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Proceedings Paper

Vibration control of adaptive aircraft wings modeled as tapered thin-walled beams
Author(s): Liviu I. Librescu; Sungsoo Na
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Paper Abstract

A study of the vibrational control of adaptive doubly- tapered cantilevered beams, simulating an aircraft wing, exposed to time-dependent external pulses is presented. Whereas the beam structure encompasses non-classical properties such as transverse shear, anisotropy and heterogeneity of their constituent materials, the active control capabilities are based upon the implementation of the adaptive materials technology. Herein, the adaptive feature is achieved through the converse piezoelectric effect that consists of the generation of localized strains in response to an applied voltage. Piezoactuators in the form of patches or spread allover the beam span are considered. The active control involves the dynamic response to arbitrary time-dependent external pulses. The closed-loop dynamic response time histories are obtained via the use of the piezoelectrically induced boundary moment control, and through the implementation of a modified bang- bang control strategy that involves a maximum value constraint imposed on the input voltage. Numerical simulations emphasizing the performance of the adopted control strategies intended to contain and even reduce to zero the response quantities when time unfolds are presented, and pertinent conclusions are outlined.

Paper Details

Date Published: 21 August 2001
PDF: 12 pages
Proc. SPIE 4326, Smart Structures and Materials 2001: Modeling, Signal Processing, and Control in Smart Structures, (21 August 2001); doi: 10.1117/12.436486
Show Author Affiliations
Liviu I. Librescu, Virginia Polytechnic Institute and State Univ. (United States)
Sungsoo Na, Korea Polytechnic Univ. (South Korea)

Published in SPIE Proceedings Vol. 4326:
Smart Structures and Materials 2001: Modeling, Signal Processing, and Control in Smart Structures
Vittal S. Rao, Editor(s)

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