Method of coupled aerodynamic/structural integration optimization for transport-wing design

A new method was presented for coupled aerodynamic/structural integration optimization of transport wing. It was developed based on experiment design method and approximation techniques. Experiment design method was utilized to provide sample points of wing design. High-fidelity analysis tool of both aerodynamics and structures were permitted to carry out aeroelastic analysis on these sample design scenarios. Approximation analysis models were constructed using quadratic response surface method, Kriging model or neural networks. By this way, tightly coupled relationship between aerodynamic and structural discipline was decoupled. A general framework of this MDO (Multidisciplinary Design Optimization) method was carefully designed, and how to improve the accuracy of approximation model by choosing appropriate approximation method was discussed. A numerical example of designing a high aspect-ratio supercritical wing of wing/body configuration was presented, which preliminarily showed that the present method is effective and applicable.