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Retardation effects due to overloads in aluminium-alloy aeronautical components

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posted on 2017-04-10, 08:49 authored by Angelo R. Maligno, R. Citarella, Vadim SilberschmidtVadim Silberschmidt
© 2017 Wiley Publishing Ltd.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.

History

School

  • Mechanical, Electrical and Manufacturing Engineering

Published in

Fatigue and Fracture of Engineering Materials and Structures

Citation

MALIGNO, A.R., CITARELLA, R. and SILBERSCHMIDT, V.V., 2017. Retardation effects due to overloads in aluminium-alloy aeronautical components. Fatigue and Fracture of Engineering Materials and Structures, 40 (9), pp. 1484–1500.

Publisher

© Wiley

Version

  • AM (Accepted Manuscript)

Publisher statement

This work is made available according to the conditions of the Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International (CC BY-NC-ND 4.0) licence. Full details of this licence are available at: https://creativecommons.org/licenses/by-nc-nd/4.0/

Acceptance date

2017-01-25

Publication date

2017

Notes

This is the peer reviewed version of the following article: MALIGNO, A.R., CITARELLA, R. and SILBERSCHMIDT, V.V., 2017. Retardation effects due to overloads in aluminium-alloy aeronautical components. Fatigue and Fracture of Engineering Materials and Structures, 40 (9), pp. 1484–1500., which has been published in final form at http://dx.doi.org/10.1111/ffe.12591. This article may be used for non-commercial purposes in accordance with Wiley Terms and Conditions for Self-Archiving

ISSN

8756-758X

eISSN

1460-2695

Language

  • en

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