Abstract: Based on the wing panel test results of a transport airplane and others, an engineering model and numerical results for the reliability analysis of wing panels are given in this paper through statistical analysis. TheP-da/ dn-ΔKCurves are obtained by using Weibull distribution under a given confidence. Furthermore, a comparison is made between the fatigue crack growth rates of panels for the same reliability and different stiffness ratios. These results can be used as an important reference in durability, damage tolerance design and reliability design of aircraft structures.

Key words: reliability, fatigue crack growth, statistical nature, Weibull distribution