Abstract
This work describes about the stress of a splice joint in a medium transport aircraft. Typical splice joint panel forming part of a fuselage, consisting of skin plates are riveted is considered for the study. The calculations have been performed by considering the cabin pressurization load on the panel. Aluminium alloy 2014 - T6 material considered for structural elements of the panel. Two dimensional finite element analyses have been carried out on the splice joint panel. The distribution of fasteners loads and local stress field at rivet locations read using element analysis. The global finite element analysis linear static analysis first segment of typical fuselage will be carried out. The Global finite element analysis results will be benchmark for comparing the result from the splice joint panel analysis. Repeated finite element analysis will be carried out to get the response of the parent structure fuselage find location the maximum stress location will be identified from the analysis.
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