David L. DuQuesnay

TL;DR: In this paper, the authors investigated the growth behavior of fatigue cracks initiated at corrosion pits in laboratory coupons of 7075-T6511 aluminium alloy subjected to a transport aircraft loading spectrum.

TL;DR: Stress relief in the substrate due to enhanced heat transfer mechanisms was identified as the most likely source of the observed reductions in substrate fatigue life in the 150 microm coupons.

TL;DR: In this paper, the authors examined the corrosion-fatigue behavior of 7075-T651 aluminum alloy subjected to periodic overloads and found that the reduced fatigue life was due primarily to corrosion pit formation and a combination of anodic dissolution at the crack tip and hydrogen embrittlement.

TL;DR: In this paper, the authors examined the hypothesis that variations in the crack opening stress level of short cracks can account for the observed variations in fatigue strength with mean stress under constant-amplitude cyclic loading.

TL;DR: In this article, the load interaction effect of large stress cycles on the fatigue behavior of subsequent smaller cycles was investigated on an aluminium alloy and the results indicated that small cycles, including those below the constant-amplitude fatigue limit, can contribute significantly to damage accumulation, and therefore small cycles should not be ignored when predicting fatigue lives.