• Journal of Aerospace System Engineering
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• v.18 no.5
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• pp.41-50
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• 2024

Optimal design and verification studies were performed on an orthogrid-stiffened cylinder for a propellant tank of a space launch vehicle. Hypersizer, an optimal design code for aerospace structures, was used in the present optimal design study. Design optimization was conducted to minimize structural weight of the orthogrid-stiffened cylinder. In this study, KDFs with different values (0.40, 0.83, and 0.92) were considered for the design optimization. Three optimal cylinders were designed. As the KDF increased from 0.40 to 0.83 and 0.92, structural weights of optimal design models decreased by 27.70% and 30.08%, respectively. Postbuckling analysis was conducted using ABAQUS. Results showed that global buckling loads of those optimally designed models were higher than the design load. Global buckling loads of those optimal design models with initial imperfection were derived to be at least 1.64% higher than the design load (2,860 kN). Results of this study demonstrated that the optimal design satisfying the design load was appropriately conducted.