Delamination analysis of holed composite laminates using interface elements

H. Hosseini-Toudeshky, M. Jalalvand, B. Mohammadi

Research output: Contribution to journalArticle

3 Citations (Scopus)
13 Downloads (Pure)

Abstract

In this paper interface element with de-cohesive constitutive law is used to predict the failure load of laminates containing a central hole in which delamination is the dominant failure mode of them. For this purpose, the initiation and propagation of inter- laminar crack are modeled using our in hose FEM code. It is shown that at a certain load step, the interface elements between the two layers of -45° and 0° fail abruptly. It is also shown that the predicted failure stresses of laminates with various thicknesses are in an acceptable agreement with the experimental results.

Original languageEnglish
Pages (from-to)39-42
Number of pages4
JournalProcedia Engineering
Volume1
Issue number1
Early online date21 Jul 2009
DOIs
Publication statusPublished - 31 Jul 2009

Fingerprint

Delamination
Laminates
Hose
Composite materials
Failure modes
Cracks
Finite element method

Keywords

  • composite
  • delamination
  • hole
  • interface element
  • laminate

Cite this

Hosseini-Toudeshky, H. ; Jalalvand, M. ; Mohammadi, B. / Delamination analysis of holed composite laminates using interface elements. In: Procedia Engineering. 2009 ; Vol. 1, No. 1. pp. 39-42.
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Delamination analysis of holed composite laminates using interface elements. / Hosseini-Toudeshky, H.; Jalalvand, M.; Mohammadi, B.

In: Procedia Engineering, Vol. 1, No. 1, 31.07.2009, p. 39-42.

Research output: Contribution to journalArticle

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AB - In this paper interface element with de-cohesive constitutive law is used to predict the failure load of laminates containing a central hole in which delamination is the dominant failure mode of them. For this purpose, the initiation and propagation of inter- laminar crack are modeled using our in hose FEM code. It is shown that at a certain load step, the interface elements between the two layers of -45° and 0° fail abruptly. It is also shown that the predicted failure stresses of laminates with various thicknesses are in an acceptable agreement with the experimental results.

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