Static Flexure of Soft Core Sandwich Beams using Trigonometric Shear Deformation Theory

Document Type: Research Paper

Authors

1 Department of Civil Engineering, SRES’s College of Engineering, Savitribai Phule Pune University, Kopargaon, Maharashtra, India

2 Department of Applied Mechanics, Government College of Engineering, Karad, Maharashtra, India

Abstract

This study deals with the applications of a trigonometric shear deformation theory considering the effect of the transverse shear deformation on the static flexural analysis of the soft core sandwich beams. The theory gives realistic variation of the transverse shear stress through the thickness, and satisfies the transverse shear stress free conditions at the top and bottom surfaces of the beam. The theory does not require a problem-dependent shear correction factor. The governing differential equations and the associated boundary conditions of the present theory are obtained using the principle of the virtual work. The closed-form solutions for the beams with simply supported boundary conditions are obtained using Navier solution technique. Several types of sandwich beams are considered for the detailed numerical study. The axial displacement, transverse displacement, normal and transverse shear stresses are presented in a non-dimensional form and are compared with the previously published results. The transverse shear stress continuity is maintained at the layer interface, using the equilibrium equations of elasticity theory.

Keywords



 

 

Mechanics of Advanced Composite Structures 2 (2015) 45-53

 

 

 

 

 

 

Semnan University

Mechanics of Advanced Composite Structures

journal homepage: http://macs.journals.semnan.ac.ir

 

Static Flexure of Soft Core Sandwich Beams using Trigonometric Shear Deformation Theory

A.S. Sayyada*, Y.M. Ghugalb

a Department of Civil Engineering, SRES’s College of Engineering, Savitribai Phule Pune University, Kopargaon, Maharashtra, India

b Department of Applied Mechanics, Government College of Engineering, Karad, Maharashtra, India

 

Paper INFO

 

ABSTRACT

Paper history:

Received 17 April 2015

Received in revised form 6 November 2015

Accepted 7 November 2015

This study deals with the applications of a trigonometric shear deformation theory considering the effect of the transverse shear deformation on the static flexural analysis of the soft core sandwich beams. The theory gives realistic variation of the transverse shear stress through the thickness, and satisfies the transverse shear stress free conditions at the top and bottom surfaces of the beam. The theory does not require a problem-dependent shear correction factor. The governing differential equations and the associated boundary conditions of the present theory are obtained using the principle of the virtual work. The closed-form solutions for the beams with simply supported boundary conditions are obtained using Navier solution technique. Several types of sandwich beams are considered for the detailed numerical study. The axial displacement, transverse displacement, normal and transverse shear stresses are presented in a non-dimensional form and are compared with the previously published results. The transverse shear stress continuity is maintained at the layer interface, using the equilibrium equations of elasticity theory.

 

Keywords:

Laminated beam

Soft core

Sandwich beam

Flexure

Trigonometric shear deformation theory

 

 

© 2015 Published by Semnan University Press. All rights reserved.

 

 

  1. 1.      Introduction   

Sandwich beam is a special form of laminated composite beam which has stiff face sheets and light weight but thick core. The modulus of the core material is significantly lower than that of the face sheets. The main benefit of using the sandwich concept in the structural components is its high bending stiffness and high strength to weight ratio. In addition, the sandwich constructions are much preferred to conventional materials because of their superior mechanical and durability properties. Due to these properties the composite sandwich structures have been widely used in the automotive, aerospace, marine and other industrial applications. Therefore, the analytical study of the sandwich beams becomes increasingly important.

Since the Classical Beam Theory (CBT) neglects the effect of the shear deformation and the First-order Shear Deformation Theory (FSDT) of Timoshenko [1] requires a shear correction factor, these theories are not suitable for the analysis of the laminated composite and the sandwich beams. These limitations of CBT and FSDT have led to the development of the Higher-order Shear Deformation theories (HSDTs) taking into account the effect of the transverse shear deformation, obviating the need of a shear correction factor.

The beam theories can be developed by expanding the displacements in power series of the coordinate normal to the neutral axis. In principle, the theories developed by this means can be made as accurate as desired simply by including the sufficient number of terms in the series. These higher-order theories are cumbersome and computationally more demanding, because with an additional power of the thickness coordinate, an additional dependent variable is introduced into the theory. It has been noted by Lo et al. [2, 3] that due to the higher-order terms included in their theory, it has become inconvenient to use. This observation is more or less true for many other higher-order theories as well. Thus, there is a wide scope to develop a simple to use higher-order beam or plate theory.

Several theories have been proposed by researchers in the last two decades. Among many theories, some of the well-known theories are the parabolic shear deformation theories [4-5], the trigonometric shear deformation theory [6], the hyperbolic shear deformation theory [7] and the exponential shear deformation theory [8]. Recently, these theories are accounted into a unified shear deformation theory developed by Sayyad [9] and Sayyad et al. [10]. In accordance with Reddy’s third-order shear deformation theory, Sayyad [11] has developed the refined theories and applied them for the static and vibration analysis of the isotropic beams.

 Mechab et al. [12] studied the deformations of the short composite beams using the refined theories. Carrera and Giunta [13] developed refined beam theories based on a unified formulation. Carrera et al. [14, 15] carried out the static and free vibration analysis of laminated beams using polynomial, trigonometric, exponential and zig-zag theories. Giunta et al. [16] presented a thermo-mechanical analysis of isotropic and composite beams via collocating with radial basis functions. Chakrabarti et al. [17] and Chalak et al. [18] carried out a finite element analysis for the bending, buckling and free vibration of the soft core sandwich beams. Gherlone et al. [19] developed C0 beam elements based on the refined zig-zag theory for the multilayered laminated composite and sandwich beams.

In the class of Trigonometric Shear Deformation Theories (TSDTs), the shear deformation is assumed to be trigonometric with respect to the thickness coordinate. These theories are accounted cosine distribution of transverse shear stress. The TSDTs are taking into account the kinematics of higher-order theories more effectively without loss of the physics of the problem. Some of the well-known articles on trigonometric theories are published by Touratier [6], Shimpi and Ghugal [20], Ghugal and Shinde [21], Arya et al. [22], Sayyad and Ghugal [23], Mantari et al. [24], Ferreira et al. [25], Zenkour [26] and Sayyad et al. [27].  Recently, Dahake and Ghugal [28, 29] and Ghugal and Dahake [30] have applied the trigonometric shear deformation theory for the bending analysis of the single-layer isotropic beams with various boundary conditions using general solution technique.    

In the current study, a trigonometric shear deformation theory is applied for the bending analysis of the laminated composite and the soft core sandwich beams. The theory involves three unknowns. The theory satisfies the transverse shear stress free conditions at the top and bottom surfaces of the beam and does not require shear correction factor. The governing equations are obtained using the principle of the virtual work. The closed-form solutions for the beam with simply supported boundary conditions are obtained using Navier solution technique. The displacements and stresses of three different types of lamination scheme are obtained.

The exact elasticity solution for the three-layered (00/900/00) laminated composite developed by Pagano [31] is used as a basis for the comparison of the present results. However, the exact elasticity solutions for the three-layered (00/core/00) and five-layered (00/900/core/900/00) sandwich beams are not available in the literature. Authors have generated the numerical results using FSDT of Timoshenko [1], HSDT of Reddy [5] and CBT being not available. It is found that the present results are in excellent agreement with those of HSDT, FSDT, CBT and exact elasticity solution.   

  1. 2.      Sandwich Beam under Consideration

Consider a beam of length ‘L’ along x direction, width ‘b’ along y direction and thickness ‘h’ along z direction. The coordinate system and geometry of the beam under consideration are shown in Fig. 1. The beam consists of the face sheets at the top and bottom surfaces and the middle portion is made up of a soft core.

The beam is bounded in the region 0 ≤ xL,                -b/2 ≤ yb/2, -h/2 ≤ zh/2 in Cartesian coordinate system. u and w are the displacements in x and z directions, respectively.

 

 

Figure 1. The beam geometry and the coordinate system

 

 

 

2.1. The Assumptions made in the Theoretical Formulation

In the present equivalent single-layer trigonometric shear deformation theory, the theoretical formulation is based on the six following assumptions:

1)      The axial displacement u in x direction consists of two parts including (a) a displacement component analogous to the displacement in the classical beam theory and (b) a displacement component due to the shear deformation which is assumed to be sinusoidal in nature with respect to the thickness coordinate.

2)      The transverse displacement w in the z direction is assumed to be a function of the x coordinate only.

3)      The beam is made up of ‘N’ number of layers which are perfectly bonded together.

4)      One dimensional Hooke’s law is used.

5)      The beam is subjected to the lateral load only.

6)      The body forces are ignored.

2.2. The Kinematics of the Present Theory

Based on the above mentioned assumptions, the displacement field of the present trigonometric shear deformation theory is written as:

           (1)

where u and w are the displacements in x and z directions, respectively and is the thickness coordinate. ,  and  are the unknown functions to be determined. The normal and shear strains obtained within the framework of the linear theory of elasticity are as follows:

                                     (2)

where

 and            (3)

‘, x’ represents the derivative with respect to x.     

2.3. The constitutive relations

The normal and transverse shear stresses are obtained using one-dimensional constitutive relations. These relations for the kth layer of the beam are given by the following equations:  

 (4)

where and  are the stiffness coefficients of the kth layer of the beam and are defined as follows:

and             

where is the Young’s modulus and is the shear modulus of k-th layer of the beam. 

  1. Governing Equations and Boundary Conditions

In order to derive the governing equations, the principle of the virtual work is used.

(5)

Using the expressions for strains from Eq. (2) and stresses from Eq. (4), the Eq. (5) can be written as:

        

(6)

Integrating Eq. (6) with respect to the z-direction, Eq. (6) can be simplified as:

           (8)

where Aij, Bij, etc. are the beam stiffnesses as defined below:

         (9)

Integrating Eq. (8) by the parts and setting the coefficients of , and equal to zero, we obtain the coupled Euler-Lagrange equations which are the governing differential equations and associated boundary conditions of the beam. The governing equations of the beam are as follow:

                  (10)               (11)            (12)

The associated consistent natural boundary conditions at the ends x = 0 and x = L are as follows:

   or      is prescribed                                   (13)                      

  or      is prescribed                                 (14)

 or    is   prescribed                                  (15)

 or      is  prescribed                                     (16)

where the resultants  are defined using the following equations:

         (17)

    (18)

(19)

Thus, the variationally consistent governing differential equations and boundary conditions are obtained.

  1. A static Flexure of Sandwich Beam

The Navier solution satisfies the governing differential equation and boundary conditions when the beam is simply supported at the ends. Therefore, a static flexural analysis of the simply supported laminated composite and the soft core sandwich beams subjected to transverse distributed load has been carried out using Navier solution technique. According to this technique, the following solution form for unknown functions  is assumed.

                                             (20)

where  and  are the unknown Fourier coefficients to be determined for each m value. A beam of length L and thickness h is considered. The transverse load acting on the top surface of the beam is expanded in the following form:

                    (21)

                       (22)                                                                                                  

where  is the maximum intensity of the load. Substituting the solution form from Eq. (20) and transverse load from Eqs. (21) and (22) into the three governing Eqs. (10)-(12), leads to the following set of simultaneous equatios.

                (23)

Eq. (23) can be solved to obtain the Fourier coefficients , and . Further, the final expressions for displacements and stresses are obtained using Eqs. (1)-(4). 

  1. Illustrative Examples and Numerical Results

To prove the efficacy of the present theory, it is applied to the flexural analysis of the following examples on the laminated composite and soft core sandwich beams.

Example 1:

A static flexure of the three-layered (00/900/00) laminated composite beams, as shown in Fig. 2 (a).

Example 2:

A static flexure of the three-layered (00/core/00) soft core sandwich beams, as shown in Fig. 2 (b).

Example 3:

A static flexure of the five-layered (00/900/core/900/00) soft core sandwich beams, as shown in Fig. 2 (c).

The following material properties are used in the above examples:

Example 1:

00 layer: Q11= 25×106 psi, Q55= 0.5×106 psi

900 layer: Q11= 1.0×106 psi, Q55= 0.2×106 psi

Examples 2 and 3:

Face sheets (00): Q11= 25×106 psi, Q55= 0.5×106 psi

Face sheets (900): Q11= 1.0×106 psi, Q55= 0.2×106 psi

Core: Q11= 0.04×106 psi, Q55= 0.06×106 psi.

The numerical results obtained for the displacements and stresses at the critical points are presented in the following non-dimensional form (Take E3 = 1).

        (24)

Example 1:

In this example, the bending response of the simply supported three-layered (0°/90°/0°) laminated composite beam is investigated as shown in Fig. 2 (a). The numerical results for the non-dimensional displacements and stresses are presented in Tables 1 and 2. For the comparison purpose, the numerical results are specially generated using the Higher-order Shear Deformation Theory (HSDT) of Reddy [5], the First-order Shear Deformation Theory (FSDT) of Timoshenko [1] and the Classical Beam Theory (CBT). The examination of Tables 1 and 2 reveals that when the laminated composite beam is subjected to the sinusoidal/uniform load, the displacements and normal stresses are in excellent agreement with those of Higher-order Shear Deformation Theory (HSDT) of Reddy [5]. The transverse shear stress is obtained using the equilibrium equation of the elasticity theory with the shear stress continuity at the layer interface.

 

 

 

Figure 2. The lamination scheme and the thickness coordinate for the simply supported beams

 

 

Table 1: The comparison of the axial displacement ( ), the transverse displacement ( ), the normal stress ( ), and the transverse shear stress (), for three-layered (0°/90°/0°) laminated composite beam subjected to the sinusoidal load

L/h

Theory

       

100

Present

8037.5

0.5148

6312.6

44.22

 

HSDT [5]

8034.9

0.5146

6310.6

44.27

 

FSDT [1]

8025.7

0.5135

6303.3

44.22

 

CBT

8025.7

0.5109

6303.3

44.22

 

Exact [31]

8040.0

0.5153

6315

44.15

10

Present

9.019

0.8836

70.853

4.320

 

HSDT [5]

8.939

0.8751

70.212

4.330

 

TSDT [27]

9.016

0.8828

70.836

4.322

 

FSDT [1]

8.025

0.8149

63.033

4.422

 

CBT

8.025

0.5109

63.033

4.420

 

Exact [31]

9.105

0.8800

71.300

4.200

4

Present

0.892

2.7340

17.540

1.532

 

HSDT [5]

0.865

2.7000

17.006

1.557

 

TSDT [27]

0.891

2.7252

17.500

1.528

 

FSDT [1]

0.514

2.4107

10.085

1.769

 

CBT

0.514

0.5109

10.085

1.769

 

Exact [31]

0.915

2.8870

17.880

1.425

 

The detailed procedure to obtain this stress using equilibrium equation is given by Sayyad et al. [27]. The through thickness distributions of axial displacement, normal stress and transverse shear stress are shown in Figs. 3-5.

 

 

 

 

Example 2:

This example investigates the bending response of the three-layered (0°/core/0°) soft core sandwich beams as shown in Fig. 2 (b). The beam has thin top and bottom face sheets of thickness 0.1h each and thick core of thickness 0.8h. The comparison of results for the beam subjected to the sinusoidal load is shown in Table 3.

 

Table 2: The comparison of the axial displacement ( ), the transverse displacement ( ), the normal stress ( ), and the transverse shear stress (), for the three-layered (0°/90°/0°) laminated composite beam subjected to the uniform load

L/h

Theory

       

100

Present

10386.3

0.6528

7786.5

68.239

 

HSDT [5]

10382.8

0.6527

7784.2

68.243

 

FSDT [1]

10368.6

0.6518

7776.7

68.387

 

CBT

10368.6

0.6480

7776.7

68.387

10

Present

11.844

1.108

85.68

6.042

 

HSDT [5]

11.733

1.098

85.03

6.090

 

FSDT [1]

10.368

1.023

77.76

6.838

 

CBT

10.368

0.648

77.76

6.838

4

Present

1.195

3.413

20.30

2.629

 

HSDT [5]

1.161

3.368

19.67

2.795

 

FSDT [1]

0.663

2.991

12.44

2.735

 

CBT

0.663

0.648

12.44

2.735

 

Table 3: The comparison of the axial displacement ( ), the transverse displacement ( ), the normal stress ( ), and the transverse shear stress (), for the three-layered (0°/core/0°) soft core sandwich beam subjected to the sinusoidal load

L/h

Theory

       

4

Present

1.7678

10.091

34.710

1.3732

 

HSDT [5]

1.7413

10.047

34.189

1.3681

 

FSDT [1]

1.0134

5.2868

19.898

1.4106

 

CBT

1.0134

1.0081

19.898

1.4106

10

Present

17.758

2.4887

139.47

3.5094

 

HSDT [5]

17.687

2.4805

138.91

3.5091

 

FSDT [1]

15.834

1.6927

124.36

3.5264

 

CBT

15.831

1.0081

124.36

3.5264

20

Present

130.55

1.3794

512.67

7.0451

 

HSDT [5]

130.39

1.3771

512.05

7.0441

 

FSDT [1]

126.67

1.1792

497.46

7.0528

 

CBT

126.67

1.0081

497.46

7.0528

50

Present

1989.3

1.0677

3124.8

17.6313

 

HSDT [5]

1988.6

1.0672

3123.7

17.6285

 

FSDT [1]

1979.3

1.0355

3109.1

17.6319

 

CBT

1979.3

1.0081

3109.1

17.6319

100

Present

15856

1.0231

12453

35.2678

 

HSDT [5]

15853

1.0229

12451

35.2624

 

FSDT [1]

15834

1.0149

12436

35.2639

 

CBT

15834

1.0081

12436

35.2639

 

 

Figure 3. The through thickness variation of the axial displacement for the three-layered (0°/90°/0°) laminated composite beam subjected to the sinusoidal load

 

 

 

Figure 4. The through thickness variation of the normal stress for the three-layered (0°/90°/0°) laminated composite beam subjected to the sinusoidal load

 

 

 

Figure 5. The through thickness variation of the transverse shear stress for the three-layered (0°/90°/0°) laminated composite beam subjected to the sinusoidal load

 

 

 

It is observed from the results that the present theory is in excellent agreement with HSDT to predict the bending response of soft core sandwich beams. The through thickness distributions of displacement and stresses are shown in Figs. 6-8.

 

Example 3:

In this example, the bending response of the five-layered (0°/90°/core/90°/0°) soft core sandwich beams is investigated as shown in Fig. 2 (c). The beam has two face sheets at the top and bottom and transversely flexible core at the center. The thickness of each face sheet is 0.05h each and thickness of core is 0.8h. The comparison of displacements and stresses for the beam subjected to the sinusoidal load is shown in Table 4 for various aspect ratios (L/h).

 

 

Figure 6. The through thickness variation of the axial displacement for the three-layered (0°/core/0°) soft core sandwich beam subjected to the sinusoidal load

 

 

Figure 7. The through thickness variation of the normal stress for the three-layered (0°/core/0°) soft core sandwich beam subjected to the sinusoidal load

 

 

Figure 8. The through thickness variation of the transverse shear stress for the three-layered (0°/core/0°) soft core sandwich beam subjected to the sinusoidal load

 

 

Table 4: The comparison of the axial displacement ( ), the transverse displacement ( ), the normal stress ( ), and the transverse shear stress (), for five-layered (0°/90°/core/90°/0°) soft core sandwich beam subjected to the sinusoidal load

L/h

Theory

       

4

Present

2.2146

10.929

43.484

1.3402

 

HSDT [5]

2.2070

10.925

43.334

1.3376

 

FSDT [1]

1.7660

7.1233

34.676

1.3469

 

CBT

1.7660

1.7567

34.676

1.3469

10

Present

28.718

3.2141

225.55

3.3630

 

HSDT [5]

28.702

3.2315

225.42

3.3623

 

FSDT [1]

27.594

2.6154

216.73

3.3674

 

CBT

27.594

1.7567

216.73

3.3674

20

Present

223.00

2.1212

875.74

6.7326

 

HSDT [5]

222.97

2.1257

875.62

6.7322

 

FSDT [1]

220.75

1.9714

866.92

6.7322

 

CBT

220.75

1.7567

866.92

6.7347

50

Present

3454.9

1.8151

5427.0

16.8359

 

HSDT [5]

3454.9

1.8150

5426.9

16.8359

 

FSDT [1]

3449.3

1.7911

5418.2

16.8368

 

CBT

3449.3

1.7567

5418.2

16.8368

100

Present

27606

1.7713

21681

33.6734

 

HSDT [5]

27606

1.7714

21681

33.6734

 

FSDT [1]

27594

1.7653

21673

33.6735

 

CBT

27594

1.7567

21673

33.6735

 

The results show that the axial displacement and stresses are increased with an increase in the aspect ratio, while the transverse displacement is decreased. Since an exact solution for this example is not available in the literature, the results of the present theory are compared with other theories and are found to agree well with each other. Table 5 shows the displacements and stresses for the five-layered soft core sandwich beams subjected to the uniform load. The through thickness distributions of the axial displacement, the normal stress and the transverse shear stress via equilibrium equation are shown in Figs. 9-11.

 

Figure 9. The through thickness variation of the axial displacement for the five-layered (0°/90°/core/90°/0°) soft core sandwich beam subjected to the sinusoidal load

 

 

Table 5: The comparison of the axial displacement ( ), the transverse displacement ( ), the normal stress ( ), and the transverse shear stress (), for five-layered (0°/90°/core/90°/0°) soft core sandwich beam subjected to the uniform load

L/h

Theory

       

4

Present

2.9647

13.449

51.694

2.2517

 

HSDT [5]

2.9438

13.556

51.532

2.1906

 

FSDT [1]

2.2816

8.8491

42.782

2.0828

 

CBT

2.2816

2.2282

42.782

2.0828

10

Present

37.382

4.0263

276.38

5.1818

 

HSDT [5]

37.350

4.0479

276.22

5.1653

 

FSDT [1]

35.650

3.2875

267.38

5.2070

 

CBT

35.650

2.2282

267.38

5.2070

20

Present

288.67

2.6778

1078.58

10.378

 

HSDT [5]

288.60

2.6834

1078.44

10.375

 

FSDT [1]

285.20

2.4930

1069.55

10.414

 

CBT

285.20

2.2282

1069.55

10.414

50

Present

4464.9

2.3001

6693.68

26.020

 

HSDT [5]

4464.8

2.3010

6693.67

26.019

 

FSDT [1]

4456.2

2.2705

6684.60

26.035

 

CBT

4456.2

2.2282

6684.60

26.035

100

Present

35667.0

2.2464

26747.8

52.062

 

HSDT [5]

35667.0

2.2464

26747.8

52.062

 

FSDT [1]

35650.0

2.2387

26738.6

52.069

 

CBT

35650.0

2.2282

26738.8

52.070

  1. Conclusions

In this study, a trigonometric shear deformation theory has been presented for the bending analysis of the soft core sandwich beams. The theory is a displacement-based theory which includes the transverse shear deformation effect. The number of unknown variables is the same as that of the first-order shear deformation theory. The theory satisfies zero shear stress conditions on the top and bottom surfaces of the beam perfectly. Hence, the theory obviates the need for the shear correction factor.

 

 

Figure 10. The through thickness variation of the normal stress for the five-layered (0°/90°/core/90°/0°) soft core sandwich beam subjected to the sinusoidal load

 

 

Figure 11. The through thickness variation of the transverse shear stress for the five-layered (0°/90°/core/90°/0°) soft core sandwich beam subjected to the sinusoidal load

 

From the numerical study and discussion it is concluded that the present theory is in an excellent agreement with other theories, while predicting the bending response of the laminated composite and soft core sandwich beams with transversely flexible core.

References

[1]       Timoshenko SP. On the Correction for Shear of the Differential Equation for Transverse Vibrations of Prismatic Bars. Philos Mag 1921; 41(6): 742–746.

[2]       Lo KH, Christensen RM, Wu EM. A High-order Theory of Plate Deformation, Part-1: Homogeneous Plates, ASME J Appl Mech 1977; 44: 663–668.

[3]       Lo KH, Christensen RM, Wu EM. A High-order Theory of Plate Deformation, Part-2: Laminated Plates, ASME J Appl Mech 1977; 44: 669–676.

[4]       Levinson M. A New Rectangular Beam Theory. J Sound Vib 1981; 74: 81–87.

[5]       Reddy JN. A Simple Higher Order Theory for Laminated Composite Plates. ASME J Appl Mech 1984; 51: 745–752.

[6]       Touratier M. An Efficient Standard Plate Theory. Int J Eng Sci 1991; 29(8): 901–916.

[7]       Soldatos KP. A Transverse Shear Deformation Theory for Homogeneous Monoclinic Plates. Acta Mech 1992; 94: 195–200.

[8]       Karama M, Afaq KS, Mistou S. A Refinement of Ambartsumian Multi-layer Beam Theory. Comput Struct 2008; 86: 839–849.

[9]       Sayyad AS. Comparison of Various Refined Beam Theories for the Bending and Free Vibration Analysis of Thick Beams. Appl Comput Mech 2011; 5: 217–230.

[10]   Sayyad AS., Ghugal YM, Borkar RR. Flexural Analysis of Fibrous Composite Beams under Various Mechanical Loadings using Refined Shear Deformation Theories. Compos Mech Comput Appl 2014; 5(1): 1–19.

[11]   Sayyad AS. Static Flexure and Free Vibration Analysis of Thick Isotropic Beams using Different Higher Order Shear Deformation Theories.  Int J Appl Math Mech 2012; 8(14): 71–87.

[12]   Mechab I, Tounsi A, Benatta MA, Bedia EAA. Deformation of Short Composite Beam using Refined Theories. J Math Anal Appl 2008; 346: 468–479.

[13]   Carrera E, Giunta G. Refined Beam Theories based on A Unified Formulation, Int J Appl Mech 2010; 2(1): 117–143.

[14]   Carrera E, Filippi M, Zappino E. Laminated Beam Analysis by Polynomial, Trigonometric, Exponential and Zig-zag Theories. Eur J Mech A Solids 2013; 41: 58–69.

[15]   Carrera E, Filippi M, Zappino E. Free Vibration Analysis of Laminated Beam by Polynomial, Trigonometric, Exponential and Zig-zag Theories. J Compos Mater 2014; 48(19): 2299–2316.

[16]   Giunta G, Metla N, Belouettar S, Ferreira AJM, Carrera E. A Thermo-Mechanical Analysis of Isotropic and Composite Beams via Collocation with Radial Basis Functions. J Therm Stresses 2013; 36: 1169–1199.

[17]   Chakrabarti A, Chalak HD, Iqbal MA, Sheikh AH. A New FE Model based on Higher Order Zigzag Theory for the Analysis of Laminated Sandwich Beam with Soft Core. Compos Struct 2011; 93: 271–279.

[18]   Chalak HD, Chakrabarti A, Iqbal MA, Sheikh AH. Vibration of Laminated Sandwich Beams Having Soft Core, J Vib Control 2011; 18(10): 1422–1435.

[19]   Gherlone M, Tessler A, Sciuva MD. A C0 Beam Elements based on the Refined Zig-zag Theory for Multi-layered Composite and Sandwich Laminates. Compos Struct 2011; 93: 2882–2894.

[20]   Shimpi RP, Ghugal YM. A New Layerwise Trigonometric Shear Deformation Theory for Two-layered Cross-ply Beams. Compos Sci Technol 2001; 61: 1271–1283.

[21]   Ghugal YM, Shinde SB. Flexural Analysis of Cross-ply Laminated Beams using Layerwise Trigonometric Shear Deformation Theory. Latin Am J Solids Struct 2013; 10(4): 675–705.

[22]   Arya H. A New Zig-zag Model for Laminated Composite Beams: Free Vibration Analysis. J Sound Vib 2003; 264: 485–490.

[23]   Sayyad AS, Ghugal YM. Effect of Transverse Shear and Transverse Normal Strain on Bending Analysis of Cross-ply Laminated Beams. Int J Appl Math Mech 2011; 7(12): 85–118.

[24]   Mantari JL, Oktem AS,  Soares CG. A New Trigonometric Shear Deformation Theory for Isotropic, Laminated Composite and Sandwich Plates. Int J Solids Struct 2012; 49(1): 43–53.

[25]   Ferreira AJM, Roque CMC, Jorge RMN. Analysis of Composite Plates by Trigonometric Shear Deformation Theory and Multi-quadrics. Comput Struct 2005; 83(27): 2225–2237.

[26]   Zenkour AM. Benchmark Trigonometric and 3-D Elasticity Solutions for an Exponentially Graded Thick Rectangular Plate. Arch Appl Mech 2007; 77: 197–214.

[27]   Sayyad AS, Ghugal YM, Naik NS. Bending Analysis of Laminated Composite and Sandwich Beams according to Refined Trigonometric Beam Theory. Curved and Layered Struct 2015; 2: 279–289.

[28]   Dahake AG, Ghugal YM. A Trigonometric Shear Deformation Theory for Flexure of Thick Beams. Procedia Eng 2013; 51: 1–7.

[29]   Dahake AG, Ghugal YM. A Trigonometric Shear Deformation Theory for Flexure of Thick Beams. Int J Sci Res Publ 2012; 2(11): 1–7.

[30]   Ghugal YM, Dahake AG. Flexure of Cantilever Thick Beams using Trigonometric Shear Deformation Theory. Int J Mech Aerosp Ind Mechatronic Manuf Eng 2013; 7(5): 380–389.

[31]   Pagano NJ. Exact Solutions for Composite Laminates in Cylindrical Bending. Compos Mater 1969; 3: 398–411.

 

 

[1]        Timoshenko SP. On the Correction for Shear of the Differential Equation for Transverse Vibrations of Prismatic Bars. Philos Mag 1921; 41(6): 742–746.

[2]        Lo KH, Christensen RM, Wu EM. A High-order Theory of Plate Deformation, Part-1: Homogeneous Plates, ASME J Appl Mech 1977; 44: 663–668.

[3]        Lo KH, Christensen RM, Wu EM. A High-order Theory of Plate Deformation, Part-2: Laminated Plates, ASME J Appl Mech 1977; 44: 669–676.

[4]        Levinson M. A New Rectangular Beam Theory. J Sound Vib 1981; 74: 81–87.

[5]        Reddy JN. A Simple Higher Order Theory for Laminated Composite Plates. ASME J Appl Mech 1984; 51: 745–752.

[6]        Touratier M. An Efficient Standard Plate Theory. Int J Eng Sci 1991; 29(8): 901–916.

[7]        Soldatos KP. A Transverse Shear Deformation Theory for Homogeneous Monoclinic Plates. Acta Mech 1992; 94: 195–200.

[8]        Karama M, Afaq KS, Mistou S. A Refinement of Ambartsumian Multi-layer Beam Theory. Comput Struct 2008; 86: 839–849.

[9]        Sayyad AS. Comparison of Various Refined Beam Theories for the Bending and Free Vibration Analysis of Thick Beams. Appl Comput Mech 2011; 5: 217–230.

[10]      Sayyad AS., Ghugal YM, Borkar RR. Flexural Analysis of Fibrous Composite Beams under Various Mechanical Loadings using Refined Shear Deformation Theories. Compos Mech Comput Appl 2014; 5(1): 1–19.

[11]      Sayyad AS. Static Flexure and Free Vibration Analysis of Thick Isotropic Beams using Different Higher Order Shear Deformation Theories.  Int J Appl Math Mech 2012; 8(14): 71–87.

[12]      Mechab I, Tounsi A, Benatta MA, Bedia EAA. Deformation of Short Composite Beam using Refined Theories. J Math Anal Appl 2008; 346: 468–479.

[13]      Carrera E, Giunta G. Refined Beam Theories based on A Unified Formulation, Int J Appl Mech 2010; 2(1): 117–143.

[14]      Carrera E, Filippi M, Zappino E. Laminated Beam Analysis by Polynomial, Trigonometric, Exponential and Zig-zag Theories. Eur J Mech A Solids 2013; 41: 58–69.

[15]      Carrera E, Filippi M, Zappino E. Free Vibration Analysis of Laminated Beam by Polynomial, Trigonometric, Exponential and Zig-zag Theories. J Compos Mater 2014; 48(19): 2299–2316.

[16]      Giunta G, Metla N, Belouettar S, Ferreira AJM, Carrera E. A Thermo-Mechanical Analysis of Isotropic and Composite Beams via Collocation with Radial Basis Functions. J Therm Stresses 2013; 36: 1169–1199.

[17]      Chakrabarti A, Chalak HD, Iqbal MA, Sheikh AH. A New FE Model based on Higher Order Zigzag Theory for the Analysis of Laminated Sandwich Beam with Soft Core. Compos Struct 2011; 93: 271–279.

[18]      Chalak HD, Chakrabarti A, Iqbal MA, Sheikh AH. Vibration of Laminated Sandwich Beams Having Soft Core, J Vib Control 2011; 18(10): 1422–1435.

[19]      Gherlone M, Tessler A, Sciuva MD. A C0 Beam Elements based on the Refined Zig-zag Theory for Multi-layered Composite and Sandwich Laminates. Compos Struct 2011; 93: 2882–2894.

[20]      Shimpi RP, Ghugal YM. A New Layerwise Trigonometric Shear Deformation Theory for Two-layered Cross-ply Beams. Compos Sci Technol 2001; 61: 1271–1283.

[21]      Ghugal YM, Shinde SB. Flexural Analysis of Cross-ply Laminated Beams using Layerwise Trigonometric Shear Deformation Theory. Latin Am J Solids Struct 2013; 10(4): 675–705.

[22]      Arya H. A New Zig-zag Model for Laminated Composite Beams: Free Vibration Analysis. J Sound Vib 2003; 264: 485–490.

[23]      Sayyad AS, Ghugal YM. Effect of Transverse Shear and Transverse Normal Strain on Bending Analysis of Cross-ply Laminated Beams. Int J Appl Math Mech 2011; 7(12): 85–118.

[24]      Mantari JL, Oktem AS,  Soares CG. A New Trigonometric Shear Deformation Theory for Isotropic, Laminated Composite and Sandwich Plates. Int J Solids Struct 2012; 49(1): 43–53.

[25]      Ferreira AJM, Roque CMC, Jorge RMN. Analysis of Composite Plates by Trigonometric Shear Deformation Theory and Multi-quadrics. Comput Struct 2005; 83(27): 2225–2237.

[26]      Zenkour AM. Benchmark Trigonometric and 3-D Elasticity Solutions for an Exponentially Graded Thick Rectangular Plate. Arch Appl Mech 2007; 77: 197–214.

[27]      Sayyad AS, Ghugal YM, Naik NS. Bending Analysis of Laminated Composite and Sandwich Beams according to Refined Trigonometric Beam Theory. Curved and Layered Struct 2015; 2: 279–289.

[28]      Dahake AG, Ghugal YM. A Trigonometric Shear Deformation Theory for Flexure of Thick Beams. Procedia Eng 2013; 51: 1–7.

[29]      Dahake AG, Ghugal YM. A Trigonometric Shear Deformation Theory for Flexure of Thick Beams. Int J Sci Res Publ 2012; 2(11): 1–7.

[30]      Ghugal YM, Dahake AG. Flexure of Cantilever Thick Beams using Trigonometric Shear Deformation Theory. Int J Mech Aerosp Ind Mechatronic Manuf Eng 2013; 7(5): 380–389.

[31]      Pagano NJ. Exact Solutions for Composite Laminates in Cylindrical Bending. Compos Mater 1969; 3: 398–411.

 

 

[1]       Timoshenko SP. On the Correction for Shear of the Differential Equation for Transverse Vibrations of Prismatic Bars. Philos Mag 1921; 41(6): 742746.

[2]       Lo KH, Christensen RM, Wu EM. A High-order Theory of Plate Deformation, Part-1: Homogeneous Plates, ASME J Appl Mech 1977; 44: 663–668.

[3]       Lo KH, Christensen RM, Wu EM. A High-order Theory of Plate Deformation, Part-2: Laminated Plates, ASME J Appl Mech 1977; 44: 669–676.

[4]       Levinson M. A New Rectangular Beam Theory. J Sound Vib 1981; 74: 81–87.

[5]       Reddy JN. A Simple Higher Order Theory for Laminated Composite Plates. ASME J Appl Mech 1984; 51: 745–752.

[6]       Touratier M. An Efficient Standard Plate Theory. Int J Eng Sci 1991; 29(8): 901–916.

[7]       Soldatos KP. A Transverse Shear Deformation Theory for Homogeneous Monoclinic Plates. Acta Mech 1992; 94: 195–200.

[8]       Karama M, Afaq KS, Mistou S. A Refinement of Ambartsumian Multi-layer Beam Theory. Comput Struct 2008; 86: 839–849.

[9]       Sayyad AS. Comparison of Various Refined Beam Theories for the Bending and Free Vibration Analysis of Thick Beams. Appl Comput Mech 2011; 5: 217–230.

[10]   Sayyad AS., Ghugal YM, Borkar RR. Flexural Analysis of Fibrous Composite Beams under Various Mechanical Loadings using Refined Shear Deformation Theories. Compos Mech Comput Appl 2014; 5(1): 1–19.

[11]   Sayyad AS. Static Flexure and Free Vibration Analysis of Thick Isotropic Beams using Different Higher Order Shear Deformation Theories.  Int J Appl Math Mech 2012; 8(14): 7187.

[12]   Mechab I, Tounsi A, Benatta MA, Bedia EAA. Deformation of Short Composite Beam using Refined Theories. J Math Anal Appl 2008; 346: 468–479.

[13]   Carrera E, Giunta G. Refined Beam Theories based on A Unified Formulation, Int J Appl Mech 2010; 2(1): 117–143.

[14]   Carrera E, Filippi M, Zappino E. Laminated Beam Analysis by Polynomial, Trigonometric, Exponential and Zig-zag Theories. Eur J Mech A Solids 2013; 41: 5869.

[15]   Carrera E, Filippi M, Zappino E. Free Vibration Analysis of Laminated Beam by Polynomial, Trigonometric, Exponential and Zig-zag Theories. J Compos Mater 2014; 48(19): 22992316.

[16]   Giunta G, Metla N, Belouettar S, Ferreira AJM, Carrera E. A Thermo-Mechanical Analysis of Isotropic and Composite Beams via Collocation with Radial Basis Functions. J Therm Stresses 2013; 36: 11691199.

[17]   Chakrabarti A, Chalak HD, Iqbal MA, Sheikh AH. A New FE Model based on Higher Order Zigzag Theory for the Analysis of Laminated Sandwich Beam with Soft Core. Compos Struct 2011; 93: 271–279.

[18]   Chalak HD, Chakrabarti A, Iqbal MA, Sheikh AH. Vibration of Laminated Sandwich Beams Having Soft Core, J Vib Control 2011; 18(10): 1422–1435.

[19]   Gherlone M, Tessler A, Sciuva MD. A C0 Beam Elements based on the Refined Zig-zag Theory for Multi-layered Composite and Sandwich Laminates. Compos Struct 2011; 93: 2882–2894.

[20]   Shimpi RP, Ghugal YM. A New Layerwise Trigonometric Shear Deformation Theory for Two-layered Cross-ply Beams. Compos Sci Technol 2001; 61: 1271–1283.

[21]   Ghugal YM, Shinde SB. Flexural Analysis of Cross-ply Laminated Beams using Layerwise Trigonometric Shear Deformation Theory. Latin Am J Solids Struct2013; 10(4): 675–705.

[22]   Arya H. A New Zig-zag Model for Laminated Composite Beams: Free Vibration Analysis. J Sound Vib 2003; 264: 485–490.

[23]   Sayyad AS, Ghugal YM. Effect of Transverse Shear and Transverse Normal Strain on Bending Analysis of Cross-ply Laminated Beams. Int J Appl Math Mech 2011; 7(12): 85–118.

[24]   Mantari JL, Oktem AS,  Soares CG. A New Trigonometric Shear Deformation Theory for Isotropic, Laminated Composite and Sandwich Plates. Int J Solids Struct 2012; 49(1): 4353.

[25]   Ferreira AJM, Roque CMC, Jorge RMN. Analysis of Composite Plates by Trigonometric Shear Deformation Theory and Multi-quadrics. Comput Struct 2005; 83(27): 22252237.

[26]   Zenkour AM. Benchmark Trigonometric and 3-D Elasticity Solutions for an Exponentially Graded Thick Rectangular Plate. Arch Appl Mech 2007; 77: 197–214.

[27]   Sayyad AS, Ghugal YM, Naik NS. Bending Analysis of Laminated Composite and Sandwich Beams according to Refined Trigonometric Beam Theory. Curved and Layered Struct 2015; 2: 279–289.

[28]   Dahake AG, Ghugal YM. A Trigonometric Shear Deformation Theory for Flexure of Thick Beams. Procedia Eng 2013; 51: 1–7.

[29]   Dahake AG, Ghugal YM. A Trigonometric Shear Deformation Theory for Flexure of Thick Beams. Int J Sci Res Publ 2012; 2(11): 1–7.

[30]   Ghugal YM, Dahake AG. Flexure of Cantilever Thick Beams using Trigonometric Shear Deformation Theory. Int J Mech Aerosp Ind Mechatronic Manuf Eng2013; 7(5): 380–389.

[31]   Pagano NJ. Exact Solutions for Composite Laminates in Cylindrical Bending. Compos Mater 1969; 3: 398–411.