Research Article
InPlane Free Vibration of Functionally Graded Rectangular Plates with Elastic Restraint
Changjian Ji^{1}, Linquan Yao^{1}, Jiping Shen*^{1}, Tonghao Hu^{1} and Cheng Li^{1}
^{1}School of Rail Transportation, Soochow University, China
Jiping Shen, School of Rail Transportation, Soochow University, Suzhou 215131, China.
Received Date: May 08, 2019; Published Date: May 17, 2019
Abstract
The inplane free vibration of a rectangular plate made of functional graded materials (FGM) is studied based on the twodimensional linear elasticity theory. The material parameters of FGM rectangular plates are assumed to vary along with the length and width directions according to an exponential law. The governing equation of motion for the FGM rectangular plate is derived using the D’Alembert principle. Subsequently, the equation of motion is solved by the Differential Quadrature Method (DQM), and the natural frequencies for inplane free vibration of FGM rectangular plate are obtained accordingly. The effects of gradient index, lengthwidth ratio and stiffness of elastic boundary on the natural frequency of FGM rectangular plates are discussed, and the modes for inplane free vibration are provided.
Keywords:Functionally graded rectangular plates; Elastic restraint; Inplane free vibration; Differential Quadrature Method
Introduction
The vibration and stability of engineering structures play significant roles in structural mechanics. The related research on free vibration, forced vibration, dynamical buckling and stability responses is one of the most important subjects in engineering. The onedimensional structures, e.g. strings, rods, beams, have been studied sufficiently, especially in recent years [15]. The research results provide important reference for the analysis and design of onedimensional engineering structures including the traveling strings, beams, viscoelastic belts and so on [15]. On the other hand, for twodimensional plate structures, the free vibrations include the outofplane vibration (or called transverse vibration) and inplane vibration, in which the outofplane vibration plays a dominant role in energy conversion due to its good coupling properties between frequency band and sound field. Many investigators have carried out a lot of research work on the outofplane vibration of plates using different methods. However, more and more experiments have proved that besides the outofplane vibration, the inplane vibration acting as a high frequency component also affects the energy conversion [6]. Therefore, it is also indispensable to study the inplane vibration of plate structures, and it has attracted much research attention [728].
For examples, Kobayashi et al. [7] researched the inplane vibration behavior of rectangular plate by Ritz method. The inplane vibration frequencies of rectangular plate under different boundary conditions were solved. Moreover, four modal forms were defined according to the order of power series, and the modal characteristics of rectangular plate under different support conditions were analyzed. Gutierrez and Laura [8] studied the inplane vibration characteristic of rectangular plate with normal elastic constraints by Ritz method. It was assumed that the displacement of inplane vibration is the superposition of triangular function modes, and the effects of elastic constraints stiffness on the frequency were discussed. Based on thin plate theory and hysteretic damping model, Farag and Pan [9] investigated the resonant characteristics for the inplane vibration behavior of finite flat plates. The mode shapes of the inplane vibration were depicted for frequencies below and above the first resonance frequency. On this basis, Farag and Pan [10] analyzed the propagation characteristics of inplane waves, considering the longitudinal and shear waves. The frequency bands for attenuation and propagation of the waves are identified. Based on Kantorovich Krylov variational method, Wang and Wereley [11] analyzed the inplane free vibration characteristics and modal characteristics of rectangular plates under three boundary conditions. The modal response functions of rectangular plates under inplane excitation are given, and the modal characteristics of rectangular plates are discussed. Xing and Liu [18] used the direct separation of variables method to obtain the exact solutions for the free inplane vibrations of rectangular plates under all classical boundary conditions. The frequency and modal characteristics of rectangular plates are discussed, and the problems of frequency loss and repetition are solved. A Ritz method using a set of trigonometric functions is developed to obtain accurate inplane modal properties of rectangular plates with arbitrary nonuniform elastic edge restraints [21].
All the above papers are concerned with inplane vibration of rectangular plates with uniform materials. However, there are also many studies on inplane vibration of rectangular plates with inhomogeneous materials [2228]. Gorman [22] obtained the accurate solutions analytical type solutions are obtained for the free inplane vibration frequencies and mode shapes of fully clamped orthotropic rectangular plates by the method of superposition. Based on Reddy’s thirdorder shear deformation theory, Hosseini Hashemi et al. [23] solved the exact analytical approach for inplane and outofplane free vibration analysis of thick laminated transversely isotropic plates. The inplane and outofplane deformed mode shapes are plotted for different boundary conditions. Shi et al. [25] studied the free inplane vibration analysis of orthotropic rectangular plates with nonuniform boundary conditions and internal line supports using a modified Fourier solution. Rostami and Ranji [26] provided the results for inplane vibrations of rotating orthotropic cantilever plates. The equations of motion are derived by Hamilton’s principle and solved by the Extended Kantorovich Method (EKM). The effects of the dimensionless parameters on the natural frequency were investigated, and the resonant frequencies and tune speeds were also discussed. Papkov [27] obtained a new method for inplane free vibration analysis of rectangular orthotropic plate under the completely clamped or completely free boundary condition. The boundary value problem was assumed to essentially reduce to infinite systems of linear algebraic equations. The accuracy and computational efficiency of the method were demonstrated by examples.
In recent years, a new type of FGM composite material has emerged. FGM has excellent physical and chemical properties, and it has been extensively studied. Therefore, this paper presents the inplane free vibration behaviors of FGM rectangular plates with elastic restraints. It is assumed that the material physical parameters vary along with two directions according to the exponential law. The equation of motion is solved by DQM, and the natural frequencies are thus obtained. Through numerical examples, the effects of gradient index, lengthwidth ratio, and stiffness of elastic boundary on inplane free vibration frequency and modes are discussed in detail.
Mechanical Model and Governing Equations
For an inplane functionally graded rectangular plates as shown in Figure 1, the length and width of thin plates are a and b respectively, and the thickness is d (much less than a and b). Springs are evenly distributed along the normal and tangent directions on the boundary of rectangular plates, and the stiffness of springs are n K and Kτ respectively. The subscript n represents the normal direction, and the subscript τ represents the tangent direction.
The material parameters of functionally graded plates are assumed to vary along the length and width direction according to exponential law, and the material parameters can be described by
where P(x, y) represents the modulus of elasticity E and density ρ . 0 P stands for the material parameters at (0, 0), and 1 P stands for the material parameters at (a, b). α and β are the gradient index.
According to the twodimensional linear elasticity theory, the geometric equations of rectangular plate can be expressed as
Where ( , , ) x u = u x y t and ( , , ) y u = v x y t stand for the transverse and longitudinal displacement component of FGM rectangular plate, respectively. xx ε and yy ε represent the normal strain in x and y directions, respectively. xy γ is the shear strain.
The constitutive equation of functionally graded rectangular plates is
where x σ and y σ represent the normal stress in x and y directions, respectively. xy τ is the shear stress. ij c represents the elastic modulus coefficients, and these coefficients are functions of position (x, y).
According to D’Alembert principle, the equations of motion for inplane vibration of rectangular plates can be obtained as
where u and v represent the second derivative of displacement component u and v for time, ρ is density of rectangular plates.
For rectangular plates with quadrilateral elastic constraints, the boundary conditions are as follows
where nx0 k and x0 kτ represent the stiffness coefficients at x=0, ny0 k and y0 kτ represent the stiffness coefficients at y=0, nx1 k and x1 kτ represent the stiffness coefficients at x=a, ny1 k and y1 kτ represent the stiffness coefficients at y=b.
By introducing the following nondimensional terms:
in which 0 330 k = c b , i, j =1,3,5 . 330 c and 0 ρ represent the elastic modulus and density of materials at (0,0), respectively. Ω stands for the nondimensional natural frequency.
Substituting Eq. (6) into Eq. (4), the nondimensional equations of motion can be established as
Since the mode of FGM plate is harmonic to time, the displacement can be assumed to be as
Substituting Eq. (8) into Eq. (7), the nondimensional characteristic equations of inplane free vibration of functionally graded rectangular plates are obtained as
Substituting Eqs. (6) and (8) into Eq. (5), the boundary conditions expressed by mode shapes can be expressed as
When n K and Kτ take different values, different boundary conditions can be obtained as
Clamped boundary(C): nx0 x0 K Kτ = = ∞ , Free boundary(F): 0 0 0 nx x K Kτ = = ,
Special boundary 1(S1):K_{nx0} =0, K_{τx0} = ∞ ,
Special boundary 2(S2):K_{nx0} =∞, K_{τx0} = 0 ,
As can be seen, equation (9) is a second order coupled differential equation with variable coefficients. It is very difficult to solve it directly, so the differential quadrature method (DQM) is used to solve it.
Method of Solution
In this section, the DQM is used to solve the equations. In DQM, we can express the derivative of a function at a given point as a weighted linear summation of the values of the function at all the points in the domain [29]. Therefore, the differential equation can be transformed into a set of algebraic equations expressed by the value of the function at the node. When using this method, there are two questions to be determined:
Selection of node
A well accepted kind of sampling points in the DQM is the socalled GaussLobattoChebyshev points [21]:
where Nξ and Nη represent the number of nodes selected in the direction of ξ and η , respectively.
Determination of weight coefficient
By introducing Lagrange interpolation function, the weight coefficient of first derivative for ξ is expressed as [30]
According to formula (12), the weight coefficients of second derivative can be obtained as
The weight coefficient for η is similar to that for ξ , and the specific expression is omitted.
Using DQM to discretize the equations of motion (9), the discretized equations of motion are obtained as follows
Using DQM to discretize the boundary conditions (10), the discretized boundary conditions are obtained as follows
Combining differential equation (14) and boundary condition (15), the matrix form of motion equations for free vibration of rectangular plate with elastically constrained boundary is expressed as
where bb K and bd K represent the stiffness matrix of motion equations, db K and dd K stand for the stiffness matrix of boundary conditions. b q and d q represent the Column vectors of nodal displacements at the interior and boundary, respectively, expressed as
By eliminating the d q in formula (16), the eigenvalue equation of free vibration for a functionally graded rectangular plate can be obtained as
Numerical Examples and Analysis
Frequency characteristics for inplane free vibration of FGM rectangular plate
In this section, the frequency characteristics for inplane free vibration of FGM rectangular plate are studied. In the examples, it is assumed that the material at coordinate (0, 0) is pure metal Ti6Al4V, and the material at coordinates (a, b) is pure ceramics ZrO2. Their physical parameters are 0 0 E =132.2Gpa, μ = 0.3, 3 3 0 1 1 1 ρ = 3657kg/m , E =122.7Gpa, μ = 0.288, ρ = 4420kg/m . The number of nodes Nξ and Nη are assumed to be 17.
Effect of gradient indexes on frequency: Figure 2 shows the effect of gradient indexes α and β on the fundamental frequency 1 Ω of FGM rectangular plate under various boundary conditions, in which the lengthwidth ratio s is equal to 1 and the gradient indexes vary from 0 to 4. In Figure 2(a), when α and β are both equal to zero, the firstorder frequency 1 Ω of FGM rectangular plate under the foursided clamped boundary condition (CCCC) is 3.55. In reference [2], the analytical solution of the firstorder frequency is equal to 3.51. It can be seen that DQM has high accuracy and good astringency and stability. From Figure 2(a) to Figure 2(i), it can be seen that with the increase of gradient indexes, the fundamental frequency increases gradually and then tends to the constant.
Effect of lengthwidth ratio on fundamental frequency: Figure 3 shows the effect of lengthwidth ratio s on the fundamental frequency 1 Ω of FGM rectangular plate under various boundary conditions, in which the gradient indexes are assumed to be α = β =1 and lengthwidth ratio s varies from 1 to 3. It can be seen from Fig. 3 that the influence of lengthwidth ratio on fundamental frequency plate is different for different boundary conditions. In detail, The fundamental frequencies of FGM rectangular plate under CCCC and S1CS1C boundary conditions increase with the increase of lengthwidth ratio, while those under CFS1F, CFS2 F, CFCF and S1FS1F boundary conditions decrease with the increase of lengthwidth ratio, and those under S1S1S1S1 boundary condition remain unchanged with the increase of lengthwidth ratio. Therefore, we should pay particular attention to the specific boundary constraints when designing an FGM rectangular plate especially when the inplane vibration cannot be neglected.
Effect of stiffness of elastic boundary on frequency: Figure 4 shows the relationship between the stiffness coefficient and the fundamental frequency under a special boundary condition (S1S1S2S2). It is assumed that the normal stiffness coefficient nx0 K and ny0 K are both expressed as n K , the tangential stiffness coefficient x1 Kτ and y1 Kτ are both expressed as Kτ , and other stiffness coefficients 1 1 0 0 , , , nx ny x y K K K K τ τ are equal to ∞ . n K and Kτ vary from 0.01 to 103, and logarithmic coordinates are used in abscissa. Figure 4(a) shows the effect of tangential stiffness coefficient Kτ on the fundamental frequencies with different normal stiffness coefficients. It can be seen that with the increase of tangential stiffness coefficient, the fundamental frequency increases, especially when Kτ varies from 1 to 10. From another angle, increasing the n K leads to the increase of 1 Ω .
Figure 4(b) shows the effect of normal stiffness coefficient n K on the fundamental frequencies with different tangential stiffness coefficients. It can be seen that the effect of normal stiffness coefficient n K on the fundamental frequencies is the same as the effect of tangential stiffness coefficient Kτ on the fundamental frequencies. However, comparing Figures 4(a) & 4(b), it can be seen that the influence of normal stiffness coefficients on fundamental frequency is more remarkable than that of tangential stiffness coefficients.
Modal characteristics for inplane free vibration of FGM rectangular plate
In order to reveal the inplane vibration mechanism of FGM rectangular plates, it is necessary to study the modal characteristics of them. Figure 5 shows the first six order modal diagrams of rectangular plates under various boundary conditions when s is equal to 1.5, α and β are both equal to 1. From Figure 5, it can be seen that the vibration frequency of foursided clamped(CCCC) FGM plates is the largest, and the vibration frequency of S1FS1F FGM plates is the smallest. Moreover, for the clamped boundary, symmetric or antisymmetric modes will appear at the interior points of FGM rectangular plate, and this property is also suitable for the S1 and S2 boundaries. For the free boundary, symmetric or antisymmetric modes will appear at the interior points and boundaries of FGM rectangular plate, and coupled vibration occurs at normal and tangential directions.
Conclusion
The inplane free vibration of FGM rectangular plate is studied based on the twodimensional linear elasticity theory. The equation of motion is established, and the natural frequencies are determined. The variations of natural frequencies concerning the gradient index, lengthwidth ratio and stiffness of elastic boundary are obtained. It is found that DQM has better accuracy in analyzing the inplane vibration of FGM rectangular plates. Moreover, with the increase of gradient index, the fundamental frequency increases gradually and then tends to a constant, the influence of lengthwidth ratio on fundamental frequency is different for different boundary conditions, and with the increase of stiffness coefficient, the fundamental frequency increases. Finally, the modal characteristics of FGM rectangular plates are studied. It is found that symmetric or antisymmetric modes appear at the interior points of FGM rectangular plate for the clamped, S1 and S2 boundaries. For the free boundary, symmetric or antisymmetric modes appear at the interior points and boundaries, and coupled vibration occurs at normal and tangential directions. According to the above characteristics, the frequency required in a certain range can be obtained by changing these parameters of FGM rectangular plates. Therefore, this study can provide a reference for the twodimensional FGM rectangular plate structural engineering where the inplane free vibration plays a remarkable role.
Acknowledgement
This work is supported by the National Natural Science Foundation of China (No. 11572210) and the Postgraduate Research and Practice Innovation Program of Jiangsu province (No. KYCX17_1983).
Conflict of Interest
No conflict of interest.
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Jiping Shen, Changjian Ji, Linquan Yao, Tonghao Hu, Cheng Li. InPlane Free Vibration of Functionally Graded Rectangular Plates with Elastic Restraint. Glob J Eng Sci. 2(3): 2019. GJES.MS.ID.000537.

Functionally graded rectangular plates, Elastic restraint, Inplane free vibration, Differential Quadrature Method

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