Topology optimisation of a bulkhead component used in aircrafts using an evolutionary algorithm

The paper demonstrates the application of a modified Evolutionary Structural Optimisation (ESO) algorithm for optimal design of topology for an aerospace component. The capabilities of ESO for producing an optimal design against a specified strength constraint are illustrated using an aerospace design problem of optimisation of the topology of a bulkhead used in an aircraft structure. It has been shown that topology optimisation using ESO can result in considerable reduction in the weight of a structure and an optimum material utilisation by generating a uniformly stressed structure. The paper evaluates and establishes the ESO method as a practical tool for optimum topology design problems for complex industrial structures.