Stress Analysis of a Critical Splice Joint in the Fuselage Structure of an Airframe and Fatigue Life Estimation Due to Pressurization Cycles

Structural joints are the critical structural elements in the airframe structure. To ensure the structural integrity of the airframe one has to address all the joints first. Stress analysis plays an important role in identifying the critical locationsThis project describes about the stress analysis of a splice joint in a transportaircraft. Typical splice joint panel consisting of skin plates, doubler plate & longitudinal stiffener is considered for the study. Aluminium alloy 2024-T351material 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. Distribution of fasteners loads and local stress field at rivet locations will be studied from finite element analysis .This paper also describes the modifications required to correct the boundary effects of the panel. The global finite element analysis of a segment of typical fuselage will be carried out. This global finite element analysis results will be bench mark for comparing the results from the splice joint panel analysis. Repeated finite element analysis will be carried out to get the response of the parent structure (fuselage) at the joint location. The response of the splice joint will be evaluated through finite element analysis. Cabin pressurization is one of the critical load cases for the fuselage structure Fuselage experiences constant amplitude load cycles due to pressurization.The splice joint is one of the critical locations for fatigue crack to initiate. In this project prediction of fatigue life for crack initiation will be carried out at maximum stress location