Design and analysis of bird wing for flapping-wing aircraft based on CFD method
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摘要: 提出一种采用双“S”形对偶力矩传动机构的扑翼飞行器，为提高其运动性能，基于CFD方法对扑翼模型进行深入分析与优化。重点调整翼型的几何设计，包含前缘半径、后缘角、翼展长度以及翼型厚度等关键参数，以获得更优的气动升阻比。在ANSYS软件中利用优化后的网格算法生成高质量网格，并采用动网格技术对飞行器的运动过程进行流体力学仿真，分析飞行器在不同飞行姿态下的压力云图和速度云图，验证改进后的飞行器结构。结果表明，改进后的翼型能够有效减少压力集中并抑制涡流。Abstract: In order to improve the motion performance of a flapping-wing aircraft with a double “S” shaped dual-moment transmission mechanism, an in-depth analysis and optimization of the proposed novel flapping-wing model were conducted based on the computational fluid dynamics (CFD) method. The geometric design of the airfoil was adjusted by focusing on key parameters such as leading edge radius, trailing edge angle, wingspan length, and airfoil thickness to achieve a better aerodynamic lift-to-drag ratio. High-quality meshes were generated in ANSYS software using an optimized mesh algorithm, and the dynamic mesh technique was adopted to simulate the fluid dynamics of the vehicle’s movement. The pressure contours and velocity contours of the vehicle under different flight attitudes were analyzed to verify the improved vehicle structure. The results show that the improved airfoil can effectively reduce pressure concentration and suppress vortices.
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Key words:
- flapping-wing aircraft /
- flexible wing /
- fluid simulation /
- mesh algorithm /
- dynamic mesh /
- cloud map
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图 12 改进后不同迎角下的压力云图
Figure 12. Improved pressure contours at different angles of attack
图 13 改进后的不同迎角下的速度云图
Figure 13. Improved velocity contours at different angles of attack
表 1 机翼几何参数
Table 1. Geometric parameters of wing
参数名称 数值 机翼弦长$ c $ /mm 120 机翼弯度$ f $ /mm 10.76 机翼相对弯度$ \stackrel{-}{f} $/mm 0.089 机翼厚度$ t $ /mm 21.22 机翼相对厚度$ \stackrel{-}{t} $/mm 0.176 机翼前缘半径$ {r}_{1} $/mm 6.2 机翼相对前缘半径$ \bar{{r}_{1}} $/mm 0.051 机翼后缘角$ \tau $/(°) $ {\text{tan}}\left(\dfrac{\tau }{2}\right)=0.5 $ 
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表 2 几何尺寸与升力、阻力之间的关系
Table 2. Relationship between geometric dimensions and lift resistance
主翼面积
S/mm2副翼面积
S/mm2翼展
b/mm升力
F/N阻力
F/N26 350 41 250 578.2 −0.84 0.00 39 525 61 875 867.3 −1.92 −0.01 52 700 82 500 1 156.4 −3.43 −0.02 65 875 103 125 1 445.4 −5.37 0.00 79 050 123 750 1 734.5 −7.88 −0.02 105 400 165 000 2 312.7 −0.04 −13.93
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表 3 网格无关性验证结果
Table 3. Mesh independence verification results
尺寸/mm 网格数 升力/N 升力误差/% 12 169 603 −0.613 8 1.10 6 461 017 −0.624 6 0.64 4 912 260 −0.627 1 1.04 2 3 123 450 −0.608 7 1.92 1 11 695 895 −0.629 0 1.35
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