• Login
    View Item 
    •   Home
    • Research Publications
    • Engineering & Technology
    • Institute for Innovation in Sustainable Engineering
    • View Item
    •   Home
    • Research Publications
    • Engineering & Technology
    • Institute for Innovation in Sustainable Engineering
    • View Item
    JavaScript is disabled for your browser. Some features of this site may not work without it.

    Browse

    All of UDORACommunitiesTitleAuthorsIssue DateSubmit DateSubjectsThis CollectionTitleAuthorsIssue DateSubmit DateSubjects

    My Account

    LoginRegister

    About and further information

    AboutOpen Access WebpagesOpen Access PolicyTake Down Policy University Privacy NoticeUniversity NewsTools for ResearchersLibraryUDo

    Statistics

    Display statistics

    Retardation effects due to overloads in aluminium-alloy aeronautical components

    • CSV
    • RefMan
    • EndNote
    • BibTex
    • RefWorks
    Thumbnail
    Name:
    Maligno_2017_Retardation_effec ...
    Size:
    207.0Kb
    Format:
    PDF
    Description:
    Accepted Manuscript
    Download
    Authors
    Maligno, Angelo
    Citarella, Roberto
    Silberschmidt, Vadim V.
    Affiliation
    University of Derby
    University of Salerno
    University of Loughborough
    Issue Date
    2017-02-08
    
    Metadata
    Show full item record
    Abstract
    Fatigue 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.
    Citation
    Maligno, 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.
    Publisher
    Wiley
    Journal
    Fatigue & Fracture of Engineering Materials & Structures
    URI
    http://hdl.handle.net/10545/621555
    DOI
    10.1111/ffe.12591
    Additional Links
    http://doi.wiley.com/10.1111/ffe.12591
    Type
    Article
    Language
    en
    ISSN
    8756758X
    ae974a485f413a2113503eed53cd6c53
    10.1111/ffe.12591
    Scopus Count
    Collections
    Institute for Innovation in Sustainable Engineering

    entitlement

     
    DSpace software (copyright © 2002 - 2021)  DuraSpace
    Quick Guide | Contact Us
    Open Repository is a service operated by 
    Atmire NV
     

    Export search results

    The export option will allow you to export the current search results of the entered query to a file. Different formats are available for download. To export the items, click on the button corresponding with the preferred download format.

    By default, clicking on the export buttons will result in a download of the allowed maximum amount of items.

    To select a subset of the search results, click "Selective Export" button and make a selection of the items you want to export. The amount of items that can be exported at once is similarly restricted as the full export.

    After making a selection, click one of the export format buttons. The amount of items that will be exported is indicated in the bubble next to export format.