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dc.contributor.authorWan, L
dc.contributor.authorIsmail, Y
dc.contributor.authorSheng, Yong
dc.contributor.authorWu, K
dc.contributor.authorYang, D
dc.date.accessioned2021-08-17T11:46:23Z
dc.date.available2021-08-17T11:46:23Z
dc.date.issued2020-09-30
dc.identifier.citationWan, L., Ismail, Y., Sheng, Y., Wu, K. and Yang, D. (2020) Progressive failure analysis of CFRP composite laminates under uniaxial tension using a discrete element method. Journal of Composite Materials, 55(8), pp. 1091–1108.en
dc.identifier.issn0021-9983en
dc.identifier.doi10.1177/0021998320961460en
dc.identifier.urihttp://hdl.handle.net/2436/624269
dc.description© 2020 The Authors. Published by SAGE. This is an open access article available under a Creative Commons licence. The published version can be accessed at the following link on the publisher’s website: https://doi.org/10.1177/0021998320961460en
dc.description.abstractThis study presents a 3D Discrete Element Method (DEM) model for the progressive failure analysis of Carbon Fiber Reinforced Polymer (CFRP) composite materials subjected to uniaxial tensile loading. Particles in the model are packed and bonded in regular patterns (hexagonal or square). The relationship between the bond stiffness and material properties is established based on the average strain energy method. The random distribution of bond strengths calibrated from experiments with a variation of 30% and 10% following a normal distribution law is assigned to the bonds in 0∘ and 90∘ plies to capture random cracks, respectively. Tsai-Hill failure criterion is utilized for the calibration of bond strength of (Formula presented.) plies to predict their failures in composite laminates. Quantitative and qualitative analyses were conducted for predicting the damage initiation and propagation of the cross-ply and Quasi-Isotropic (QI) composite laminates under tensile loading, respectively. Two interface stiffnesses were utilized in the failure prediction of cross-ply composite laminates, and it was found that the numerical results with the interface stiffness calculated from fracture energy are in good, quantitative agreements with the experiments. All the four stages of the failure process of QI composite laminates are well captured by the 3D DEM model, including isolated cracks, inner delamination cracks, outer delamination cracks and final failure.en
dc.description.sponsorshipThis work was supported by the China Scholarship Council (CSC) and University of Leeds.en
dc.formatapplication/pdfen
dc.languageen
dc.language.isoenen
dc.publisherSAGEen
dc.relation.urlhttps://journals.sagepub.com/doi/10.1177/0021998320961460en
dc.subjectTsai-Hill Criterionen
dc.subjectCFRPen
dc.subjectfailure progressionen
dc.subjectcomposite laminatesen
dc.subjectdiscrete element methoden
dc.titleProgressive failure analysis of CFRP composite laminates under uniaxial tension using a discrete element methoden
dc.typeJournal articleen
dc.identifier.eissn1530-793X
dc.identifier.journalJournal of Composite Materialsen
dc.date.updated2021-08-17T10:55:15Z
rioxxterms.funderChina Scholarship Council (CSC) and University of Leedsen
rioxxterms.identifier.projectUOW17082021YSen
rioxxterms.versionVoRen
rioxxterms.licenseref.urihttps://creativecommons.org/licenses/by-nc/4.0/en
rioxxterms.licenseref.startdate2021-08-17en
dc.source.volume55
dc.source.issue8
dc.source.beginpage1091
dc.source.endpage1108
dc.description.versionPublished version
refterms.dateFCD2021-08-17T11:45:34Z
refterms.versionFCDVoR
refterms.dateFOA2021-08-17T11:46:23Z


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