Fatigue crack growth behavior of Al7050-T7451 attachment lugs under flight spectrum variation

Force Measurement and Evaluation Lab., Korea Research Institute of Standards and Science (KRISS), Daejeon 305-701, South Korea
Theoretical and Applied Fracture Mechanics (Impact Factor: 1.14). 09/2003; DOI: 10.1016/S0167-8442(03)00041-7

ABSTRACT This paper discusses an analytical and experimental investigations of the fatigue crack growth behavior in attachment lugs subjected to a randomized flight-by-flight spectrum. In the analysis, the stress intensity factors for through-the-thickness cracks initiating from lug holes were compared by weight function method, boundary element method (BEM), the interpolation of Brussat’s solution. The stress intensity factors of a corner crack at a transition region were obtained using two parameter weight function method and correction factors. Fatigue life under a load spectrum was predicted using stress intensity factors and Willenborg retardation model considering the effects of a tensile overload. Experiments were performed under a load spectrum and compared with the fatigue life prediction using the stress intensity factors by different methods. Changes of fatigue life and aspect ratio according to the clipping level of the spectrum were discussed through experiment and prediction. Effect of the spectrum clipping level on the fatigue life was experimentally evaluated by using beach marks of fractured surface.

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Available from: Soon-Bok Lee, Jun 23, 2015
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