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Static and high-rate loading of single and multi-bolt carbon-epoxy aircraft fuselage joints

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dc.contributor.author Egan, Brian
dc.contributor.author McCarthy, Conor T.
dc.contributor.author McCarthy, Michael A.
dc.contributor.author Gray, P.J.
dc.contributor.author O'Higgins, Ronan M.
dc.date.accessioned 2013-10-23T10:51:07Z
dc.date.available 2013-10-23T10:51:07Z
dc.date.issued 2013
dc.identifier.citation Egan, B., McCarthy, C.T., McCarthy, M.A., Gray, P.J., O'Higgins, R.M. (2013) 'Static and high-rate loading of single and multi-bolt carbon-epoxy aircraft fuselage joints'. Composites Part A-Applied Science And Manufacturing, 53 :97-108. en_US
dc.identifier.uri http://hdl.handle.net/10344/3411
dc.description peer-reviewed en_US
dc.description.abstract Single-lap shear behaviour of carbon epoxy composite bolted aircraft fuselage joints at quasi-static and dynamic (5 m/s and 10 m/s) loading speeds is studied experimentally. Single and multi-bolt joints with countersunk fasteners were tested. The initial joint failure mode was bearing, while final failure was either due to fastener pull-through or fastener fracture at a thread. Much less hole bearing damage, and hence energy absorption, occurred when the fastener(s) fractured at a thread, which occurred most frequently in thick joints and in quasi-static tests. Fastener failure thus requires special consideration in designing crashworthy fastened composite structures; if it can be delayed, energy absorption is greater. A correlation between energy absorption in multi-bolt and single-bolt joint tests indicates potential to downsize future test programmes. Tapering a thin fuselage panel layup to a thicker layup at the countersunk hole proved highly effective in achieving satisfactory joint strength and energy absorption. en_US
dc.language.iso eng en_US
dc.publisher Elsevier en_US
dc.relation info:eu-repo/grantAgreement/EC/FP7/213371 en_US
dc.relation.ispartofseries Composities Part A: Applied Science and Manufacturing;53, pp. 97-108
dc.relation.uri http://www.sciencedirect.com/science/article/pii/S1359835X13001401#!
dc.relation.uri http://dx.doi.org/10.1016/j.compositesa.2013.05.006
dc.rights This is the author’s version of a work that was accepted for publication in Composites Part A: Applied Science and Manufacturing. Changes resulting from the publishing process, such as peer review, editing, corrections, structural formatting, and other quality control mechanisms may not be reflected in this document. Changes may have been made to this work since it was submitted for publication. A definitive version was subsequently published in Composities Part A: Applied Science and Manufacturing 2013, 53, pp. 97-108, http://dx.doi.org/10.1016/j.compositesa.2013.05.006. en_US
dc.subject polymer matrix composities en_US
dc.subject fracture en_US
dc.subject mechanical testing en_US
dc.subject joints/joining en_US
dc.title Static and high-rate loading of single and multi-bolt carbon-epoxy aircraft fuselage joints en_US
dc.type info:eu-repo/semantics/article en_US
dc.type.supercollection all_ul_research en_US
dc.type.supercollection ul_published_reviewed en_US
dc.date.updated 2013-10-22T12:57:20Z
dc.description.version ACCEPTED
dc.contributor.sponsor ERC en_US
dc.relation.projectid 213371 en_US
dc.rights.accessrights info:eu-repo/semantics/openAccess en_US
dc.internal.rssid 1444995
dc.internal.copyrightchecked Yes
dc.description.status peer-reviewed


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