A fundamental aspect of the replacement of the riveted to welded aluminum aircraft fuselage sections is the fatigue behavior. In this work, a fiber laser was used to produce different types of T-joint coupons in order to evaluate their crack propagation procedure during standard C(T) tests. Some defects such as cracks and pores had been observed and directly influenced the lifetime during testing. The cracks observed in high-speed regimes were associated with the hot cracking phenomena, and those coupons were not considered for crack propagation tests. These tests were carried out with the stringer parallel or perpendicular to the crack tip. The stringer has a positive effect on the fatigue crack propagation results, but the appearance of defects dramatically decreases the fatigue lives. The better results were those where the stringer was placed perpendicular to the crack, because of a retardation of the crack growth, in particular, 4 mm before reaching the joint.
The International Journal of Advanced Manufacturing Technology – Springer Journals
Published: Apr 11, 2017
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