Abstract
A procedure including highly automated computer programs for the optimum weight design of fuselage type stiffened cylinders subjected to combined torsion and axial compression with and without lateral pressure is developed. The objective function is the composite weight of the cylinder. The known parameters are the specified material properties, radius, length and the loadings. One desires to find the size, shape, spacings of stiffeners and the skin thickness so as to safely carry the given loads with minimum weight. The procedure is demonstrated through practical design problems. The general computer programs developed can be obtained by writing to the authors.
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