Show simple item record

dc.contributor.authorMaligno, Angelo
dc.contributor.authorCitarella, Roberto
dc.contributor.authorSilberschmidt, Vadim V.
dc.date.accessioned2017-04-19T14:52:50Z
dc.date.available2017-04-19T14:52:50Z
dc.date.issued2017-02-08
dc.identifier.citationMaligno, A. et al (2017) 'Retardation effects due to overloads in aluminium-alloy aeronautical components', Fatigue & Fracture of Engineering Materials & Structures, DOI: 10.1111/ffe.12591.en
dc.identifier.issn8756758X
dc.identifier.doi10.1111/ffe.12591
dc.identifier.urihttp://hdl.handle.net/10545/621555
dc.description.abstractFatigue data are generally derived under constant-amplitude loading conditions, but aircraft components are subjected to variable-amplitude loading. Without interaction effects, caused by overloads and underloads intermingled in a loading sequence, it could be relatively easy to establish a crack growth curve by means of a cycle-by-cycle integration. However, load-spectrum effects largely complicate a crack growth under variable-amplitude cycling. In this paper, fatigue crack growth behaviour of aeronautical aluminium alloy 2024-T3 was studied. Effects of various loading conditions such as stress ratio and amplitude loadings were investigated. In particular, the effect of different overloads on the fatigue crack growth was simulated using Zencrack code. Preliminary analyses on Compact Tension (CT) specimens proved that the numerical results generated were in agreement with the results provided by an afgrow code for the same conditions. A case study was carried out on a helicopter component, undergoing repeated overloads, to compare numerical results obtained implementing yield zone models in Zencrack.
dc.description.sponsorshipN/Aen
dc.language.isoenen
dc.publisherWileyen
dc.relation.urlhttp://doi.wiley.com/10.1111/ffe.12591en
dc.rightsArchived with thanks to Fatigue & Fracture of Engineering Materials & Structuresen
dc.subjectFatigue crack propagationen
dc.subjectLoad spectrum effectsen
dc.subjectYield zoneen
dc.subjectFinite element modellingen
dc.titleRetardation effects due to overloads in aluminium-alloy aeronautical componentsen
dc.typeArticleen
dc.contributor.departmentUniversity of Derbyen
dc.contributor.departmentUniversity of Salernoen
dc.contributor.departmentUniversity of Loughboroughen
dc.identifier.journalFatigue & Fracture of Engineering Materials & Structuresen
dc.contributor.institutionInstitute for Innovation in Sustainable Engineering; University of Derby; Quaker Way, Derby DE1 3HD UK
dc.contributor.institutionDepartment of Industrial Engineering; University of Salerno; via Giovanni Paolo II, Fisciano SA Italy
dc.contributor.institutionWolfson School of Mechanical and Manufacturing Engineering; Loughborough University; Loughborough UK
dcterms.dateAccepted2017-01-18
refterms.dateFOA2018-02-08T00:00:00Z
html.description.abstractFatigue data are generally derived under constant-amplitude loading conditions, but aircraft components are subjected to variable-amplitude loading. Without interaction effects, caused by overloads and underloads intermingled in a loading sequence, it could be relatively easy to establish a crack growth curve by means of a cycle-by-cycle integration. However, load-spectrum effects largely complicate a crack growth under variable-amplitude cycling. In this paper, fatigue crack growth behaviour of aeronautical aluminium alloy 2024-T3 was studied. Effects of various loading conditions such as stress ratio and amplitude loadings were investigated. In particular, the effect of different overloads on the fatigue crack growth was simulated using Zencrack code. Preliminary analyses on Compact Tension (CT) specimens proved that the numerical results generated were in agreement with the results provided by an afgrow code for the same conditions. A case study was carried out on a helicopter component, undergoing repeated overloads, to compare numerical results obtained implementing yield zone models in Zencrack.


Files in this item

Thumbnail
Name:
Maligno_2017_Retardation_effec ...
Size:
207.0Kb
Format:
PDF
Description:
Accepted Manuscript

This item appears in the following Collection(s)

Show simple item record