A 3D computational meshfree model for the mechanical and thermal buckling analysis of rectangular composite laminated plates with embedded delaminations

2017 ◽  
Vol 24 (6) ◽  
pp. 937-949
Author(s):  
Jie Chen ◽  
Hai Wang ◽  
Yingchun Zhang ◽  
Lihua Zhan
Keyword(s):  
Governing Equation ◽  
Composite Laminates ◽  
Present Model ◽  
Interpolation Method ◽  
Composite Plates ◽  
Hamiltonian Function ◽  
Thermal Buckling ◽  
Buckling Analysis ◽  
Laminated Plates ◽  
State Variables

AbstractA three-dimensional (3D) semi-analytical model is developed by introducing meshfree local radial point interpolation method into a Hamilton system to analyze the mechanical and thermal buckling behavior of rectangular laminated plates with embedded delaminations. A modified Hamiltonian function for mechanical and thermal buckling analysis of rectangular laminated composite plates subjected to in-plane axial compressive or thermal loads is proposed. The final governing equation is deduced with the transfer matrix technique and a spring layer model based on the modified Hellinger-Reissner variational principle. One of the main superiorities of the present model is that the scale of final governing equation, which involves only the so-called state variables at the top and bottom surfaces, is insensitive to the thickness and the number of layers of composite laminates. Several relevant numerical examples are carried out to validate the present model, and the present results are in good agreement with pre-existing results.

Buckling and vibration analyses of composite laminates with weak interfaces by a coupled meshfree and finite element method

2016 ◽  
Vol 23 (1) ◽  
pp. 93-105
Author(s):  
Jie Chen ◽  
Hai Wang ◽  
Jie Wang
Keyword(s):  
Finite Element Method ◽  
Finite Element ◽  
Composite Laminates ◽  
Interpolation Method ◽  
Three Dimensional ◽  
Hamiltonian Function ◽  
Laminated Plates ◽  
Hamilton System ◽  
Point Interpolation Method ◽  
Element Method

AbstractBuckling and free vibration analyses for composite laminates with weak interfaces were performed based on a three-dimensional hybrid semianalytical model. The model was established by coupling the radial point interpolation method and finite element method (FEM) in a Hamilton system. A direct coupling approach was developed based on the FEM background cell algorithm, and a modified Hamiltonian function for buckling analysis of rectangular laminated plates was given. The governing equations were deduced with the transfer matrix technique and a general linear spring layer model based on the modified Hellinger-Reissner variational principle. Several numerical examples are also presented to validate the efficiency and accuracy of the present method.

Physical Ultrasonics of Composites

2011 ◽  
Author(s):  
Dale Chimenti ◽  
Stanislav Rokhlin ◽  
Peter Nagy
Keyword(s):  
Composite Laminates ◽  
Stiffness Matrix ◽  
Composite Plates ◽  
Anisotropic Media ◽  
Anisotropic Materials ◽  
Ultrasonic Waves ◽  
Laminated Plates ◽  
Structure Characteristic ◽  
Major Advance

Physical Ultrasonics of Composites is a rigorous introduction to the characterization of composite materials by means of ultrasonic waves. Composites are treated here not simply as uniform media, but as inhomogeneous layered anisotropic media with internal structure characteristic of composite laminates. The objective here is to concentrate on exposing the singular behavior of ultrasonic waves as they interact with layered, anisotropic materials, materials which incorporate those structural elements typical of composite laminates. This book provides a synergistic description of both modeling and experimental methods in addressing wave propagation phenomena and composite property measurements. After a brief review of basic composite mechanics, a thorough treatment of ultrasonics in anisotropic media is presented, along with composite characterization methods. The interaction of ultrasonic waves at interfaces of anisotropic materials is discussed, as are guided waves in composite plates and rods. Waves in layered media are developed from the standpoint of the "Stiffness Matrix", a major advance over the conventional, potentially unstable Transfer Matrix approach. Laminated plates are treated both with the stiffness matrix and using Floquet analysis. The important influence on the received electronic signals in ultrasonic materials characterization from transducer geometry and placement are carefully exposed in a dedicated chapter. Ultrasonic wave interactions are especially susceptible to such influences because ultrasonic transducers are seldom more than a dozen or so wavelengths in diameter. The book ends with a chapter devoted to the emerging field of air-coupled ultrasonics. This new technology has come of age with the development of purpose-built transducers and electronics and is finding ever wider applications, particularly in the characterization of composite laminates.

scholarly journals Buckling and postbuckling behavior of shell type structures under thermo-mechanical loads

2021 ◽  
pp. 79-79
Author(s):  
Zoran Vasic ◽  
Katarina Maksimovic ◽  
Mirko Maksimovic ◽  
Ivana Vasovic ◽  
Nenad Vidanovic ◽  
...  
Keyword(s):  
Finite Element ◽  
Shear Deformation ◽  
Composite Laminates ◽  
Shear Deformation Theory ◽  
Higher Order ◽  
Thermal Buckling ◽  
Laminated Plates ◽  
Postbuckling Behavior ◽  
Mechanical Loads ◽  
Shell Type

The thermomechanical buckling and postbuckling behavior of layered composite shell type structure are considered with the finite element method (FEM) under the combination of temperature load and applied mechanical loads. To account for through-thickness shear deformation effects, the thermal elastic, Higher-Order Shear deformation Theory (HOST) is used in this study. The refined higher order theories, that takes into account the effect of transverse normal deformation, is used to develop discrete finite element models for the thermal buckling analysis of composite laminates. Attention in this study is focused on analyzing the temperature effects on buckling and postbuckling behavior of thin shell structural components. Special attention in this paper is focused on studying of values of the hole in curved panel on thermal buckling behavior and consequently to expend and upgrade previously conducted investigation. Using FEM, a broader observation of the critical temperature of loss of stability depending on the size of the hole was conducted. The presented numerical results based on HOST can be used as versatile and accurate method for buckling and postbuckling analyzes of thin-walled laminated plates under thermo-mechanical loads.

scholarly journals A Five Variable Refined Plate Theory For Thermal Buckling Analysis Uniform And Nonuniform Of Cross-Ply Laminated Plates

2022 ◽  
Vol 28 (1) ◽  
pp. 86-107
Author(s):  
Hussein A. Hashim ◽  
Ibtehal Abbas Sadiq
Keyword(s):  
Boundary Condition ◽  
Virtual Work ◽  
Plate Theory ◽  
Plate Thickness ◽  
Linear Thermal Expansion ◽  
Composite Plates ◽  
Thermal Buckling ◽  
Buckling Analysis ◽  
Temperature Fields ◽  
Refined Plate Theory

This research is devoted to investigating the thermal buckling analysis behaviour of laminated composite plates subjected to uniform and non-uniform temperature fields by applying an analytical model based on a refined plate theory (RPT) with five unknown independent variables. The theory accounts for the parabolic distribution of the transverse shear strains through the plate thickness and satisfies the zero-traction boundary condition on the surface without using shear correction factors; hence a shear correction factor is not required. The governing differential equations and associated boundary conditions are derived by using the virtual work principle and solved via Navier-type analytical procedure to obtain critical buckling temperature. Results are presented for: uniform and linear cross-ply lamination with symmetry and antisymmetric stacking, simply supported boundary condition, different aspect ratio (a/b), various orthogonality ratio (E1/E2), varying ratios of coefficient of uniform and linear thermal expansion (α2⁄α1), uniform and linearly varying temperature thickness ratio (a/h) and numbers of layers on thermal buckling of the laminated plate. It can be concluded that this theory gives good results compared to other theories.

scholarly journals Thermal Buckling Analysis of Composite Plates using Isogeometric Analysis based on Bezier Extraction

2021 ◽  
Author(s):  
balakrishnan devarajan
Keyword(s):  
Finite Element Analysis ◽  
Finite Element ◽  
Isogeometric Analysis ◽  
Composite Plates ◽  
Thermal Buckling ◽  
Buckling Analysis ◽  
Basis Functions ◽  
Element Analysis ◽  
Order Deformation ◽  
Bézier Extraction

Data transmission back and forth between finite element analysis (FEA) and computer-aided design (CAD) is a matter of huge concern today [2] and Isogeometric analysis [1] has been successful in merging these two fields in the recent past. The presentation will address isogeometric finite element approach (IGA) in combination with the first-order deformation plate theory (FSDT) for thermal buckling analysis of laminated composite plates. The IGA utilizes non-uniform rational B-spline (NURBS) as basis functions, resulting in both exact geometric representation and high order approximations [3] [4]. It enables to achieve easily the smoothness with arbitrary continuous order. The analyses have been performed using Bezier extraction and conventional IGA. In conventional isogeometric analysis the basis functions are not confined to one single element, but span a global domain whereas the Bézier extraction operator decomposes a set of linear combinations of Bernstein polynomials. The presentation will give a theoretical overview of B-splines, as well as NURBS, and also the concept of Bézier decomposition of these spline functions. The focus will then be on how the use of Bézier extraction eased the implementation into an already existing finite element code. This theoretical background will then be used to explain an isogeometric finite element analysis program. With the advent of More Electric Aircrafts [5], solving thermal structural problems [6] are of utmost importance in the aerospace industry. A static thermal structural validation problem will be presented for both constant and linear thermal temperature variation along the thickness. The presentation will then explain the procedures implemented for stress recovery and computing the geometric stiffness matrix. Numerical results of circular and elliptical plates will be provided to validate the effectiveness of the proposed method as compared to traditional FEA. The final section of the presentation proposes to detail the influences of length to thickness ratio, aspect ratio, boundary conditions, stacking sequence and material property on the critical buckling temperature. A special section would cover the idea of third order deformation theory for thicker plates and the effect of degree of NURBS basis on the results.

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