Analysis of composite laminates with intra- and interlaminar damage

Maria Kashtalyan, Costas Soutis

Research output: Contribution to journalArticle

89 Citations (Scopus)

Abstract

Failure process of composite laminate under quasi-static or fatigue loading involves sequential accumulation of intra-and interlaminar damage. Matrix cracking parallel to the fibres in the off-axis plies is the first intralaminar damage mode observed. These cracks are either arrested at the interface or cause interlaminar damage (delamination) due to high interlaminar stresses at the ply interface. This paper summarises recent theoretical modelling developed by the authors on stiffness property degradation and mechanical behaviour of general symmetric laminates with off-axis ply cracks and crack-induced delaminations. Closed-form analytical expressions are derived for Mode 1, Mode 11 and the total strain energy release rates associated with these damage modes. Dependence of strain energy release rates on crack density, delamination area and ply orientation angle in balanced and unbalanced symmetric laminates is examined and discussed. Also, stiffness degradation due to various types of damage is predicted and analysed. (c) 2005 Elsevier Ltd. All rights reserved.

Original languageEnglish
Pages (from-to)152-173
Number of pages22
JournalProgress in Aerospace Sciences
Volume41
Issue number2
DOIs
Publication statusPublished - Feb 2005

Keywords

  • energy release rate
  • thermomechanical constitutive theory
  • multiple matrix cracking
  • transverse ply cracks
  • stiffness reduction
  • variational approach
  • local delaminations
  • distributed damage
  • elastic composites
  • immersed fatigue

Cite this

Analysis of composite laminates with intra- and interlaminar damage. / Kashtalyan, Maria; Soutis, Costas.

In: Progress in Aerospace Sciences, Vol. 41, No. 2, 02.2005, p. 152-173.

Research output: Contribution to journalArticle

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