本文通过建立反映机身横截面外形特征的控制点概念，及在控制点间分配网格点数方式，给出了一种非常实用、交互式的表面网格生成方法，所生成的网格失真度小，物体保形好，生成适用于CFD计算需要的表面网格花费的时间少，适用性强。基于无限插值理论，引入本文提出的网格正交控制、物面法向量控制、加权平均光顺措施，给出了一种改进的空间网格生成方法，有效克服了传统无限插值网格生成方法在复杂外形网格生成方面的缺陷，有效改善了网格的法向疏密性、贴体性及周向网格的均匀性，对真实飞行器部件网格生成非常迅速。以某飞行器复杂机身表面与空间网格生成，及无人机翼身组合体空间网格生成为例，检验了本文网格生成方法的实用性和有效性。%We introduce the control point concept defining body surface's geometry features, then distributing grid points between adjacent control points. A surface mesh method for complex-shaped fuselage is proposed in an interactive interface. Using the above method, a complete surface grid with little distortion can be gained rapidly.rn Based on the transfinite interpolation theory, an improved algebraic grid generation method is presented in this paper. Our improvements of existing algebraic grid generation method include: (1) orthogonality control， which greatly improves grid orthogonality adapted to viscous flow calculation; (2) weighted average smoothing, which efficiently handles with grid intersection due to concave corner existence; (3) normal vector control, which adjusts grid smoothing near convex corner. For the grid generation of complex-shaped aircraft, The usage of the above measures result in the satisfactory mesh which has appropriate normal mesh spacing、body-fitted quality and peripheral grid fairness. Being algebraic grid generation technique, The improved method is quite practical and effective.
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