 Open Access
 Authors : Komal U. Navale , Dr. C. P. Pise
 Paper ID : IJERTV10IS010156
 Volume & Issue : Volume 10, Issue 01 (January 2021)
 Published (First Online): 30012021
 ISSN (Online) : 22780181
 Publisher Name : IJERT
 License: This work is licensed under a Creative Commons Attribution 4.0 International License
A Review on High Order Shear Deformation Theory for Orthotropic Composite Laminates
Ms. Komal U. Navale Dr. C. P. Pise
Department of Civil Engineering Department of Civil Engineering
SKN Sinhgad College of Engineering Korti Pandharpur SKN Sinhgad College of Engineering Korti Pandharpur Maharashtra, India Maharashtra, India
Abstract The new higherorder shear deformation theory is developed and accessed for the bending, buckling and free vibration response of the thick and thin laminated composite and sandwich plates. The proposed theories assume nonlinear variation of transverse shear strain through the plate thickness and give transverse shear stressfree top and the bottom surface of the plate. The governing differentials equation of the laminated composite and sandwich plates derived through Hamiltons principle are solved employing analytical solution technique i.e. navier solution methodology for the crossply plates with simply supported boundary conditions over all the edges. In order to demonstrate the accuracy and applicability of the proposed higherorder shear deformation theories, a wide range of the numerical examples for the bending, buckling and free vibration response are considered. The present results are found to be in good agreement with those published earlier in the literature using equivalent single layer theories and three dimensional exact solutions.
Keywords Shear deformation theory, Orthotropic laminates, Static and Buckling analysis

INTRODUCTION
In materials science, a composite laminate is an assembly of layers of fibrous composite materials which can be joined to provide required engineering properties, including inplane stiffness, bending stiffness, strength, and coefficient of thermal expansion. The individual layers consist of highmodulus, highstrength fibers in a polymeric, metallic, or ceramic matrix material. Typical fibers used include cellulose, graphite, glass, boron, and silicon carbide, and some matrix materials are epoxies, polyimides, aluminum, titanium, and alumina. Layers of different materials may be used, resulting in a hybrid laminate. The individual layers generally are orthotropic (that is, with principal properties in orthogonal directions) or transversely isotropic (with isotropic properties in the transverse plane) with the laminate then exhibiting anisotropic (with variable direction of principal properties), orthotropic, or quasiisotropic properties. Quasiisotropic laminates exhibit isotropic (that is, independent of direction) inplane response but are not restricted to isotropic outofplane (bending) response. Depending upon the stacking sequence of the individual layers, the laminate may exhibit coupling between in plane and outofplane response. An example of bendingstretching coupling is the presence of curvature developing as a result of inplane loading.
In the orthotropic materials deformation is, in general, direction dependent. An exception occurs when loads are applied in natural (material) coordinates. These are by definition coordinates in the plane of the lamina, wherein the longitudinal coordinate is aligned with the fiber reinforcement and the transverse coordinate is aligned normal to the fiber reinforcement. Longitudinal and transverse directions are material axes of symmetry in a unidirectional reinforced composite. When loads are applied in these natural coordinates the material response is similar to that of isotropic materials, i.e., normal stresses produce normal strains only and shear stresses produce shear strains only. Here the longitudinal and transverse axes are respectively. Unidirectionally reinforced composites are often referred to as especially orthotropic. Furthermore, unidirectionally reinforced laminas are isotropic in the outofplane (normal to the plane of the lamina) direction
Fig. 1 Crosssection of crossply laminate

CLASSIFICATION OF STRUCTURAL THEORIES

Equivalent Single Layer (ESL) Theory

Classical Laminated Plate Theory

Shear Deformation Plate Theory


Three Dimensional Elasticity theory

Layerwise or ZigZag theory



Classical Laminated Plate Theory
The classical laminate theory is a direct extension of the classical plate theory for isotropic and homogeneous material as proposed by Kirchhoff. However, the extension of this theory to laminates requires some modifications to take into account the inhomogeneity in thickness direction. In the following, the assumptions made in this theory along with the assumptions made for classical plate theory are given.
The straindisplacement field is derived using two approaches. In the first approach the deformation of the laminate according to the Kirchhoff – Law assumptions for bending and stretching is used. The undeformed and deformed geometries of laminate are used to develop the displacement field. In the second approach the transverse strain components resulting from the above assumptions are used. Further, using mathematical definitions of these strain components the displacement field is obtained. Thus, from this displacement field all strain components are obtained the complete displacement field for a generic point in the laminate according to the classical laminate theory is given below:
The strain displacement relations for infinitesimal strains using the displacement field as in Equation can be given as
The above equation can be written as
B.Shear Deformation Plate Theory
In the ReissnerMindlin theory, also called Firstorder Shear Deformation Theory (FSDT), the third part of Kirchhoff hypothesis is removed, so the transverse normals do not remain perpendicular to the midsurface after deformation. In this way, transverse shear strains xz and yz are included in the theory. However, the inextensibility of transverse normal remains
Fig.2 Distribution of displacements in FSDT
So displacement uz is constant in the thickness direction z.
The displacement field in the case of FSDT is
ux(x, y, z) = ux0 (x, y) + x(x, y)z
uy(x, y, z) = uy0 (x, y) + y(x, y)z uz(x, y, z) = uz0 (x, y)
The quantities (ux0 , uy0 , uz0 ,x,y) will be the unknowns. For thin plates, i.e., when the plate inplane characteristic dimension to thickness ratio is on the order 50 or greater, the rotation functions x and y should approach the respective slopes of the transverse deflection uz0 x and uz0 y . Figure shows the typical distribution of displacement components according to FSDT: linear for ux and uy and constant for uz. Also the physical meaning of the rotations, x and y, is represented. The strain components are obtained by substituting the displacement field in the geometrical relations.
Only strain zz is zero, so the notnull strains are
xx = ux x = ux0,x + x,xz yy = uy y = uy0,y + y,yz
xy = ux y + uy x = ux0,y + uy0,x + x,yz + y,xz xz = ux z + uz x = x + uz0,x
xy = ux y + uy x = y + uz0,y
The constitutive relations are used to obtain the inplane stresses and the shear stress components
Where is the shear correction factor
C.Layerwise or ZigZag theory Displacement Field
In the layerwise theory of Reddy the displacement of the k the layer is given by,
Stresses and Strains
The Strains associated with the displacement field
III PRESENT THEORIES
M. Narwariya et al., [1] presented the vibration and harmonic analysis of orthotropic laminated composite plate. The response of plate is determined using Finit Element Method. The eight noded shell 281 elements are used to analyze the orthotropic plates and results are obtained so that the right choice can be made in applications such as aircrafts, rockets, missiles, etc. to reduce the vibration amplitudes.
M. Nasihatgozara et al., [2] in this study the effect of different boundary conditions on the free vibration analysis response of a sandwich plate is presented using the higher order shear deformation theory. The face sheets are orthotropic laminated composites that follow the first order shear deformation theory (FSDT) based on the Rissners Mindlin (RM) kinematics field. The motion equations are derived considering the continuity boundary conditions between the layers based on the energy method and Hamilton's principle.
Durgesh Bahadur Singh et al., [3] Proposed three dimensional braided composites exhibit several distinct advantages which are not realized in traditional laminates. This is due to the out of plane orientation of some fibers & fully integrated nature of fiber arrangements of three dimensional braided composites that enhance stiffness/strength in the thickness direction and eliminate the interlaminar surface characteristics. A recently developed Inverse Hyperbolic Shear Deformation Theory (IHSDT) has proved its accuracy and efficiency for static and buckling analysis of laminated composite and sandwich structures.
Neeraj Grover et al., [4] studied; an inverse trigonometric shear deformation theory developed by the authors is extended to assess the flutter behavior of multilayered composite plates subjected to yawed supersonic flow. The shear deformation is
considered in terms of an inverse cotangent function which yields nonlinear distribution of shear stresses. A generalized finite element formulation is presented to consider the shear strain function based theories.
Nguyen et al., [5] presented unified structure for modeling and analysis of composite plate which is polynomial form of higher shear deformation theory in unified formulation with consideration of thickness stretching consideration. The various nonpolynomial shear deformation theories are constructed in diagram which also called as Best Theory Diagrams for composite laminated plates. Best theory diagrams used to calculate number of variables required to reduce the fixed error based on axiomatic/asymptotic method which gives accurate results for composite plates.
A.H. Akbarzadeh et al., [6] examined the influence of various micromechanical models on the macroscopic behavior of a functionally graded plate based on classical and shear deformation plate theories. Different micromechanical models are tested to obtain the effective material properties of a two phase particle composite as a function of the volume fraction of particles which continuously varies through the thickness of a functionally graded plate. The static, buckling, and free and forcedvibration analyses are conducted for a simply supported functionally graded plate resting on a Pasternak type elastic foundation. The volume fractions of particles are assumed to change according to the power law, Sigmoid, and exponential functions.
Neeraj Grover al., [7] presented a secant function based shear deformable finite element model is developed for the flexural behavior of laminated composite and sandwich plates with various conditions. The structural kinematics of the plate is expressed by means of secant function based shear deformation theory newly developed by the authors. The theory possesses nonlinear shear deformation and also satisfies the zero transverse shear conditions on top and bottom surfaces of the plate. The field variables are elegantly utilized in order to ensure C0 continuity requirement. Penalty parameter is implemented to secure the constraints arising due to independent field variables. A biquadratic quadrilateral element with eight nodes and 56 degrees of freedom is employed to discretize the domain.
J.L. Mantari et al., [8] Presents the comparison of polynomial, trigonometric, hyperbolic trigonometric and Exponential shear deformation was carried out and used exponential shear stress parameter to develop higher shear deformation theory.Neeraj
Grover et al [9] the proposed theory based upon shear strain shape function yields nonlinear distribution of transverse shear stresses and also satisfies traction free boundary conditions. Principle of virtual work is employed to develop the governing differential equations assuming the linear kinematics. A Navier type closed form solution methodology is also proposed for crossply simply supported plates which limits its applicability. However, it provides accurate solution which is free from any numerical/ computational error
Yiyo Kuo et al [10] proposed a greybased Taguchi method to solve the multiresponse simulation problem. The greybased Taguchi method is based on the optimizing procedure of the Taguchi method, and adopts grey relational
analysis (GRA) to transfer multiresponse problems into singleresponse problems. A practical case study from an integratedcircuit packaging company illustrates that differences in performance of the proposed greybased Taguchi method and other methods found in the literature were not significant.
J.N. Reddy et al., [11] Presents a higherorder shear deformation theory is used to determine the natural frequencies and buckling loads of elastic plates. The theory accounts for parabolic distribution of the transverse shear strains through the thickness of the plate and rotary inertia. Exact solutions of simply supported plates are obtained and the results are compared with the exact solutions of three dimensional elasticity theory, the firstorder shear deformation theory, and the classical plate theory. The present theory predicts the frequencies and buckling loads more accurately when compared to the firstorder and classical plate theories.
J.L. Mantari11, A.S. Oktem2, C. Guedes Soares3 [12] A new inverse hyperbolic shear deformation theory is developed and implemented in the present work for the static and buckling distribution of transverse shear stresses and also satisfies the zero tangential traction boundary conditions on the surface of the plate. Principle of virtual work is applied to derive the governing differential equations assuming the linear kinematics followed by a closed form solution methodology based upon Navier solution technique, which limits the applicability of solution technique to simply supported plates; however the solution free from any numerical/computational error is obtained. Various numerical examples are worked out to ensure the accuracy and efficacy of the proposed theory.
Yiyo Kuo1, Taho Yang2, [13] The greybased Taguchi method to solve a multiresponse simulation optimization problem. Following the procedure of the Taguchi method, GRA was used to transform a multiresponse problem into a singleresponse problem. A practical case study illustrated that the difference in performance between the proposed method and other methods identified in the Literature was not significant. However, the results of this study illustrate that the GRA procedure is simple and straightforward in calculations and optimization; it is therefore a very suitable method for solving multiresponse simulation problems.
Fan Yell 1 , Lin Fangyong 2 [14] On the basis of the Reddy's higherorder theory of composites, this paper introduces a displacement function t~ into it and transforms its three differential equations for symmetric crossply composites into only one eightorder differential equation generated by the displacementfunction. When a proper ~ is chosen, both solutions are obtained, namely, tire Naviertype solution of simply supported rectangular laminated plates and the Levytype solution with the boundary condition where two opp6site edges are simply supported and remains are arbitrary.
K. Vijayakumar [15] presented shear deformation and higher order theories of plates in bending are (generally) based on plate element equilibrium equations derived either through variational principles or other methods. They involve coupling of flexure with torsion (torsiontype) problem and if applied vertical load is along one face of theplate, coupling even with extension problem. These coupled problems with reference to vertical deflection of plate in flexure result in artificial deflection due to torsion and increased deflection of faces of the plate due to extension.
G. A. MAUGIN [ 16] A new standard plate theory, that accounts for cosine shear stress distribution and free boundary conditions for shear stress upon the top and bottom surfaces of the plate, is presented. The theory is of the same order of complexity as the first order shear deformation theory, but does not use shear correction factors, and is more efficient than the first order shear deformation theory and some refined plate theories. The theory is based on the kinematical approach in which the shear is represented by a certain sinusoidal function. The boundary value problem is deduced from the virtual power principle.
Chien H. Thai1, A.J.M. Ferreira2, [17] presented a new inverse tangent shear deformation theory (ITSDT) for the static, free vibration and buckling analysis of laminated composite and sandwich plates. In the present theory, shear stresses are vanished at the top and bottom surfaces of the plates and shear correction factors are no longer required. A weak form of the static, free vibration and buckling models for laminated composite and sandwich plates based on ITSDT is then derived and is numerically solved using an isogeometric analysis (IGA).
J.L. Mantari1, A.S. Oktem2, [18] developed new higher order shear deformation theory for elastic composite/sandwich plates and shells. The new displacement field depends on a parameter m, whose value is determined so as to give results closest to the 3D elasticity bending solutions. The present theory accounts for an approximately parabolic distribution of the transverse shear strains through the shell thickness and tangential stressfree boundary conditions on the shell boundary surface. The governing equations and boundary conditions are derived by employing the principle of virtual work.
Sandeep Singp , Jeeoot Singp [19] In this study, buckling analysis of isotropic, orthotropic, laminated composite and sandwich plates utilizing trigonometric shear deformation theory and mesh less method based on the finite point formulation using thin plate, polynomial and inverse multiquadric radial basis function is presented. The convergence of the present method is studied for isotropic and laminated composite plates for different radial basis functions with optimal value of shape parameter. Numerical examples of laminated and sandwich plates subjected to various types of inplane loads are solved to demonstrate accuracy and applicability of present method.

CONCLUSIONS

The newly developed higherorder shear deformation theory is accessed for the bending, buckling and free vibration response of the laminated composite and sandwich plates. The proposed plate theory assumes nonlinear variation of transverse shear strain through the plate thickness and thus delivers transverse shear stressfree top and bottom surface of the plate.

The governing equation of plate is solved using Navier solution technique with simply supported boundary conditions to investigate the accuracy of the proposed theories. From the proposed higherorder shear deformation theory predicted better deflection of laminated composite plates

The proposed higherorder shear deformation theory with combination of trigonometric and polynomial function as a transverse shear strain function predicted results close of those of predicted with TSDT of Reddy

The results predicted with different proposed higher order shear deformation theory differ marginally for the thick plates and these differences disappear for the thin plates.

For the sandwich plates, the higherorder shear deformation theory a transverse shear strain function predicted results closed those of obtained thorough exact solution.

The presents results are found to be in good agreement when compared to results due to three dimensional elasticity solutions due to Refs.



ACKNOWLEDGMENT
I am very thankful to my guide Dr. C.P. Pise and all the faculty members of the department, especially Structural Engineering specialization for their constant encouragement, invaluable advice, inspiration and blessings during the paper.
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