A Two‐Level Procedure for the Global Optimum Design of Composite Modular Structures–Application to the Design of an Aircraft Wing

This work concerns a two‐level procedure for the global optimum design of composite modular structures. The case‐study considered is the least weight design of a stiffened wing‐box for an aircraft structure. The method is based on the use of the polar formalism and on a genetic algorithm. In the first level of the procedure, the optimal structure is designed as composed by a single equivalent layer, while a laminate realizing the optimal structure is found in the second level. The method is able to automatically find the optimal number of modules; no simplifying assumptions are used and it can be easily generalized to other problems. The work is divided into two parts: the theoretical formulation in the first part, the genetic procedure and some numerical examples in this second one.