Non-linear analysis of tapered (in steps) laminated plate under uniform inplane load

Research output: Journal Publications and Reviews (RGC: 21, 22, 62)21_Publication in refereed journalNot applicablepeer-review

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Original languageEnglish
Pages (from-to)205-223
Journal / PublicationComposite Structures
Volume7
Issue number3
Publication statusPublished - 1987
Externally publishedYes

Abstract

An initial stress iteration method using a quasi-three-dimensional element has been developed for the material non-linear analysis of Carbon Fibre Reinforced Plastic (CFRP) laminates of infinite width subjected to a uniform inplane load. Analyses of variable thickness (stepped) laminated plates with various arrangements for the ply fibre directions have been carried out. Linear and non-linear numerical results are given for a single step plate with resin layers included. The non-linear results show that peak stresses predicted by the linear analysis are reduced. This is a result of non-linear (plastic) deformation of the resin. A maximum strain failure criterion is used and failure modes of the free edge and stepped plate problems are predicted. The delaminating stress for the [90/90/90/90]s stepped plate compares well with experiments. © 1987.