Efficient Quadrature Solution for Composite Plates with Variable Thickness Resting on
Non-Uniform and Nonlinear Elastic Foundation

Ola Ragb; M. S. Matbuly

doi:10.17577/IJERTV8IS120057

Volume 08, Issue 12 (December 2019)

Efficient Quadrature Solution for Composite Plates with Variable Thickness Resting on Non-Uniform and Nonlinear Elastic Foundation

DOI : 10.17577/IJERTV8IS120057

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Authors : Ola Ragb , M. S. Matbuly
Paper ID : IJERTV8IS120057
Volume & Issue : Volume 08, Issue 12 (December 2019)
Published (First Online): 11-12-2019
ISSN (Online) : 2278-0181
Publisher Name : IJERT
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Efficient Quadrature Solution for Composite Plates with Variable Thickness Resting on Non-Uniform and Nonlinear Elastic Foundation

Ola Ragb*, M. S. Matbuly

Department of Physics and Engineering Mathematics, Faculty of Engineering, Zagazig University,

P.O. 44519, Zagazig, Egypt

AbstractTwo Different schemes are examined for vibration analysis of composite plate with variable thickness resting on non-uniform and nonlinear elastic foundation problems. On the basis of first order transverse shear theory a basic equation of vibration is derived. Investigations are made over non-uniform and nonlinear Winkler and uniform Pasternak foundation model. Examined schemes are based on discrete singular convolution and moving least square differential quadrature method. Also, the obtained nonlinear algebraic system is solved by using iterative quadrature technique. This problem is solved for different boundary conditions, different shear correction factor and varying thickness in one and two directions. Numerical analysis is applied to investigate influence of different computational characteristics on convergence and accuracy of the obtained results. The obtained results agreed with the previous analytical and numerical ones. Further a parametric study is introduced to explore the influence of elastic and geometric characteristics of the vibrated plate, on results.

KeywordsComposite; Vibration; Shear Correction Factor; Non-uniform Elastic Foundation; Nonlinear Winkler Foundation; Variable Thickness; Discrete Singular Convolution; Moving Least Square.

INTRODUCTION

Non-uniform elastic plates with varying thickness are commonly used in ship and offshore structures, pavement of roads, footing of buildings and bases of machines. Therefore, the vibration analysis of like plates is of great importance for practical design and structural components.

Depending upon the requirement, durability and reliability, materials are being developed so that these may provide better strength, efficiency and economy. Therefore a study of character and behavior of these plates is required so that the full potential of these plates may be used. So, these plates have been studied analytically and numerically. In most cases, their closed form solutions are extremely difficult to establish. But, for some special cases of variable thickness of rectangular plate, investigations have been made and solutions have been obtained [1-4].The most commonly used numerical methods for such applications are Spline function approximation technique [5-6], Rayleigh-Ritz

method [7-8], Mesh-free method[9], Mixed boundary node method [10], Finite strip method [11] and Finite element method [12], have been widely applied for the plate resting on uniform elastic foundation. Most of these studies are computationally expensive.

In seeking a more efficient numerical method is differential quadrature method (DQM) which requires fewer grid points yet achieves acceptable accuracy [13-15]. By applying DQM, the free vibration problem of plate is translated into the eigenvalue problem. According to the selection of basis functions and influence domain for each point, there are more than versions of DQM. Discrete singular convolution differential quadrature method (DSCDQM) [16-18], Moving least square differential quadrature method (MLSDQM) [19-21] are the most reliable versions. DSCDQ method is that they exhibit exponential convergence of spectral methods while having the flexibility of local methods for complex boundary conditions. MLSDQ exploits the merits of both the DQ and meshless method.

The main aim of present work to apply two different schemes,( DSCDQM and MLSDQM) to solve vibration problems of composite plates with varying thickness. These plates are resting on non-uniform and nonlinear Winkler and uniform Pasternak elastic foundation. Based on a transverse shear theory, the governing equations of the problem are formulated. The unknown field quantities and their derivatives are approximated using DQ approximations. Then the obtained nonlinear algebraic system is solved by using iterative quadrature technique. The program of MATLAB is designed to solve the reduced eign-value problem. Numerical analysis is implemented to investigate convergence and efficiency of each scheme. Accuracy of the obtained results is compared with the existing previous results. Further a parametric study is introduced to investigate the influence of elastic and geometric characteristics on natural frequencies and mode shapes.
FORMULATION OF THE PROBLEM

Consider a composite consisting of n plates interfacialy bonded with variable thickness h(x,y) and resting on non-uniform and nonlinear elastic foundation of Winkler and uniform Pasternak type , as shown in Fig.(1).

D (x , y ) E h 3 (x , y ) / [12(1 2 )]
is the flexural rigidity

of the plate. G, E and v are shear modulus, Youngs modulus and Poisson's ratio of the plate. k is the shear correction factor [25-27].

Assuming harmonic behavior of the problem, the field quantities can be written as:

x (x , y ,t ) x e i t ,

Fig.1 Composite Plate with Variable Thickness resting on Non-uniform and Nonlinear Winkler- Pasternak Foundation.

y (x , y ,t ) y e i t ,

w (x , y ,t ) W e i t

(5)

Each plate occupies (ai 1 x ai , 0 y b, i 1,n) ,

Where is the natural frequency of the plate and

where a and b are width and length of the composite.

Based on a first-order shear deformation theory, the equations of motion for each plate can be written as [20, 22]:

i 1 .

x , y ,W are the amplitudes for x , y , and w ,

2 (1 ) 2 (1 ) 2 y

respectively.

D (x , y ) x x

x 2 2 y 2 2 x y

(1)

Substituting from Eq.(5) into (1-4), One can reduce the

kGh (x , y ) w

2

x I1 x ,

problem to:

2 2 2

x

t 2

x

(1 ) x

(1 ) y

D(x, y)

2 2 x2

2 y2 2 xy

y

y

D (x , y )

(1 ) y

(1 ) 2x

(6)

y 2

2 x 2

2 x y

(2)

W 2

kGh(x, y) x

x

I1x ,

y 1

y 1

kGh (x , y ) w

y

I

2 y

,

t 2

2

(1 ) 2

(1 ) 2

2w

2w

D(x, y) y y

x

kGh (x , y )

x

y

y2 2 x2

2 xy

x 2

y 2 x

y

(3)

(7)

3 2w 2w 2w

kGh(x, y) W

2 I ,

2 0

2 0

K1 (x )w
- K 3w
  
  K 2 x 2
  
  I
  
  y
  
  t 2
  
  y y 1 y
  
  Where Io and I1 are mass moments of inertias [23]:
  
  h /2
  
  2W
  
  kGh(x, y)
  
  2W
  
  x
  
  y 3
  
  K1(x)W K3W
  
  0 x2
  
  y2 x
  
  y
  
  (8)
  
  I0 , I1
  
  (1 , z2 ) dz,
  
  (4)
  
  h0 /2
  
  2W
  
  K2 x2
  
  2W
  
  y2
  
  2 I0W
  
  is the plate mass density. K
  
  1 (x ) K1
  
  (1 x / a)
  
  is the non-uniform Winkler foundation stiffness which linearly varying along x-direction. is variation parameter of stiffness of foundaion. K2 is shear modulus of foundation
  
  Boundary conditions can be expressed as follows:
  - Clamped edge:
    
    reaction.
    
    K 3 is the non-linear Winkler foundation. t: time.
    
    W 0,
    
    nx y
    - ny x
      
      0,
      
      x (x , y ,t ),y (x , y ,t ),w (x , y ,t ) are normal strain
      
      n n 0
      
      (9)
      
      rotations and transverse deflection [24].
      
      The thickness variation function of plate is
      
      x x y y
      
      h(x , y ) h0 (1 x / a)(1 y / b). h0 is the constant
      
      reference thickness value and , are variation parameter of thickness.
  - Simply Supporting of the first kind: SS1
    
    (x ,b )
    
    W 0,
    
    W (x ,b
    
    i ) W (x ,bi ),
    - D ( x i
      
      x
      
      (x ,b )
      
      (x ,b )
      
      (x ,b )
      
      (n 2 n 2 ) x
      
      (1 )n n
      
      x
      
      y i ) D ( x i y i ),
      
      x y x
      
      x y y
      
      1
      
      y
      
      x (x ,bi )
      
      x y
      
      y (x ,bi )
      
      (13)
      
      x y
      
      x y
      
      ( n 2 n 2 ) y
      
      y
      
      (1 )nx ny
      
      y 0,
      
      x
      
      (10)
      
      2
      
      1
      
      ( y
      
      (x ,b )
      
      x )
      
      (x ,b )
      
      1
      
      D ((n 2 n 2 ) x 2n n
      
      x
      
      ( x i
      
      2 y
      
      y i ), (i 1, n )
      
      x
      
      2 x y y
      
      x y x
      
      (n 2 n 2 ) y x y x
      
      2n n y ) 0
      
      x y y
SOLUTION OF THE PROBLEM

Two different differential quadrature techniques are employed to reduce the governing equations into nonlinear eigenvalue problem, as follows [16-21]:
- Simply Supporting of the second kind: SS2
  
  W 0, nx y ny x 0,
- Discrete Singular Convolution Differential Quadrature Method (DSCDQM)
  
  In this technique, regularized Shannon kernel (RSK) may be used as a shape function such that the unknown u(x)
  
  (n 2 n 2 ) x (1 )n n x
  
  (11)
  
  and its derivatives can be approximated over a narrow
  
  x y
  
  ( n 2 n 2 )
  
  x
  
  y
  
  x y
  
  (1 )n n
  
  y
  
  x 0
  
  bandwidth
  
  ( x x M , x x M ) as [16-18]:
  
  2
  
  x y x y
  
  M sin[ (x x ) / h ]
  ( (x i x j ) )
  
  y x
  
  u (x )
  
  i j x e
  
  2 2
  
  u (x
  
  ), (14)
  
  i (x x ) / h j
- Free edge:
j M i j x

(i N , N ),

kG h (n

W n

W n
- n
) 0,

x x

y y

x x y y

where hx is the step size, 2M+1 is the effective

(n 2 n 2 ) x

(1 )n n

x

computational band width, is regularization parameter,

x y

x y

x y

( n 2 n 2 )

x

y

y

x y

(1 )nx ny

y

y 0,

x

(12)

= r hx and r is a computational parameter.

Derivatives of u, can be approximated as a weighted linear sum of ui , (i=-N,N) as [16-18]:

1 D ((n 2 n 2 ) x
- 2n n
x

u M x

2 x y y

x y x

x x x

i j M

Cij u (x j ),

(15)

2 2 y

y

y

(nx n ) x

y
- 2nx ny y ) 0
  
  2u
  
  x 2
  
  x x
  
  M
  
  ij j
  
  ij j
  
  C xx u (x ),
  
  i N , N ,
  
  nx and ny are the directional cosines at a point on the
  
  Where
  
  i j M
  
  boundary edge.
  
  Along the interface between ith plate and (i+1) th one, the
  
  (1)i j
  
  hx (
  
  e
  
  (i j )2
  
  2 2 ) ,
  
  i j
  
  continuity boundary conditions can be described as:
  
  hx (i j )
  
  C
  
  C
  
  x
  
  ij
  
  0
  
  0
  
  ,
  
  i j
  
  (16)
  
  i j 1
  
  2 (i j )2
  
  x by minimizing the following weighted quadratic for
  
  ( 2(1)
  
  hx 2 (i j )2
  
  xx
  
  1 )e
  
  2
  
  hx ( 2 2 ) ,
  1. j
    1. N 1
      
      h 2
      
      C ij
      
      1 2
      
      (a) (x – xi )(u
      
      i 1
      
      (xi ) ui )
      
      (20)
      
      1
      
      1
      
      i j
      
      2
      
      3hx 2
      
      N
      
      (x – xi )(PT (xi )a(x) ui )2
      
      i 1
      
      Similarly, one can approximateu y ,u yy and calculated
      
      C
      
      C
      
      , C
      
      , C
      
      y yy
      
      ij ij .
      - Moving Least Squares Differential Quadrature Method (MLSDQM)
        
        Where (x-xi) is a positive weight function defined over the influence domain, (i, i=1,N)
        
        The stationary value of (a) with respect to a(x) leads to a linear equation, such as:
        
        In this technique, the influence domain, (i, i=1: N), for each node is determined as shown in Fig. (2). Over each
        
        A(x)a(x) B(x)u
        
        (21)
        
        influence domain, the nodal unknowns can be approximated as [19-21]:
        
        from which
        
        a(x) A1 (x)B(x)u , (22)
        
        u (xi ) u h
        
        N
        
        1
        
        1
        
        (xi ) j (xi ) u (x j ),(i 1, N ),
        
        (18)
        
        where
        
        T
        
        j 1
        
        A(x) P(xi ) i (x)P
        
        (xi )
        
        1
        
        1
        
        N
        
        i i
        
        i i
        
        n
        
        n
        
        i 1
        
        (x)P(x )PT
        
        (xi ),
        
        u=u1 u2
        
        u T ,
        
        B(x)=P(x) (x)
        
        1 (x)P(x1)
        
        2 (x)P(x2 )
        
        n (x)P(xn )
        
        .
        
        Fig.2 Domain discretization for moving least
        
        On suitable substitution from Eq. (22) into (19), uh(x) can then be expressed as:
        
        u h (x) PT (x)a(x)
        
        1
        
        1
        
        i
        
        i
        
        N
        
        squares differential quadrature.
        
        PT (x)A1 (x)B
        
        xu=i (x)ui
        
        (23)
        
        Where the shape function j (xi
        
        ) can be obtained using
        
        i 1
        
        MLS approximation as follows:
        
        Where the nodal shape function:
        
        Let
        
        m
        
        i
        
        i
        
        u h (x) Pi (x)ai (x) PT
        
        (x)a(x),
        
        (19)
        
        i (x) = PT (x)A1 (x) B
        
        x
        
        (24)
        
        i 1
        
        W here a(x) a (x),a (x), ,a
        
        (x) T is a vector of
        
        Determination of the shape function i (x) and its partial
        
        1 2 m
        
        unknown coefficients.
        
        derivatives can be simplified as follows [19-21]:
        
        i x PT xA1 xBi x T xBi x
        
        (25)
        
        PT (x) p1 (x), p2 (x), , pm (x) is a complete set
        
        of monomial basis. m is the number of basis terms. The coefficients aj (x),( j 1, m ) , can be obtained at any point
        
        Since A(x) is a symmetric matrix, then obtained through
        
        Ax x P x
        
        x
        
        can be
        
        (26)
        
        Therefore, the problem of determination of the shape function is reduced to solution of Eq.(26). This Equation can be solved using LU decomposition and back-substitution, which requires fewer computations than the inversion of
        
        A(x). Further, the first and second order partial derivatives of
        
        W i 0,
        
        n i n i 0, n i
        
        n
        
        n
        
        y y
        
        y y
        
        j (xi ) can be determined as follows [19-21]:
        
        x y y x x x
        
        Differentiate Eq. (26) with respect to L, K, (L, K =X,Y) such as:
        
        i 0, (i 1, N )
        
        (34)
        
        A(x),L (x) P,L (x) A,L (x) (x),
        
        Simply supporting of the first kind: SS1
        
        (L X ,Y )
        
        (27)
        
        W i 0,
        
        N (n 2 n 2 ) c x (1 )n n c y j
        
        x y ij x y ij x
        
        0,
        
        A(x),LK (x) P,LK (x) A,LK (x)(x)
        
        j 1 ( n 2 n 2 )c y
        
        (1 )n n c x j
        
        (35)
        
        (28)
        
        x y ij x y ij y
        
        A,L (x),K (x) A,K (x),L (x), (L, K X ,Y )
        
        N (n 2 n 2 ) c y 2n n c x j
        
        1 D ij
        
        x y ij x y ij x
        
        0,
        
        2 j 1 (n 2 n 2 ) c x 2n n c y j
        
        The first and second order partial derivatives of the shape function can be described as:
        
        x y ij x y ij y
        
        (i 1, N )
        
        (x ) c L (x ) T (x )B (x )
      - Simply supporting of the second kind: SS2
      j ,L i j i j ,L i j i
      
      T (x )B (x
      
      ), (L x , y ),
      
      (29)
      
      W i 0,
      
      n i n i
      
      0,
      
      j i j ,L i
      
      x y y x
      
      N (n 2 n 2 )c x (1 )n n c y j
      
      (x ) c LK (x ) T
      
      (x )B (x )
      
      x y ij x y ij x
      
      0
      
      j ,LK i j i j ,LK i j i
      
      j 1 ( n 2 n 2 )c y (1 )n n c x j
      
      (36)
      
      T (x )B (x ) T (x )B (x ) T
      
      (x )B (x ),
      
      x y ij x y ij y
  2. i j ,LK i j ,L i j ,K i j ,K i j ,L i
  (L, K x , y )
  
  (30)
  - Free edge:
  (i 1, N )
  
  On suitable substitution from Eqs.(14-30) into (6-8), the problem can be reduced to the following nonlinear eigenvalue problem:
  
  N
  
  N
  
  x ij y ij x x y y
  
  x ij y ij x x y y
  
  kG h ij ((n c x n c y )W j ) kG h ij (n i n i ) 0,
  
  j 1
  
  N (n 2 n 2 )c x (1 )n n c y j
  
  kGhij c xW j D ij c xx 1 c yy kGh ij j
  
  x y ij x y ij x
  
  0,
  
  N ij
  
  ij
  
  2 ij
  
  x
  
  j 1 ( n 2 n 2 )c y (1 )n n c x j
  
  (37)
  
  x y ij x y ij y
  
  j 1 D ij 1 c x c y j
  
  (31)
  
  N (n 2 n 2 )c y 2n n c x j
  
  2 ik kj y
  
  1 D ij x y ij x y ij x
  
  0
  
  2
  
  2 2 x y j
  
  2 I j , (i , k 1, N )
  
  j 1 (nx ny )cij 2nx ny cij y
  
  1 x (i 1, N )
  
  kGhij c yW
  
  j D ij 1 c x c y
  
  j
  
  N ij
  
  2 ik
  
  kj x

NUMERICAL RESULTS

j 1 D ij c yy

1 c xx

kGhij j

(32)

This section presents numerical results that

ij

2 ij

y

demonstrate convergence and efficiency of each one of

the proposed schemes for vibration analysis of non-

y

2 I1 j , (i , k

N

kGhij c xx

1, N )

c yy W

j c x j c y j

uniform and nonlinear Winkler and uniform Pasternak foundation of composite plate. This plate varying with thickness. For all results, the boundary conditions (34-37) are augmented in the governing equations (31-33). Then

j 1

ij ij

ij x

ij y

the obtained nonlinear algebraic system is solved by

K c xx

c yy

W j K iW

j K

(W 2 )W j

(33)

using

u

iterative quadrature

ar f

technique

[34]. The

e

2 ij ij 1 3

comp tational ch acteristics o each schem are adapted

2 I 0W j , (i 1, N )

to reach accurate results with error of order 10-10. The obtained frequencies are normalized such as:

The boundary conditions (9-13) can also be approximated using DQMs as:

Clamped edge:

( I (20 ) where 0 is the fundamental

frequency of isotropic squared plate.

For DSCDQ scheme based on regularized Shannon kernel (RSK), the problem is also solved over a uniform grids ranging from 7*7 to 19*19. The bandwidth 2M+1

ranges from 5 to 15 and the regularization parameter = r hx ranges from 1.5hx to 3 hx , where hx =1/N-1.

Table (1) shows convergence of the obtained

fundamental frequency to the exact and numerical ones [28-31] over grid size 13*13, bandwidth 11 and regulization parameter = 2.82 hx.

TABLE. 1 Comparison between the fundamental frequency due to DSCDQM-RSK with the bandwidth 2M+1

fundamental frequency	Number of grid points		9	11	13	15	17
fundamental frequency	regularization parameter	Band width	9	11	13	15	17
DSCDQM- RSK	=1.8 hx	2M+1 =7	2.03	2.46	2.74	2.89	2.9545
		2M+1 =9	2.23	2.69	2.82	2.93	2.9736
		2M+1 =11	2.58	2.88	2.91	2.95	2.9828
		2M+1 =13	2.79	2.92	2.96	2.99	2.9991
	=2.4 hx	2M+1 =7	2.29	2.64	2.83	2.92	2.9683
		2M+1 =9	2.52	2.72	2.88	2.96	2.9743
		2M+1 =11	2.61	2.91	2.94	2.98	2.9915
		2M+1 =13	2.86	2.95	2.99	2.99	2.9976
	=2.62 hx	2M+1 =7	2.58	2.72	2.89	2.96	2.9697
		2M+1 =9	2.70	2.85	2.94	2.99	2.9953
		2M+1 =11	2.76	2.94	2.99	3.01	3.0224
		2M+1 =13	2.89	2.98	3.01	3.02	3.0213
	=2.82 hx	2M+1 =7	2.86	2.92	2.98	2.99	3.0026
		2M+1 =9	2.89	2.98	2.99	3.005	3.0141
		2M+1 =11	2.94	2.99	3.02	3.022	3.0215
		2M+1 =13	2.97	3.01	3.02	3.022	3.0215
Exact results [28]			3.0215
Ritz method[29]			3.0214
Radial basis[30]			3.0216
Element free Galerkin[31] (15×15)			3.0225

fundamental frequency	Number of grid points		9	11	13	15	17
fundamental frequency	regularization parameter	Band width	9	11	13	15	17
DSCDQM- RSK	=1.8 hx	2M+1 =7	2.03	2.46	2.74	2.89	2.9545
		2M+1 =9	2.23	2.69	2.82	2.93	2.9736
		2M+1 =11	2.58	2.88	2.91	2.95	2.9828
		2M+1 =13	2.79	2.92	2.96	2.99	2.9991
	=2.4 hx	2M+1 =7	2.29	2.64	2.83	2.92	29683
		2M+1 =9	2.52	2.72	2.88	2.96	2.9743
		2M+1 =11	2.61	2.91	2.94	2.98	2.9915
		2M+1 =13	2.86	2.95	2.99	2.99	2.9976
	=2.62 hx	2M+1 =7	2.58	2.72	2.89	2.96	2.9697
		2M+1 =9	2.70	2.85	2.94	2.99	2.9953
		2M+1 =11	2.76	2.94	2.99	3.01	3.0224
		2M+1 =13	2.89	2.98	3.01	3.02	3.0213
	=2.82 hx	2M+1 =7	2.86	2.92	2.98	2.99	3.0026
		2M+1 =9	2.89	2.98	2.99	3.005	3.0141
		2M+1 =11	2.94	2.99	3.02	3.022	3.0215
		2M+1 =13	2.97	3.01	3.02	3.022	3.0215
Exact results [28]			3.0215
Ritz method[29]			3.0214
Radial basis[30]			3.0216
Element free Galerkin[31] (15×15)			3.0225

,regularization parameter , the grid points N and the previous results for a regular discretized isotropic simply supported squared plate:( h0/a=0.01,v=0.3, k=5/6,K1=500,=0,=0,=0, K2=0, K3=0).

For MLSDQ scheme, circular influence domain, (i, i=1,N), is considered as shown in Fig.2. Gaussian weight function is employed such as [19-21]:

size 11*11 , completeness order 4 and raduis of support domain dmax = 5 .

TABLE.2 Comparison between the fundamental frequency due to MLSDQM with the radius of support domain dmax completeness order Nc , the grid points N and the previous results for a regular discretized isotropic simply supported squared plate: (h/a=0.01,v=0.3, k=5/6, K1=100,=0,=0,=0, K2=0, K3=0).

fundamental frequency	Number of grid points		7	9	11	13
fundamental frequency	completeness order	Radius of support domain	7	9	11	13
MLSDQM	Nc=2	dmax =5	2.64	2.516	2.446	2.4509
		dmax =6	2.31	2.295	2.272	2.2612
		dmax =7	2.26	2.254	2.251	2.2491
		dmax =8	2.25	2.247	2.246	2.2436
	Nc =3	dmax =5	2.25	2.245	2.245	2.2441
		dmax =6	2.25	2.243	2.243	2.2421
		dmax =7	2.24	2.242	2.242	2.2414
		dmax =8	2.24	2.241	2.241	2.2413
	Nc =4	dmax =5	2.24	2.241	2.2413	2.2413
		dmax =6	2.24	2.241	2.2413	2.2413
		dmax =7	2.24	2.241	2.2413	2.2413
		dmax =8	2.24	2.241	2.2413	2.2413
	Nc =5	dmax =5	2.74	2.244	2.2413	2.2413
		dmax =6	2.25	2.249	2.2413	2.2413
		dmax =7	2.26	2.241	2.2413	2.2413
		dmax =8	2.26	2.241	2.2413	2.2413
Exact results [28]			2.2413
Ritz method[29]			2.2413
Radial basis[30]			2.2414
Element free Galerkin[31] (15×15)			2.2427

Table (3) shows that the best value of Shear factor correction is to be taken (5 /6-v). Tables (3,4) show that the fundamental frequency decrease with increasing Poisson ratio and Shear factor correction. Also ,the value of shear factor correction helps to achieve more accurate results.

TABLE.3 Comparison between the fundamental frequency, Poisson , shear factor correction K and the previous results

exp((d

i

/ c )2 ) exp((r / c )2 )

Poisson ratio v	Discrete Green function [33]	=	= ( + ( )) (( ))	= ( + ( )) ( ( ))	=	=
0.15		8.1424	8.1638	8.1639	8.164	8.163
0.23	8.1110	8.1110	8.1112	8.1112	8.111	8.111
0.3		8.0640	8.04586	8.0460	8.046	8.046
0.5		7.8090	7.7430	7.7432	7.743	7.744

Poisson ratio v	Discrete Green function [33]	=	= ( + ( )) (( ))	= ( + ( )) ( ( ))	=	=
0.15		8.1424	8.1638	8.1639	8.164	8.163
0.23	8.1110	8.1110	8.1112	8.1112	8.111	8.111
0.3		8.0640	8.04586	8.0460	8.046	8.046
0.5		7.8090	7.7430	7.7432	7.743	7.744

2

di r

(38)

for CCCS squared plate: (h0/a=0.01, K1=0,=0.5,=0.5,=0, K =0 , K =0,E /E =2.45).

w i (x )

0

1 exp((r / c ) )

di r

2 3 1 2

Where di is the distance from a nodal point xi

to a field one

x located in the influence domain of xi. r is the radius of support domain and c is the dilation parameter. In the present work, the dilation parameter is selected such as: c=r/4.

The scheme is employed with varying completeness order Nc ranges from 2 to 5 and the raduis of support domain dmax = r/ hx ranges from 4 to 9. Also, the problem is also solved over a uniform grids ranging from 5*5 to 19*19. Table (2) shows convergence of the obtained fundamental frequency to the exact and numerical ones [28-31] over grid

Boundary coditions	natural frequency		1	2	3	Execution time (sec)
Boundary coditions	variable thickness	results	1	2	3	Execution time (sec)
SSSS	=0	DSCDQM- RSK	4.902	7.253	8.374	1.780280
		MLSDQM	4.902	7.253	8.374	1.839144
		Element free Galerkin [31]	4.900	7.256	8.382
		Discrete Green function [33]	4.902	7.253	8.374
	=0.4	DSCDQM- RSK	5.360	7.928	9.150	1.889903
		MLSDQM	5.360	7.928	9.150	1.918841
		Element free Galerkin [31]	5.356	7.931	9.159
		Discrete Green function [33]	5.360	7.928	9.150
	=0.8	DSCDQM- RSK	5.770	8.525	9.831	1.900178
		MLSDQM	5.770	8.525	9.831	1.928867
		Element free Galerkin [31]	5.772	8.529	9.845
		Discrete Green function [33]	5.770	8.525	9.831
CCCC	=0	DSCDQM- RSK	6.780	8.953	10.29	1.632990
		MLSDQM	6.780	8.953	10.29	1.646533
		Element free Galerkin [31]	6.748	8.905	10.24
		Discrete Green function [33]	6.780	8.953	10.29
	=0.4	DSCDQM- RSK	7.402	9.770	11.23	1.716354
		MLSDQM	7.402	9.770	11.23	1.726170
		Element free Galerkin [31]	7.371	9.723	11.18
		Discrete Green function [33]	7.402	9.770	11.23
	=0.8	DSCDQM- RSK	7.945	10.48	12.05	1.731625
		MLSDQM	7.945	10.48	12.05	1.742609
		Element free Galerkin [31]	7.915	10.43	12.01
		Discrete Green function [33]	7.945	10.48	12.05

Boundary coditions	natural frequency		1	2	3	Execution time (sec)
Boundary coditions	variable thickness	results	1	2	3	Execution time (sec)
SSSS	=0	DSCDQM- RSK	4.902	7.253	8.374	1.780280
		MLSDQM	4.902	7.253	8.374	1.839144
		Element free Galerkin [31]	4.900	7.256	8.382
		Discrete Green function [33]	4.902	7.253	8.374
	=0.4	DSCDQM- RSK	5.360	7.928	9.150	1.889903
		MLSDQM	5.360	7.928	9.150	1.918841
		Element free Galerkin [31]	5.356	7.931	9.159
		Discrete Green function [33]	5.360	7.928	9.150
	=0.8	DSCDQM- RSK	5.770	8.525	9.831	1.900178
		MLSDQM	5.770	8.525	9.831	1.928867
		Element free Galerkin [31]	5.772	8.529	9.845
		Discrete Green function [33]	5.770	8.525	9.831
CCCC	=0	DSCDQM- RSK	6.780	8.953	10.29	1.632990
		MLSDQM	6.780	8.953	10.29	1.646533
		Element free Galerkin [31]	6.748	8.905	10.24
		Discrete Green function [33]	6.780	8.953	10.29
	=0.4	DSCDQM- RSK	7.402	9.770	11.23	1.716354
		MLSDQM	7.402	9.770	11.23	1.726170
		Element free Galerkin [31]	7.371	9.723	11.18
		Discrete Green function [33]	7.402	9.770	11.23
	=0.8	DSCDQM- RSK	7.945	10.48	12.05	1.731625
		MLSDQM	7.945	10.48	12.05	1.742609
		Element free Galerkin [31]	7.915	10.43	12.01
		Discrete Green function [33]	7.945	10.48	12.05

TABLE.4 Comparison between the fundamental frequency, Poisson , shear facor correction K and different boundary condition for squared plate: (h /a=0.01, K =100,=0,=0,=0,

0 1

K2=50 , K3=0,E1/E2=2.45).

Poisson ratio v	shear factor correction =	SSSS	CCCC	CSSS	CCSC
0.15	0.8547	3.9382	5.20912	4.2312	4.87028
0.23	0.8666	3.9207	5.18596	4.2123	4.84863
0.3	0.8772	3.8935	5.1501	4.1831	4.8151
0.5	0.9091	3.7429	4.95105	4.0213	4.62899

Tables (5, 6) show that execution time of DSCDQM-RSK scheme is less than that of MLSDQM. Therefore, it is more efficient than MLSDQM for vibration analysis of variable thickness, non-uniform and nonlinear elastically supported composite plate.

TABLE. 5 Comparison between the obtained natural frequencies and the previous results for isotropic clamped plate: (h0/a=0.015,v=0.15 ,=0,=0,=0, K2=0,K3=0).

Subgrade reaction	K1=1390.2			K1=2780.4			Execution time (sec)
Results		2	3	1	2	3	Execution time (sec)
MLSDQM (11×11), Nc=4 and dmax =5	5.245	8.316	8.316	6.463	9.132	9.132	1.676119
DSCDQM- RSK(13×13) =2.82hx and M=5	5.245	8.316	8.316	6.463	9.132	9.132	1.656792
Mixed finite element [32]	5.245	8.316	8.316	6.463	9.132	9.132
Element free Galerkin[31]	5.267	8.391	8.392	6.477	9.202	9.203
Ritz method[29 ]	5.259	8.432	8.432	6.460	9.248	9.248
Radial basis[30 ]	5.244	8.313	8.313	6.463	9.130	9.130

Also, for different boundary conditions and varying thickness in one and two directions, tables (6,7) insist that DSCDQM-RSK scheme is the best choice for such problem.

TABLE. 6 Comparison between the natural frequency due to DSCDQM-RSK and MLSDQM with the variable thickness in one direction ,different boundary conditions and the previous results for a squared plate: (h/a=0.01,E1/E2=2.45 v=0.23, K1=0, =0, K2=0,K3=0).

TABLE. 7 Comparison between the natural frequency due to DSCDQM-RSK and MLSDQM with the variable thickness , in two direction ,different boundary conditions and the previous results for a squared plate: (h0/a=0.01,E1/E2=2.45, v=0.23, K1=0, K2=0, K3=0).

Boundary coditions	natural frequency
	variable thickness		results
			results
SSSS	-0.5	-0.5	DSCDQM- RSK	3.635	5.335	6.087
			MLSDQM	3.635	5.335	6.087
			Element free Galerkin [31]	3.633	5.3460	6.0957
			Discrete Green function [33]	3.635	5.335	6.087
	-0.5	0.5	DSCDQM- RSK	4.704	6.937	7.966
			MLSDQM	4.704	6.937	7.966
			Element free Galerkin [31]	4.707	6.9422	7.9751
			Discrete Green function [33]	4.704	6.937	7.966
	0.5	-0.5	DSCDQM- RSK	4.708	6.933	7.904
			MLSDQM	4.708	6.933	7.904
			Element free Galerkin [31]	4.708	6.9420	7.9146
			Discrete Green function [33]	4.708	6.933	7.904
	0.5	0.5	DSCDQM- RSK	6.086	9.022	10.350
			MLSDQM	6.086	9.022	10.350
			Element free Galerkin [31]	6.099	9.013	10.359
			Discrete Green function [33]	6.086	9.022	10.350
CCCC	-0.5	-0.5	DSCDQM- RSK	4.955	6.548	7.440
			MLSDQM	4.955	6.548	7.440
			Element free Galerkin [31]	4.936	6.532	7.4167
			Discrete Green function [33]	4.955	6.548	7.440
	-0.5	0.5	DSCDQM- RSK	6.453	8.510	9.748
			MLSDQM	6.453	8.510	9.748
			Element free Galerkin [31]	6.427	8.481	9.715
			Discrete Green function [33]	6.453	8.510	9.748
	0.5	-0.5	DSCDQM- RSK	6.447	8.525	9.671
			MLSDQM	6.447	8.525	9.671
			Element free Galerkin [31]	6.420	8.501	9.639
			Discrete Green function [33]	6.45	8.525	9.671
	0.5	0.5	DSCDQM- RSK	8.390	11.076	12.666
			MLSDQM	8.390	11.076	12.666
			Element free Galerkin [31]	8.36	11.040	12.632
			Discrete Gree function [33]	8.390	11.076	12.666

Boundary coditions	natural frequency
	variable thickness		results
			results
SSSS	-0.5	-0.5	DSCDQM- RSK	3.635	5.335	6.087
			MLSDQM	3.635	5.335	6.087
			Element free Galerkin [31]	3.633	5.3460	6.0957
			Discrete Green function [33]	3.635	5.335	6.087
	-0.5	0.5	DSCDQM- RSK	4.704	6.937	7.966
			MLSDQM	4.704	6.937	7.966
			Element free Galerkin [31]	4.707	6.9422	7.9751
			Discrete Green function [33]	4.704	6.937	7.966
	0.5	-0.5	DSCDQM- RSK	4.708	6.933	7.904
			MLSDQM	4.708	6.933	7.904
			Element free Galerkin [31]	4.708	6.9420	7.9146
			Discrete Green function [33]	4.708	6.933	7.904
	0.5	0.5	DSCDQM- RSK	6.086	9.022	10.350
			MLSDQM	6.086	9.022	10.350
			Element free Galerkin [31]	6.099	9.013	10.359
			Discrete Green function [33]	6.086	9.022	10.350
CCCC	-0.5	-0.5	DSCDQM- RSK	4.955	6.548	7.440
			MLSDQM	4.955	6.548	7.440
			Element free Galerkin [31]	4.936	6.532	7.4167
			Discrete Green function [33]	4.955	6.548	7.440
	-0.5	0.5	DSCDQM- RSK	6.453	8.510	9.748
			MLSDQM	6.453	8.510	9.748
			Element free Galerkin [31]	6.427	8.481	9.715
			Discrete Green function [33]	6.453	8.510	9.748
	0.5	-0.5	DSCDQM- RSK	6.447	8.525	9.671
			MLSDQM	6.447	8.525	9.671
			Element free Galerkin [31]	6.420	8.501	9.639
			Discrete Green function [33]	6.45	8.525	9.671
	0.5	0.5	DSCDQM- RSK	8.390	11.076	12.666
			MLSDQM	8.390	11.076	12.666
			Element free Galerkin [31]	8.36	11.040	12.632
			Discrete Green function [33]	8.390	11.076	12.666

Furthermore, a parametric study is introduced to investigate the influence of elastic and geometric characteristics of the composite on the values of natural frequencies.

Figures (3-15) show that the natural frequencies decrease with increasing variable thickness (, ), Young's modulus gradation ratio and thickness ratio. As well as, Figs. (3- 10,12-13) show that the natural frequencies are increased with increasing variation parameter of foundation stiffness , Winkler and Pasternak foundation, shear modulus gradation ratio and aspect ratio a/b . The case of (E1=E2=E3=E4=E5, G1=G2=G3=G4=G5 and p=p=p=h4=p) is a limiting case of this study which was previously solved in [28] and [29-33]. Figures(12-15) show the first three mode shapes of the vibration waves along the interface.Furthermore, Figs.(14-

show that the amplitudes of W increase with increasing linear and nonlinear elastic foundation parameters.Also, these figures show that the natural frequencies do not affect significantly by nonlinear elastic foundation parameter k3.

Normalized fundamental frequency

Normalized fundamental frequency

28

26 =1000

24

22 =500

20

18

16 =100

14

12

10 =0

8

6

-1.0 -0.8 -0.6 -0.4 -0.2 0.0 0.2 0.4 0.6 0.8 1.0
1. Thickness variable
  
  Normalized fundamental frequency
  
  Normalized fundamental frequency
  
  28
  
  26 =1000
  
  24
  
  22 =500
  
  20
  
  18
  
  16 =100
  
  14
  
  12
  
  10 =0
  
  8
  
  6
  
  -1.0 -0.8 -0.6 -0.4 -0.2 0.0 0.2 0.4 0.6 0.8 1.0
2. Thickness variable

FIG. 3 Variation of the normalized fundamental frequency withthickness variable (, ) and non-uniform Winkler foundationfor squared simply supported plates. A: =0, B: =0.5(K1=1000, K2=0,K3=0).

Normalized fundamental frequency

44 42

42 40

=1000

40 38

38

=500

36

36 =100 34

34

32

32 =0 30

30

28

=1000

=500

=100

=0

-1.0 -0.8 -0.6 -0.4 -0.2 0.0 0.2 0.4 0.6 0.8 1.0

Thikness variable

-1.0 -0.8 -0.6 -0.4 -0.2 0.0 0.2 0.4 0.6 0.8 1.0
Thikness variable

Normalized fundamental frequency

42

40 =1000

38 =500

36 =100

34

FIG. 5 Variation of the normalized fundamental frequency with thickness variable (, )

,non-uniform ,nonlinear Winkler and Pasternak foundation for squared simply supported plates. A: =0, B: =0.5 (K1=1000, K2=10, K3=50)

Normalized fundamental frequency

32 =0 18

30

28 15

-1.0 -0.8 -0.6 -0.4 -0.2 0.0 0.2 0.4 0.6 0.8 1.0

B Thikness variable

12

=-0.5,-0.5

9 =0.5,0.5

FIG. 4 Variation of the normalized fundamental frequency with thickness variable (, ) and non-uniform Winkler and uniform Pasternak foundation for squared simply

supported plates. A: =0, B: =0.5 (K1=1000, K2=10,K3=0)

Normalized fundamental frequency

44

=-0.5,0.5

=0.5,0.5

6

3

0 2000 4000 6000 8000 10000

A

42

=1000

40

38 =500

36 =100

34

32 =0

30

28

27

Normalized fundamental frequency

Normalized fundamental fequency

24

21

18 =-0.5,-0.5

15 =0.5,0.5

12 =-0.5,0.5

=0.5,0.5

9

6

-1.0 -0.8 -0.6 -0.4 -0.2 0.0 0.2 0.4 0.6 0.8 1.0

Thikness variable

3

0 2000 4000 6000 8000 10000

FIG. 6 Variation of the normalized fundamental frequency with thickness variable (, ) and non-uniform Winkler foundation for squared simply supported plates . A: K1=10, B: K1=100 ( K2=0,K3=0)

Normalized fundamental frequency

30

28

26

24 =-0.5,-0.5

22 =0.5,0.5

=-0.5,0.5

20

=0.5,0.5

18

16

0 2000 4000 6000 8000 10000

51

Normalized fundamental frequency

Normalized fundamental frequency

48

45

42

39 =-0.5,-0.5

36 =0.5,0.5

33

30 =-0.5,0.5

27 =0.5,0.5

24

21

18

0 2000 4000 6000 8000 10000

Normalized fundamental frequency

51

48

45

42

39 =-0.5,-0.5

36 =0.5,0.5

33

30 =-0.5,0.5

27 =0.5,0.5

24

21

18

FIG. 8 Variation of the normalized fundamental frequency with thickness variable (, ) and non-uniform, nonlinear Winkler and Pasternak foundation for squared simply supported plates. A: K1=10, B: K1=100 ( K2=10,K3=100)

60

54

Natural frequencies

48

42

0 2000 4000

B

6000 8000 10000

36

30 E3=E2=0.2E1

E5=0.2E4

FIG. 7 Variation of the normalized fundamental frequency 24

E3=E2=E1=E4=E5=1

E4=E5=2E1

with thickness variable (, ) and non-uniform 18

E =E =E =3E

Winkler and Pasternak foundation for squared

12 E3=0.3E2 E =E =E =5E

1 4 5 2

simply supported plates. A: K1=10, B: K1=100 ( K2=10,K3=0)

3 2 1 4

6

0

Normalized fundamental frequency

30

28

26

24 =-0.5,-0.5

-0.5 -0.4 -0.3 -0.2 -0.1 0.0 0.1 0.2 0.3 0.4 0.5

A Location along the interface.

60

54

Natural frequencies

48

42

22 =0.5,0.5

=-0.5,0.5

20

=0.5,0.5

36

30 G1=G4=G5=1.5G2

24

G4=G5=2G1

G5=1.75G4 G3=G2=G1=G4=G5=1

18

16

0 2000 4000 6000 8000 10000

A

18 G3=0.75G2

12

6

0

G3=G2=G1=0.5G4 G3=G2=0.25G1

-0.5 -0.4 -0.3 -0.2 -0.1 0.0 0.1 0.2 0.3 0.4 0.5

B Location along the interface.

FIG. 9 Variation of the natural frequencies with Young's and Shear modulus gradation ratio of a squared simply supported composite (K1=100, K2=10,K3=50, h0/a=0.01,=1000, =-0.5, =-0.5, v1=v2=v3=v4=v5).

250

225

Natural frequencies

200

175

150

125

a1=a4=a5=3a2

a5=4a4

48

Natural frequencies

42

36

h =h =0.5h

100 a =a =2a

3 2 1

30

p=p=p=.7h4

h =h =h =h =h =1

4 5 1

75

p=.6p

24

3 2 1 4 5

50

3 2

a =(2/3)a

25 a =a =0.5a

a =a =a =.75a

a3=a2=a1=a4=a5=1

18 h =h =h =3h

h4=p=2p

3 2 1

0

3 2 1 4

1 4 5 2

p=4h4

-0.5 -0.4 -0.3 -0.2 -0.1 0.0 0.1 0.2 0.3 0.4 0.5

A Location along the interface.

130

120

110

Natural frequencies

100

90

12

-0.5 -0.4 -0.3 -0.2 -0.1 0.0 0.1 0.2 0.3 0.4 0.5

B Location along the interface.

FIG. 11 Variation of the natural frequencies with thickness of a squared elastically supported composite. A: Simply supported plates, B: Clamped plates

80

70 a1=a4=a5=3a2

60

50

40

30

a5=4a4

a4=a5=2a1

0.100

(K1=1000, K2=1000, K3=1000, =1000, =-0.5, =-0.5;E1=E2=E3=E4=E5, G1=G2=G3=G4=G5, v1=v2=v3=v4=v5).

20 a3=(2/3)a2

a =a =a =a =a =1

10 a3=a2=0.5a1 a3=a2=a1=.75a4

0

3 2 1 4 5

Lateral mode shape: w

0.075

Fundamental mode

-0.5 -0.4 -0.3 -0.2 -0.1 0.0 0.1 0.2 0.3 0.4 0.5

B Location along the interface.

FIG. 10 Variation of the natural frequencies with aspect ratio (a/b) and thickness (h/a) for Clamped composite plates. A: h0/a=0.01, B: h0/a=0.1 (K1=500, K2=100, K3=100,=1000, =-0.5, =- 0.5;E1=E2=E3=E4=E5, G1=G2=G3=G4=G5,

v1=v2=v3=v4=v5).

0.050

0.025

0.000

-0.025

Second mode Third mode

50 A

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

Time along the interface: (x, y=0)

45

Natural frequencies

40

35 h =h =0.5h

0.25

Lateral mode shape: w

0.20

Fundamental mode

3 2 1

30

p=p=p=.7h4

h =h =h =h =h =1

0.15

25 p=.6p

3 2 1 4 5

20

p=h4=p=3p

15

10

h4=p=2p

p=4h4

0.10

0.05

0.00

Second mode

Third mode

-0.5 -0.4 -0.3 -0.2 -0.1 0.0 0.1 0.2 0.3 0.4 0.5

Location along the interface.

-0.05

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0
Time along the interface: (x, y=0)

FIG. 12 Variation of the lateral mode shapes with time and non-uniform Winkler foundation for squared clamped plate at =0, =0,K2=0,K3=0, =1000. A: K1=10, B: K1=100

0.150

Lateral mode shape: w

0.125

0.100

0.075

0.050

0.025

0.000

-0.025

-0.050

Fundamental mode

Second mode Third mode

0.440

0.385

Lateral mode shape: w

0.330

0.275

0.220

0.165

0.110

0.055

0.000

Fundamental mode

Second mode Third mode

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

Time along the interface: (x, y=0)

0.385

Fundamental mode

-0.055

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0
Time along the interface: (x, y=0)

FIG. 14 Variation of the lateral mode shapes with time and non-uniform and nonlinear Winkler

Lateral mode shape: w

0.330

0.275

0.220

0.165

0.110

0.055

0.000

-0.055

Second mode Third mode

0.200

0.175

Lateral mode shape: w

0.150

0.125

foundation for squared clamped plate at =-0.5, =0.5,K2=0, K3=100, =1000. A: K1=10, B: K1=500

Fundamental mode

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

B Time along the interface: (x, y=0)

FIG. 13 Variation of the lateral mode shapes with time and non-uniform Winkler and Pasternak foundation for squared clamped plate at =-0.5, =0.5,K2=100, K3=0, =1000. A: K1=10, B: K1=500

0.100

0.075

0.050

0.025

0.000

-0.025

-0.050

Second mode Third mode

0.150

0.125

Fundamental mode

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

A Time along the interface: (x, y=0)

0.585

Lateral mode shape: w

0.100

0.075

0.050

0.025

0.000

-0.025

-0.050

Second mode Third mode

0.520

Lateral mode shape: w

0.455

0.390

0.325

0.260

0.195

0.130

0.065

0.000

-0.065

Fundamental mode

Second mode Third mode

A

0.150

Lateral mode shape: w

0.125

0.100

0.075

0.050

0.025

0.000

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

Time along the interface: (x, y=0)

Fundamental mode

Second mode Third mode

-0.130

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

B Time along the interface: (x, y=0)

FIG. 15 Variation of the lateral mode shapes with time and non-uniform and nonlinear Winkler and Pasternak foundation for squared clamped plate at =-0.5, =0.5,K2=100, K3=100, =1000. A: K1=10, B: K1=500

-0.025

-0.050

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

Time along the interface: (x, y=0)

CONCLUSION

Different Quadrature schemes have been successfully applied for vibration analysis of composite plate with variable thickness resting on non-uniform and nonlinear elastic foundation. Iterative quadrature technique is used to solve the nonlinear algebraic system. A matlab program is designed for each scheme such that the maximum error (comparing with the previous exact results) is 1010 . Also, Execution time for each scheme, is determined. It is concluded that discrete singular convolution differential quadrature method based on regularized Shannon kernel (DSCDQM-RSK) with grid size 13*13 , bandwidth 2M+1

11 and regulization parameter = 2.82 hx leads to best accurate efficient results for the concerned problem. shear factor correction (K=5/6-v )is considered for such problem. Based on this scheme, a parametric study is introduced to investigate the influence of elastic and geometric characteristics of the vibrated plate, on results. It is aimed that these results may be useful for design purposes of engineering fields.

REFERENCES

Y. P. Xu , D. Zhou, Three-dimensional elasticity solution for simply supported rectangular plates with variable thickness, Journal of Strain Analysis for Engineering Design, 43 (2008)165-
Y. Xu, D. Zhou, K. Liu, Three-dimensional thermo elastic analysis of rectangular plates with variable thickness subjected to thermo- mechanical loads, Journal of Thermal Stresses, 33 (2010) 1136- 1155.
A.H. Sofiyev, H.M. Halilov, N. Kuruoglu, Anal1y7ti6c.al solution of the dynamic behavior of non-homogenous orthotropic cylindrical shells on elastic foundations under moving loads, Journal of Engineering Mathematics , 69(2011) 359371.
D. Shi, H. Zhang, Q. Wang, S. Zha, Free and Forced Vibration of the Moderately Thick Laminated Composite Rectangular Plate on Various Elastic Winkler and Pasternak Foundations, Shock and Vibration, 2017 (2017) 1-24.
K.K. Viswanathan, P.V. Navaneethakrishnan , Z. A. Aziz, Buckling Analysis of Rectangular Plates with Variable Thickness Resting on Elastic Foundation, Earth and Environmental Science, 23 (2015) 1-8.
K.K. Viswanathan, J. Saira, A. A. Zainal, Free Vibration of Symmetric Angle-Ply Laminated Conical Shell Frusta of Variable Thickness including Shear Deformation Theory by Spline Method. Structural Engineering & Mechanics, An International Journal, 45 (2013) 259- 275.
S. Chakraverty, K. K. Pradhan, Free Vibration Of Functionally Graded Thin Rectangular Plates Resting On Winkler Elastic Foundation With General Boundary Conditions Using RayleighRitz Method, Int. J. Appl. Mechanics, 6(2014).
A. Khanna, A. K. Sharma, Vibration Analysis Of Visco- Elastic Square Plate Of Variable Thickness With Thermal Gradient, International Journal of Engineering and Applied Sciences (IJEAS), 3 (2011) 1-6.
L. Chen, Y. M. Cheng, The complex variable reproducing kernel particle method for bending problems of thin plates on elastic foundations, Computational Mechanics, 62, (2018) 6780.
M. Huang, J. Ma, J. N. Tang , H. Yuan, Mixed boundary node method for free vibration analysis of rectangular plates with variable thickness and general boundary conditions, WIT Transactions on Modelling and Simulation, 56(2013).
A. S. Ashour, vibration of variable thickness plates with edges elastically restrained against rotational and translation,Thin-Walled Structures, 42(2004) 1-24.
H. Zafarmand, M. Kadkhodayan, Free vibration analysis of thick disks with variable thickness containing orthotropic and nonhomogeneous material using finite element method , Journal of theoretical and applied mechanics , 53(2015) 1005-1018.
V. Tahouneh, Free vibration analysis of bidirectional functionally graded annular plates resting on elastic foundations using differential quadrature method, Structural Engineering and Mechanics, 52(2014) 663-686.
R. Saini, R. Lal, Transverse Vibration of Non-Homogeneous Rectangular Plates of Variable Thickness Using GDQ, International Journal of Computer and Information Engineering, 8(2014)1197- 1202.
A. G. Arani, M. Khani , Z. K. Maraghi, Dynamic analysis of a rectangular porous plate resting on an elastic foundation using high- order shear deformation theory, Journal of Vibration and Control , 24, (2018) 37133698.
O.Ragb, M.Mohamed, M.S. Matbuly, Free Vibration of a Piezoelectric Nanobeam Resting on Nonlinear Winkler-Pasternak Foundation by Quadrature Methods , Heliyon, 5(2019) e01856.
O.Ragb, M.Mohamed, M.S. Matbuly , Vibration Analysis of Magneto-Electro-Thermo NanoBeam Resting on Nonlinear Elastic Foundation Using Sinc and Discrete Singular Convolution Differential Quadrature Method , Modern Applied Science, 13(2019)
O.Ragb, M. salah, M.S. Matbuly, R.M. Amer, Vibration analysis of piezoelectric composite using Sinc and Discrete Singular Convolution differential quadrature techniques , Journal of Engineering and Applied Sciences, (2019)6540-6553.
A. Sayyidmousavi, M. Foroutan, Z. Fawaz, Free Vibration Analysis of Functionally Graded Nanocomposite Beams on Elastic Foundation Using a Mesh-Free Method, Latin American Journal of Solids and Structures, 14 (2017) 2107-2122.
O. Ragb, M.S. Matbuly, M. Nassar, Analysis Of Composite plates Using Moving Least Squares Differential Quadrature Method,Applied Mathematics and Computation, , 238(2014) 225-236.
R.M. Dastjerdi, G. Payganeh , S.R.Mirakabad, M. J. M.Taheri, Static and Free Vibration Analyses of Functionally Graded Nano composite Plates Reinforced by Wavy Carbon Nanotubes Resting on a Pasternak Elastic Foundation, Mechanics of Advanced Composite Structures, 3 (2016) 123-135.
V.Panc. , Theory of elastic plates, Leydon : Noordhoff International Publishing, (1975) 13-41.
J.N. Reddy, Mechanics of Laminated Composite Plates. Theory and Analysis, CRC Press, Boca Raton, FL(1997).
J.N. Reddy, Theory and analysis of elastic plates, Taylor& Francis: Philadelphia, PA(1999).
V. Birman , C. W. Bert, On the Choice of Shear Correction Factor in Sandwich Structures, Journal of Sandwich Structures and Materials , 4 (2002) 8395.
V.Birman , C. W. Bert, Effect of Shear Correction Factor on Response of Cross-ply Laminated Plates using FSDT, Defence Science Journal, 55 (2005) 377-387.
F. Gruttmann, W. Wagner, Shear correction factors for layered plates and shells,Comput Mech, 59 (2017) 129146.
Y. Xiang, C. M. Wang , S. Kitipornchai, Exact vibration solution for initially stressed Mindlin plates on Pasternak foundation, International Journal of Mechanic Science, 36 , (1994) 311-316.
D. Zhou, Y. K. Cheung, S. H. Lo , F. T. K. Au, Three dimensional vibration analysis of rectangular thick plates on Pasternak foundation, International Journal of Numerical Methods in Engineering, 59 (2004) 1313-1334.
J. M. Ferreira, C. M. C. Roque, A. M. A. Neves, R. M. N. Jorge , C.

M. M. Soares, Analysis of plates on Pasternak foundations by radial basis functions, Computational Mechanics, 46(2010)791-803.
E. Bahmyari, A. R. Ranji, Free vibration analysis of orthotropic plates with variable thickness resting on non-uniform elastic foundation by element freeGalerkin method,Journal of Mechanical Science and Technology, 26 (2012) 2685-2694.
M. H. Omurtag, A.Ozutok , A. Y. Akoz, Free vibration analysis of Kirchhoff plates resting on elastic foundation by mixed finite element formulation based on gateaux differential, International Journal of Numerical Methods in Engineering, 40 (1997) 295-317.
M. Huang, X. Q. Ma, T.Sakiyama, H. Matuda, C. Morita, Free vibration analysis of orthotropic rectangular plates with variable thickness and general boundary conditions, Journal of Sound and Vibration, 288(2005) 931-955.
O. Ragb, L. F. Seddek, M. S. Matbuly, Iterative differential quadrature solutions for Bratu problem, Computers & Mathematics with Applications , 74, 2 (2017) 249-257.

Efficient Quadrature Solution for Composite Plates with Variable Thickness Resting on Non-Uniform and Nonlinear Elastic Foundation

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