中空长航时无人机两段翼型设计和应用研究

Investigation of the Design and Application for the Two Element Airfoil of Medium Altitude Long Endurance UAV

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。

According to the design requirements related to high endurance factor,short take-off and landing,deforming resistance of medium altitude long endurance(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.The geometry of the two-element airfoil is generated with the method of controllable conic curves accompanied with the control points.Meanwhile optimum design of the UAV inner wing is carried out using the designed slot airfoil and improvement effect is evaluated.The results indicate that the endurance factor,take-off lift and lift-to-drag ratio of the optimum UAV are substantially improved.At the same time,the drag of full flap increases under the certain lift conditions which is beneficial to the landing deceleration.This method can meet the requirements such as the efficient cruise,short take off and landing and is significant to the MALE UAV design.