Buckling of composite laminates subjected to In-plane partial edge compression using a refined plate theory

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dc.contributor.authorChakrabarti, A.
dc.contributor.authorSheikh, A.
dc.date.issued2006
dc.descriptionCopyright © 2006 SAGE Publications
dc.description.abstract<jats:p> The buckling of composite laminates subjected to in-plane partial edge compression is studied using a refined plate theory. In this theory, transverse shear stresses are continuous at the layer interfaces along with stress-free conditions at the top and bottom surfaces of the plate. It is quite interesting to note that the plate model having all these refined features requires unknowns only at the reference plane. However, this theory demands C<jats:sup>1</jats:sup> continuity of transverse displacement at the element edges, which is difficult to accommodate in any existing finite element. The present study is made by a new triangular element developed for the purpose. </jats:p>
dc.identifier.citationJournal of Reinforced Plastics and Composites, 2006; 25(11):1189-1204
dc.identifier.doi10.1177/0731684406066368
dc.identifier.issn0731-6844
dc.identifier.issn1530-7964
dc.identifier.orcidSheikh, A. [0000-0002-2839-1707]
dc.identifier.urihttp://hdl.handle.net/2440/46328
dc.language.isoen
dc.publisherTechnomic Publ Co Inc
dc.source.urihttp://jrp.sagepub.com/cgi/content/abstract/25/11/1189
dc.subjectlaminates
dc.subjectbuckling
dc.subjectpartial edge load
dc.subjectfinite element analysis
dc.titleBuckling of composite laminates subjected to In-plane partial edge compression using a refined plate theory
dc.typeJournal article
pubs.publication-statusPublished

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