翼身融合造型方法研究与实现

发布时间：2018-03-26 00:35

本文选题：几何连续　切入点：翼身融合　出处：《华中科技大学》2015年硕士论文

【摘要】：现在大多数机械系统对其中涉及到的零部件造型要求越来越严格,不仅仅涉及比较复杂的曲面造型,而且还要求模型曲面之间能够光滑连接。保证曲面间的几何连续性一直都是计算机辅助几何的难点和重点。本文基于特定的复杂飞行器造型系统,对翼身融合造型进行了研究。其中涉及到了曲面造型、曲面插值、曲面拼接技术,实现翼身融合造型的关键在于保证曲面间几何连续性。本文首先基于翼身融合飞行器的定义,给出了翼身融合构造要求。并利用常规方法对翼身融合进行了实现和研究,分析了这些方法在实现翼身融合上的局限性。然后基于对上述方法的总结和参考,提出了基于曲面拼接的翼身融合造型方法。这种利用过渡面来保证翼身融合的方式,并不是直接利用过渡面保证机身和机翼之间的连续性,而是先设计过渡面参数,构造过渡面;然后在机身表面上求取和过渡面存在相交的曲面集合,用一张NURBS曲面逼近该机身上的曲面集合,再将过渡面和该NURBS光滑拼接,由于NURBS曲面逼近机身上的曲面集合,所以过渡面可以认为经过拼接处理过后和机身光滑连接。同样的算法过程运用到过渡面和机翼上去,实现过渡面和机翼的光滑连接,只不过这里调整的不再是过渡面,而是机翼曲面。最终实现机身、过渡面、机翼的光滑连接。总体来说,基于曲面拼接的翼身融合造型方法,实现简单,计算效率高,具有一定工程意义。该研究方法目前已经在自主开发的复杂飞行器CAD造型系统中应用,使用该方法构造的翼身融合飞行器到达了预期效果。
[Abstract]:Now most of the mechanical system which relates to other parts of the increasingly stringent requirements, not only relates to the surface modeling of complex surface model, but also can ensure the smooth connection between geometric continuity between surfaces is always the emphasis and difficulty in computer aided geometry. The complex aircraft modeling system based on the special of the wing body the fusion model is studied. Which involves surface modeling, surface interpolation, surface splicing technology, the key is to ensure that the wing body fusion modeling surface geometric continuity. Based on the definition of blended wing body aircraft, given the blended wing body structure requirement. And using the conventional method of wing body fusion was realized research and analysis of these methods in the implementation of the limitation on the wing body fusion. Then the methods based on summarization and reference, is proposed based on Surface splicing BWB modeling method. The transition surface to ensure the wing body fusion, and not directly use the transition surface to ensure continuity between the fuselage and wings, but the first design parameters of transition surface, structure transition surface; then calculated on the surface of the fuselage and the transition surface is intersected the surface set. With a NURBS surface approximation surface of the body of the set, then the transition surface and NURBS NURBS surface smoothness, due to surface approximation, the body of the collection, so that after the transition surface splicing processing after the body and smooth connection. The same algorithm applied to the process of transition surface and wing up, a smooth transition surface connection and on the wing, but here the adjustment is no longer the transition surface, but the wing surface. Finally the fuselage, transition surface, smooth connection of the wing. In general, the wing body fusion based on surface splicing The modeling method is simple, efficient, and has certain engineering significance. This research method has been applied to the complex CAD modeling system developed by ourselves. The wing fusion fuselage constructed by this method has achieved the expected effect.

【学位授予单位】：华中科技大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V22;TP391.7

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