Predicting the compressive strength of monolithic and sandwich composite structures failing by fibre microbuckling

C. Soutis, S Mark Spearing

Research output: Chapter in Book/Report/Conference proceedingConference contributionpeer-review

Abstract

Cohesive zone models have been successfully applied to predict the damage from notches in engineering materials loaded in tension. They have also been used to determine the growth of fibre microbuckling from a hole in a composite laminate under compression. The usual strategy is to replace the inelastic deformation associated with plasticity or microbuckling with a line-crack and to assume some form of stress-displacement bridging law across the crack faces. This paper examines recent experimental data obtained by the authors for monolithic carbon fibre-epoxy laminates with an open hole and of notched glass-fibre epoxy/honeycomb sandwich panels loaded in uniaxial compression. A plastic fibre kinking analysis and a linear softening cohesive zone model are used for the prediction of the unnotched and open hole compressive strength and the theoretical results are found to be in good agreement with the experimental data.
Original languageEnglish
Title of host publication42nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference nad Exhibit Technical Papers
Place of PublicationReston, VA
PublisherAmerican Institute of Aeronautics and Astronautics
Pages340-348
Number of pages9
DOIs
Publication statusPublished - Jun 2001

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