基于高拟真度模型的高超声速飞行器静气动弹性优化

为解决基于计算流体动力学(CFD)和计算结构动力学(CSD)高拟真度模型的静气动弹性优化过程中模型更新自动化困难、求解速度慢的难点,提出了基于几何主模型技术的CFD/CSD一体化参数化建模方法和基于网格单元修正的常体积四面体(CVT)数据交换技术,并引入响应面模型来降低气动弹性优化求解难度.通过AGARD 445.6机翼静气动弹性分析对上述方法的可行性和有效性进行了验证；并以某高超声速飞行器为例,采用基于二次响应面的多目标优化算法进行了CFD/CSD气动弹性分析与优化,优化后飞行器升阻比增加16％,结构质量减少9％,且响应面模型精度拟合误差不超过1.5％.计算结果表明:所发展的CFD/CSD一体化参数化建模与优化方法能够有效地解决高拟真度模型的静气动弹性优化问题.

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.