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Session: Poster pitches day 2
Session starts: Tuesday 27 June, 10:00
Presentation starts: 10:00
Room: Theatre room: plenary

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LI Sanyuan (AVIC Aircraft Strength Research Institute, Xi’an 710065, China)
CHEN Xianmin (AVIC Aircraft Strength Research Institute, Xi’an 710065, China)
DONG Dengke (AVIC Aircraft Strength Research Institute, Xi’an 710065, China)
CHEN Li (AVIC Aircraft Strength Research Institute, Xi’an 710065, China)

Abstract:
The aircraft structure includes a variety of typical details which determine the reliability life of aircraft structures. The modern aircraft structure should meet the requirements of long lifetime, high reliability and good economy, etc. Therefore, it is significant to perform the evaluation of the reliability life for aircraft structure details. In this paper, based on the Probabilistic Fracture Mechanics Approach (PFMA), we conduct the following study on the reliability life evaluation method for aircraft structure details. (1) Normal information diffusion estimation and grey estimation method are introduced to improve the estimation accuracy of the population distribution of the 3-parameter Weibull consistent distribution. The numerical analysis results show that the grey estimation method gives the best accuracy compared with the Gauss-Newton iterative method and the common correlation coefficient method. (2) In order to definite the calculation formula of crack exceedance, a critical factor of crack growth rate is proposed. Moreover, a reliability life evaluation method is put forward by combining the probabilistic durability with damage tolerance analysis. Furthermore, the Monte Carlo method is introduced to avoid complex integral operations. It is shown that the computing efficiency of Monte Carlo method is much better than the numerical integration method within a certain accuracy. (3) The reliability life evaluation method is programmed into a software, which makes the complex calculation processes simplified and more convenient for engineers. For the fatigue problem of notch details of the stringer ends in the upper panel of aircraft central wing, the stress level calculation is conducted for the weak details through Finite Element Analysis (FEA). The crack propagation data is obtained by fractographical analysis, as well. It is proved that the reliability life evaluated in this study is in line with that in the full-scale aircraft structural fatigue test.