FAILURE BATE FUNCTION FOB RELIABILITY ANALYSIS OF PRESSURIZED FUSELAGE STRUCTURE

摘要

The purpose of this study was to estimate failure rate functions after fatigue crack initiation applied to Bayesian reliability analysis. Fatigue cracks propagating in internal fuselage structural components are computed by a Monte Carlo simulation technique. The structural components are subjected to cyclic constant loads due to differential pressures. Random variables are a parameter in the power law of fatigue crack propagation, modification coefficients for stress intensity factors, cyclic stress ranges and residual strength evaluated by Feddersen's method used for the damage tolerance design of aircraft structures. A two-parameter Weibull distribution function is applied to failure rate functions for these fuselage structural elements. The shape parameters in the distribution function are estimated using the simulation results.