A quick procedure to predict free-edge delamination in thin-ply laminates under tension

dc.contributor.author
Guillamet Busquets, Gerard
Turon Travesa, Albert
Costa i Balanzat, Josep
Linde, Peter
dc.date.accessioned
2016-02-23T12:36:43Z
dc.date.available
2016-02-23T12:36:43Z
dc.date.issued
2016-12
dc.identifier.issn
0013-7944
dc.identifier.uri
http://hdl.handle.net/10256/12125
dc.description.abstract
Delaminations at the free-edges of a laminated composite under tension can be triggered by transverse cracks or by high interlaminar stresses. The capability for predicting these phenomena when the ply thickness is reduced (thin-ply laminates) is particularly challenging because damage mechanisms are delayed or even suppressed. In this work, an existing energy-based failure criterion and a simplified finite element model with cohesive elements are combined to develop a computationally inexpensive predictive tool. Its comparison with experimental data demonstrates that this approach captures the trends of the critical strain for delamination with respect to ply thickness and ply location and the quantitative agreement with the predictions is satisfactory
dc.description.sponsorship
The authors acknowledge the financial support of the Spanish government through the Ministerio de Economía y Competitividad under the contracts DPI2012-34465 and MAT2012-37552-C03-03, which is partially funded by the FEDER funds of the EC. The first author acknowledges the support of the Generalitat de Catalunya with the pre-doctoral grant FI-DGR (2014FI B1 00123). The company CHOMARAT (Ardèche, France) is acknowledged for providing the NCF material and Aldila (Poway, California, USA) for the epoxy system pre-preg. The company AIRBUS partially funded this work through the 2genCOMP project
dc.format.mimetype
application/pdf
dc.language.iso
eng
dc.publisher
Elsevier
dc.relation
info:eu-repo/grantAgreement/MINECO//DPI2012-34465/ES/EVALUACION DE COMPOSITES LAMINADOS DE CAPAS FINAS PARA APLICACIONES AERONAUTICAS Y AEROESPACIALES/
info:eu-repo/grantAgreement/MINECO//MAT2012-37552-C03-03/ES/COMPUESTOS MULTIFUNCIONALES Y TOLERANTES AL DAÑO: INTEGRACION DE NANOREFUERZOS DE CARBONO AVANZADOS Y LAMINADOS NO-CONVENCIONALES./
dc.relation.isformatof
Reproducció digital del document publicat a: http://dx.doi.org/10.1016/j.engfracmech.2016.01.019
dc.relation.ispartof
© Engineering Fracture Mechanics, 2015, vol. 168, núm. part B, p.28-39
dc.relation.ispartofseries
Articles publicats (D-EMCI)
dc.rights
Tots els drets reservats
dc.subject
Materials laminats
Laminated materials
Assaigs de materials
Materials -- Testing
Materials compostos -- Deslaminatge
Composite materials -- Delamination
dc.title
A quick procedure to predict free-edge delamination in thin-ply laminates under tension
dc.type
info:eu-repo/semantics/article
dc.rights.accessRights
info:eu-repo/semantics/embargoedAccess
dc.embargo.terms
Cap
dc.date.embargoEndDate
info:eu-repo/date/embargoEnd/2026-01-01
dc.type.version
info:eu-repo/semantics/publishedVersion
dc.identifier.doi
http://dx.doi.org/10.1016/j.engfracmech.2016.01.019
dc.identifier.idgrec
024372
dc.contributor.funder
Ministerio de Economía y Competitividad (Espanya)
dc.relation.ProjectAcronym
COMPUESTOS MULTIFUNCIONALES Y TOLERANTES AL DAÑO: INTEGRACION DE NANOREFUERZOS DE CARBONO AVANZADOS Y LAMINADOS NO-CONVENCIONALES.
EVALUACION DE COMPOSITES LAMINADOS DE CAPAS FINAS PARA APLICACIONES AERONAUTICAS Y AEROESPACIALES
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