Layout optimization of civil airplane wing structure based on automated finite element modeling

Focusing on the widely-applied two spar wing structure on civil airplanes, a wing CAD model was created parametrically according to the numbers of its stringers and ribs. Then a wing structure finite element method (FEM) model was constructed automatically by Patran command language (PCL), it was realized by 4 major steps, which were geometry model segmentation, geometry segment renumbering, segment mesh definition and FEM model generation. A complete procedure was fulfilled to construct and analyze a wing structure FEM model automatically after the numbers of its stringers and ribs had been changed, then it was integrated into a wing structure layout optimization that could be applied in preliminary design. In the end, a case study model was constructed referring to a typical civil airplane wing. Under the constraints of static strength, stiffness and skin stability, the numbers of stringers and ribs were optimized to achieve a minimum structure weight. Results show that the optimal layout brought a 10.1% structure weight reduction, which indicates the effectiveness and feasibility of the optimization.