National Research Council of Canada. NRC Institute for Aerospace Research
aircraft; corrosion; finite element method; joints
Finite element techniques were used to determine the effect that pillwing, caused by the presence of corrission products, has on the stress in fuselarge lap joints. The stress caused byt he internal pressure and the riviring process were taken into account, and the fuselarge curvature was ignored. The results show that the joint stress increases as the following increases (i.e. material loss increases). It is shown that pillowing can significantly increase the stress in a lap for material loss below the detection limit of current nondestructive inspection techniques thus increasing the risk of present cracking.