Effect of bird-strike on sandwich composite aircraft wing leading edge

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dc.contributor.authorArachchige, B.
dc.contributor.authorGhasemnejad, Hessam
dc.contributor.authorYasaee, Mehdi
dc.date.accessioned2020-06-16T14:13:19Z
dc.date.available2020-06-16T14:13:19Z
dc.date.issued2020-06-15
dc.description.abstractIn this paper, a parametric numerical study is performed on the sandwich composite leading edge to analyse the effect of skin thickness, layups, impact velocities to compare the performance of the two different reinforcements within sandwich leading-edge structures. The detailed numerical analysis of a composite leading edge reinforced with honeycomb and foam is developed using explicit finite element software, LS-DYNA. Initially, the study proposes the most suitable equations of state for impact on the metallic leading edge for different bird geometries made from Lagrangian and SPH methods. All the numerical results are verified with available experimental data in the literature. The results will deliver a cost-efficient and accurate numerical model which assists aircraft designers in deciding the combination of design variables resulting in improved impact resistance for sandwich aircraft structures under soft body impacts.en_UK
dc.identifier.citationArachchige B, Ghasemnejad H, Yasaee M. (2020) Effect of bird-strike on sandwich composite aircraft wing leading edge. Advances in Engineering Software, Volume 148, October 2020, Article number 102839en_UK
dc.identifier.issn0965-9978
dc.identifier.uri10.1016/j.advengsoft.2020.102839
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/15493
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.subjectBird strikeen_UK
dc.subjectLagrangianen_UK
dc.subjectSandwichen_UK
dc.subjectLeading edgeen_UK
dc.subjectLS-DYNASPHen_UK
dc.titleEffect of bird-strike on sandwich composite aircraft wing leading edgeen_UK
dc.typeArticleen_UK

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