Abstract:

The fatigue experimental studies of some multiple holed and cracked plates and fastener joints exposed to constant amplitude as well as flight by flight loading spectra have been carried out for the damage tolerance evaluation of typical aircraft wing structural components. The experimental results have shown some major features and models of multiple crack initiation and growth, which provide the experimental evidence served for the study of multiple site fracture theory and residual strength criterion in multiple cracked structures.

Key words: multiple cracked structure, fastener joint, flight-by-flight spectr um loading, damage toler ance test