基于展向参数主动控制的机翼外形设计方法

传统的机翼外形设计方法包括平面形状设计和关键剖面翼型控制,但有限的机翼剖面翼型无法完全控制机翼参数沿展向的完整分布。以主动控制机翼参数沿展向分布规律为出发点,基于 CATA 中创成式曲面设计模块,提出了一种新的机翼外形设计方法。在所展示的建模实例中,实现了对机翼弦长、几何扭转角、翼型厚度等参数沿展向分布规律的主动控制。建模结果显示,与传统的机翼外形设计方法相比,获得了理论弦曲面和理论前后缘曲线,而非理论弦平面和理论前后缘直线,同时得到前后缘线以外的其余条展向引导线。该方法可以很容易地推广到对后掠角、最大厚度、最大弯度等参数沿展向分布的主动控制,具有工程应用价值。

Wing Shape Design Method Based on Active Control of Spanwise Parameters

Traditional airfoil shape design methods include plane shape design and airfoil control ofkey profile. However , the limited airfoil profile can not completely control the spanwise distributionof wing parameters. Taking active control of spanwise parameters distribution as the starting point, anew method for wing shape design is created based on generative surface design module in CATIA.In the modeling example presented in this paper , the active control of spanwise distribution for pa-rameters such as wing chord length , geometric torsion angle and airfoil thickness are realized. Fromthe modeling results, compared with the traditional wing shape design method, the theoretical chordsurface and the theoretical leading and trailing edge curves are obtained, instead of the theoreticalchord plane and the theoretical leading and trailing edge lines. This method can be easily extended tothe active control of sweep angle , maximum thickness , maximum camber and other parameters alongthe spanwise distribution.