Metamodels for Composite Lattice Fuselage Design

This paper presents a novel design of an anisogrid composite aircraft fuselage by a global metamodel-based optimization approach. A 101-point design of numerical experiments (DOE) has been developed to generate a set of individual fuselage barrel designs and these designs have further been analyzed by the finite element (FE) method. Using these training data, global metamodels of all structural responses of interest have been built as explicit expressions of the design variables using a Genetic Programming approach. Finally, the parametric optimization of the fuselage barrel by genetic algorithm (GA) has been performed to obtain the best design configuration in terms of weight savings subject to stability, global stiffness and strain requirements.