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Research Papers

Prebuckling Enhancement of Imperfect Composite Plates Using Piezoelectric Actuators

[+] Author and Article Information
Alfredo R. de Faria

Department of Mechanical Engineering, Instituto Tecnológico de Aeronáutica, CTA-ITA-IEM, São José dos Campos, SP 12228-900, Brazilarfaria@ita.br

Donatus C. D. Oguamanam1

Department of Mechanical and Industrial Engineering, Ryerson University, Toronto, ON, M5B 2K3, Canadadoguaman@ryerson.ca

Maurício V. Donadon

Department of Aeronautical Engineering, Instituto Tecnológico de Aeronáutica, CTA-ITA-IEM, São José dos Campos, SP 12228-900, Brazildonadon@ita.br

1

Corresponding author.

J. Appl. Mech 78(3), 031007 (Feb 07, 2011) (8 pages) doi:10.1115/1.4003352 History: Received November 11, 2009; Revised December 27, 2010; Posted January 04, 2011; Published February 07, 2011; Online February 07, 2011

The nonlinear response of initially imperfect composite plates with piezoelectric actuators is investigated. The nonlinearity is limited to the prebuckling regime, where higher order terms present in the strain energy expression can be neglected. The advantage of the electromechanical coupling is exploited in two ways. First, the in-plane piezoelectric stress stiffening effect is used to tailor a stress distribution that inherently increases the critical buckling loads of perfect composite plates by posing an optimization problem that efficiently handles eventual uncertainties involved in the application of mechanical loadings. Second, piezoelectric bending moments are applied in order to avoid or ameliorate the undesirable effects of initial imperfections. An actuation strategy, where the piezoelectric membrane forces and bending moments are decomposed via an appropriate selection of voltages applied to piezoelectric patches that are symmetrically bonded to the top and bottom surfaces of the plate, is proposed and shown to be effective.

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Copyright © 2011 by American Society of Mechanical Engineers
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Figures

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Figure 1

Basic configuration

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Figure 2

Stability surface

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Figure 3

Stability surface orientation

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Figure 4

Voltage envelope

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Figure 5

The variation of buckling load with voltage for different laminates

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Figure 6

[0/90]S laminated plate, βx=βy=0

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Figure 7

[0/90]S laminated plate, βx=βy=5

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