This report is a compilation of bulging factor solutions obtained at the Federal Aviation Administration William J. Hughes Technical Center for cracks in typical transport category aircraft. The solutions were obtained for longitudinal cracks in the critical rivet row of longitudinal lap splice joints. Both unstiffened and frame- and longeron-stiffened configurations were considered. The loading, crack length, skin thickness, substructure spacing, and properties were varied. Baseline solutions for cracks in an unstiffened shell were also obtained. The results from these studies are compiled in this report, and the effects of the parameters that were varied on the bulging factor are discussed.
Bulging Factor Solutions for Cracks in Longitudinal Lap Joints of Pressurized Aircraft Fuselages
2004
42 pages
Report
No indication
English