Boundary-element shape optimization system for aircraft structural components

AN efficient system for the shape optimization of aircraft components based on the boundary-element method is presented. The design sensitivities required by the numerical optimization algorithm are obtained economically by implicit differentiation of the boundary integral equations. The mesh generation and regeneration is done using a parametric and auxiliary geometry concept that allows the original mesh to remain adequate for a wide range of subsequent evolving geometries as the optimization proceeds. The overall system represents an efficient coupling of the geometry definition, mesh generation and regeneration, boundary-element analysis, design sensitivity analysis, geometric consistency maintenance, and numerical optimization. Numerical examples are presented.