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


Research units

  • Tampere University


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.


Original languageEnglish
Title of host publication31st Congress of the International Council of the Aeronautical Sciences, ICAS 2018
Publication statusPublished - 1 Jan 2018
MoE publication typeA4 Article in a conference publication
EventInternational Council Of The Aeronautical Sciences Congress - Belo Horizonte, Brazil
Duration: 9 Sep 201814 Sep 2018
Conference number: 31


ConferenceInternational Council Of The Aeronautical Sciences Congress
Abbreviated titleICAS
CityBelo Horizonte

    Research areas

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

ID: 31626820