The influence of surface ply fibre angle on the compressive strength of composite laminates containing delamination

Andrew T Rhead, Richard Butler, Wenli Liu, Neil Baker

Research output: Contribution to journalArticle

7 Citations (Scopus)

Abstract

A combination of uniaxial compression tests and Strip Model and Finite Element analyses of laminates artificially delaminated to create circular [±θ] sublaminates is used to assess the influence of fibre angle on the compressive strength of composite laminates.
Sublaminates with 0° < θ < 40° are found to fail by sublaminate-buckling-driven delamination propagation and provide poor tolerance of delamination. This is a consequence of their relatively high axial stiffnesses, low sublaminate buckling strains, Poisson’s ratio induced compressive transverse strains and extension-twist coupling which produces unexpected sublaminate buckling mode shapes. Sublaminates with 40° < θ < 60° are most tolerant to delamination; axial and transverse stiffnesses are minimal, formation of sublaminate buckles is resisted, high laminate buckling strains reduce interaction between laminate and sublaminate buckling mode shapes and extension-twist coupling is minimal. Sublaminates with 60° < θ < 90° are shown to produce varied tolerance of delamination. Sublaminate buckling is generally prevented owing to transverse tensile strains induced by mismatches between laminate and sublaminate Poisson’s ratios but may occur in laminates with low Poisson’s ratios.
Original languageEnglish
Pages (from-to)1315-1330
Number of pages16
JournalAeronautical Journal
Volume116
Issue number1186
Publication statusPublished - Dec 2012

Keywords

  • damage tolerance

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