Comparison between two and three parameters of fatigue crack growth models in airframe structures
Vol 9 No 2 (2005): Proceedings of the sixth international seminar on “Recent Research and Design Progress in Aeronautical Engineering and its Influence on Education” – Riga, Latvia
Comparison of two and three parameters models of fatigue crack growth is discussed. For calculation of failure probability, the Monte Carlo (MC) method is used. The number of MC trials was 60. Multiple site fatigue damage specimens corroded to 5% to 6% average thickness loss and non‐corroded specimens were used in the fatigue tests. As initial data, the result of these fatigue tests of corroded and non‐corroded specimens are used. It is shown that at a small number of inspections there is a significant difference between probabilities of failure (fatigue crack is not discovered before specified life). But if the number of inspections is large enough, than the difference between considered models is negligible for both corroded and non‐corroded specimens.
Wahab, M. S., & Paramonov, Y. M. (2005). Comparison between two and three parameters of fatigue crack growth models in airframe structures. Aviation, 9(2), 17-23. https://doi.org/10.3846/16487788.2005.9635899
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