A. Sane1,*, P. M. Padole1, R. V. Uddanwadiker1
CMES-Computer Modeling in Engineering & Sciences, Vol.115, No.2, pp. 281-294, 2018, DOI:10.3970/cmes.2018.05046
Abstract T shaped skin-stiffener joint are one of the most commonly used structures in aerospace components. It has been proven in various studies that these joints are susceptible to failure when loaded in pull out conditions however, in specific applications these joints undergo pull loading. De-lamination/de-bond nucleation and its growth is one of the most common failure mechanisms in a fiber reinforced composite structure. Crack growth takes place due to the induced interlaminar normal and shear stresses between different structural constituents when a load is applied. In this study, Finite Element Analysis has been performed using… More >
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