中空长航时无人机两段翼型设计和应用研究

中空长航时无人机追求高续航性能和任务多样化,故应满足高效巡航、短距起降、抗变形等多性能要求。在原始飞机单段翼型的基础上,通过控制点加分段可控二次曲线方法并结合优化算法开展两段翼型的设计优化;利用新设计的两段翼型完成对无人机机翼内侧段(襟翼段)的改进设计及其结果分析。结果表明:改进后的无人机在续航因子、起飞升力和起飞升阻比方面得到大幅提升;襟翼大角度偏转时,在保持一定升力的同时阻力增加,满足飞机着陆减速要求;此方法可以满足中空长航时无人机巡航和起降多设计点综合设计要求。

Investigation of the design methodology for the two-element airfoil of the low speed and long endurance UAV

According to the design requirements related to high endurance factor, short take-off and landing , deforming resistance of MALE UAV, the investigation of the design methodology on multi-constraint of the two-element airfoil is conducted based upon the earlier studies of the one-element airfoil design. In this paper, the geometry of the two-element airfoil is generated with the method of controllable conic curves accompanied with the control points, and the parameters of control curves, slot and spin axis position are optimized using Genetic Algorithms. The results indicate that comparing to the ellipse cutting method, the present method using more control parameters is more flexible to the earlier airfoil and the pressure distributions is more reasonable. At the same time, the endurance factor, take-off lift and lift-to-drag ratio of the designed slot airfoil are improved substantially which satisfies the multi demands. This method in this paper is significant to the MALE UAV design.