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Fatigue crack growth of aircraft aluminum alloys

dc.creatorPantelakis, Sp G.en
dc.creatorKermanidis, Al Then
dc.date.accessioned2015-11-23T10:42:31Z
dc.date.available2015-11-23T10:42:31Z
dc.date.issued2008
dc.identifier10.1007/978-1-4020-8520-8-13
dc.identifier.isbn9781402085192
dc.identifier.issn9250042
dc.identifier.urihttp://hdl.handle.net/11615/31611
dc.description.abstractThe microstructural characteristics and the influence of existing corrosion on fatigue crack growth in 2024 T351 aircraft aluminium alloy are investigated. Examined is the elongated grain morphology due to the rolling process that exhibited higher crack growth resistance than the microstructure of the sheet material with smaller equiaxed grains. Moreover, plate microstructure with high purity composition offered better damage tolerance characteristics in contrast to the conventional sheet microstructure. Shown is the need to account for the influence of pre-existing corrosion on the aluminum alloys in order to obtain more reliable results from fatigue and damage tolerance analyses of components with corroded areas. © Springer Science+Business Media B.V. 2008.en
dc.source.urihttp://www.scopus.com/inward/record.url?eid=2-s2.0-84884874107&partnerID=40&md5=9d9356298490dd8125a421fa2ef7b155
dc.subjectAircraft aluminiumen
dc.subjectCrack-growth resistanceen
dc.subjectElongated grainsen
dc.subjectEqui-axed grainsen
dc.subjectFatigue and damage tolerance analysisen
dc.subjectMicro-structural characteristicsen
dc.subjectReliable resultsen
dc.subjectRolling processen
dc.subjectCorrosionen
dc.subjectDamage toleranceen
dc.subjectFatigue crack propagationen
dc.subjectFits and tolerancesen
dc.subjectMicrostructureen
dc.subjectCracksen
dc.titleFatigue crack growth of aircraft aluminum alloysen
dc.typeotheren


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