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Multi-site delamination analysis using virtual crack closure technique for a composite aircraft wing flap

Research output: Chapter in Book/Report/Conference proceedingConference contributionScientificpeer-review

Details

Original languageEnglish
Title of host publication31st Congress of the International Council of the Aeronautical Sciences (Proceedings)
Subtitle of host publicationBelo Horizonte, Brazil September 9-14, 2018
PublisherICAS Press
ISBN (Electronic)978-3-932182-88-4
Publication statusPublished - Sep 2018
Publication typeA4 Article in a conference publication
EventINTERNATIONAL COUNCIL OF THE AERONAUTICAL SCIENCES CONGRESS -
Duration: 1 Jan 1900 → …

Conference

ConferenceINTERNATIONAL COUNCIL OF THE AERONAUTICAL SCIENCES CONGRESS
Period1/01/00 → …

Abstract

In this study, we investigate the application of virtual crack closure technique (VCCT) for a multi-site delamination damage in the F-18 Hornet fighter aircraft’s wing flap. The work focuses on the interaction between multiple delamination sites at different ply interfaces. The effects of numerical analysis parameters, such as energy release rate tolerance, on the criticality of the delamination and on the delamination growth are also studied.

Keywords

  • Multi-site damage, Finite element analysis, Fighter aircraft, Flap

Publication forum classification

Field of science, Statistics Finland