H. Sato, Y. Yamada, Y. Tanoue, T. Sakagawa

Friction stir welding is the one of the advanced joining methods for aircraft. In this study fatigue and crack propagation properties of FSW lap joints were examined using coupon specimens and sub-component structures compared with riveted structures. Fatigue properties of FSW joints are not always superior to those of riveted joints, because of high stress concentration near the FSW area. From the coupon fatigue tests, frame mouse hole areas of skin-stringer/frame panels were supposed to be one of the critical points. So sub-component tests simulated the mouse area hole were conducted. The results show that the crack occurs at FSW area as expected, while the fatigue life of the components meets our target. Crack propagation properties of FSW joints were also evaluated using coupon specimens and sub-component structures. Crack propagation properties were strongly affected by residual stresses due to FSW. Tensile residual stresses accelerate the crack growth, and compressive residual stresses suppress crack growth. These crack growth behaviors can be explained by the linear fracture mechanics which is used for the conventional welded structures.

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

Conference Poster

englisch

A5, 12 Seiten

DGLR-Bericht, 2005, 2005-03, 23rd ICAF Symposium of the international Committee on Aeronautical Fatique - Proceedings; S.645-656; 2005; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

crack propagation, friction stir welding, panels

Bestellbar

2005