Please use this identifier to cite or link to this item: http://hdl.handle.net/2440/109333
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Type: Journal article
Title: Buckling response of laminated composite stiffened plates subjected to partial in-plane edge loading
Author: Patel, S.
Sheikh, A.
Citation: International Journal for Computational Methods in Engineering Science and Mechanics, 2016; 17(5-6):322-338
Publisher: Taylor & Francis
Issue Date: 2016
ISSN: 1550-2295
1550-2295
Statement of
Responsibility: 
S.N. Patel and A.H. Sheikh
Abstract: This article presents the buckling analysis of laminated composite stiffened plates subjected to partial in-plane edge loading. The finite element method is used to carry out the analysis. The eight-noded isoparametric degenerated shell element with C0 continuity and first-order shear deformation and a compatible three-noded curved beam element are used to model the plate skin and the stiffeners, respectively. The eigen value analysis is carried out to track the buckling load. The convergence study is performed for some specific problems and the results are compared with the available results in the literature. It is observed that the convergence of results is very fast for this finite element model. Effect of different parameters like orientation of fibers, number of layers, and loading types are considered in the present investigation. It is also observed that all these parameters have significant effect on the buckling response of the composite stiffened plate.
Keywords: Buckling; finite element; laminated composite; stiffened plate
Rights: © 2016 Taylor & Francis Group, LLC
RMID: 0030056674
DOI: 10.1080/15502287.2016.1231235
Appears in Collections:Civil and Environmental Engineering publications

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