Mechanical response of carbon fiber reinforced epoxy composite parts joined with varying bonding techniques for aerospace applications

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dc.authoridYunus, Doruk/0000-0003-1500-7347
dc.contributor.authorKaraboga, Furkan
dc.contributor.authorGolec, Fatih
dc.contributor.authorYunus, Doruk Erdem
dc.contributor.authorToros, Serkan
dc.contributor.authorOz, Yahya
dc.date.accessioned2024-11-07T13:32:26Z
dc.date.available2024-11-07T13:32:26Z
dc.date.issued2024
dc.departmentNiğde Ömer Halisdemir Üniversitesi
dc.description.abstractAs a result of the widespread use of composite materials in primary structures of aerospace platforms, composite joining became more crucial. This study addresses the effect of joining methods on the strength of composite joints experimentally, numerically and analytically. Single lap joint shear strengths of carbon fiber reinforced epoxy composite parts joined by mechanical fastening with a pop and solid rivet, secondary bonding with a paste adhesive, co-curing and co-bonding techniques were compared. In addition, the effect of adhesive thicknesses (0.2, 0.4, 0.6, 0.76 mm) on the single lap shear strength was investigated. Carbon fiber reinforced composite (CFRP) samples were produced according to the ASTM 5868 standard. After the production of samples with varying joining methods, single lap shear tests were implemented. Moreover, the interface damage in the composites was examined by use of a scanning electron microscope (SEM) for the purpose of studying the damage mechanism. Fracture mechanisms corresponding with bonding methods were also assessed by examining the fracture surface of the composite samples. Furthermore, results were analyzed by Hypermesh, ABAQUS and ESAComp. For instance, the co-bonded sample with an adhesive film exhibits an experimental shear strength of 24.03 MPa which deviates only 3 % from the numerical expectation.
dc.description.sponsorshipScientific and Technological Research Council of Turkey [20AG020]; The 2209-A programs; [20AG001]
dc.description.sponsorshipAuthors thank N. Ercan and M. Ozkutlu Demirel for support. More-over, authors are grateful to Turkish Aerospace, Turkey, and acknowledge financial support by the Scientific and Technological Research Council of Turkey within the 1004 (project ns. 20AG001 as well as 20AG020) and 2209-A programs.
dc.identifier.doi10.1016/j.compstruct.2024.117920
dc.identifier.issn0263-8223
dc.identifier.issn1879-1085
dc.identifier.scopus2-s2.0-85183167175
dc.identifier.scopusqualityQ1
dc.identifier.urihttps://doi.org/10.1016/j.compstruct.2024.117920
dc.identifier.urihttps://hdl.handle.net/11480/15414
dc.identifier.volume331
dc.identifier.wosWOS:001173585900001
dc.identifier.wosqualityN/A
dc.indekslendigikaynakWeb of Science
dc.indekslendigikaynakScopus
dc.language.isoen
dc.publisherElsevier Sci Ltd
dc.relation.ispartofComposite Structures
dc.relation.publicationcategoryMakale - Uluslararası Hakemli Dergi - Kurum Öğretim Elemanı
dc.rightsinfo:eu-repo/semantics/closedAccess
dc.snmzKA_20241106
dc.subjectAerospace applications
dc.subjectComposite joining
dc.subjectCo-bonding
dc.subjectCo-curing
dc.subjectLap shear strength
dc.subjectMechanical joining
dc.subjectOverlap joining
dc.titleMechanical response of carbon fiber reinforced epoxy composite parts joined with varying bonding techniques for aerospace applications
dc.typeArticle

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