Abstract
An attempt has been made in this work to obtain a minimum weight design software for the airplane fuselage type of stiffened cylindrical shell under pure bending load. This design problem has been formulated as a non-linear constrained minimization problem. The two numerical methods used for the solution of this problem are: (1) penalty function technique and (2) method of complex box. The general computer programs based on the above methods are prepared. The minimum weight design is carried out by considering the shell which is stiffened in longitudinal and circumferential directions and treating their dimensions as well as their spacings and skin thickness as design variables. The numerical results have been obtained for a simplified case under the specified assumptions. The programs can be further extended for the practical problems such as design of a minimum weight fuselage.
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