半转翼悬停状态下气动特性实验研究

Experimental Investigation of Aerodynamic Characteristics for Half-rotating Wing in Hovering Flight

半转翼是一种以转动式扑动替代摆动式扑动的新型类扑翼仿生飞行系统。为了探索半转翼悬停状态下气动特性影响规律,在介绍半转翼工作原理的基础上,给出了升力测试装置方案及其测试计算模型,分别从翼片布局、翼片材料特性对气动特性的影响展开实验研究。实验结果表明:左右对称布置的翼片运动后产生的流场相互干扰,导致双翼式半转翼平均升力系数小于单翼式半转翼;柔性翼片平均升力系数一般比刚性翼片大;在合适松弛度范围内,柔性翼片平均升力随松弛度增加而增大。研究结果揭示了半转翼悬停状态下的气动特性。

Half-rotating wing(HRW)is a new flapping-imitating wing system with rotating-type flapping instead of oscillating-type flapping.The working principle of HRW was firstly introduced in this paper.The design scheme of lift testing device and lift computational model were then given to explore the aerodynamic characteristics of HRW in hovering flight.The aerodynamic experiment was performed by two wing layout with different wing material.The experiment results showed that:the flow field generated by the motion of the wing arranged symmetry in body would interfere with each other,by which the average lift coefficient of the double-wing HRW was less than that of the single-wing HRW;on the other hand,the average lift coefficient of flexible wing was larger than that of the rigid wing;in addition,the average lift of the flexible wing would go up with the increasing of degree of relaxation when it was within the appropriate range.Above research results revealed the aerodynamic characteristics of HRW in hovering flight.