Document Type : Research Paper
Authors
^{1} Yasouj University
^{2} Isfahan University of Technology
^{3} Western Sydney University
Abstract
Keywords

Mechanics of Advanced Composite Structures 3 (2016) 1530 

Semnan University 
Mechanics of Advanced Composite Structures journal homepage: http://macs.journals.semnan.ac.ir 
Dynamic Stiffness Method for Free Vibration of Moderately Thick Functionally Graded Plates
M. Soltani^{a}, S. Hatami^{a,}*, M. Azhari^{b}, H.R. Ronagh^{c}
^{a}Department of Civil Engineering, Yasouj University, Yasouj, Iran
^{b}Department of Civil Engineering, Isfahan University of Technology, Isfahan, Iran
^{c}Institute for Infrastructure Engineering, Western Sydney University, Sydney, Australia
Paper INFO 

ABSTRACT 
Paper history: Received 20151127 Revision Received 20160429 Accepted 20160508 
In this study, a dynamic stiffness method for free vibration analysis of moderately thick functionally graded material plates is developed. The elasticity modulus and mass density of the plate are assumed to vary according to a powerlaw distribution in terms of the volume fractions of the constituents whereas Poisson’s ratio is constant. Due to the variation of the elastic properties through the thickness, the equations of motion governing the inplane and transverse deformations are initially coupled. Using a new reference plane instead of the midplane of the plate, the uncoupled differential equations of motions are derived. The outofplane equations of motion are solved by introducing the auxiliary and potential functions and using the separation of variables method. Using the method, the exact natural frequencies of the Functionally Graded Plates (FGPs) are obtained for different boundary conditions. The accuracy of the natural frequencies obtained from the present dynamic stiffness method is evaluated by comparing them with those obtained from the methods suggested by other researchers. 



Keywords: Dynamic stiffness method Free vibration Functionally graded material Firstorder shear deformation theory Exact solution



© 2016 Published by Semnan University Press. All rights reserved. 
Functionally Graded Materials (FGMs) are inhomogeneous composites made from different phases of material constituents (usually ceramic and metal). The FGMs were initially designed as thermal barriers for aerospace structures and fusion reactors. In the plate form the Functionally Graded Plates (FGPs) are widely used in structural applications and their behaviour has been studied by several investigators. Mizuguchi and Ohnabe [1] used Galerkin method to analyse a clamped rectangular plate subjected to an arbitrary symmetrical temperature and a load distribution about the midpoint of the plate, while the plate was prevented from inplane motions on the boundaries. Parveen and Reddy investigated the response of functionally graded ceramic metal plates using a finite element technique that accounted for the transverse shear strains, rotary inertia and moderately large rotations. The static and dynamic responses of the FGPs were investigated by varying the volume fraction of the ceramic and metallic constituents using a simple power law distribution [2]. In this regard, Yang and Shen dealt with the dynamic response of initially stressed functionally graded rectangular thin plates subjected to partially distribute impulsive lateral loads resting on an elastic foundation [3]. Then, they analysed free and forced vibration for initially stressed FGPs in thermal environment [4]. The thirdorder shear deformation plate theory was employed to solve the axisymmetric bending and buckling problems of functionally graded circular plates by Ma and Wang [5]. Kitipornchai et al. [6] investigated the nonlinear vibration of imperfect shear deformable laminated rectangular plates comprising a homogeneous substrate and two layers of FGMs. The thermal buckling of circular plates composed of FGMs was considered by Najafizadeh and Heydari [7]. A recently developed plate theory using the concept of shape function of the transverse coordinate parameter was extended to determine the stress distribution in an orthotropic FGP subjected to the cylindrical bending by Bian et al. [8]. Based on the threedimensional fundamental equations of anisotropic elasticity, a state equation with variable coefficients was derived in a unified matrix form by Chen et al. [9]. The free vibration analysis of arbitrary shaped thick plates by differential cubature method was analysed by Wu and Liu [10]. Abrate [11] investigated a functionally graded isotropic elastic rectangular plate with inplane material inhomogeneity. An closedform procedure was proposed by HosseiniHashemi et al. [12] for the free vibration analysis of moderately thick rectangular plates simply supported at the two opposite edges (i.e. Levytype rectangular plates). Their procedure was based on the Reissner–Mindlin plate theory. Then, HosseiniHashemi et al. [13] worked on free vibration analysis of moderately thick rectangular plates, which were composed of functionally graded materials and supported by either Winkler or Pasternik elastic foundations.
The finite element based simulation of the dynamic response is regularly employed by the FGM manufacturers in order to improve their products' comfort and reliability. For instance, the asymmetric free vibration characteristics and thermoelastic stability of functionally graded circular plates were investigated using finite element procedure by Parkash and Ganapathi [14]. Shariyat [15] analysed the vibration and dynamic buckling of functionally graded rectangular plates using a finite element formulation based on a higherorder shear deformation theory. Afsar and Go [16] focused on the finite element analysis of thermoelastic field in a thin circular FGM disk subjected to a thermal load and an inertia force due to the rotation of the disk. Moreover, the large amplitude flexural vibration characteristics of FGPs were investigated by Parkash et al. [17] using a shear flexible Finite Element Method (FEM). The FEM is a powerful tool to analyse a complex geometry of modelled structures which is essential for industrial applications. However, with highfrequency excitation, many structures of interest require very large computer models which reduce the computational efficiency when the finite element technique is used for discretization. Hence, for specific geometries, periodic or semiinfinite boundary conditions, the frequency domain methods such as dynamic stiffness matrix, strip element and spectral finite element were developed to overcome the problem.
Among the frequency domain methods, Dynamic Stiffness Method (DSM) is very suitable for solving dynamic problems. The method is often referred to as an exact method as it is based on exact shape functions obtained from the solution of the differential equations of motion. The DSM, which yields exact results for certain class of plate structures, is used to analyse free vibration frequencies of various structures. Leung and Fung [18] extended the DSM to a large amplitude free and forced vibration of frames. A general theory to develop the dynamic stiffness matrix of a structural element has been outlined by Banerjee [19]. A directDSM was presented for the vibration analysis of orthotropic plate structures by Bercin [20]. Bercin and Langley [21] extended the DSM to include inplane vibrations of the plate. The directDSM was extended to the vibration analysis of Mindlin plates by Bercin, then investigated the effects of shear distortion and rotary inertia on the flexural energy transmission of a representative stiffened plate structure [22]. Later, Bercin employs the DSM to calculate the free vibration of various simplysupported plate and sees that while for the directly coupled plate assemblies the inplane effects are negligible for loworder modes, for the stiffened plate assembly the effect of inplane motion equals a reduction in the free vibration frequencies [23]. Application of the DSM to turbulent boundary layer was presented by Birgersson et al. [24]. Hatami and Azhari [25] formulated the DSM for orthotropic plates moving on some rollers and an elastic foundation. Boscolo and Banerjee [26] developed the DSM for plates based on the firstorder shear deformation theory to carry out the exact free vibration analysis of the plate assemblies. In addition, the dynamic stiffness formulation for both inplane and bending free vibration based on the firstorder shear deformation theory for composite plates was presented by the same team [27]. They investigated the inplane free vibration behaviour of plates using the DSM. Some distinctive modes which were unnoticed in earlier investigations using the DSM were addressed by revisiting the problem and focusing on the special set of missing solutions [28]. Then, The DSM for composite plate elements based on the firstorder shear deformation theory was implemented in a program called DySAP that computed the exact natural frequencies and mode shapes of composite structures by them [29]. Based on a higher order shear deformation theory, Fazzolari et al. [30] developed an DSM in order to carry out the free vibration analysis of composite plate assemblies. To derive the governing differential equations of motion and natural boundary conditions, they implemented Hamilton’s principle. They used Wittrick–Williams algorithm [31] as a solution technique to compute the natural frequencies and mode shapes for a range of laminated composite plates and stepped panels. The dynamic stiffness matrix for isotropic rectangular plate with arbitrary boundary conditions undergoing inplane free vibration was developed by NefovskaDanilovic and Petronijevic [32]. An exact method for free vibration analysis of plates with arbitrary boundary conditions is presented by Liu and Banerjee [33] which the formulation satisfies the governing differential equation exactly and any arbitrary boundary conditions are satisfied in a series sense.
In this study, the free vibration of moderately thick FGPs is studied by DSM using Firstorder Shear Deformation Theory (FSDT). Based on the knowledge of the authors, there are no studies available in the literature (including the articles reviewed in this section) developing dynamic stiffness matrices for FGPs using FSDT.
The basic characteristic of the “moderately thick” plate theories is that the rotations of plate cross sections cannot be merely expressed in terms of the transverse displacement. Thus, there exist three basic quantities at the plate edge including outofplane displacement and rotations. For solving the equations of motion by DSM, the potential functions presented by Bercin [22] are used to convert the three outofplane equations in to three independent equations. Solving these independent equations and composing the results of each equation, the dynamic stiffness matrix of a plate element is derived which allows the calculation of the free vibration frequencies of the moderately thick plate. Several cases dealing with free vibration problems are presented in order to illustrate the accuracy of results obtained by the suggested method.
In the laminated composite plates, the stress concentrations generate along the interfaces, more specifically when high temperatures are involved. This can lead to delamination, matrix cracking and other damage mechanisms which result from the abrupt change of the mechanical properties at the interface of the layers. One way to overcome this problem is to use Functionally Graded Materials (FGMs) within which the material properties have continuous variation from one surface to the other.
The FGMs are composite materials, the mechanical properties of which vary continuously in the thickness direction. However, a detailed description of actual graded microstructure is usually not available, perhaps except for the volume fraction distribution. The FGMs are often manufactured by two phases of materials with different properties. Since the volume fraction of each phase gradually varies in the graded direction, the effective properties of the FGMs change along this direction, as shown in Fig. 1. In this study, a continuous variation is assumed for the volume fraction of ceramic or metal, and the metal volume fraction can be represented by the following function of the transverse coordinate z.
(1) 

Figure 1. The schematic illustration of a twophase FGM 
Figure 2.The variation of volume fraction through the dimensionless thickness of the plate

Where h is the thickness of the structure, and P is a volume fraction exponent that denotes the material variation profile through the FGP thickness. As the variation of P is presented in Fig. 2, changing the value of P generates an infinite number of composition distributions.
(2) 
Where the subscripts m and c refer to the metallic and ceramic constituents, respectively, and the material’s property T, can be the modulus of the elasticity , the density , or the Poisson’s ratio .
According to the firstorder shear deformation theory, the displacements of the plate are represented as the following [34]:


(3) 


Where u and v are the inplane displacements and w, and are the outof plane displacements and rotations about y and x axes, respectively. The zero index identifies the midplane displacement along the x, y and z axes (Fig. 3).
The strains associated with the displacement field in Eq. (3) are given by the following equations:




(4) 






Note that the inplane strains are linear through the plate thickness, while the transverse shear strains are constant. The strains in Eq. (4) can be expressed in the vector form as the following:
(5.a) 

(5.b) 
The stresses resultant is related to the strains by the following expressions:
(6) 
Figure 3. A rectangular moderately thick plate, a) coordinate system of the plate, b) deformation of the plate section, c) inplane and outofplane forces on an infinitesimal element of the plate 
Where Q_{ii} is referred to as the reduced stiffness component. For an isotropic FGM plate they are obtained as what follow:
(7) 
Where and G are Poisson’s ratio and shear modules, respectively. The forces and moment resultants are defined by Eq. 8 as follows:
(8) 
Where N, M and Q are the vectors of inplane forces, moments and transverse shear forces, respectively as follows:
(9) 
And A_{ii }(i,j=4,5), are the shear stiffness resultants defined as the following:
(10) 
For isotropic materials, there is no coupling between the shear deformations in two directions, i.e., A_{45}=0 and A_{44}=A_{55}. Therefore, it is sufficient to identify only one of the components A_{44} or A_{55}. The shear correction factor k_{s}^{2}, is assumed to be [34]. The components of extensional (A), coupling (B) and bending (D) stiffness matrices in Eq. 9 are defined as the following:
(11) 
Using the Hamilton's principle [34], and eliminating first moment of inertia, the equations of motion in terms of forces and moment resultants are governed by the following relations:
(12.a) 

(12.b) 

(12.c) 

(12.d) 

(12.e) 
In which
(13) 
Where I_{0} and I_{2} are the mass of the plate per unit area and its mass moment of inertia, respectively. The density, , can potentially vary through the thickness.
Substituting Eqs. (5) and (8) to Eqs. (12a12e), the equations of motion for a rectangular moderately thick FGM plate, based on the midplane displacements are obtained as what follow:
(14.a) 

(14.b) 

(14.c) 

(14.d) 

(14.e) 
Even when inplane inertias are ignored, these equations of motion (Eqs. 14) show that inplane and outofplane are coupled. Nevertheless, Abrate [35] shows that the equations of motion can be uncoupled if a different reference surface rather than the midplane of plate is selected. He uses a new reference plane (z'=0) with a distance of from midplane (z=0), as shown in Fig. 4. The distance is calculated as the elements of the coupling matrix are zero according to the new reference surface.
Figure 4. The new coordinate system (z') which B'_{ii}=0 
To obtain the stiffness properties of the plate according to the new reference plane (A'_{ii},B'_{ii},D'_{ii}), as proposed by Abrate [35], z is replaced with in Eq. (11); then, we have the following:
(15) 

(16) 
Eqs. (15) and (16) yield what follows:
(17) 
Also
(18) 
Using Eqs. (15), (17) and (18) we can obtain the following:
(19) 

or 
(20) 
Where z'_{t} and z'_{b} are the values of z' on the top and bottom surfaces of the plate, respectively. A_{ij} and A'_{ij} are equal, because both of A_{ij} and A'_{ij} are the area under Q_{ij} function when z or z' varies along the plate thickness.
Setting B'_{ij} in Eq. (17) to zero, the distance of the midplane to the new plane is =B_{ij}/ A_{ij}. is not dependent on ij subscript in the case of constant Poisson's ratio. In this case, all elements of B' become zero only with a single . Even though the Poisson's ratio varies along the plate thickness, by considering ; , , and also become small amounts.
So, substituting and into Eq. (19), can be rewritten as follows:
(21) 
Using Eqs. (11) and (21), the following relations are obtained for the elements of :
(22.a) 

(22.b) 
In which D^{'}_{0} is just introduced for simplicity of the notations.
Using flexural rigidity around new reference plane from Eqs. (22) and setting B'_{ij} to zero, Eq. (8) gives us the bending moments around the new reference plane. Replacing those bending moments into Eqs. (12 c, d, e), out of plane free vibration differential equations for a moderately thick FGM are obtained as follows:
(23.a) 

(23.b) 

(23.c) 
In these relations, and .
The basic characteristic of “moderately thick” plate theories is that the rotations and (Fig. 5) of the plate cross sections about the inplane coordinate axes x and y cannot be merely expressed in terms of the normal deflection w. Thus, there exist three basic quantities , and w (transverse displacement) at the plate edge rather than just w as in the thin plate theory. So, for solving the equations of motion presented in Eqs. (23.a, b, c) by DSM, there is a need to uncouple these equations. Introducing some potential functions, Mindlin [36] developed a method for uncoupling such equations. Using the Mindlin method and the formulation presented by Bercin [22], Eqs. (23) can be written as the following:
(24.a) 

(24.b) 

(24.c) 
Where W_{1}, W_{2} and H are potential functions. , and represent the wave numbers, which are given by the following equations:
(25) 

(26) 
Where , , and is the classical plate flexural wave number defined as what follows:
(27) 
The rotations and , and the normal deflection w are calculated from the potential functions as the following:
(28) 
In which
(29) 




Figure 5. Nodal displacement and forces acting on the edges of a thick plate element

The DSM is similar to the FEM in that the structure is discretised into the number of elements or substructures at the natural structural boundaries. Since the mode shape of a member varies with the vibration frequency, the FEM requires a subdivision of a structure into many finite elements for accurate solution of the free vibration equations. Alternatively, using the DSM in which the shape functions are frequency dependent, the exact solution is obtained employing only a few elements.
Fig. 3(a) shows a FGM rectangular plate with simple boundary conditions along the x direction. For such a plate, the general form of the three potential functions of Eqs. (24) may be expressed as the following[22]:
(30.a) 

(30.b) 

(30.c) 
, and (m=1,2) are coefficients of the equation solution, is the wave number of the n th mode in y direction (n=1,2,…), and is the frequency of vibration. Substituting Eq. (30) into Eq. (24), the problem then essentially becomes onedimensional where , and are given by the following equations:
(31) 
Substituting Eqs. (30) into Eqs. (28) implies that the form of the potential functions satisfies the simple boundary conditions along the x direction i.e. the displacements since vibration varies sinusoidally in the direction. Also, using Eqs. (5) and (8), it is evident the moments and transverse shear forces (M_{xy}, M_{x}, Q_{x}), which are dependent on the displacements, vary sinusoidally in this direction. Satisfying the boundary conditions on two sides of the plate edges parallel to yaxis, the dynamic stiffness matrix of the element can be obtained. As shown in Fig. 5, these boundary conditions are what follow:
(32) 
at

(33) 
at 
So, the edge displacements and forces vectors can be defined as the following:
(34) 

(35) 
Using expressions (8) and (30)(35), for the case of isotropic FGPs, the edge displacements and forces vectors may be written as the following:
(36) 

(37) 
where
(38) 

(39) 
Combining Eqs. (38) and (39) by eliminating , we may have what follows:
(40) 
Where
(41) 
Here, [S_{n}] is the dynamic stiffness matrix of a component of the plate. Assembling the stiffness matrices of all components of a FGM plate and imposing the boundary conditions, the overall stiffness matrix of the FGM plate is obtained. The exact natural frequencies, , for lateral vibration of the plate are extracted by the following equation:
(42) 
5.1 General
The following nondimensional variables are used in the results:
(43) 
Where denotes dimensionless natural frequency, and and are the aspect ratios of the plate.
In the present method, the parameter n determines the number of halfwavelengths along ydirection. The symbol CSFG, for example, identifies a plate with edges clamped, simply supported, free and guided; start counting counter clockwise from the left edge of the plate.
Table 1 summarizes the mechanical properties of metal and ceramics used in the FGP. According to the literature reviewed in the current study, most researchers use the powerlaw function as stated in Eqs. (1) and (2) to describe the material properties and volume fraction of the plate. Therefore, in the current study, FGPs with powerlaw function is considered.
5.2 Validity
To demonstrate the reliability of the present DSM in the analysis of FGPs, the natural frequencies of isotropic SSSS plates are compared with those obtained by Reddy [34] using the Mindlin method. The natural frequencies for different aspect ratios , are shown in Table 2. The shear correction factor is equal to . The DSM results are obtained from the first mode n = 1 and show a good agreement with the results of Ref. [1].
The natural frequency parameters of the SSSS square FGPs for different values of the thickness to length ratios including 0.05, 0.1 and 0.2 are presented in Table 3. The fundamental frequency and the lowest second frequency parameters are given when = 0.05, 0.1 and 0.2 respectively. The values of power law index P are selected as 0, 0.5, 1, 4, 10 and . The plates are made of a mixture of aluminium (Al) and alumina (Al_{2}O_{3}). It should be noted that the solutions reported by HosseiniHashemi et al. [12] present an exact closedform procedure for the free vibration analysis of moderately thick rectangular plates based on the Reissner–Mindlin plate theory. As observed in Table 3, the present DSM results are almost the same as those obtained by the FSDT exact closedform procedure. Zhao et al. [37] employed the FSDT using the elementfree kpRitz method. For simplicity in comparison, we use nondimensional frequencies . As observed, when = 0.05, the present exact results are in excellent agreement with those obtained by the numerical method based on the FSDT [37]. It is also seen that the present solution has a good agreement with that obtained by the HSDT [38] for the thicker FG square plates ( =0.1, 0.2), particularly at the higher modes of vibration.
Table 1. The material properties of the FGPs [12] 

Material 
Properties 

Metallic 



Steel (St) 
200 
0.3 
7800 
Aluminum (Al) 
70 
0.3 
2702 
Ceramic 



Alumina (Al_{2}O_{3}) 
380 
0.3 
3800 
Zirconia (ZrO_{2}) 
200 
0.3 
5700 
Table 2. The free vibration of isotropic simply support plate for different
Ref. [1] 
Present 

0.20 
209.28 
209.27 
0.10 
56.943 
56.943 
0.05 
14.587 
14.588 
0.04 
9.4032 
9.4038 
0.02 
2.3508 
2.3514 
0.01 
0.5880 
0.5828 
Table 3. The comparison of the natural frequency parameter for SSSS, Al/Al_{2}O_{3} square plates 
Mode 
Theory 
Powerlaw index (P) 

0 
0.5 
1 
4 
10 

0.05 
1 
Present 
0.0148 
0.0125 
0.0113 
0.0098 
0.0094 
0.0075 
FSDT [12] 
0.0148 
0.0125 
0.0113 
0.0098 
0.0094 
0.0075 

FSDT [37] 
0.0146 
0.0124 
0.0112 
0.0097 
0.0093 


0.1 
1 
Present 
0.0577 
0.0490 
0.0442 
0.0383 
0.0366 
0.0294 
FSDT [12] 
0.0577 
0.0490 
0.0442 
0.0381 
0.0364 
0.0293 

FSDT [37] 
0.0568 
0.0482 
0.0435 
0.0376 
0.0363 
 

HSDT [38] 
0.0577 
0.0492 
0.0443 
0.0381 
0.0364 
0.0393 

2 
present 
0.1376 
0.1173 
0.1061 
0.0915 
0.0869 
0.0701 

FSDT [12] 
0.1376 
0.1174 
0.1059 
0.0903 
0.0856 
0.0701 

FSDT [37] 
0.1354 
0.1154 
0.1042 
0.0850 
 

HSDT [38] 
0.1381 
0.1180 
0.1063 
0.0904 
0.0859 
0.0701 

0.2 
1 
present 
0.2112 
0.1805 
0.1634 
0.1405 
0.1329 
0.1076 
FSDT [12] 
0.2112 
0.1805 
0.1631 
0.1397 
0.1324 
0.1076 

FSDT [37] 
0.2055 
0.1757 
0.1620 
0.1371 
0.1304 
 

HSDT [38] 
0.2121 
0.1819 
0.1640 
0.1383 
0.1306 
0.1077 

2 
present 
0.4618 
0.3981 
0.3616 
0.3078 
0.2874 
0.2351 

FSDT [12] 
0.4618 
0.3978 
0.3604 
0.3049 
0.2856 
0.2352 

HSDT [38] 
0.4658 
0.4040 
0.3644 
0.3000 
0.2790 
0.2365 
5.3 Numerical Results and Discussion
Some cases of FGPs with different boundary conditions are considered in this study. The material properties of FGPs are introduced in Table 1.
The stiffness matrix components are transcendental functions of the eigenvalues. The wellknown Wittrick–Williams algorithm [31] may be used to solve this nonstandard eigenvalue problem. Here, a trialanderror procedure is used to derive the natural frequencies from the eigen function of the plate presented in Eq. (42). Fig. 6 shows the variation of determinant of S_{n}( ) in logarithmic scale with respect to the free vibration frequency . The natural frequency of the simplysupported square FGPs for the thickness to length ratio of 0.2 and the power law index of 4.0 are also presented in this figure. The values of the natural frequencies are shown as where is the wave number in the y–direction for the ith mode. As shown in Fig. 6, the first and the second natural frequencies of this case are derived from one half wave in the y–direction and their values are =7200 radians/sec ( =0.1405) and =15400 radians/sec respectively as listed in Table 3. Also, the third frequency is associated with two half waves in the y–direction (n=2).
To demonstrate the effect of volume fraction on the free vibration, the first six natural frequencies of the FGP with SSSS boundary condition are presented in Fig. 7. The first and second natural frequencies are compared with those obtained by an exact analytical approach [12]. The method developed in the present study and the one presented in Ref. [12] are both exact solutions of the differential equations of motion for the moderately thick FGP, thus the results are the same. It can be implied from Fig. 7 that increasing powerlaw index, P, results in decreasing the frequency of all modes. In simplysupported boundary condition (SSSS), the second and the third frequency parameters of a FG square plate are equal for every powerlaw index. Similarly, the frequencies of fifth and sixth modes of vibration are the same (as shown in Fig. 7). To explain the reason of this matter, mode shapes of the first six modes of vibration are presented in Fig. 8.
Figure 6. The overall stiffness matrix determinant with respect to the frequency parameter

As it can be seen in Fig. 8b, the second mode corresponds to n = 1, which means there is one half sinusoidal wave along ydirection. In this mode, the plate experiences two half sinusoidal waves along xdirection. On the other hand, the third mode of Fig. 8c happened corresponds to n = 2 which means there are two half sinusoidal waves along ydirection. In this mode, the plate experiences one half sinusoidal wave along xdirection. As the vibration is relevant to a SSSS square plate, there is symmetry with respect to x and y axes. Thus, the second and third modes create similar mode shapes, and they have the same frequencies. A similar symmetry exists between fifth and sixth modes (see Fig. 8e and 8f).
The first three dimensionless frequencies (eigenvalues) of the FGP with SimplyClamped (SSSC), SimplySimply (SSSS), ClampedGuided (SCSG) and SimplyGuided (SSSG) boundary conditions are given in Table 4 for different values of the power law index , as 0, 0.5, 1, 10 and . A squared shape plate is considered with three different thickness to length ratios including 0.05 (corresponding to thin plates), 0.1 and 0.2 (corresponding to moderately thick plates).
It is found that when the powerlaw index increases, the frequencies decrease for all boundary conditions. As it is expected, among these four boundary conditions, the maximum and minimum natural frequencies are according to SSSC and SSSG, respectively. The frequencies in this table are mainly presented to show the ability of the formulation to solve different FG materials and boundary conditions. These results can be used as a benchmark to evaluate the precision of other analytical or numerical methods.
Figure 7. The dimensionless frequencies for the simplysupported (SSSS) moderately thick FGP (β =0.2)
25 
Figure 8. The first Six mode shapes for free vibration of the simply supported (SSSS) moderately thick FGP
In this investigation, a dynamic stiffness method for free vibration analysis of moderately thick functionally graded material plates was developed. Due to the variation of the elastic properties through the thickness, the equations of motion governing the inplane and transverse deformations were coupled. However, this coupling was due to the arbitrary selection of the midplane as the reference plane in the development of plate theories. But we can always find a reference plane in which the outofplane displacements are uncoupled from the inplane displacements, so that the FG plates behave as homogeneous plates. Then, for solving the equations of motion by the DSM, the potential functions were used to convert the three extant outofplane equations to three independent equations. Solving these independent equations and composing the results of each equation, the exact stiffness matrix of a plate element was derived and the free vibration frequencies of a moderately thick plate were obtained. Using the method, the results are obtained for different boundary conditions. This study offers a new solution and insight into the effect of various parameters on the free vibration analysis of moderately thick functionally graded material plates.
Table 4. The first three dimensionless frequencies of the FGPs for different and P values and in four boundary conditions 
Boundary Conditions 
P 






0 
0.0577 
0.1376 
0.1376 
0.2112 
0.4618 
0.4618 


(n=1) 
(n=1) 
(n=2) 
(n=1) 
(n=1) 
(n=2) 

0.5 
0.0490 
0.1173 
0.1173 
0.1805 
0.3981 
0.3981 


(n=1) 
(n=1) 
(n=2) 
(n=1) 
(n=1) 
(n=2) 
SSSS 
1.0 
0.0442 
0.1061 
0.1061 
0.1634 
0.3616 
0.3616 


(n=1) 
(n=1) 
(n=2) 
(n=1) 
(n=1) 
(n=2) 

10 
0.0366 
0.0869 
0.0869 
0.1329 
0.2874 
0.2874 


(n=1) 
(n=1) 
(n=2) 
(n=1) 
(n=1) 
(n=2) 

0.0294 
0.0701 
0.0701 
0.1076 
0.2351 
0.2351 



(n=1) 
(n=1) 
(n=2) 
(n=1) 
(n=1) 
(n=2) 

0 
0.06762 
0.14222 
0.15752 
0.23638 
0.46858 
0.49758 


(n=1) 
(n=2) 
(n=1) 
(n=1) 
(n=2) 
(n=1) 

0.5 
0.05757 
0.12142 
0.13472 
0.20318 
0.40457 
0.43163 


(n=1) 
(n=2) 
(n=1) 
(n=1) 
(n=2) 
(n=1) 
SSSC 
1 
0.05202 
0.10982 
0.12197 
0.18436 
0.36781 
0.39331 


(n=1) 
(n=2) 
(n=1) 
(n=1) 
(n=2) 
(n=1) 

10 
0.04282 
0.08972 
0.09902 
0.14760 
0.29094 
0.30711 


(n=1) 
(n=2) 
(n=1) 
(n=1) 
(n=2) 
(n=1) 

0.03452 
0.07252 
0.08021 
0.12035 
0.23861 
0.25335 



(n=1) 
(n=2) 
(n=1) 
(n=1) 
(n=2) 
(n=1) 

0 
0.04291 
0.11002 
0.12761 
0.16505 
0.36755 
0.44565 


(n=1) 
(n=1) 
(n=2) 
(n=1) 
(n=1) 
(n=2) 

0.5 
0.03642 
0.09324 
0.10852 
0.14045 
0.31965 
0.38005 


(n=1) 
(n=1) 
(n=2) 
(n=1) 
(n=1) 
(n=2) 
SGSC 
1 
0.03273 
0.08432 
0.09802 
0.12705 
0.28811 
0.34395 


(n=1) 
(n=1) 
(n=2) 
(n=1) 
(n=1) 
(n=2) 

10 
0.02742 
0.06982 
0.08091 
0.10505 
0.22849 
0.27505 


(n=1) 
(n=1) 
(n=2) 
(n=1) 
(n=1) 
(n=2) 

0.02184 
0.05570 
0.06502 
0.08405 
0.18725 
0.22495 



(n=1) 
(n=1) 
(n=2) 
(n=1) 
(n=1) 
(n=2) 

0 
0.03902 
0.09392 
0.12552 
0.15311 
0.33465 
0.43661 


(n=1) 
(n=1) 
(n=2) 
(n=1) 
(n=1) 
(n=2) 

0.5 
0.03302 
0.08002 
0.10673 
0.13005 
0.28695 
0.37517 


(n=1) 
(n=1) 
(n=2) 
(n=1) 
(n=1) 
(n=2) 
SSSG 
1 
0.03002 
0.07202 
0.09632 
0.11731 
0.26005 
0.34045 


(n=1) 
(n=1) 
(n=2) 
(n=1) 
(n=1) 
(n=2) 

10 
0.02492 
0.06002 
0.08002 
0.09735 
0.20995 
0.27285 


(n=1) 
(n=1) 
(n=2) 
(n=1) 
(n=1) 
(n=2) 

0.01985 
0.04782 
0.06392 
0.08005 
0.17045 
0.22245 



(n=1) 
(n=1) 
(n=2) 
(n=1) 
(n=1) 
(n=2) 

the thickness of the structure 

volume fraction exponent 

volume fraction 

the material’s property 

the modulus of elasticity 

u and v 
inplane displacements 

the outofplane displacement 

the reduced stiffness components 

the shear modules 

N, M, Q 
the vectors of inplane forces 

the shear stiffness resultants 

the shear correction factor 

and 
potential functions 

n 
mode in y direction 

the dynamic stiffness matrix of a component of the plate 

the frequency of vibration 



, , 
the wave numbers 

dimensionless natural frequency 

and 
the aspect ratios of the plate 

the density 

the Poisson’s ratio 

and 
the outofplane displacements 

inplane strains 

the transverse shear strains 
Appendix
Some coefficients referred to in this study are given as follows:
Where . For simplicity, is assumed to be constant.
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