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Fatigue life analysis of the integral skin-stringer panel using xfem

dc.creatorSghayer, Abulgasem
dc.creatorGrbović, Aleksandar
dc.creatorSedmak, Aleksandar
dc.creatorDinulović, Mirko
dc.creatorDoncheva, Elisaveta
dc.creatorPetrovski, Blagoj
dc.date.accessioned2022-09-19T18:19:58Z
dc.date.available2022-09-19T18:19:58Z
dc.date.issued2017
dc.identifier.issn1451-3749
dc.identifier.urihttps://machinery.mas.bg.ac.rs/handle/123456789/2711
dc.description.abstractFatigue life of integral skin-stringer panels produced by laser beam welding (LBW) is analysed. This type of panel is used in airframe construction where fatigue and damage tolerance are of paramount importance, since aircrafts must be designed to tolerate relatively large fatigue cracks. The analysed integral skin-stringer panel is made of AL-AA 6156T6/2.8 mm, where stringers are laser beam welded to the airframe skin. By using the extended finite element method (XFEM), fatigue life of simple flat plate, as well of the skin-stringer panel, are numerically simulated in order to investigate the effect of stringers.en
dc.publisherInstitut za ispitivanje materijala, Beograd
dc.rightsopenAccess
dc.rights.urihttps://creativecommons.org/licenses/by-nc-nd/4.0/
dc.sourceStructural Integrity and Life
dc.subjectXFEMen
dc.subjectstress intensity factor (SIF)en
dc.subjectintegral skin-stringer structuresen
dc.subjectcrack propagation modellingen
dc.titleFatigue life analysis of the integral skin-stringer panel using xfemen
dc.typearticle
dc.rights.licenseBY-NC-ND
dc.citation.epage10
dc.citation.issue1
dc.citation.other17(1): 7-10
dc.citation.rankM24
dc.citation.spage7
dc.citation.volume17
dc.identifier.fulltexthttp://machinery.mas.bg.ac.rs/bitstream/id/1415/2708.pdf
dc.identifier.rcubhttps://hdl.handle.net/21.15107/rcub_machinery_2711
dc.identifier.scopus2-s2.0-85021669920
dc.identifier.wos000425514700002
dc.type.versionpublishedVersion


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