The results of a parametric study assessing the effects of corrosion on fatigue characteristics in riveted fuselage joints are described. Using a uniaxial specimen, known to produce realistic multiple site damage (MSD), testing of seven specimens, four pre-corroded and three non-corroded, was completed. This work is part of the ageing aircraft research activities being conducted by Carleton University, in collaboration with the National research Council of Canada (NRC).; Corrosion pitting is known to play an important role in expediting fatigue crack nucleation in fuselage joints. However, corrosion-fatigue research incorporating the effects of corroded surface topography is limited. The work described herein, addresses this issue and develops an approach for quantifying corrosion pitting damage, suitable for use in fracture mechanics modelling. Measurement of corrosion topography is accomplished using digitised x-ray (DXR) images of fuselage joint specimens. Using finite element modelling, a relationship has been established between corrosion pitting geometry and the corresponding stress concentration factor (SCF). A probabilistic approach was utilised for representing corrosion damage in fuselage joints. Therefore, probability distributions of pit depth and SCF have been developed, for varying levels of material thickness loss.
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