Convergence of frequency parameters of completely free FGM square plates with different thickness-to-width ratios * h*/

*(*b

*= 1).*p

Open access peer-reviewed chapter

Submitted: May 27th, 2015 Reviewed: February 1st, 2016 Published: March 31st, 2016

DOI: 10.5772/62335

From the Edited Volume

Edited by Farzad Ebrahimi

Three-dimensional (3-D) vibration analysis of thick functionally graded plates and cylindrical shells with arbitrary boundary conditions is presented in this chapter. The effective material properties of functionally graded structures vary continuously in the thickness direction according to the simple power-law distributions in terms of volume fraction of constituents and are estimated by Voigt’s rule of mixture. By using the artificial spring boundary technique, the general boundary conditions can be obtained by setting proper spring stiffness. All displacements of the functionally graded plates and shells are expanded in the form of the linear superposition of standard 3-D cosine series and several supplementary functions, which are introduced to remove potential discontinuity problems with the original displacements along the edge. The Rayleigh-Ritz procedure is used to yield the accurate solutions. The convergence, accuracy and reliability of the current formulation are verified by numerical examples and by comparing the current results with those in published literature. Furthermore, the influence of the geometrical parameters and elastic foundation on the frequencies of rectangular plates and cylindrical shells is investigated.

- Three-dimensional elasticity theory
- functional graded materials
- plate and cylindrical shell
- general boundary conditions

Functionally graded materials (FGMs) are a new type of composite materials with smooth and continuous variation in material properties in desired directions. This is achieved by gradually varying the volume fraction of the constituent materials. Such materials possess various advantages over conventional composite laminates, such as smaller stress concentration, higher fracture toughness and improved residual stress distribution. Recently, the FGMs have been used to build plate and shell components in various engineering applications, especially mechanical, aerospace, marine and civil engineering. In some cases, those FGM plates and shells are frequently subjected to dynamic loads, which leads to the vibration behaviours, which may cause fatigue damage and result in severe reduction in the strength and stability of the whole structures. Therefore, the vibration analysis of the FGM plates and shells is required and it is important to provide insight into dynamic behaviours and optimal design.

It is well known that vibration problems deal with two main concepts: plate and shell theories and computational approaches. The development of plate and shell theories has been subjected to significant research interest for many years, and many plate and shell theories have been proposed and developed. The main plate and shell theories can be classified into two categories: two-dimensional (2-D) plate and shell theories, including classic plate and shell theory (CPT) [1–4], the first-order shear deformation theory (FSDT) [5–16], and the higher order shear deformation theory (HSDT) [17–26], and three-dimensional (3-D) theory of elasticity [27–35]. However, all 2-D theories are approximate because they were developed based on certain kinematic assumptions that result in relatively simple expression and derivation of solutions. Actually, 3-D elasticity theory, which does not rely on any hypotheses about the distribution field of deformations and stress, not only provides realistic results but also allows for further physical insight. More attempts have been made for 3-D vibration analysis of plates and shells in the recent decades. Furthermore, many analytical, semi-analytical and numerical computational methods have also been developed, such as Ritz method, state-space method, differential quadrature method (DQM), Galerkin method, meshless method, finite element method (FEM) and discrete singular convolution (DSC) approach.

However, a close scrutiny of the literature in this field reveals that most investigations were carried out based on 2-D plate and shell theories, and a general 3-D solution for this subject seems to be limited. Moreover, the review also reveals that most of previous research efforts were restricted to vibration problems of FGM plates and shells with limited sets of classical boundary conditions. It is well recognized that there exist various possible boundary restraint cases for plates and shells in practical assembly and engineering applications. Consequently, it is necessary and of great significance to develop a unified, efficient and accurate method that is capable of universally dealing with FGM plates and shells with general boundary conditions.

In view of these apparent voids, the aim of this chapter is to develop an accurate semi-analysis method that is capable of dealing with vibrations of FGM plates and shells with general boundary conditions, including classical boundaries, elastic supports and their combinations and to provide a summary of known 3-D results of plates and shells with general boundary conditions, which may serve as benchmark solutions for future researches in this field.

In this chapter, 3-D vibration analysis of thick functionally graded plates and cylindrical shells with arbitrary elastic restraints is presented. The effective material properties of functionally graded structures vary continuously in the thickness direction according to the simple power-law distributions in terms of volume fraction of constituents and are estimated by Voigt’s rule of mixture. By using the artificial spring boundary technique, the general boundary conditions can be obtained by setting proper spring stiffness. All displacements of the functionally graded plates and shells are expanded in the form of the linear superposition of standard 3-D cosine series and several supplementary functions, which are introduced to remove potential discontinuity problems with the original displacements along the edge. The RayleighRitz procedure is used to yield the accurate solutions.

Advertisement## 2. Theoretical formulations

### 2.1. Preliminaries

ε α α = 1 h α ∂ u ∂ α + 1 h α h β ∂ h α ∂ β v + 1 h α h z ∂ h α ∂ z w ![]()

E1ε β β = 1 h β ∂ v ∂ β + 1 h β h z ∂ h β ∂ z w + 1 h β h α ∂ h β ∂ α u ![]()

E2ε z z = 1 h z ∂ w ∂ z + 1 h z h α ∂ h z ∂ α u + 1 h z h β ∂ h z ∂ β v ![]()

E3γ β z = 1 h β h z ( h β ∂ v ∂ z + h z ∂ w ∂ β − ∂ h β ∂ z v − ∂ h z ∂ β w ) ![]()

E4γ α z = 1 h α h z ( h α ∂ u ∂ z + h z ∂ w ∂ α − ∂ h α ∂ z u − ∂ h z ∂ α w ) ![]()

E5γ α β = 1 h α h β ( h α ∂ u ∂ β + h β ∂ v ∂ α − ∂ h β ∂ α v − ∂ h α ∂ β u ) ![]()

E6[ σ α α σ β β σ z z σ β z σ α z σ α β ] = [ Q 11 Q 12 Q 13 0 0 0 Q 12 Q 22 Q 23 0 0 0 Q 13 Q 23 Q 33 0 0 0 0 0 0 Q 44 0 0 0 0 0 0 Q 55 0 0 0 0 0 0 Q 66 ] [ ε α α ε β β ε z z γ β z γ α z γ α β ] ![]()

E7Q 11 = Q 22 = Q 33 = E ( r ) [ 1 − μ ( r ) ] [ 1 + μ ( r ) ] [ 1 − 2 μ ( r ) ] , Q 12 = Q 13 = Q 23 = μ ( r ) E ( r ) [ 1 + μ ( r ) ] [ 1 − 2 μ ( r ) ] , Q 44 = Q 55 = Q 66 = E ( r ) [ 2 ( 1 + μ ( r ) ] , ![]()

E8E ( r ) = ( E c − E m ) V c + E m μ ( r ) = ( μ c − μ m ) V c + μ m ρ ( r ) = ( ρ c − ρ m ) V c + ρ m ![]()

E9V c = ( z h ) p , V m = 1 − ( z h ) p ( 0 ≤ z ≤ h ) ![]()

E10k u α 1 u = σ α α , k v α 1 v = σ α β , k w α 1 w = σ α z ![]()

E11k u α 2 u = σ α α , k v α 2 v = σ α β , k w α 2 w = σ α z ![]()

E12### 2.2. Energy functional

Π = T − U − P ![]()

E13T = 1 2 ∭ ρ ( z ) ( u ˙ 2 + v ˙ 2 + w ˙ 2 ) d α d β d z ![]()

E14U = 1 2 ∭ ( σ α α ε α α + σ β β ε β β + σ z z ε z z + σ β z γ β z + σ α z γ α z + σ α β γ α β ) d α d β d z ![]()

E15P = 1 2 [ ∫ S α i ( k u α i u 2 + k v α i v 2 + k w α i w 2 ) d S α i + ∫ S β i ( k u β i u 2 + k v β i v 2 + k w β i w 2 ) d S β i ] ![]()

E16### 2.3. Admissible functions

u ( α , β , z , t ) = { ∑ m = 0 M ∑ n = 0 N ∑ q = 0 Q A m n q cos λ m α cos λ n β cos λ q z + ∑ l = 1 2 ∑ n = 0 N ∑ q = 0 Q a l n q ξ l α ( α ) cos λ n β cos λ q z + ∑ m = 0 M ∑ l = 1 2 ∑ q = 0 Q a ¯ l m q cos λ m α ξ l β ( β ) cos λ q z + ∑ m = 0 M ∑ n = 0 N ∑ l = 1 2 a ˜ l m n cos λ m α cos λ n β ξ l z ( z ) + } e j ω t ![]()

E17v ( α , β , z , t ) = { ∑ m = 0 M ∑ n = 0 N ∑ q = 0 Q B m n q cos λ m α cos λ n β cos λ q z + ∑ l = 1 2 ∑ n = 0 N ∑ q = 0 Q b l n q ξ l α ( α ) cos λ n β cos λ q z + ∑ m = 0 M ∑ l = 1 2 ∑ q = 0 Q b ¯ l m q cos λ m α ξ l β ( β ) cos λ q z + ∑ m = 0 M ∑ n = 0 N ∑ l = 1 2 b ˜ l m n cos λ m α cos λ n β ξ l z ( z ) + } e j ω t ![]()

E18w ( α , β , z , t ) = { ∑ m = 0 M ∑ n = 0 N ∑ q = 0 Q C m n q cos λ m α cos λ n β cos λ q z + ∑ l = 1 2 ∑ n = 0 N ∑ q = 0 Q c l n q ξ l α ( α ) cos λ n β cos λ q z + ∑ m = 0 M ∑ l = 1 2 ∑ q = 0 Q c ¯ l m q cos λ m α ξ l β ( β ) cos λ q z + ∑ m = 0 M ∑ n = 0 N ∑ l = 1 2 c ˜ l m n cos λ m α cos λ n β ξ l z ( z ) + } e j ω t ![]()

E19ξ 1 α = α ( α L α − 1 ) 2 , ξ 2 α = α 2 L α ( α L α − 1 ) ![]()

E20ξ 1 β = β ( β L β − 1 ) 2 , ξ 2 β = β 2 L β ( β L β − 1 ) ![]()

E21ξ 1 z = z ( z L z − 1 ) 2 , ξ 2 z = z 2 L z ( z L z − 1 ) ![]()

E22ξ 1 α ( 0 ) = ξ 1 α ( L α ) = ξ 1 α ' ( L α ) = 0 , ξ 1 α ' ( 0 ) = 1 ![]()

E23ξ 2 α ( 0 ) = ξ 2 α ( L α ) = ξ 2 α ' ( 0 ) = 0 , ξ 2 α ' ( L α ) = 1 ![]()

E24### 2.4. Solution procedure

{ K − ω 2 M } X = 0 ![]()

E25X = [ X u , X v , X w ] T ![]()

E26X u = { A 000 , ⋯ , A m n q , ⋯ , A M N Q , a 100 , ⋯ , a l n q , ⋯ , a 2 N Q , a ¯ 100 , ⋯ , a ¯ l m q , ⋯ a ¯ 2 M Q , a ˜ 100 , ⋯ , a ˜ l m n , ⋯ a ˜ 2 M N } ![]()

E27X v = { B 000 , ⋯ , B m n q , ⋯ , B M N Q , b 100 , ⋯ , b l n q , ⋯ , b 2 N Q , b ¯ 100 , ⋯ , b ¯ l m q , ⋯ b ¯ 2 M Q , b ˜ 100 , ⋯ , b ˜ l m n , ⋯ b ˜ 2 M N } ![]()

E28X w = { C 000 , ⋯ , C m n q , ⋯ , C M N Q , c 100 , ⋯ , c l n q , ⋯ , c 2 N Q , c ¯ 100 , ⋯ , c ¯ l m q , ⋯ c ¯ 2 M Q , c ˜ 100 , ⋯ , c ˜ l m n , ⋯ c ˜ 2 M N } ![]()

E29

A differential element of a shell with uniform thickness * h*is considered

where

In engineering applications, plates and shells are the basic structural elements. For the sake of brevity, this chapter will be confined to rectangular plates and cylindrical shells. According to Fig. 2, the coordinate systems and Lame coefficients are given as follows [36]: for rectangular plates,

where * i*,

where * E*(

where * E*,

where * z*is the thickness coordinate, and

In this work, the general boundary conditions can be described in terms of three groups of springs (* α*= constant, for example, the boundary conditions can be given as follows:

where the superscripts * α*1 and

The energy functional of plates or shells can be expressed as follows:

where * T*is kinetic energy,

The kinetic energy * T*can be written as follows:

where the over dot represents the differentiation with respect to time.

The strain energy * U*can be written in an integral form as follows:

Substituting Eqs. (1–16) into Eq. (15) together with Lame coefficients, one can obtain the explicit expressions of strain energy for rectangular plates and cylindrical shells.

The potential energy (* P*) stored in the boundary springs is given as follows:

where

It is crucially important to construct the appropriate admissible displacement functions in the Rayleigh–Ritz method. Beam functions, orthogonal polynomials and Fourier series are often used as displacement functions of plates and shells. However, the use of beam function will lead to at least a very tedious solution process [38]. The problem with using a complete set of orthogonal polynomials is that the higher-order polynomials tend to become numerically unstable because of the computer round-off errors [38, 39]. These numerical difficulties can be avoided by the Fourier series because the Fourier series constitute a complete set and exhibit an excellent numerical stability. However, when the displacements are expressed in terms of conventional Fourier series, discontinuities potentially exist in the original displacements and their derivatives. In this chapter, a modified Fourier series defined as the linear superposition of a 3-D Fourier cosine series and some auxiliary polynomial functions is used to express the displacement components, which are given as follows [40–43]:

where * ω*is the circular frequency and

It is easy to verify that

The similar conditions exist for the * β*- and

Substituting Eqs. (14–16) into Eq. (13) together with the displacement functions defined in Eqs. (17–19) and performing the Rayleigh–Ritz operation, a set of linear algebraic equation against the unknown coefficients can be obtained as follows:

where ** K**is the total stiffness matrix for the structure and

where

The frequencies can be determined by solving Eq. (25) via the eigenfunction of MATLAB program. The mode shape corresponding to each frequency can be obtained by back substituting the eigenvector to the displacement functions in Eqs. (17–19).

Advertisement## 3. Numerical examples and discussion

σ α α = σ α β = σ α z = 0 ![]()

BB1u = v = w = 0 ![]()

BB2σ α α = v = w = 0 ![]()

BB3u ≠ 0 , v = w = 0 ![]()

BB4u = 0 , v ≠ 0 , w ≠ 0 ![]()

BB5u ≠ 0 , v ≠ 0 , w ≠ 0 ![]()

BB6### 3.1. Rectangular plates

#### 3.1.1. Convergence study

Ω = ω a 2 / h ρ c / E c ![]()

BB7

#### 3.1.2. Plate with general boundary conditions

### 3.2. Cylindrical shells

#### 3.2.1. Convergence study

#### 3.2.2. Cylindrical shells with general boundary conditions

In this section, several vibration results of FGM plates and cylindrical shells with general boundary conditions are presented to illustrate the accuracy and reliability of the current formulation. To simplify presentation, C, S, F and E denote the clamped, simply supported, free and elastic restraints. Three types of elastic boundary conditions designated by symbols E_{1}, E_{2} and E_{3} are considered. E_{1}-type edge is considered to be elastic in normal direction; the support type E_{2} only allows elastically restrained displacement in both tangential directions; when all of three displacements along the edges are elastically restrained, the edge support is defined by E_{3}. The expressions of the different boundary conditions along the edge * α*= 0 are given as follows:

Free boundary condition (F):

Clamped boundary condition (C):

Simply supported boundary condition (S):

First type of elastic restraint (E_{1}):

Second type of elastic restraint (E_{1}):

Three type of elastic restraint (E_{1}):

A simple letter is used to describe the boundary conditions of structure. For example, SFCE denotes a plate having simply supported boundary condition at * α*= 0, free boundary condition at

In this section, several numerical examples concerning the free vibration of FGM rectangular plates with different geometrical parameters and boundary conditions have been investigated to verify the convergence, accuracy and reliability of the present method. Some new vibration results of rectangular plates with elastic boundary conditions are given. Unless stated otherwise, the material properties for ceramic and metallic constituents of FGM plates are given as follows: _{c}= 380 GPa, _{c}= 0.3 and _{c}= 3800 kg/m^{3} and _{m}= 70 GPa, _{m}= 0.3 and _{m}= 2702 kg/m^{3}.

Theoretically, there are infinite terms in the modified Fourier series solution. However, the series is numerically truncated, and only finite terms are counted in actual calculations. The convergence of this method will be checked. Table 1 presents the first seven frequency parameters Ω of completely free FGM square plates. The frequency parameter Ω is defined as follows:

The geometrical parameters are given as follows: * a*/

_{1} | _{2} | _{3} | _{4} | _{5} | _{6} | _{7} | ||

0.1 | 9 × 9 × 4 | 2.9579 | 4.3853 | 5.4058 | 7.4361 | 7.4361 | 12.903 | 12.903 |

11 × 11 × 4 | 2.9558 | 4.3851 | 5.4054 | 7.4293 | 7.4293 | 12.901 | 12.901 | |

11 × 11 × 8 | 2.9524 | 4.3802 | 5.4018 | 7.4256 | 7.4256 | 12.898 | 12.898 | |

13 × 13 × 8 | 2.9514 | 4.3802 | 5.4016 | 7.4225 | 7.4225 | 12.897 | 12.897 | |

13 × 13 × 10 | 2.9513 | 4.3800 | 5.4015 | 7.4223 | 7.4223 | 12.897 | 12.897 | |

0.2 | 9 × 9 × 4 | 2.7261 | 4.0298 | 4.9324 | 6.4506 | 6.4506 | 10.093 | 10.642 |

11 × 11 × 4 | 2.7257 | 4.0297 | 4.9322 | 6.4492 | 6.4492 | 10.093 | 10.640 | |

11 × 11 × 8 | 2.7250 | 4.0287 | 4.9315 | 6.4485 | 6.4485 | 10.093 | 10.639 | |

13 × 13 × 8 | 2.7247 | 4.0286 | 4.9314 | 6.4479 | 6.4479 | 10.093 | 10.637 | |

13 × 13 × 10 | 2.7247 | 4.0286 | 4.9313 | 6.4478 | 6.4478 | 10.093 | 10.637 | |

0.5 | 9 × 9 × 4 | 2.0442 | 2.8571 | 3.4668 | 3.9777 | 3.9777 | 4.0369 | 4.3056 |

11 × 11 × 4 | 2.0442 | 2.8571 | 3.4667 | 3.9776 | 3.9776 | 4.0369 | 4.3055 | |

11 × 11 × 8 | 2.0441 | 2.8568 | 3.4665 | 3.9773 | 3.9773 | 4.0368 | 4.3053 | |

13 × 13 × 8 | 2.0440 | 2.8568 | 3.4665 | 3.9772 | 3.9772 | 4.0368 | 4.3052 | |

13 × 13 × 10 | 2.0440 | 2.8568 | 3.4664 | 3.9772 | 3.9772 | 4.0368 | 4.3052 |

As aforementioned, the boundary conditions can be easily obtained via changing the value of boundary springs. Therefore, the accuracy of the current method is strongly influenced by the values of springs’ stiffness. To determine the appropriate values of spring’s stiffness, the effects of elastic parameters on the frequencies of the FGM plate are investigated. The elastic parameter * Γ*is defined as ratios of corresponding spring’s stiffness to bending stiffness

_{u }= ΓD, k_{v }= k_{w }= 0 | _{v }= ΓD, k_{u }= k_{w }= 0 | _{w }= ΓD, k_{u }= k_{v }= 0 | |||||||

_{1} | _{2} | _{3} | _{1} | _{2} | _{3} | _{1} | _{2} | _{3} | |

10^{−1} | 0.0167 | 0.0464 | 0.0654 | 0.0167 | 0.0654 | 0.0802 | 0.0650 | 0.0654 | 0.1117 |

10^{0} | 0.0419 | 0.1463 | 0.2069 | 0.0419 | 0.2069 | 0.2533 | 0.2028 | 0.2061 | 0.3514 |

10^{1} | 0.1285 | 0.4615 | 0.6536 | 0.1286 | 0.6513 | 0.7985 | 0.6294 | 0.6301 | 1.1044 |

10^{2} | 0.3984 | 1.4270 | 2.0440 | 0.3996 | 1.9750 | 2.4251 | 1.5056 | 1.7178 | 3.2905 |

10^{3} | 1.0903 | 2.8583 | 3.7961 | 1.1184 | 3.0710 | 4.2125 | 2.0002 | 2.7732 | 5.9372 |

10^{4} | 1.8471 | 3.1625 | 4.5503 | 2.0317 | 3.8426 | 4.3529 | 2.0785 | 3.0227 | 6.4327 |

10^{5} | 2.0625 | 3.2758 | 4.5745 | 2.3675 | 4.2459 | 4.3815 | 2.0880 | 3.0600 | 6.5168 |

10^{6} | 2.0904 | 3.2915 | 4.5774 | 2.4305 | 4.3436 | 4.3859 | 2.0891 | 3.0657 | 6.5299 |

10^{7} | 2.0934 | 3.2932 | 4.5777 | 2.4464 | 4.3740 | 4.3870 | 2.0893 | 3.0664 | 6.5316 |

10^{8} | 2.0937 | 3.2934 | 4.5778 | 2.4490 | 4.3790 | 4.3871 | 2.0893 | 3.0665 | 6.5318 |

10^{9} | 2.0937 | 3.2934 | 4.5778 | 2.4493 | 4.3796 | 4.3871 | 2.0893 | 3.0665 | 6.5319 |

10^{10} | 2.0937 | 3.2934 | 4.5778 | 2.4493 | 4.3796 | 4.3871 | 2.0893 | 3.0665 | 6.5319 |

To illustrate the accuracy of the present method, the comparisons of the current results with those in the published literature are presented. Table 3 presents the first two frequency parameters of the FGM square plates with different boundary conditions. The results are compared with those presented by Huang et al. [32] using the Ritz method on the basis of 3-D elasticity theory. Table 4 presents the fundamental frequency parameters of the FGM square plates with SSSS boundary conditions. Numerical vibration results for the same problems have been reported by Hosseini-Hashemi et al. [18] and Matsunaga [20] using HSDTs, showing that excellent agreement of the results is achieved.

Ω_{1} | 3.406 | 3.406 | 0.000 | 0.6637 | 0.6657 | 0.347 | 3.400 | 3.421 | 0.618 |

Ω_{2} | 6.296 | 6.296 | 0.000 | 1.432 | 1.434 | 0.140 | 3.820 | 3.840 | 0.524 |

Ω_{3} | 6.296 | 6.296 | 0.000 | 2.154 | 2.158 | 0.186 | 5.774 | 5.787 | 0.225 |

Ω_{4} | 7.347 | 7.345 | 0.027 | 3.396 | 3.405 | 0.265 | 5.976 | 5.989 | 0.218 |

Ω_{5} | 7.347 | 7.345 | 0.027 | 4.347 | 4.348 | 0.023 | 7.609 | 7.657 | 0.631 |

0.1 | Ref. [18] | 0.0577 | 0.0490 | 0.0443 | 0.0381 | 0.0364 | 0.0293 |

Ref. [20] | 0.0577 | 0.0492 | 0.0442 | 0.0381 | 0.0364 | 0.0293 | |

Present | 0.0578 | 0.0491 | 0.0443 | 0.0381 | 0.0364 | 0.0294 | |

0.2 | Ref. [18] | 0.2113 | 0.1807 | 0.1631 | 0.1378 | 0.1301 | 0.1076 |

Ref. [20] | 0.2121 | 0.1819 | 0.1640 | 0.1383 | 0.1306 | 0.1077 | |

Present | 0.2122 | 0.1816 | 0.1640 | 0.1383 | 0.1306 | 0.1080 |

= 1 | = 2 | ||||||||

CSSS | 0.1 | 5.660 | 5.235 | 4.434 | 4.272 | 12.66 | 11.71 | 10.01 | 9.671 |

0.3 | 4.415 | 4.096 | 3.263 | 3.083 | 11.01 | 10.20 | 8.354 | 7.676 | |

0.5 | 3.391 | 3.156 | 2.435 | 2.265 | 6.866 | 6.464 | 5.023 | 4.591 | |

CCSS | 0.1 | 6.416 | 5.936 | 5.008 | 4.819 | 17.17 | 15.88 | 13.48 | 13.00 |

0.3 | 4.807 | 4.464 | 3.520 | 3.313 | 13.68 | 12.69 | 10.12 | 9.566 | |

0.5 | 3.582 | 3.336 | 2.549 | 2.366 | 10.54 | 9.807 | 7.548 | 7.037 | |

CCCS | 0.1 | 7.437 | 6.884 | 5.772 | 5.544 | 17.71 | 16.38 | 13.90 | 13.40 |

0.3 | 5.264 | 4.894 | 3.815 | 3.572 | 14.01 | 13.00 | 10.36 | 9.782 | |

0.5 | 3.797 | 3.540 | 2.681 | 2.479 | 10.75 | 10.00 | 7.679 | 7.153 | |

CFFF | 0.1 | 0.864 | 0.799 | 0.687 | 0.664 | 0.862 | 0.797 | 0.687 | 0.665 |

0.3 | 0.816 | 0.755 | 0.637 | 0.613 | 0.845 | 0.781 | 0.669 | 0.647 | |

0.5 | 0.746 | 0.690 | 0.568 | 0.543 | 0.821 | 0.759 | 0.645 | 0.622 | |

CCFF | 0.1 | 1.684 | 1.558 | 1.330 | 1.285 | 4.230 | 3.911 | 3.356 | 3.246 |

0.3 | 1.473 | 1.363 | 1.125 | 1.076 | 3.900 | 3.608 | 3.021 | 2.902 | |

0.5 | 1.253 | 1.160 | 0.932 | 0.885 | 3.479 | 3.220 | 2.627 | 2.506 | |

CCCF | 0.1 | 5.643 | 5.223 | 4.393 | 4.222 | 7.628 | 7.056 | 6.031 | 5.825 |

0.3 | 4.074 | 3.785 | 2.956 | 2.774 | 6.594 | 6.107 | 5.009 | 4.781 | |

0.5 | 2.944 | 2.738 | 2.080 | 1.932 | 5.503 | 5.102 | 4.053 | 3.831 |

Several new numerical results for free vibration of FGM plates with general boundary conditions, including classical and elastic boundary conditions, are presented in Tables 5 and 6. The geometrical parameters are given as: * a*/

= 1 | = 2 | ||||||||

E_{1}E_{1}E_{1}E_{1} | 0.1 | 4.798 | 4.437 | 3.786 | 3.655 | 12.138 | 11.228 | 9.626 | 9.303 |

0.3 | 4.113 | 3.837 | 3.142 | 2.983 | 11.145 | 10.426 | 8.736 | 8.339 | |

0.5 | 3.444 | 3.236 | 2.522 | 2.352 | 10.019 | 9.439 | 7.495 | 7.035 | |

E_{2}E_{2}E_{2}E_{2} | 0.1 | 1.975 | 2.006 | 2.090 | 2.109 | 6.541 | 6.592 | 6.748 | 6.780 |

0.3 | 3.043 | 3.025 | 2.844 | 2.773 | 9.601 | 9.476 | 8.804 | 8.569 | |

0.5 | 3.083 | 2.979 | 2.487 | 2.343 | 9.597 | 9.238 | 7.680 | 7.238 | |

E_{3}E_{3}E_{3}E_{3} | 0.1 | 1.823 | 1.823 | 1.828 | 1.826 | 5.690 | 5.649 | 5.586 | 5.563 |

0.3 | 2.594 | 2.541 | 2.357 | 2.298 | 7.867 | 7.670 | 7.063 | 6.874 | |

0.5 | 2.724 | 2.634 | 2.234 | 2.123 | 8.308 | 8.014 | 6.799 | 6.471 |

This section is concerned with the free vibration of FGM cylindrical shells with different boundary conditions. The convergence, accuracy and reliability of the present method are demonstrated by numerical examples and comparisons. New numerical results for the FGM cylindrical shells with the elastic boundary conditions are also presented. Unless stated otherwise the material properties for ceramic and metallic constituents of FGM cylindrical shells are given as follows: _{c}= 168 GPa, _{c}= 0.3 and _{c}= 5700 kg/m^{3} and _{m}= 70 GPa, _{m}= 0.3 and _{m}= 2707 kg/m^{3}.

The convergence studies of the first two frequencies for the completely free cylindrical shells with different circumferential wave numbers * n*are presented in Table 7. The different thickness-to-radius ratios (i.e.,

_{0} | |||||||||

_{1} | _{2} | _{1} | _{2} | _{1} | _{2} | _{1} | _{2} | ||

0.1 | 10 × 10 | 675.95 | 775.84 | 72.216 | 93.963 | 202.45 | 236.49 | 383.66 | 422.39 |

11 × 11 | 675.95 | 775.84 | 72.213 | 93.900 | 202.44 | 236.37 | 383.64 | 422.20 | |

12 × 12 | 675.95 | 775.82 | 72.211 | 93.898 | 202.43 | 236.36 | 383.61 | 422.19 | |

13 × 13 | 675.95 | 775.82 | 72.209 | 93.859 | 202.42 | 236.28 | 383.60 | 422.07 | |

14 × 14 | 675.95 | 775.81 | 72.208 | 93.858 | 202.42 | 236.28 | 383.58 | 422.06 | |

0.2 | 10 × 10 | 702.69 | 829.15 | 156.06 | 195.32 | 426.43 | 484.16 | 782.43 | 843.50 |

11 × 11 | 702.69 | 829.14 | 156.06 | 195.27 | 426.42 | 484.05 | 782.41 | 843.32 | |

12 × 12 | 702.69 | 829.12 | 156.05 | 195.27 | 426.41 | 484.04 | 782.37 | 843.29 | |

13 × 13 | 702.68 | 829.12 | 156.05 | 195.24 | 426.40 | 483.98 | 782.36 | 843.19 | |

14 × 14 | 702.68 | 829.11 | 156.05 | 195.24 | 426.39 | 483.97 | 782.34 | 843.18 | |

0.5 | 10 × 10 | 813.89 | 990.82 | 472.71 | 513.27 | 1119.84 | 1157.84 | 1798.22 | 1821.60 |

11 × 11 | 813.88 | 990.82 | 472.71 | 513.25 | 1119.82 | 1157.80 | 1798.18 | 1821.52 | |

12 × 12 | 813.88 | 990.81 | 472.70 | 513.25 | 1119.81 | 1157.78 | 1798.15 | 1821.49 | |

13 × 13 | 813.88 | 990.81 | 472.70 | 513.24 | 1119.80 | 1157.76 | 1798.13 | 1821.45 | |

14 × 14 | 813.88 | 990.81 | 472.70 | 513.24 | 1119.80 | 1157.75 | 1798.12 | 1821.43 |

_{u }= ΓD, k_{v }= k_{w }= 0 | _{v }= ΓD, k_{u }= k_{w }= 0 | _{w }= ΓD, k_{u }= k_{v }= 0 | |||||||

10^{−1} | 6.0482 | 156.26 | 426.50 | 6.0495 | 156.10 | 426.42 | 6.3136 | 156.05 | 426.40 |

10^{0} | 19.080 | 158.13 | 427.41 | 19.120 | 156.58 | 426.54 | 19.945 | 156.05 | 426.41 |

10^{1} | 58.929 | 174.72 | 435.81 | 60.159 | 161.25 | 427.76 | 62.811 | 156.06 | 426.42 |

10^{2} | 153.57 | 251.42 | 482.58 | 181.20 | 197.82 | 438.59 | 190.65 | 156.13 | 426.59 |

10^{3} | 233.55 | 318.79 | 529.79 | 404.21 | 306.64 | 485.62 | 424.98 | 156.65 | 427.85 |

10^{4} | 250.70 | 330.93 | 538.16 | 506.09 | 361.57 | 523.38 | 510.67 | 157.86 | 430.84 |

10^{5} | 253.21 | 332.47 | 539.14 | 519.80 | 369.75 | 532.12 | 521.32 | 158.32 | 432.03 |

10^{6} | 253.55 | 332.66 | 539.26 | 521.22 | 370.71 | 533.44 | 522.45 | 158.38 | 432.19 |

10^{7} | 253.62 | 332.69 | 539.28 | 521.37 | 370.89 | 533.83 | 522.56 | 158.39 | 432.20 |

10^{8} | 253.65 | 332.70 | 539.29 | 521.38 | 370.94 | 533.98 | 522.58 | 158.39 | 432.21 |

10^{9} | 253.66 | 332.71 | 539.29 | 521.38 | 370.95 | 534.00 | 522.58 | 158.39 | 432.21 |

10^{10} | 253.66 | 332.71 | 539.29 | 521.38 | 370.95 | 534.00 | 522.58 | 158.39 | 432.21 |

It is significant to investigate the effects of elastic parameters on the frequencies of the cylindrical shells. The cylindrical shells are restrained by only one kind of spring whose stiffness parameter ranges from 10^{−1} to 10^{10} at * x*= constant. The frequencies of the cylindrical shells with different circumferential wave numbers

To illustrate the accuracy of the present method, the comparisons of the current results with those in published literature are presented. Table 9 presents the first three frequency parameters * h*/

Several new numerical results for free vibration of FGM cylindrical shells with general boundary conditions, including classical and elastic boundary conditions, are presented in Tables 11 and 12. The geometrical parameters are given as follows: _{0} = 1 m, * L*/

_{1} | _{2} | _{3} | ||||||||

CC | 1 | 1.7860 | 1.7972 | 1.7905 | 2.6043 | 2.6222 | 2.6050 | 3.4148 | 3.4192 | 3.4245 |

2 | 1.7452 | 1.7573 | 1.7500 | 3.2942 | 3.3114 | 3.2949 | 3.4921 | 3.5150 | 3.5012 | |

3 | 1.8867 | 1.8862 | 1.8912 | 3.6024 | 3.6320 | 3.6099 | 3.9416 | 3.9257 | 3.9447 | |

4 | 2.1966 | 2.2072 | 2.2004 | 3.8126 | 3.8228 | 3.8193 | 4.2757 | 4.3215 | 4.2783 | |

5 | 2.6385 | 2.6617 | 2.6415 | 4.1302 | 4.1327 | 4.1364 | 4.7010 | 4.7322 | 4.7031 | |

CF | 1 | 0.7514 | 0.7546 | 0.7516 | 1.7563 | 1.7692 | 1.7568 | 1.8800 | 1.8996 | 1.8812 |

2 | 0.6620 | 0.6713 | 0.6622 | 1.8962 | 1.9256 | 1.8980 | 2.1305 | 2.1557 | 2.1324 | |

3 | 0.9246 | 0.9301 | 0.9247 | 2.0610 | 2.0668 | 2.0630 | 2.5165 | 2.5482 | 2.5179 | |

4 | 1.4021 | 1.4282 | 1.4021 | 2.4030 | 2.4646 | 2.4049 | 2.9919 | 3.0342 | 2.9930 | |

5 | 1.9814 | 2.0228 | 1.9814 | 2.8666 | 2.8571 | 2.8684 | 3.5251 | 3.5628 | 3.5258 | |

FF | 1 | 0.0000 | 0.0000 | 0.0000 | 0.0001 | 0.0001 | 0.0003 | 1.0710 | 1.0734 | 1.0709 |

2 | 0.2576 | 0.2608 | 0.2576 | 0.3800 | 0.3831 | 0.3799 | 1.3533 | 1.3594 | 1.3532 | |

3 | 0.6884 | 0.6890 | 0.6884 | 0.9253 | 0.9377 | 0.9252 | 1.8689 | 1.8794 | 1.8689 | |

4 | 1.2302 | 1.2525 | 1.2302 | 1.5160 | 1.5307 | 1.5158 | 2.4754 | 2.4917 | 2.4753 | |

5 | 1.8427 | 1.8694 | 1.8426 | 2.1343 | 2.1532 | 2.1341 | 3.1169 | 3.1417 | 3.1169 |

f_{1} | 152.93 | 152.13 | 150.03 | 148.67 | 149.29 | 147.76 | 148.75 | 147.10 |

f_{2} | 152.93 | 152.13 | 150.03 | 148.67 | 149.29 | 147.76 | 148.75 | 147.10 |

f_{3} | 220.06 | 219.31 | 212.94 | 211.89 | 212.22 | 211.00 | 219.49 | 218.00 |

f_{4} | 220.06 | 219.31 | 212.94 | 211.89 | 212.22 | 211.00 | 219.49 | 218.00 |

f_{5} | 253.78 | 254.30 | 250.74 | 250.36 | 249.31 | 248.68 | 243.43 | 242.86 |

f_{6} | 253.78 | 254.30 | 250.74 | 250.36 | 249.31 | 248.68 | 243.43 | 242.86 |

f_{7} | 383.55 | 384.04 | 370.63 | 370.69 | 369.46 | 369.21 | 383.71 | 382.79 |

f_{8} | 383.55 | 384.04 | 370.63 | 370.69 | 369.46 | 369.21 | 383.71 | 382.79 |

f_{9} | 420.51 | 420.86 | 415.47 | 414.68 | 412.97 | 411.88 | 402.56 | 401.57 |

f_{10} | 431.45 | 428.75 | 420.39 | 416.91 | 418.46 | 414.66 | 423.57 | 419.16 |

_{0} | ||||||||

CC | 0.1 | 390.33 | 377.23 | 374.78 | 375.39 | 379.94 | 379.62 | 376.24 |

0.3 | 621.15 | 599.34 | 594.11 | 591.68 | 594.96 | 595.70 | 593.23 | |

0.5 | 701.10 | 686.38 | 681.10 | 674.46 | 668.80 | 666.26 | 663.96 | |

CS | 0.1 | 378.25 | 365.82 | 363.43 | 363.82 | 367.81 | 367.48 | 364.19 |

0.3 | 567.55 | 548.06 | 543.23 | 540.49 | 542.33 | 542.55 | 540.43 | |

0.5 | 648.20 | 634.72 | 629.77 | 623.22 | 617.07 | 614.23 | 612.09 | |

SS | 0.1 | 367.68 | 355.76 | 353.44 | 353.68 | 357.26 | 356.85 | 353.71 |

0.3 | 528.69 | 510.67 | 506.15 | 503.35 | 504.53 | 504.51 | 502.59 | |

0.5 | 608.85 | 596.84 | 592.29 | 585.94 | 579.40 | 576.22 | 574.05 | |

CF | 0.1 | 153.27 | 149.63 | 148.75 | 148.30 | 148.46 | 147.80 | 146.56 |

0.3 | 257.65 | 254.87 | 253.62 | 251.58 | 248.56 | 246.32 | 244.47 | |

0.5 | 263.06 | 261.04 | 260.07 | 258.44 | 255.66 | 253.17 | 250.86 | |

SF | 0.1 | 149.92 | 146.38 | 145.51 | 145.06 | 145.17 | 144.51 | 143.30 |

0.3 | 247.41 | 245.02 | 243.86 | 241.81 | 238.61 | 236.30 | 234.48 | |

0.5 | 248.50 | 246.92 | 246.06 | 244.45 | 241.51 | 238.95 | 236.67 |

_{0} | ||||||||

E_{1}E_{1} | 0.1 | 368.31 | 356.53 | 354.28 | 354.66 | 358.44 | 358.13 | 355.04 |

0.3 | 558.81 | 545.07 | 542.41 | 542.83 | 548.35 | 550.42 | 549.32 | |

0.5 | 669.03 | 660.42 | 657.10 | 652.86 | 649.27 | 647.64 | 645.98 | |

E_{2}E_{2} | 0.1 | 82.564 | 91.860 | 95.778 | 101.94 | 109.61 | 113.78 | 116.41 |

0.3 | 381.14 | 384.20 | 386.62 | 392.04 | 400.91 | 405.96 | 408.78 | |

0.5 | 539.57 | 539.80 | 540.83 | 544.12 | 551.17 | 556.07 | 559.18 | |

E_{3}E_{3} | 0.1 | 80.874 | 89.444 | 93.013 | 98.592 | 105.46 | 109.13 | 111.41 |

0.3 | 331.30 | 347.67 | 354.18 | 364.51 | 377.62 | 384.51 | 388.49 | |

0.5 | 515.44 | 522.81 | 525.80 | 531.29 | 539.88 | 545.19 | 548.45 |

Advertisement## 4. Conclusions

A new 3-D exact solution for free vibration analysis of thick functionally graded plates and cylindrical shells with arbitrary boundary conditions is presented in this chapter. The effective material properties of functionally graded structures vary continuously in the thickness direction according to the simple power-law distributions in terms of volume fraction of constituents and are estimated by Voigt’s rule of mixture. By using the artificial spring boundary technique, the general boundary conditions can be obtained by setting proper spring stiffness. All displacements of the functionally graded plates and shells are expanded in the form of the linear superposition of standard 3-D cosine series and several supplementary functions, which are introduced to remove potential discontinuity problems with the original displacements along the edge. The Rayleigh-Ritz procedure is used to yield the accurate solutions. The convergence, accuracy and reliability of this formulation are verified by numerical examples and by comparng the current results with those in published literature. The influence of the geometrical parameters and elastic foundation on the frequencies of rectangular plates and cylindrical shells is investigated.

Advertisement## Acknowledgments

The authors gratefully acknowledge the financial support from the National Natural Science Foundation of China (Nos. 51175098 and 51279035) and the Fundamental Research Funds for the Central Universities of China (No. HEUCFQ1401).

- 1.
Zhang D., Zhou Y. A theoretical analysis of FGM thin plates based on physical neutral surface. Computational Material Science. 2008; 44: 716–20. - 2.
Chi S., Chung Y. Mechanical behavior of functionally graded material plates under transverse load – Part Ⅰ: Analysis. International Journal of Solids and Structures. 2006; 43: 3657–74. - 3.
Chi S., Chung Y. Mechanical behavior of functionally graded material plates under transverse load – Part Ⅱ: Numerical results. International Journal of Solids and Structures. 2006; 43: 3675–91. - 4.
Latifi M., Farhatnia F., Kadkhodaei M. Bucking analysis of rectangular functionally graded plates under various edge conditions using Fourier series expansion. European Journal of Mechanics – A/Solids. 2013; 41: 16–27. - 5.
Zhao X., Lee Y.Y., Liew K.M. Free vibration analysis of functionally graded plates using the element-free kp-Ritz method. Journal of Sound and Vibration. 2009; 319: 918–39. - 6.
Hosseini-Hashemi S., Rokni Damavandi Taher H., Akhavan H., Omidi M. Free vibration of functionally graded rectangular plates using first-order shear deformation plate theory. Applied Mathematical Modelling. 2010; 34: 1276–91. - 7.
Hosseini-Hashemi S., Fadaee M., Atashipour S.R. A new exact analytical approach for free vibration of Reissner-Mindlin functionally graded rectangular plates. International Journal of Mechanical Sciences. 2011; 53: 11–22. - 8.
Ferreira A.J.M., Batra R.C., Roque C.M.C., Qian L.F., Jorge R.M.N. Natural frequencies of functionally graded plates by a meshless method. Composite Structures. 2006; 75: 593–600. - 9.
Fallah A., Aghdam M.M., Kargarnovin M.H. Free vibration analysis of moderately thick functionally graded plates on elastic foundation using extended Kantorovich method. Archive of Applied Mechanics. 2013; 83: 177–91. - 10.
Croce L.D., Venini P. Finite elements for functionally graded Reissner-Mindlin plates. Compute Methods in Applied Mechanics and Engineering. 2004; 193: 705–25. - 11.
Kadoli R., Ganesan N. Buckling and free vibration analysis of functionally graded cylindrical shells subjected to a temperature-specified boundary condition. Journal of Sound and Vibration. 2006; 289(3): 450–80. - 12.
Tornabene F. Free vibration analysis of functionally graded conical, cylindrical shell and annular plate structures with a four-parameter power-law distribution. Computer Methods in Applied Mechanics and Engineering. 2009; 198(37): 2911–35. - 13.
Tornabene F., Viola E., Inman D.J. 2-D differential quadrature solution for vibration analysis of functionally graded conical, cylindrical shell and annular plate structures. Journal of Sound and Vibration. 2009; 328(3): 259–90. - 14.
Sheng G.G., Wang X. Thermomechanical vibration analysis of a functionally graded shell with flowing fluid. European Journal of Mechanics – A/Solids. 2008; 27(6): 1075–87. - 15.
Jin G.Y., Xie X., Liu Z.G. The Haar wavelet method for free vibration analysis of functionally graded cylindrical shells based on the shear deformation theory. Composite Structures. 2014; 108: 435–48. - 16.
Qu Y.G., Long X.H., Yuan G.Q., Meng G. A unified formulation for vibration analysis of functionally graded shells of revolution with arbitrary boundary conditions. Composites Part B: Engineering. 2013; 50: 381–402. - 17.
Reddy J.N. Analysis of functionally graded plates. International Journal of Numerical Methods in Engineering. 2000; 47: 663–84. - 18.
Hosseini-Hashemi S., Fadaee M., Atashipour S.R. Study on the free vibration of thick functionally graded rectangular plates according to a new exact closed-form procedure. Composite Structures. 2011; 93: 722–35. - 19.
Baferani A.H., Saidi A.R., Ehteshami H. Accurate solution for free vibration analysis of functionally graded thick rectangular plates resting on elastic foundation. Composite Structures. 2011; 93: 1842–53. - 20.
Matsunaga H. Free vibration and stability of functionally graded plates according to a 2-D higher-order deformation theory. Composite Structures. 2008; 82: 499–512. - 21.
Ferreira A.J.M., Batra R.C., Roque C.M.C., Qian L.F., Martins P.A.L.S. Static analysis of functionally graded plates using third-order shear deformation theory and a meshless method. Composite Structures. 2005; 69: 449–57. - 22.
Qian L.F., Batra R.C., Chen L.M. Static and dynamic deformations of thick functionally graded elastic plates by using higher-order shear and normal deformable plate theory and meshless local Petrov-Galerkin method. Composites Part B: Engineering. 2004; 35: 685–97. - 23.
Najafizadeh M.M., Isvandzibaei M.R. Vibration of functionally graded cylindrical shells based on higher order shear deformation plate theory with ring support. Acta Mechanica. 2007; 191(1–2): 75–91. - 24.
Matsunaga H. Free vibration and stability of functionally graded circular cylindrical shells according to a 2D higher-order deformation theory. Composite Structures. 2009; 88(4): 519–31. - 25.
Viola E., Rossetti L., Fantuzzi N. Numerical investigation of functionally graded cylindrical shells and panels using the generalized unconstrained third order theory coupled with the stress recovery. Composite Structures. 2012; 94(12): 3736–58. - 26.
Zozulya V.V., Zhang C. A high order theory for functionally graded axisymmetric cylindrical shells. International Journal of Mechanical Sciences. 2012; 60(1): 12–22. - 27.
Vel S.S., Batra R.C. Three-dimensional exact solution for the vibration of functionally graded rectangular plates. Journal of Sound and Vibration. 2004; 272: 703–30. - 28.
Reddy J.N., Cheng Z.Q. Three-dimensional thermoelastic deformations of a functionally graded elliptic plate. Composites Part B: Engineering. 2000; 31: 97–106. - 29.
Amini M.H., Soleimani M., Rastgoo A. Three-dimensional free vibration analysis of functionally graded material plates resting on an elastic foundation. Smart Materials and Structure. 2009; 18: 1–9. - 30.
Malekzadeh P. Three-dimensional free vibration analysis of thick functionally graded plates on elastic foundations. Composite Structures. 2009; 89: 367–73. - 31.
Malekzadeha P., Faridb M., Zahedinejadc P., Karamid G. Three-dimensional free vibration analysis of thick cylindrical shells resting on two-parameter elastic supports. Journal of Sound and Vibration. 2008; 313: 655–75. - 32.
Huang C.S., Yang P.J., Chang M.J. Three-dimensional vibration analyses of functionally graded material rectangular plates with through internal cracks. Composite Structures. 2012; 94(9): 2764–76. - 33.
Santos H., Mota Soares C.M., Mota Soares C.A., Reddy J.N. A semi-analytical finite element model for the analysis of cylindrical shells made of functionally graded materials. Composite Structures. 2009; 91(4): 427–32. - 34.
Qu Y.G., Meng G. Three-dimensional elasticity solution for vibration analysis of functionally graded hollow and solid bodies of revolution. Part I: Theory. European Journal of Mechanics – A/Solids. 2014; 44: 222–33. - 35.
Qu Y.G., Meng G. Three-dimensional elasticity solution for vibration analysis of functionally graded hollow and solid bodies of revolution. Part II: Application. European Journal of Mechanics – A/Solids. 2014; 44: 234–48. - 36.
Saada A.S. Elasticity: Theory and applications. 2nd ed. Florida: Ross Publishing, Inc; 2009. - 37.
Shen H.S. Functionally graded materials: Nonlinear analysis of plates and shells. Florida: CRC Press; 2009. - 38.
Li W.L. Vibration analysis of rectangular plates with general elastic boundary supports. Journal of Sound and Vibration. 2004; 273(3): 619–35. - 39.
Beslin O., Nicolas J. A hierarchical functions set for predicting very high order plate bending modes with any boundary conditions. Journal of Sound and Vibration. 1997; 202(5): 633–55. - 40.
Ye T.G., Jin G.Y., Shi S.X., Ma X.L. Three-dimensional free vibration analysis of thick cylindrical shells with general end conditions and resting on elastic foundations. International Journal of Mechanical Sciences. 2014; 84: 120–37. - 41.
Jin G.Y., Su Z., Shi S.X., Ye T.G., Gao S.Y. Three-dimensional exact solution for the free vibration of arbitrarily thick functionally graded rectangular plates with general boundary conditions. Composite Structures. 2014; 108: 565–77. - 42.
Su Z., Jin G.Y., Ye T.G. Three-dimensional vibration analysis of thick functionally graded conical, cylindrical shell and annular plate structures with arbitrary elastic restraints. Composite Structures. 2014; 118: 432–47. - 43.
Jin G.Y., Su Z., Ye T.G., Jia X.Z. Three-dimensional vibration analysis of isotropic and orthotropic conical shells with elastic boundary restraints. International Journal of Mechanical Sciences. 2014; 89: 207–21.

Submitted: May 27th, 2015 Reviewed: February 1st, 2016 Published: March 31st, 2016

© 2016 The Author(s). Licensee IntechOpen. This chapter is distributed under the terms of the Creative Commons Attribution 3.0 License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.