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This paper describes about the stress analysis of a circumferential splice joint in a transport aircraft. Typical splice joint panel consisting of skin plates and bulkhead is considered for the study. The aluminium alloy 2024 T351 material is considered for all the structural elements of the panel. A 2 dimensional finite element analysis will be ca...
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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...