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Active Vibration Control of Aircraft Wings Modeled as Thin-Walled Composite Beams Using Piezoelectric Actuation

[+] Author Affiliations
Kaan Yildiz, Seher Eken, Metin O. Kaya

Istanbul Technical University, Maslak, Istanbul, Turkey

Paper No. IMECE2014-38481, pp. V04BT04A066; 8 pages
  • ASME 2014 International Mechanical Engineering Congress and Exposition
  • Volume 4B: Dynamics, Vibration, and Control
  • Montreal, Quebec, Canada, November 14–20, 2014
  • Conference Sponsors: ASME
  • ISBN: 978-0-7918-4648-3
  • Copyright © 2014 by ASME


In this study the closed-loop vibrational behavior of aircraft wing is investigated. The wing is modeled as a thin-walled composite beam with a diamond shaped cross-section. This beam model incorporates a number of non-classical effects such as material anisotropy, transverse shear deformation and warping restraint. Moreover, the directionality property of thin-walled composite beams produces a wide range of elastic couplings. In this respect, an anti-symmetric lay-up configuration i.e. Circumferentially Uniform Stiffness (CUS) is employed to generate coupled motion of transverse-lateral bending and transverse shear. The active feedback control is performed by using adaptive materials. The piezoelectric layers are symmetrically embedded in the host structure and the piezoactuator is spread over the entire beam span. As a result of this a boundary moment is induced at the beam tip and in this case, the control is achieved via the boundary moment feedback control yielding an adaptive change in the dynamical characteristics of the beam. the cases of proportional and velocity feedback control procedures are applied and the effect of ply-angle orientation on the fundamental frequencies are investigated and discussed.

Copyright © 2014 by ASME



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