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Modelling of a cracked aluminium plate repaired with composite octagonal patch in mode I and mixed mode

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dc.contributor.author D, Ouinas
dc.contributor.author BB, Bouidjra
dc.contributor.author N, Benderdouche
dc.date.accessioned 2019-01-09T07:30:06Z
dc.date.available 2019-01-09T07:30:06Z
dc.date.issued 2009
dc.identifier.issn 0264-1275
dc.identifier.uri http://e-biblio.univ-mosta.dz/handle/123456789/8235
dc.description.abstract Résumé : Adhesively bonded composite patch repair technique has been successfully applied in military aircraft repair and has recently been expanded to commercial aircraft industry. This technique is applied to extend the service life of cracked aluminium components. In this paper, the finite element method is applied to analyse the central crack’s behaviour repaired by a boron/epoxy composite patch. The effects of the mechanical and geometrical properties of the patch on the variation of the stress intensity factor at the crack tip were highlighted. The obtained results show that the stress intensity factor at the crack tip, repaired by an octagonal patch of height 2c/3, is reduced by 5% with regard to the one repaired by an octagonal patch of size ‘c’. For a height patch of c/3 the reduction is about 7%. The maximum reduction of composite patch of fibres in y-direction is about 30% compared to the aluminium patch. This reduction en_US
dc.language.iso en en_US
dc.publisher Materials and Design en_US
dc.relation.ispartofseries Num 3;Vol 30
dc.subject Bonded composite, cracked aluminium, boron/epoxy patch en_US
dc.title Modelling of a cracked aluminium plate repaired with composite octagonal patch in mode I and mixed mode en_US
dc.type Article en_US


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