B.G. Journet, F. Congourdeau, C. Ithurralde, S. Bouissou, C. Meyer

Fuselage dents will be the object of the damage tolerance requirements in the future. Current fatigue crack growth calculation methods need to be improved. Tests are run on dented coupons to report on crack initiation and propagation. Two approaches to predict the fatigue crack growth rates in dented areas are presented and assessed. The first one is a simple 2D approach with assumptions on the influence of the dent in order to calculate the stress intensity factor. The second one is a finite element based approach, which better addresses the influence of the dent. This approach simulates the denting process in order to set up the 3D shape of the dent and the corresponding residual stress field. Then a through crack is introduced in the dented area. The service load is applied and the resulting stress field ahead of the crack tip is analysed in order to derive the elastic stress singularity. With the knowledge of the baseline material behavior, prediction of the fatigue crack growth rates is made. The experimental crack growth rate data are compared to the predictions given by both approaches.

23rd ICAF Symposium of the international Committee on Aeronautical Fatique, 2005, Hamburg

Conference Paper

englisch

A5, 12 Seiten

DGLR-Bericht, 2005, 2005-03, 23rd ICAF Symposium of the international Committee on Aeronautical Fatique - Proceedings; S.722-733; 2005; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

simulation, aluminum alloys, fatigue cracks, dents, finite elements analysis

Bestellbar

2005