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Materials Science » Ceramics » "Piezoelectric Materials and Devices - Practice and Applications", book edited by Farzad Ebrahimi, ISBN 978-953-51-1045-3, Published: February 27, 2013 under CC BY 3.0 license. © The Author(s).

Chapter 1

Piezoelectric Actuators for Functionally Graded Plates- Nonlinear Vibration Analysis

By Farzad Ebrahimi
DOI: 10.5772/52407

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FG circular plate with two piezoelectric actuators.
Figure 1. FG circular plate with two piezoelectric actuators.
Effect of applied voltage to the normalized center deflection for various normalized temperatures
							 (Metal plate)
Figure 2. Effect of applied voltage to the normalized center deflection for various normalized temperatures T * = ( a 2 N t / 4 D 2 ) (Metal plate)
Normalized Temperature effects to the center deflection for various values of Voltages (n=0.5)
Figure 3. Normalized Temperature effects to the center deflection for various values of Voltages (n=0.5)
Normalized Temperature effects to the center deflection for various values of Voltages (n=10)
Figure 4. Normalized Temperature effects to the center deflection for various values of Voltages (n=10)
FGM index effects on nonlinear center deflection for various normalized temperature (V=0.2)
Figure 5. FGM index effects on nonlinear center deflection for various normalized temperature (V=0.2)
FGM index effects on nonlinear center deflection for various normalized temperature (V=1)
Figure 6. FGM index effects on nonlinear center deflection for various normalized temperature (V=1)
Effect of normalized voltage to first natural frequency for various FGM indexes (T*=0.2)
Figure 7. Effect of normalized voltage to first natural frequency for various FGM indexes (T*=0.2)
Effect of normalized voltage to first natural frequency for various FGM indexes (T*=0.8)
Figure 8. Effect of normalized voltage to first natural frequency for various FGM indexes (T*=0.8)
Effects of normalized temperature on the normalized first natural frequency for various normalized voltages (n=10,n=0.5)
Figure 9. Effects of normalized temperature on the normalized first natural frequency for various normalized voltages (n=10,n=0.5)
Temperature/control effects on amplitude dependent first natural frequency (for metal plate) – amplitude ratio: w/hf, frequency ratio: (ω /ω1)
Figure 10. Temperature/control effects on amplitude dependent first natural frequency (for metal plate) – amplitude ratio: w/hf, frequency ratio: (ω /ω1)

Piezoelectric Actuators for Functionally Graded Plates-Nonlinear Vibration Analysis

Farzad Ebrahimi1

1. Introduction

Functionally graded materials (FGMs) are a new generation of composite materials wherein the material properties vary continuously to yield a predetermined composition profile. These materials have been introduced to benefit from the ideal performance of its constituents, e.g., high heat/corrosion resistance of ceramics on one side, and large mechanical strength and toughness of metals on the other side. FGMs have no interfaces and are hence advantageous over conventional laminated composites. FGMs also permit tailoring of material composition to optimize a desired characteristic such as minimizing the maximum deflection for a given load and boundary conditions, or maximizing the first frequency of free vibration, or minimizing the maximum principal tensile stress. As a result, FGMs have gained potential applications in a wide variety of engineering components or systems, including armor plating, heat engine components and human implants. FGMs are now developed for general use as structural components and especially to operate in environments with extremely high temperatures. Low thermal conductivity, low coefficient of thermal expansion and core ductility have enabled the FGM materials to withstand higher temperature gradients for a given heat flux. Structures made of FGMs are often susceptible to failure from large deflections, or excessive stresses that are induced by large temperature gradients and/or mechanical loads. It is therefore of prime importance to account for the geometrically nonlinear deformation as well as the thermal environment effect to ensure more accurate and reliable structural analysis and design.

The concept of developing smart structures has been extensively used for active control of flexible structures during the past decade [1-3]. In this regard, the use of axisymmetric piezoelectric actuators in the form of a disc or ring to produce motion in a circular or annular substrate plate is common in a wide range of applications including micro-pumps and micro-valves [4, 5], devices for generating and detecting sound [6] and implantable medical devices [7]. They may also be useful in other applications such as microwave micro-switches where it is important to control distortion due to intrinsic stresses [8]. Also in recent years, with the increasing use of smart material in vibration control of plate structures, the mechanical response of FGM plates with surface-bonded piezoelectric layers has attracted some researchers’ attention. Since this area is relatively new, published literature on the free and forced vibration of FGM plates is limited and most are focused on the cases of the linear problem. Among those, a 3-D solution for rectangular FG plates coupled with a piezoelectric actuator layer was proposed by Reddy and Cheng [9] using transfer matrix and asymptotic expansion techniques. Wang and Noda [10] analyzed a smart FG composite structure composed of a layer of metal, a layer of piezoelectric and an FG layer in between, while He et al. [11] developed a finite element model for studying the shape and vibration control of FG plates integrated with piezoelectric sensors and actuators. Yang et al. [12] investigated the nonlinear thermo-electro-mechanical bending response of FG rectangular plates that are covered with monolithic piezoelectric actuator layers on the top and bottom surfaces of the plate. More recently, Huang and Shen [13] investigated the dynamics of an FG plate coupled with two monolithic piezoelectric layers at its top and bottom surfaces undergoing nonlinear vibrations in thermal environments. In addition, finite element piezothermoelasticity analysis and the active control of FGM plates with integrated piezoelectric sensors and actuators was studied by Liew et al. [14] and the temperature response of FGMs using a nonlinear finite element method was studied by Zhai et al. [15]. All the aforementioned studies focused on the rectangular-shaped plate structures. To the authors’ best knowledge, no researches dealing with the nonlinear vibration characteristics of the circular functionally graded plate integrated with the piezoelectric layers have been reported in the literature except the author's recent works in presenting an analytical solution for the free axisymmetric linear vibration of piezoelectric coupled circular and annular FGM plates [16-20] and investigating the applied control voltage effect on piezoelectrically actuated nonlinear FG circular plate [21] in which the thermal environment effects are not taken in to account.

Consequently, a non-linear dynamics and vibration analysis is conducted on pre-stressed piezo-actuated FG circular plates in thermal environment. Nonlinear governing equations of motion are derived based on Kirchhoff’s-Love hypothesis with von-Karman type geometrical large nonlinear deformations. Dynamic equations and boundary conditions including thermal, elastic and piezoelectric couplings are formulated and solutions are derived. An exact series expansion method combined with perturbation approach is used to model the non-linear thermo-electro-mechanical vibration behavior of the structure. Numerical results for FG plates with various mixture of ceramic and metal are presented in dimensionless forms. A parametric study is also undertaken to highlight the effects of the thermal environment, applied actuator voltage and material composition of FG core plate on the nonlinear vibration characteristics of the composite structure. The new features of the effect of thermal environment and applied actuator voltage on free vibration of FG plates and some meaningful results in this chapter are helpful for the application and the design of nuclear reactors, space planes and chemical plants, in which functionally graded plates act as basic elements.


Figure 1.

FG circular plate with two piezoelectric actuators.

2. Functionally graded materials (FGM)

Nowadays, not only can FGM easily be produced but one can control even the variation of the FG constituents in a specific way. For example in an FG material made of ceramic and metal mixture, we have:

in which V c and V m are the volume fraction of the ceramic and metallic part, respectively. Based on the power law distribution [22], the variation of V c vs. thickness coordinate (z) with its origin placed at the middle of thickness, can be expressed as:


in which h f is the FG core plate thickness and n is the FGM volume fraction index (see Figure 1). Note that the variation of both constituents (ceramics and metal) is linear when n=1. We assume that the inhomogeneous material properties, such as the modulus of elasticity E, density ρ , thermal expansion coefficient α and the thermal conductivity κ change within the thickness direction z based on Voigt’s rule over the whole range of the volume fraction [23] while Poisson’s ratio υ is assumed to be constant in the thickness direction [24] as:


where subscripts m and c refer to the metal and ceramic constituents, respectively. After substituting Vc from Eq. (2) into Eqs. (3), material properties of the FGM plate are determined in the power law form-the same as those proposed by Reddy and Praveen [22]:


3. Thermal environment

Assume a piezo-laminated FGM plate is subjected to a thermal environment and the temperature variation occurs in the thickness direction and 1D temperature field is assumed to be constant in the r-θ plane of the plate. In such a case, the temperature distribution along the thickness can be obtained by solving a steady-state heat transfer equation


in which


where κ p and κ f are the thermal conductivity of piezoelectric layers and FG plate, respectively. Eq. (5) is solved by imposing the boundary conditions as


and the continuity conditions


The solution of Eq.(5) with the aforementioned conditions can be expressed as polynomial series:




where constants T 1 , T 2 and A j can be found in Appendix A.

4. Nonlinear piezo-thermo-electric coupled FG circular plate system

It is assumed that an FGM circular plate is sandwiched between two thin piezoelectric layers which are sensitive in both circumferential and radial directions as shown in Figure 1 and the structure is in thermal environment; also, the piezoelectric layers are much thinner than the FGM plate, i.e., h p << h f .An initial large deformation exceeding the linear range is imposed on the circular plate and a von-Karman type nonlinear deformation is adopted in the analysis. The von-Karman type nonlinearity assumes that the transverse nonlinear deflection w is much more prominent than the other two inplane deflections.

4.1. Nonlinear strain-displacement relations

Based on the Kirchhoff-Love assumptions, the strain components at distance z from the middle plane are given by


where the z-axis is assumed positive outward. Here ε¯rr , ε¯θθ , ε¯rθ are the engineering strain components in the median surface, and krr , kθθ , krθ are the curvatures which can be expressed in terms of the displacement components. The relations between the middle plane strains and the displacement components according to the von-Karman type nonlinear deformation and Sander's assumptions [25] are defined as:


where ur , uθ ,w represent the corresponding components of the displacement of a point on the middle plate surface. Substituting Eqs. (14) and (15) into Eqs. (13), the following expressions for the strain components are obtained


For a circular plate with axisymmetric oscillations, the strain expressions are simplified to


4.2. Force and moment resultants

The stress components in the FG core plate in terms of strains based on the generalized Hooke’s Law using the plate theory approximation of σz0 in the constitutive equations are defined as [26];


where E(z), ν(z) and α(z) are Young’s modulus, Poisson’s ratio and coefficient of thermal expansion of the FGM material, respectively, as expressed in Eq.(4), where ΔT=T(z)T0 is temperature rise from the stress-free reference temperature ( T0 ) which is assumed to exist at a temperature of T0=0 and T(z) is presented in Eqs. (10)-(12).

The moments and membrane forces include both mechanical and electric components as


where the superscripts m, e, and t, respectively, denote the mechanical, electric, and temperature components. Mechanical forces and moments of the thin circular plate made of functionally graded material can be expressed as


Substituting Eqs. (13) and (18),(19) into Eqs. (22)-(23) gives the following constitutive relations for mechanical forces and moments of FG plate :


in which the coefficients of D 1 and D 2 in the above equations are related to the plate stiffness and are given by


It is assumed that the piezoelectric layers are sensitive in both radial and circumferential directions and the piezoelectric permeability constants e31=e32. Hence, the electric membrane forces and bending moments are induced by the converse piezoelectric effect on the piezoelectric actuators, and these forces vary linearly across the plate thickness as [27];


in which Vzt and Vzb are the control voltages applied to the top and bottom piezoelectric layers, respectively.

4.3. System electromechanical equations

Axisymmetric free oscillation equations of the piezoelectric coupled circular FG plate in thermal environment can be derived from the generic piezoelectric shell equations using four system parameters: two Lame parameters, A 1 =1, A 2 =r, where r is the radial distance measured from the center, and two radii, R 1 =∞, R 2 =∞ [28,29] as


in which I1=(hf/2hf/2ρf(z)dz) and the transverse shear component Qrz is related to moments as


Note that only the normal radial strain keeps the quadratic nonlinear term. Substituting all force/moment components and strain-displacement equations into the radial and transverse equations (31), (32) yields


in which Y=(hf/2hf/2Ef(z)dz) and boundary conditions at the center of the plate with axisymmetric oscillations are defined as

(1) Plate center (r=0): Slope:wr=0
Radial force:Nrrm: finite

Boundary conditions for the simply supported (immovable) circumference are defined as:

Plate circumference (r=a):


It is further assumed that the control potentials on the top and bottom piezoelectric actuators are of equal magnitudes and opposite signs, i.e., Vzt=Vzb=V^ and the plate is subjected to a uniform temperature excitation of T(z). Accordingly, the electric and temperature induced forces and moments can be defined as:


Using these force and moment expressions, one can further simplify the open-loop plate equations and boundary conditions:


Boundary conditions become

Plate center (r=0):

  Radial force:Nrm|r=0: finite

Plate circumference (r=a):


4.4. Simplification and Normalization

Solutions of the transverse displacement w and radial force Nrm of the above open-loop plate equations and boundary conditions can be expressed as a summation of a static component and a dynamic component as


where ws(r) and Nrsm(r,t) are the static solutions, wd(r,t) and Nrdm(r,t) are the dynamic solutions, and the subscripts s and d, respectively, denote the static and dynamic solutions. Accordingly, the solution procedure can be divided into two parts. The first part deals with the nonlinear static solutions, and the second part deals with the dynamic solutions. In addition, normalized dimensionless quantities are adopted in the static and dynamic analyses. These dimensionless quantities are defined by known geometrical and material parameters [30]:

  • radial distance: y=(r/a)2 ,

  • transverse deflection: w¯s=3(1ν2)wshf ,

  • slope: Xs(y)=ydw¯sdyMathType@MTEF@5@5@+=feaagCart1ev2aaatCvAUfeBSjuyZL2yd9gzLbvyNv2CaerbuLwBLnhiov2DGi1BTfMBaeXatLxBI9gBaerbd9wDYLwzYbItLDharqqtubsr4rNCHbGeaGqiVCI8FfYJH8YrFfeuY=Hhbbf9v8qqaqFr0xc9pk0xbba9q8WqFfeaY=biLkVcLq=JHqpepeea0=as0Fb9pgeaYRXxe9vr0=vr0=vqpWqaaeaabiGaciaacaqabeaadaqaaqaaaOqaaiaadIfadaWgaaWcbaGaam4CaaqabaGccaGGOaGaamyEaiaacMcacqGH9aqpcaWG5bWaaSaaaeaacaWGKbGabm4DayaaraWaaSbaaSqaaiaadohaaeqaaaGcbaGaamizaiaadMhaaaaaaa@4171@

  • static force: Ysm(y)=(a2Nrsm/4D2)y

  • radial distance: x=(r/a) ,

  • dynamic deflection: w¯d=3(1ν2)wdhf ,

  • dynamic force: Ydm(y)=(a2Nrdm/D2)

  • voltage: V=[3(1ν2)]1/2e31(hf+hp)V^/(2D2hf)MathType@MTEF@5@5@+=feaagCart1ev2aaatCvAUfeBSjuyZL2yd9gzLbvyNv2CaerbuLwBLnhiov2DGi1BTfMBaeXatLxBI9gBaerbd9wDYLwzYbItLDharqqtubsr4rNCHbGeaGqiVCI8FfYJH8YrFfeuY=Hhbbf9v8qqaqFr0xc9pk0xbba9q8WqFfeaY=biLkVcLq=JHqpepeea0=as0Fb9pgeaYRXxe9vr0=vr0=vqpWqaaeaabiGaciaacaqabeaadaqaaqaaaOqaaiaadAfacqGH9aqpdaWcgaqaamaadmaabaGaaG4maiaacIcacaaIXaGaeyOeI0IaeqyVd42aaWbaaSqabeaacaaIYaaaaOGaaiykaaGaay5waiaaw2faamaaCaaaleqabaGaaGymaiaac+cacaaIYaaaaOGaamyzamaaBaaaleaacaaIZaGaaGymaaqabaGccaGGOaGaamiAamaaBaaaleaacaWGMbaabeaakiabgUcaRiaadIgadaWgaaWcbaGaamiCaaqabaGccaGGPaGabmOvayaajaaabaWaaeWaaeaacaaIYaGaamiramaaBaaaleaacaaIYaaabeaakiaadIgadaWgaaWcbaGaamOzaaqabaaakiaawIcacaGLPaaaaaaaaa@528E@

  • temperature load: T*=(a2Nt/4D2)

Substituting these normalized dimensionless quantities into the open-loop plate equations and boundary conditions of axisymmetric plate oscillations and separating the static parts from the dynamic parts gives the static equations and dynamic equations with their associated boundary conditions:


(1) Static Equations and Boundary Conditions


Boundary conditions at center y = 0:

Boundary conditions on circumference y = 1:


(2) Dynamic Equations and Boundary Conditions


Boundary conditions at center x = 0:


Boundary conditions on circumference x = 1:


5. Static Solutions

For the nonlinear static equations and boundary conditions of the boundary value problem derived above, static solutions of slopes Xs(y) and forces Ysm(y) can be represented in (exact) series expansion forms [30]:


where A i and B i are constant coefficients. Substituting the series solutions, Eqs. (53a& b), into static equations, Eqs. (45) & (46), and grouping coefficients of y i one can obtain the recurrence equations for coefficients A i and B i :


It is observed that only A 1 and B 1 are independent constants, and the others are dependent. As long as A 1 and B 1 are determined by the boundary conditions, other coefficients A i and B i can be calculated from the recurrence equations. Accordingly, static series solutions are completed. The series solutions of Ysm(y) and Xs(y) satisfy the boundary conditions at y = 0, Eqs. (47a,b). Substituting the assumed series solutions Ysm(y) and Xs(y) into the boundary conditions at y = 1, Eqs. (48a,b), yields


A i and B i can be determined from the nonlinear algebraic equations Eqs. (55a,b) using the Newton-Raphson iteration method [31]. Define


in which




A¯1 and B¯1 are, respectively, the iteration values of A 1 and B 1 ; Δ1 and Δ2 are the correction factors of A 1 and B 1 at each iteration. The partial derivatives α/A1 , α/B1 , β/A1 and β/B1 , can be determined from the definitions of α(A1,B1) and β(A1,B1) . These iterations are repeated until they reach their prescribed limits, say |α| , |β| , |Δ1| and |Δ2| are smaller than 10-4. Accordingly, a set of A 1 and B 1 are determined for a set of given control voltages V and temperatures T^ . Using the recurrence equations, one can determine all other A i 's and B i 's, and further the nonlinear static solutions of slope Xs(y) and static force Ysm(y) . Knowing the slope, one can determine the static deflections w¯s and ws of the nonlinear circular plate subject to voltage and temperature excitations.

6. Dynamic Solutions

It is assumed that the FG circular plate is oscillating in the vicinity of the nonlinearly deformed static equilibrium position. FG index, voltage and temperature effects to the natural frequencies and amplitude/frequency relations are investigated in this section. First, linearized eigenvalue equations are solved using the exact series solutions. Then nonlinear amplitude and frequency relations of nonlinear large amplitude free vibrations are investigated using the Galerkin method and the perturbation method.

6.1. Eigenvalue Equations

Neglect the nonlinear terms in the normalized dynamic equations, and then assume following harmonic solutions of displacement and dynamic force


where ωn is the natural frequency; Rd(x) and Sd(x) are the (linear) eigenfunctions or mode shape functions of w¯d(x,t) and Ydm(x,t) , respectively. Rd(x) defines the mode shape function, and Sd(x) defines the spatial force distribution. Both Rd(x) and Sd(x) have to satisfy the boundary conditions, and they are also assumed in the series expansion forms. Substituting Eqs. (59a, b) into the dynamic equations and boundary conditions, Eqs. (49)-(52), yields


where λ is the eigenvalue and λ=I1a4D2ωn2 . Boundary conditions become

  1. Center x=0:

  1. Circumference x=1:


Again, assume the eigenfunctions take the series expansion forms:


where ai and bi , are constants determined by eigenvalue equations and boundary conditions. The series solutions Rd(x) and Sd(x) satisfy the boundary conditions at x = 0, Eqs. (62a,b). Assume ai and bi , be represented by the linear combinations of independent constants a0 , a1 and b0 .


where fij and gij are to be determined. Substituting the series expressions of modes Rd(x) and forces Sd(x) into the dynamic equations, one can derive a set of recurrence equations of ai and bi . Then, using expressions of ai and bi of Eqs. (65a, b), one can further determine the coefficients fij and gij f01=1,f02=f03=0; f11=0,f12=1,f13=0; gik=2i(i+1)j=1ijfjkAij+1 , i=1,2,3,... , k=1,2,3. , g01=0,g02=0,g03=1; f21=λ/64,f23=A1/8 , f33=[A1g13+4f23(B1T*)+A2]/36, f32={λ+32B2+16[A1g12+4f22(B1T)]}/24 , f31=[A1g11+4f21(B1T)]/36 , f22=(B1T*)/4 f(i+2)k=[λfik16T*(i+1)2+8(i+1)×j=1i+1(2jfikBik+2+Ajg(ij+1)k)][4(i+1)(i+2)]2 i=2,3,4,..., and k=1,2,3.

Substituting these coefficients into the boundary conditions at x = 1, one can obtain an explicit matrix representation of the eigenvalue equation.


where hij are defined by


These hik coefficients are functions of eigenvalues λ , and accordingly, the determinant of the coefficient matrix leads to a nonlinear characteristic equation. Using the Newton-Raphson iteration method [31], one can calculate eigenvalues and furthermore natural frequencies and mode shape functions of the nonlinear FG circular plate.

6.2. Nonlinear Large Amplitude Free Vibrations

In this section, the perturbation method is used to investigate the nonlinear large amplitude effect to natural frequencies of the piezoelectric laminated FG circular plate. Assume an approximate solution of the nonlinear response w¯d(x,t) be a product of a spatial function w¯d*(x) and a temporal function f(t) ;


where w¯d*(x) is a test function satisfying the boundary conditions:

  1. Plate center x=0: w¯d*x|x=0=0

  2. Plate circumference x=1: w¯d*|x=1=0 ,


Substituting Eq. (68) into the dynamic equation Eq. (49) and using the Galerkin method, one can derive a nonlinear equation for f(τ)


where τ=ωt and μ1 and μ2 are the nonlinear coefficient functions, ω is defined by


c1 , c2 and c3 are defined by integrals:


in which Nrd*l(x) and Nrd*n(x) are the linear and nonlinear force components. The nonlinear coefficient functions μ1 and μ1 are defined by


where c4 and c5 are defined by integrals:


The linear and nonlinear force components are written as


The kernel function


Since the mode shape functions of the linear free vibrations were determined previously, it is convenient to select the mode shape functions as the trial functions,


and the frequency can be selected as the natural frequencies determined previously. Using the Krylov-Bogoliubov-Mitropolsky perturbation method [32] and solving the nonlinear dynamic equation Eq. (70), one can obtain the amplitude-frequency relation as


where ω is the (nonlinear vibration) frequency; ωn is the natural frequency; a^ is the dimensionless vibration amplitude; and μ1 and μ2 are the nonlinear coefficient functions. Note that the ratio is unity, i.e., p=ω/ωn=1 , if the system is linear. Once the coefficients μ1 and μ2 are calculated, one can further evaluate the amplitude and frequency relations of the nonlinear circular plate subjected to temperature excitations and control voltages.

7. Results and Discussions

Temperature effects of nonlinear static deformations, control voltages, and linear and nonlinear free vibrations of a simply supported piezoelectric laminated functionally graded circular plate are investigated in this section.

7.1. Comparison studies

To ensure the accuracy of the present analysis, an illustrative example is solved. The relevant material properties are listed in Table 1. Since there are no appropriate comparison results available for the problems being analyzed in this chapter, we decided to verify the validity of the obtained results by comparing with those of the FEM results. Our FEM model for piezo-FG plate consists of a 3D 8-noded solid element with number of total nodes 26950, number of total elements 24276, 4 DOF per node (3 translation, temperature) in the host plate element and 6 DOF per node (3 translation, temperature, voltage and magnetic properties) in the piezoelectric element. The finite element model has been programmed by the authors, while the standard bilinear interpolations have been employed in finite element approximations.

Table 2 compares the present results of normalized dimensionless central deflections Ws=3(1ν2)(ws/hf) with finite element solutions in analyzing the effect of normalized dimensionless piezoelectric voltages V=[3(1ν2)]1/2e31(hf+hp)V*/(2D2hf) to the normalized dimensionless center deflections at various normalized temperatures ( T*=(a2Nt/4D2) ) in which a nonlinear deflection-voltage relationship can be observed. As seen from Table 2 the maximum estimated difference of the proposed solution with finite element method is about 0.079%, and a close correlation between these results validates the proposed method of solution.

In general, a higher temperature induces higher deflections of the plate, and the deflection at each temperature is attenuated when the control voltage increases and the effect of imposed voltage on the center deflection is nonlinear and this effect is predominant in lesser voltage amounts. This effect can also be seen in the case of considering the temperature environment effect. For example, when T*=0.2 by increasing the imposed voltage from 0.6 to 1.2 (100%) the normalized dimensionless center deflections increases about 46.8%, while it increases about 34.5% when the imposed voltage increases from 1.2 to 2.4 (100%). In the case of T*=0.5 by increasing the imposed voltage from 0.6 to 1.2 (100%) the normalized dimensionless center deflection increases about 36.5% while it increases about 28.7% when the imposed voltage increases from 1.2 to 2.4 (100%).

Material                                                                         Property
E(GPa) ρ(kg/m3) ν α(1/C) κ(W/mK) d31,d32(m/V)

Table 1.

Material properties [13].


Figure 2.

Effect of applied voltage to the normalized center deflection for various normalized temperatures T*=(a2Nt/4D2) (Metal plate)

Voltage (V)
Normalized Temperature(T*)
T*=0 T*=0.2
PresentFEMDiff. (%)Present FEMDiff. (%)
T*=0.5 T*=0.8
PresentFEMDiff. (%)Present FEMDiff. (%)

Table 2.

Values of the normalized dimensionless center deflections with respect to the normalized dimensionless piezoelectric voltages for various normalized temperatures computed by two methods (present series solution and FEM) (v=0.3, n=1000)

7.2. Parametric studies

Having validated the foregoing formulations, we began to study the large amplitude vibration behavior of FG laminated circular plate subjected to thermo-electro-mechanical loading. The results for laminated plates with isotropic substrate layers (that is, the substrate is purely metallic or purely ceramic) and with graded substrate layers (various n) are given in both tabular and graphical forms.

To investigate the effect of the applied actuator voltage on the non-linear thermo-electromechanical vibration, the nonlinear normalized center deflection of various graded plates under various applied normalized voltages is tabulated in Table 3.
Temp. (T*)
FGM index (n) / Normalized Voltage (V)
 V=0.2  V=0.3  V=0.5  V=1V=0.2 V=0.3 V=0.5 V=1
 V=0.2 V=0.3 V=0.5 V=1 V=0.2 V=0.3  V=0.5  V=1
(T*)Ceramic (n=0)
 V=0.2  V=0.3  V=0.5  V=1 V=0.2  V=0.3  V=0.5  V=1

Table 3.

FGM index and normalized voltage effects to the nonlinear center deflection


Figure 3.

Normalized Temperature effects to the center deflection for various values of Voltages (n=0.5)


Figure 4.

Normalized Temperature effects to the center deflection for various values of Voltages (n=10)

For instance, Figs. 3 and 4. depict the normalized temperature and voltage effects on the center deflection of two graded plates (n=0.5 n=10). It shows that increasing the normalized temperature makes the center deflection increase in various voltages, but this effect is predominant at higher voltages. Figures 5~6 depict the effect of FGM index on the non-linear thermo-electro-mechanical behavior (center deflection) of FGM plates with different normalized applied voltages in logarithmic scale. It is also obvious from these figures that, by increasing the material gradients, the normalized center deflection would be increased in various temperature fields, and it is also demonstrated that larger thermal gradients will lead to greater deflections. This trend can be seen in various material gradients, which means that the non-linear deflection can be controlled by applying the appropriate voltage in the piezoelectric actuator layers.


Figure 5.

FGM index effects on nonlinear center deflection for various normalized temperature (V=0.2)


Figure 6.

FGM index effects on nonlinear center deflection for various normalized temperature (V=1)

Voltage (V)
FGM index (n) / Normalized Temp. (T*)
Normalized Temperature (T*) Normalized Temperature (T*)
0.0 4.8891 4.4249 3.5293 2.3669 5.5359 5.0103 3.9962 2.6800
0.4 5.5796 5.67452 5.92735 6.49712 6.3178 6.4253 6.7116 7.3567
0.8 6.7141 7.26308 8.00595 8.71889 7.6024 8.2240 9.0652 9.8724
1.2 7.7799 8.452 9.37002 10.1564 8.8092 9.5702 10.6097 11.5001
1.6 8.6394 9.33903 10.3511 11.2809 9.7824 10.5746 11.7206 12.7734
2.0 9.3329 10.1399 11.2449 12.2285 10.5677 11.4814 12.7326 13.8464
2.4 9.9414 10.8734 12.0351 13.0241 11.2567 12.3120 13.6274 14.7472
2.8 10.5104 11.4499 12.6036 13.7116 11.9010 12.9647 14.2711 15.5257
0.0 7.4121 6.7083 5.3506 3.5883 11.2882 10.2165 8.1487 5.4648
0.4 8.4589 8.6028 8.9861 9.8499 12.8825 13.1017 13.6854 15.0009
0.8 10.1789 11.0111 12.1374 13.2182 15.5020 16.7694 18.4846 20.1307
1.2 11.7947 12.8136 14.2054 15.3975 17.9627 19.5145 21.6340 23.4497
1.6 13.0977 14.1584 15.6927 17.1023 19.9472 21.5625 23.8992 26.0460
2.0 14.1491 15.3725 17.0478 18.5389 21.5483 23.4116 25.9629 28.2339
2.4 15.0716 16.4845 18.2458 19.7451 22.9533 25.1051 27.7874 30.0708
2.8 15.9342 17.3585 19.1076 20.7874 24.2670 26.4362 29.0999 31.6582

Table 4.

FGM index and normalized temperature effects to the first natural frequency for various normalized voltages.

We examine in this section the effect of control voltages and thermal environment on the vibration characteristics of the piezoelectric laminated circular FG plate for various FGM indexes. To this end, Table 4 as well as the Figures 4.1~4.3 show the nonlinear relationships between the first natural frequencies ωia2I1/D2 , versus the normalized temperature in various normalized control voltages V . These free vibrations are assumed to be in the vicinity of the nonlinearly deformed static equilibrium position.

Also, the effect of normalized temperature on the first natural frequency of the FG circular plate for various FGM indexes under various normalized control voltage is investigated and tabulated in Table 4, while the voltage-dependent first natural frequency changes are plotted in Figures 7~9 for various temperatures. It is seen that the imposed voltage has a significant effect on the first natural frequency of the structure, and by increasing the imposed voltage, the first natural frequency increases in a nonlinear manner. For instance, for the FGM plate with n=10 by increasing the imposed voltage from 0 to 0.2 the first natural frequency increases about 4.84%, while by increasing the voltage from 0.2 to 0.3 the first natural frequency increases about 15.12%.

It is seen that the imposed thermal environment has a significant effect on the first natural frequency of the structure, and by increasing the imposed temperature, the first natural frequency decreases in a nonlinear manner. However, this thermal tendency of decreasing the natural frequency can be compensated and corrected with the control voltages V, as shown in Fig. 7. ~ 8.

Frequency variations of large amplitude oscillations with temperature and applied voltage changes are also investigated and plotted in Figure 6. There are two sets of curves in this figure. The first set has no control voltages, and the second set has control voltages. It is observed that the control voltages actually reduce the nonlinear frequency and amplitude ratios, i.e., P1 . Accordingly, the nonlinear frequency and amplitude ratios can be actively controlled and the nonlinear effects reduced, i.e., the ratio is approaching to 1- the linear case. Other studies of the second natural frequency also suggest that the second natural frequency exhibits very much similar phenomena of the first natural frequency.


Figure 7.

Effect of normalized voltage to first natural frequency for various FGM indexes (T*=0.2)


Figure 8.

Effect of normalized voltage to first natural frequency for various FGM indexes (T*=0.8)


Figure 9.

Effects of normalized temperature on the normalized first natural frequency for various normalized voltages (n=10,n=0.5)

8. Summary and Conclusions

A piezoelectric bounded circular FG plate subjected to temperature changes and control voltages is investigated based on classical plate theory, including the effects of the thermal gradient, piezothermoelasticity and von Karman type geometric nonlinearity. Nonlinear coupled open-loop plate equations in radial and transverse oscillations were derived first, and then the equations were simplified to an axisymmetric oscillation case. An exact solution technique based on series-type solutions is used to obtain piezothermoelastic solutions for nonlinear static deformations and natural frequencies of the FG circular plate subjected to temperature and voltage excitations. Voltage controlled natural frequencies of the first mode at various temperatures are studied. It is observed that a higher temperature induces higher deflections of the plate, and the deflection at each temperature is attenuated when the control voltage increases, but this effect is predominant in higher voltages. Also by increasing the FGM gradient index the normalized center deflection will increase in a nonlinear manner in various temperature fields. It is seen that the imposed thermal environment has a significant effect on the natural frequency of the structure, and by increasing the imposed temperature, the natural frequency decreases in a nonlinear manner for various FGM indexes; this effect is predominant at higher temperatures. Both the nonlinear static deflections and natural frequencies are influenced by the temperatures and control voltages geometric and the static control voltages can be used to compensate nonlinear deflections.


Figure 10.

Temperature/control effects on amplitude dependent first natural frequency (for metal plate) – amplitude ratio: w/hf, frequency ratio: (ω /ω1)

Appendix A:

T1=T2+(TUTL)κcd+κmκm(T2TL)MathType@MTEF@5@5@+=feaagCart1ev2aaatCvAUfeBSjuyZL2yd9gzLbvyNv2CaerbuLwBLnhiov2DGi1BTfMBaeXatLxBI9gBaerbd9wDYLwzYbItLDharqqtubsr4rNCHbGeaGqiVCI8FfYJH8YrFfeuY=Hhbbf9v8qqaqFr0xc9pk0xbba9q8WqFfeaY=biLkVcLq=JHqpepeea0=as0Fb9pgeaYRXxe9vr0=vr0=vqpWqaaeaabiGaciaacaqabeaadaqaaqaaaOqaaiaadsfadaWgaaWcbaGaaGymaaqabaGccqGH9aqpcaWGubWaaSbaaSqaaiaaikdaaeqaaOGaey4kaSIaaiikaiaadsfadaWgaaWcbaGaamyvaaqabaGccqGHsislcaWGubWaaSbaaSqaaiaadYeaaeqaaOGaaiykaiabgkHiTmaalaaabaGaeqOUdS2aaSbaaSqaaiaadogaaeqaaOGaamizaiabgUcaRiabeQ7aRnaaBaaaleaacaWGTbaabeaaaOqaaiabeQ7aRnaaBaaaleaacaWGTbaabeaaaaGccaGGOaGaamivamaaBaaaleaacaaIYaaabeaakiabgkHiTiaadsfadaWgaaWcbaGaamitaaqabaGccaGGPaaaaa@52B2@ ,    T2=TL+[κmchf(TUTL)]/[κphp+κcd+κmchf]MathType@MTEF@5@5@+=feaagCart1ev2aaatCvAUfeBSjuyZL2yd9gzLbvyNv2CaerbuLwBLnhiov2DGi1BTfMBaeXatLxBI9gBaerbd9wDYLwzYbItLDharqqtubsr4rNCHbGeaGqiVCI8FfYJH8YrFfeuY=Hhbbf9v8qqaqFr0xc9pk0xbba9q8WqFfeaY=biLkVcLq=JHqpepeea0=as0Fb9pgeaYRXxe9vr0=vr0=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@5BC7@

A0=T2 ,          A1=T1T2cMathType@MTEF@5@5@+=feaagCart1ev2aaatCvAUfeBSjuyZL2yd9gzLbvyNv2CaerbuLwBLnhiov2DGi1BTfMBaeXatLxBI9gBaerbd9wDYLwzYbItLDharqqtubsr4rNCHbGeaGqiVCI8FfYJH8YrFfeuY=Hhbbf9v8qqaqFr0xc9pk0xbba9q8WqFfeaY=biLkVcLq=JHqpepeea0=as0Fb9pgeaYRXxe9vr0=vr0=vqpWqaaeaabiGaciaacaqabeaadaqaaqaaaOqaaiaadgeadaWgaaWcbaGaaGymaaqabaGccqGH9aqpdaWcaaqaaiaadsfadaWgaaWcbaGaaGymaaqabaGccqGHsislcaWGubWaaSbaaSqaaiaaikdaaeqaaaGcbaGaam4yaaaaaaa@3E20@                               A2=T1T2cκcm(N+1)κmMathType@MTEF@5@5@+=feaagCart1ev2aaatCvAUfeBSjuyZL2yd9gzLbvyNv2CaerbuLwBLnhiov2DGi1BTfMBaeXatLxBI9gBaerbd9wDYLwzYbItLDharqqtubsr4rNCHbGeaGqiVCI8FfYJH8YrFfeuY=Hhbbf9v8qqaqFr0xc9pk0xbba9q8WqFfeaY=biLkVcLq=JHqpepeea0=as0Fb9pgeaYRXxe9vr0=vr0=vqpWqaaeaabiGaciaacaqabeaadaqaaqaaaOqaaiaadgeadaWgaaWcbaGaaGOmaaqabaGccqGH9aqpcqGHsisldaWcaaqaaiaadsfadaWgaaWcbaGaaGymaaqabaGccqGHsislcaWGubWaaSbaaSqaaiaaikdaaeqaaaGcbaGaam4yaaaadaWcaaqaaiabeQ7aRnaaBaaaleaacaWGJbGaamyBaaqabaaakeaacaGGOaGaamOtaiabgUcaRiaaigdacaGGPaGaeqOUdS2aaSbaaSqaaiaad2gaaeqaaaaaaaa@4979@

A3=T1T2cκcm2(2N+1)κm2MathType@MTEF@5@5@+=feaagCart1ev2aaatCvAUfeBSjuyZL2yd9gzLbvyNv2CaerbuLwBLnhiov2DGi1BTfMBaeXatLxBI9gBaerbd9wDYLwzYbItLDharqqtubsr4rNCHbGeaGqiVCI8FfYJH8YrFfeuY=Hhbbf9v8qqaqFr0xc9pk0xbba9q8WqFfeaY=biLkVcLq=JHqpepeea0=as0Fb9pgeaYRXxe9vr0=vr0=vqpWqaaeaabiGaciaacaqabeaadaqaaqaaaOqaaiaadgeadaWgaaWcbaGaaG4maaqabaGccqGH9aqpdaWcaaqaaiaadsfadaWgaaWcbaGaaGymaaqabaGccqGHsislcaWGubWaaSbaaSqaaiaaikdaaeqaaaGcbaGaam4yaaaadaWcaaqaaiabeQ7aRnaaDaaaleaacaWGJbGaamyBaaqaaiaaikdaaaaakeaacaGGOaGaaGOmaiaad6eacqGHRaWkcaaIXaGaaiykaiabeQ7aRnaaDaaaleaacaWGTbaabaGaaGOmaaaaaaaaaa@4AC3@                                 A4=T1T2cκcm3(3N+1)κm3MathType@MTEF@5@5@+=feaagCart1ev2aaatCvAUfeBSjuyZL2yd9gzLbvyNv2CaerbuLwBLnhiov2DGi1BTfMBaeXatLxBI9gBaerbd9wDYLwzYbItLDharqqtubsr4rNCHbGeaGqiVCI8FfYJH8YrFfeuY=Hhbbf9v8qqaqFr0xc9pk0xbba9q8WqFfeaY=biLkVcLq=JHqpepeea0=as0Fb9pgeaYRXxe9vr0=vr0=vqpWqaaeaabiGaciaacaqabeaadaqaaqaaaOqaaiaadgeadaWgaaWcbaGaaGinaaqabaGccqGH9aqpcqGHsisldaWcaaqaaiaadsfadaWgaaWcbaGaaGymaaqabaGccqGHsislcaWGubWaaSbaaSqaaiaaikdaaeqaaaGcbaGaam4yaaaadaWcaaqaaiabeQ7aRnaaDaaaleaacaWGJbGaamyBaaqaaiaaiodaaaaakeaacaGGOaGaaG4maiaad6eacqGHRaWkcaaIXaGaaiykaiabeQ7aRnaaDaaaleaacaWGTbaabaGaaG4maaaaaaaaaa@4BB4@

A5=T1T2cκcm4(4N+1)κm4MathType@MTEF@5@5@+=feaagCart1ev2aaatCvAUfeBSjuyZL2yd9gzLbvyNv2CaerbuLwBLnhiov2DGi1BTfMBaeXatLxBI9gBaerbd9wDYLwzYbItLDharqqtubsr4rNCHbGeaGqiVCI8FfYJH8YrFfeuY=Hhbbf9v8qqaqFr0xc9pk0xbba9q8WqFfeaY=biLkVcLq=JHqpepeea0=as0Fb9pgeaYRXxe9vr0=vr0=vqpWqaaeaabiGaciaacaqabeaadaqaaqaaaOqaaiaadgeadaWgaaWcbaGaaGynaaqabaGccqGH9aqpdaWcaaqaaiaadsfadaWgaaWcbaGaaGymaaqabaGccqGHsislcaWGubWaaSbaaSqaaiaaikdaaeqaaaGcbaGaam4yaaaadaWcaaqaaiabeQ7aRnaaDaaaleaacaWGJbGaamyBaaqaaiaaisdaaaaakeaacaGGOaGaaGinaiaad6eacqGHRaWkcaaIXaGaaiykaiabeQ7aRnaaDaaaleaacaWGTbaabaGaaGinaaaaaaaaaa@4ACB@                                A6=T1T2cκcm5(5N+1)κm5MathType@MTEF@5@5@+=feaagCart1ev2aaatCvAUfeBSjuyZL2yd9gzLbvyNv2CaerbuLwBLnhiov2DGi1BTfMBaeXatLxBI9gBaerbd9wDYLwzYbItLDharqqtubsr4rNCHbGeaGqiVCI8FfYJH8YrFfeuY=Hhbbf9v8qqaqFr0xc9pk0xbba9q8WqFfeaY=biLkVcLq=JHqpepeea0=as0Fb9pgeaYRXxe9vr0=vr0=vqpWqaaeaabiGaciaacaqabeaadaqaaqaaaOqaaiaadgeadaWgaaWcbaGaaGOnaaqabaGccqGH9aqpcqGHsisldaWcaaqaaiaadsfadaWgaaWcbaGaaGymaaqabaGccqGHsislcaWGubWaaSbaaSqaaiaaikdaaeqaaaGcbaGaam4yaaaadaWcaaqaaiabeQ7aRnaaDaaaleaacaWGJbGaamyBaaqaaiaaiwdaaaaakeaacaGGOaGaaGynaiaad6eacqGHRaWkcaaIXaGaaiykaiabeQ7aRnaaDaaaleaacaWGTbaabaGaaGynaaaaaaaaaa@4BBC@






The work described in this chapter was funded by a grant from International University of Imam Khomeini (Grant No. 385022-1391) The author is grateful for this financial support.


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