Investigation of Crack-Closure Prediction Models for Fatigue in Aluminum Alloy Sheet under Flight-Simulation Loading

摘要

The aims of the investigation are: Analysis and evaluation of the crack closure models (2nd generation); Collecting a representative data bank of flight simulation loading; Completing that data bank with new experiment on variables not yet well studied empirically; Improvement of models, mainly the CORPUS model. Because the closure models (2nd generation models) developed so far were almost exclusively checked by the originators of the model, a general comparative study of these models would seem to be most opportune. The load spectra involved are mainly representative for aircraft wing tension skins, and the materials considered are aluminum alloy sheet materials widely used in the aircraft industry, i.e. 2024-T3 and 7075-T6.