Static aeroelastic optimization of hypersonic aircraft based on high-fidelity model

Static aeroelastic optimization was proposed for an entire aircraft vehicle based on computational fluid dynamics (CFD) and computational structural dynamics (CSD) coupling numerical computational methodology. To solve the problem of automatic modeling and computational demand on multidisciplinary optimization based on high-fidelity model, a geometric master model technology was presented to generate the CFD/CSD integrated models, an improved constant volume tetrahedral (CVT) method based on elements was used for the grid deformation and force transition between the CFD and CSD mesh, and the response surface model (RSM) was used in stead of the traditional optimization algorithms. The above methods were validated by AGARD 445.6 wing static aeroelastic analysis. A hypersonic aircraft multi-objective optimization based on RSM was accomplished through CFD/CSD static aeroelastic optimization. The optimized aircraft lift-to-drag ratio increased by 16%, structural weight reduced by 9%, and the fitting error of RSM was less than 1.5%. Results show the CFD/CSD integrated modeling and optimization method could solve effectively the static aeroelastic optimization problem with high-fidelity models.