期刊名称：International Journal of Innovative Research in Science, Engineering and Technology
印刷版ISSN：2347-6710
电子版ISSN：2319-8753
出版年度：2015
卷号：4
期号：5
页码：3182
DOI：10.15680/IJIRSET.2015.0405101
出版社：S&S Publications
摘要：Aircraft designer needs to ensure the structural integrity of the airframe without compromising on thesafety of the structure. This requires several stress analysis of different components, which represents the features ofthe airframe. Also these analysis predictions have to be substantiated by structural testing during the developmentalphase. In current study a representative stiffened panel from a centre fuselage segment of an aircraft will be consideredfor the evaluation. The stress analysis of the stiffened panel will be carried out by using FEM approach. Aluminiumalloy 2024-T351 material is used for the stiffened panel. Fuselage structure experiences the hoop tension andlongitudinal tension because of the internal pressurization. If there is a crack in the unstiffened fuselage, under theflight condition it could lead to catastrophic failure of the structure. The fatigue crack will initiate normally from thehighest tensile stress locations. Therefore rivet locations are the most probable locations for fatigue crack initiation.Miner’s rule will be employed for the fatigue damage calculation and life estimation of the structure. S-N curve of thealuminium alloy 2024-T351 will be used for obtaining the number of cycles to failure at particular stress magnitudes.
