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Modelling Piezoelectric Actuation During Structural Flutter

[+] Author Affiliations
M. Hariri, S. John, P. Trivailo

RMIT University, Bundoora, VIC, Australia

Paper No. SMASIS2009-1250, pp. 33-43; 11 pages
doi:10.1115/SMASIS2009-1250
From:
  • ASME 2009 Conference on Smart Materials, Adaptive Structures and Intelligent Systems
  • Volume 1: Active Materials, Mechanics and Behavior; Modeling, Simulation and Control
  • Oxnard, California, USA, September 21–23, 2009
  • Conference Sponsors: Aerospace Division
  • ISBN: 978-0-7918-4896-8 | eISBN: 978-0-7918-3857-0
  • Copyright © 2009 by ASME

abstract

Aeroelasticity is a major concern in structural control. It results from the interaction between the air-stream and the structure. Wing flutter is a well known problem of the aero-elasticity. It occurs when the two lowest system eigenvalues (plunge and pitch motion) coalesce at a certain air speed known as the flutter speed. The increasing use of active material induced-strain actuation such as piezoelectric materials in the suppression of structural vibrations has seen its extension to wing flutter control. Higher flutter speed and hence, a wider operating envelope was achieved by delaying the coalescence of these two eigenvalues. This delay is obtained by adding more strain energy to the system as a result of the activation of the piezoelectric actuators. This paper models a simple beam under nominal aerodynamic loading conditions for the determination of analytically-derived onset of flutter speeds. Also shown in this paper, is the effect of orientation of actuated piezoelectric patches, on the shift of the flutter speed.

Copyright © 2009 by ASME

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