Received: Jun 20, 2010
Accepted: Mar 29, 2011
Published online: Mar 31, 2011
Published in print: Apr 1, 2012
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