Optimised laser peening strategies for damage tolerant aircraft structures

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dc.contributor.authorBusse, David Osman
dc.contributor.authorGanguly, Supriyo
dc.contributor.authorFurfari, Domenico
dc.contributor.authorIrving, Philip E.
dc.date.accessioned2020-10-28T16:53:59Z
dc.date.available2020-10-28T16:53:59Z
dc.date.issued2020-08-14
dc.description.abstractSimulation models were constructed to explore the influence of compressive residual stress on fatigue crack growth rates in aluminium sheet. Balanced residual stress fields resulting from imposition of compressive stresses in laser peen patches were calculated. Growth rates of cracks approaching, traversing and propagating away from peen patches were calculated using modified superposition models. Effects of patch dimensions and position on residual stress fields, growth rates and life were investigated. Overall life varied widely depending on the balance between retardation and acceleration; many peen arrangements had little or no life benefit. Implications of the results for damage tolerant design are discussed.en_UK
dc.identifier.citationBusse D, Ganguly S, Furfari D, Irving PE. (2020) Optimised laser peening strategies for damage tolerant aircraft structures. International Journal of Fatigue, Volume 141, December 2020, Article number 105890en_UK
dc.identifier.issn0142-1123
dc.identifier.urihttps://doi.org/10.1016/j.ijfatigue.2020.105890
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/15930
dc.language.isoenen_UK
dc.publisherElsevieren_UK
dc.rightsAttribution-NonCommercial-NoDerivatives 4.0 International*
dc.rights.urihttp://creativecommons.org/licenses/by-nc-nd/4.0/*
dc.subjectLaser peeningen_UK
dc.subjectResidual stress fielden_UK
dc.subjectFatigue crack growthen_UK
dc.subjectModified superpositionen_UK
dc.subjectDamage tolerance designen_UK
dc.titleOptimised laser peening strategies for damage tolerant aircraft structuresen_UK
dc.typeArticleen_UK

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