高超声速飞行器参数化几何建模研究

Parametric Geometric Modeling for Quasi-waverider Vehicle

针对高超声速飞行器设计由于采用吸气式冲压发动机带来的机体/推进系统一体化而带来的优化设计问题,同时也为了进行总体优化布局,必须建立参数化几何模型。通过采用部件分解法,拟合曲线,坐标变换和旋转,拉伸截面,从而建立了高超声速飞行器类乘波体的完整的参数化几何模型。同时采用工程算法和CFD软件对其进行气动特性计算,工程算法的思路是先采用面元法对其进行无粘气动力计算,再通过经验公式来计算粘性阻力系数。两者结果显示类乘波体气动特性良好。

It is necessary to establish a parameter geometric model for airframe/scramjet integration optimizing design adopting air- breathing athodyd, and for integral optimization design. A complete parameter geometric model for hypersonic vehicle quasi - waverider is established by using decomposing components, fitting curve, streching section, transforming and circumgyrating coordinate. Both engineering method and CFD method are adopted to compute this model＇s aerodynamic performance. Engineering method computes inviscous aerodyanmics by using surface element method, then computes viscous drag coefficient. The outcome of both methods shows that the aerodynamics performance of the quasi - waverider vehicle is good.