FATIGUE FAILURE PREDICTION FOR FUSELAGE SKIN MADE OF ALCLAD ALUMINIUM ALLOY
DOI:
https://doi.org/10.18372/2310-5461.18.4868Keywords:
damage tolerance, fatigue crack, deformation reliefAbstract
In spite of significant progress achieved in last years in the field of the providing the strength and lifespan of aircraft structures, fatigue cracks remain to be common defect that can be revealed at the diagnostic of the aircraft technical state. The skin of the majority of modern planes made of alclad aluminium alloy. The presented paper directed on the development of the new empirical-analytical method for the estimation of the duration of fatigue crack propagation in alclad aluminium alloys. The method is based on the usage of the regression equations, establishing the relationship between fatigue crack kinetic and damage accumulated near the stress concentrator. As the characteristics of the local damage, the following quantitative parameters of the deformation relief are used: the damage parameter D, which characterizes saturation of the relief; fractal dimension of the deformation relief clusters Dp/s,, which is a characteristic of the shape of deformation relief clusters. The quantitative analysis of the relief may be conducted by the analysis of the digital photos, obtained with magnification 200x-400xReferences
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