Some Computational Tools for the Analysis of through Cracks in Stiffened FuselageShells

摘要

A method for computing the energy release rate for cracks of varying length in atypical stiffened metallic fuselage under general loading conditions is presented. Reliable analytical methods that predict the structural integrity and residual strength of aircraft fuselage structures containing cracks are needed to help to understand the behavior of pressurized stiffened shells with damage, to determine the safe life of such a shell. The models used in the simulation are derived from an extensive analysis of a fuselage barrel section subjected to operational flight loads. Energy release rates are computed as a function of the length of the crack, its location, and the crack propagation mode.