Crack growth life prediction based on Monte-Carlo method for high cycle fatigue dynamic component

The sensibility analysis of the factors to crack growth life has been done. The results show that the input parameters have the following precedence ordering: fatigue crack growth threshold, fracture spectrum, initial crack, fracture toughness, the sensibility values are 11.25, 8.5417, 0.8333, 0.1125, respectively. The model parameters have the following precedence ordering: n, p, C, q. the sensibility values are 6.0417, -3.9583, 1.25, 0.1812, respectively. The reliability analysis was conducted by Monte-Carlo method, the results show that the crack growth life accord with lognormal distribution. The lives with different reliability were obtained. The reliability analysis results of the crack growth life has provided the data for a hybrid approach based on a mixture of the traditional safe-life and damage tolerance techniques which were used as an optimal strategy for ensuring the helicopter structural integrity.