Language and Style Advisors
G. Baskaran, Ph.D.
Sam Mohanlal, Ph.D.
|
Back Issues of Engineering & Technology in India - From 2016
BOOKS FOR YOU TO READ AND DOWNLOAD FREE!
BACK ISSUES
Copyright © 2015 |
Stability Analysis of Laminated Composite Plates with an Elliptical/Circular/Square Cut-out using FEMPandiarajan. P., Sivaraj. P., Jeyakanth. S., and Theerkkatharisanan. R.Abstract This paper addresses the e?ects of a cut-out on the buckling behaviour of square plates made of polymer matrix composites (PMC). The study is concentrated on the behaviour of square symmetric cross-ply laminates. The laminated plates were symmetrically orderly arranged into the following way [0/90]2S.The resistance to buckling of the laminated plates subjected to mono-axial compression is highlighted according to e?ect of boundary condition; the unloaded edges are modelled in clamped and simply supported boundary condition. Finite element analysis is performed to predict the e?ects of cut out of circular, square and elliptical hole aligned in along the loading direction and aligned in perpendicular to the loading direction on the buckling behaviour of these plates. Keywords: stability analysis, laminated composite plates, FEM cut out. Introduction Application fields of composite materials are continuously expanding, from traditional application areas such as military aircraft to various engineering fields including commercial aircrafts, automobiles, robotic arms and even architecture [1]. The correct understanding of their structural behaviour is necessary, such as the deflections, buckling loads and modal characteristics, the through-thickness distributions of stresses and strains, the large deflection behaviour and, of extreme significance for obtaining strong, reliable multi-layered structures, the failure characteristics [2]. Throughout operation the composite laminate plates are generally subjected to compression loads that may basis buckling if overloaded. Consequently their buckling behaviours are significant factors in safe and reliable design of these structures [3]. For predicting the buckling load and buckling mode form of a structure in the finite element program, the linear (or eigenvalue) buckling analysis is an existing technique for estimation [4]. In general, the analysis of composite laminated plates is more complicated than the analysis of homogeneous isotropic ones [5]. In the literature, there are a range of published studies on the buckling of composite plates. Akbulut and Sayman [6] carried out a buckling analysis of a rectangular composite laminates with a central square hole. Using the first order shear deformation theory, the critical buckling loads of composite plates which were designed as symmetric angle-ply, antisymmetric cross-ply or angle ply under the in plane loads were found for constant or various thicknesses, simple or clamped boundary conditions, various modules ratios, simple or biaxial loading versus hole sizes. Kundu and Sinha [7] performed the geometrically nonlinear post buckling analysis of laminated composite doubly curved shells by finite element method. Pandiarajan. P.
|