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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 studies the method of parametric geometric model generation for wing-fuselage aircraft. Wing fuselage integration of the various components of the aircraft are regarded as airfoil components, the use of shape functions and classification function transformation method to describe the various aircraft wing profiles. The cubic Schmidt curve is used to describe the thickness variation of the airplane along the span and the shape of the trailing edge curve, and the segmentation curve is used to describe the complex leading edge shape. Winglets are divided into two parts: the transitional section and the main section respectively, and the coordinates of the key parameters of the main wing section are calculated through the transformation matrix. Apply CATIA Secondary Development Technology to Automatically Generate Parametric Geometric Model.