Stress Analysis of A Splice Joint in an Aircraft Fuselage with the Prediction of Fatigue Life to Crack Initiation

The objective of this dissertation is to Stress analysis and prediction of fatigue life to crack initiation in an in a transport aircraft fuselage. Typical splice joint panel consisting of skin plates, doubler plate is considered for the study. Aluminium alloy 2024-T351 material is considered for all the structural elements of the panel. A two dimensional finite element-analysis will be carried out on the splice joint panel. A panel consisting of a splice joint of a fuselage is considered for the linear static analysis, and then applying loads and boundary conditions on it. Cyclic pressurization loading is considered.