A procedure for automating the design of transport aircraft fuselage structures has been developed and implemented in the form of an operational program. The structure is designed in two stages. First, an over-all distribution of structural material is obtained by means of optimality criteria to meet strength and displacement constraints. Subsequently, the detailed design of selected rings and panels consisting of skin and stringers is performed by mathematical optimization accounting for a set of realistic design constraints. As a result one obtains a procedure whose practicality and computer efficiency is demonstrated on cylindrical and area-ruled large transport fuselage.
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Sobieszczanski et al. (1972) studied this question.