An aeroelastic optimization design approach for structural configuration of flying wings

An integrated aeroelastic optimization design approach based on the genetic algorithm is developed for the preliminary configuration design of a flying wing. An equivalent multi-plate model is adopted to resolve the structural dynamics characteristics. A panel approach is used to compute the aerodynamic force. A simple parameterization method is used to describe the wing geometry. The approach is applied to a flying wing and the objective is to minimize the structural mass subject to the static aeroelastic deformation and critical flutter speed constraints. It is found that the configuration parameter is more important for reducing the structure mass and a multilevel optimization is advised when the configuration and sizing variables are considered. The method provides a useful tool for the preliminary configuration design of a flying wing.