Deflection of Cross-Ply Composite Laminates Induced by Piezoelectric Actuators

Abstract

The coupling effects between the mechanical and electric properties of piezoelectric materials have drawn significant attention for their potential applications as sensors and actuators. In this investigation, two piezoelectric actuators are symmetrically surface bonded on a cross-ply composite laminate. Electric voltages with the same amplitude and opposite sign are applied to the two symmetric piezoelectric actuators, resulting in the bending effect on the laminated plate. The bending moment is derived by using the classical laminate theory and piezoelectricity. The analytical solution of the flexural displacement of the simply supported composite plate subjected to the bending moment is solved by using the plate theory. The analytical solution is compared with the finite element solution to show the validation of present approach. The effects of the size and location of the piezoelectric actuators on the response of the composite laminate are presented through a parametric study. A simple model incorporating the classical laminate theory and plate theory is presented to predict the deformed shape of the simply supported laminate plate.

Vibration Analysis of Composite Laminate Plate Excited by Piezoelectric Actuators

“…The bending moments per unit length m x and m y induced by the actuators to the cross-ply composite laminate have been derived in the previous work [16] as follows: $m_x=C_1{\varepsilon }_{pe}$ $m_y=C_2{\varepsilon }_{pe}$ ${\text{C}}_1=({\text{A}}_1{({\text{D}}_{11})}_{\text{p}}+{\text{A}}_2{({\text{D}}_{12})}_{\text{p}})$ ${\text{C}}_2=({\text{A}}_1{({\text{D}}_{12})}_{\text{p}}+{\text{A}}_2{({\text{D}}_{12})}_{\text{p}})$ $A_1=\frac{B_{11pe}(1+v_{pe})}{{(D_{11})}_p+D_{11pe}}+\frac{(({(D_{12})}_p+D_{12pe})(-B_{11pe}({(D_{11})}_p+D_{11pe})(1+v_{pe})+B_{11pe}({(D_{12})}_p+D_{12pe})(1+v_{pe})))}{(({(D_{11})}_p+D_{11pe})(-}$…”

A novel explicit solution for twisting control of smart laminated cantilever composite plates/beams using inclined piezoelectric actuators

“…dij is the piezoelectric dielectric constant. The in-plane stress-strain relationship for the k th smart orthotropic piezo-composite plate is shown in Eq.6a [38]. For the beam type laminates, the plane stress assumption is adapted and the width along y direction is assumed to be stress free.…”

“…ω ω (12) Pn, ta, and tp in Eq.12 are the number of inclined piezoelectric actuators, and actuator thickness, and host structure (composite laminate) thickness, respectively (See Fig.1). Governing partial differential equation relating the transverse bending and twisting moments to mid-plane displacements and electro-mechanical loads in a smart laminated piezo composite plate is stated in Eq.13 [38]. In this study, thin symmetrical cross-ply laminates are considered.…”

“…There are also numerous studies regarding the FE simulation of laminated thin/thick composite cylindrical shells under arbitrarily static [33] [34] [35]and dynamic [36] [37]loads. There are several studies regarding the FE simulation of composite plates induced by piezoelectric actuators [38] [39].…”

Design and Analysis of a Morphing Composite Airfoil Using Unbalanced Layup and Unconventional Ply Angles

“…27,28) To study this phenomenon, the JavaFoil airfoil analysis program 29) is used to investigate the aerodynamic characteristics of the designed morphing airfoil in order to determine the effect of altering the location and number of actuation forces. The JavaFoil program is able to calculate the distribution of the velocity on the airfoil surface and integrate it to obtain the lift and the moment coefficient.…”