长边条翼身融合过渡曲面的构造方法

Generating Blending Surface with Long Fringe Between Wing and Fuselage of Missile

针对飞航导弹长边条翼身融合过渡曲面的构造展开研究,为满足融合过渡曲面过渡线能够由设计人员确定和长边条面必须是等截面的直纹面等要求,综合应用基于局部重新参数化构造过渡曲面和基于物理的能量曲面造型构造过渡曲面方法,并结合导弹弹身曲面是等截面直纹面的特点,通过构造翼身融合面、长边条面和头锥面3张曲面拼接来构造G1连续的长边条翼身融合过渡曲面。提出了预先构造中间辅助面和辅助基曲面的方法,通过辅助基曲面和弹翼面上重新参数化局部基曲面间线性组合来构造翼身融合面。通过使中间辅助过渡面的边界切矢与弹身的纵向切矢一致,来保证长边条面与翼身融合面间的G1连续性。最后利用基于物理的能量曲面造型方法构造与弹身和长边条面G1连续的头锥过渡面。

A method of generating blending surface with long fringe between wing and fuselage of a missile is presented. The blending surface consists of a blending surface between wing and fuselage, a long fringe surface and a forward 3-sided surface which are G1 smoothly connected. An auxiliary surface and an auxiliary base surface are generated in advanced. The blending surface between wing and fuselage is generated by a linear combination of a reparameterized local base surface on the wing and an auxiliary based surface. The directions of cross boundary derivatives of the auxiliary surface at the common boundary between the auxiliary surface and the long fringe surface are the same as the lengthways directions of the missile＇s body. And this ensures that the blending surface between wing and fuselage and the long fringe surface are G^1 connected. Then the forward 3-sided surface is generated based on energy minimization and is G^1 continuous contact with the missile＇s body and the long fringe surface.