翼身融合飞机参数化几何模型

Parametric Geometric Model for Blended Wing Body Configuration

本文研究翼身融合飞机的参数化几何模型生成的方法。翼身融合飞机各部件均视作翼面类部件,运用形状函数和分类函数变换方法描述飞机各个剖面翼型。用三次施密特曲线描述飞机沿展向的厚度变化与后缘曲线形状,用分段曲线描述复杂的前缘形状。翼梢小翼划分为过渡段与主段两部分分别描述,并通过变换矩阵计算主翼段关键参数坐标。应用CATIA二次开发技术实现参数化几何模型的自动生成。

This paper aims at the geometric model generation of Blend-Wing-Body(BWB) aircraft configuration.The BWB configuration is divided into several wing sections.The airfoils are represented by the function and shape function transformation method.The thickness distribution and trailing edge shape of the BWB configuration is described by the Hermite curve,and the complex leading edge shape is represented by using several curves.The winglet is divided into transitional part and primary part which coordinates are computed by transition matrix method.The geometric CAD model BWB aircraft configuration is automatically generated using API of the commercial CAD software CATIA.