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dc.contributor.authorPitta, Siddharth
dc.contributor.authorRojas Gregorio, José Ignacio
dc.contributor.authorCrespo Artiaga, Daniel
dc.contributor.otherUniversitat Politècnica de Catalunya. Departament de Física
dc.date.accessioned2017-09-28T14:46:40Z
dc.date.available2017-09-28T14:46:40Z
dc.date.issued2017
dc.identifier.citationPitta, S., Rojas, J.I., Crespo, D. Comparison of fatigue crack growth of riveted and bonded aircraft lap joints made of Aluminium alloy 2024-T3 substrates – A numerical study. A: International Conference on Fracture Fatigue and Wear. "Journal of Physics: Conference Series, Volume 843, conference 1". Porto: Institute of Physics (IOP), 2017, p. 1-10.
dc.identifier.isbn1742-6596
dc.identifier.urihttp://hdl.handle.net/2117/108095
dc.description.abstractAircraft lap joints play an important role in minimizing the operational cost of airlines. Hence, airlines pay more attention to these technologies to improve efficiency. Namely, a major time consuming and costly process is maintenance of aircraft between the flights, for instance, to detect early formation of cracks, monitoring crack growth, and fixing the corresponding parts with joints, if necessary. This work is focused on the study of repairs of cracked aluminium alloy (AA) 2024-T3 plates to regain their original strength; particularly, cracked AA 2024-T3 substrate plates repaired with doublers of AA 2024-T3 with two configurations (riveted and with adhesive bonding) are analysed. The fatigue life of the substrate plates with cracks of 1, 2, 5, 10 and 12.7mm is computed using Fracture Analysis 3D (FRANC3D) tool. The stress intensity factors for the repaired AA 2024-T3 plates are computed for different crack lengths and compared using commercial FEA tool ABAQUS. The results for the bonded repairs showed significantly lower stress intensity factors compared with the riveted repairs. This improves the overall fatigue life of the bonded joint.
dc.format.extent10 p.
dc.language.isoeng
dc.publisherInstitute of Physics (IOP)
dc.rightsAttribution-NonCommercial-NoDerivs 3.0 Spain
dc.rights.urihttp://creativecommons.org/licenses/by-nc-nd/3.0/es/
dc.subjectÀrees temàtiques de la UPC::Física
dc.subject.lcshAluminum alloys
dc.subject.lcshFatigue
dc.subject.otherFatigue
dc.subject.otherstress intensity factor
dc.subject.otherfinite element analysis
dc.subject.othercrack
dc.subject.otherjoint
dc.subject.otherrepair
dc.titleComparison of fatigue crack growth of riveted and bonded aircraft lap joints made of Aluminium alloy 2024-T3 substrates – A numerical study
dc.typeConference report
dc.subject.lemacFatiga
dc.subject.lemacAlumini -- Aliatges
dc.contributor.groupUniversitat Politècnica de Catalunya. GCM - Grup de Caracterització de Materials
dc.identifier.doi10.1088/1742-6596/843/1/012035
dc.description.peerreviewedPeer Reviewed
dc.relation.publisherversionhttp://iopscience.iop.org/
dc.rights.accessOpen Access
local.identifier.drac21101185
dc.description.versionPostprint (published version)
local.citation.authorPitta, S.; Rojas, J.I.; Crespo, D.
local.citation.contributorInternational Conference on Fracture Fatigue and Wear
local.citation.pubplacePorto
local.citation.publicationNameJournal of Physics: Conference Series, Volume 843, conference 1
local.citation.startingPage1
local.citation.endingPage10


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Except where otherwise noted, content on this work is licensed under a Creative Commons license : Attribution-NonCommercial-NoDerivs 3.0 Spain