扑旋翼刚度和翼梢形状对气动升力和效率的影响
收稿日期: 2022-07-08
修回日期: 2022-08-30
录用日期: 2022-10-25
网络出版日期: 2022-11-04
基金资助
国家自然科学基金(11972079)
Effect of stiffness and wingtip shape on aerodynamic lift and efficiency of flapping wing rotors
Received date: 2022-07-08
Revised date: 2022-08-30
Accepted date: 2022-10-25
Online published: 2022-11-04
Supported by
National Natural Science Foundation of China(11972079)
具有垂直起降及悬停性能的扑旋翼刚度分布和形状对其气动升力和效率的影响与传统仿昆虫扑翼明显不同。针对扑旋翼刚度和翼梢形状对其悬停飞行模式下的气动升力和效率的影响开展实验研究，研制了12种不同结构构型及翼梢后掠角的传统矩形扑旋翼样件和一种仿蜻蜓翅外形的扑旋翼样件，通过实验测试定量分析了各扑旋翼样件的展向和弦向刚度、翼梢刚度及形状对其运动、气动升力和效率的影响。结果表明，弦向刚度和翼梢形状对扑旋翼运动影响显著，优化展向和弦向刚度分布对翼膜的支撑和采用仿蜻蜓翅梢形状可显著提高扑旋翼的气动升力和效率。以本实验中采用的重量为30.1 g的扑旋翼模型为例，在输入电压3.4 V时，优化后的仿生扑旋翼平均升力（49.6 g）比初始矩形扑旋翼提高74%，升力效率从3.5 g/W提高到5.9 g/W。本研究对扑旋翼微型飞行器气动性能的提升具有重要意义。
贺媛媛 , 张航 , 王琦琛 , 杨炫 . 扑旋翼刚度和翼梢形状对气动升力和效率的影响[J]. 航空学报, 2023 , 44(12) : 127779 -127779 . DOI: 10.7527/S1000-6893.2022.27779
The influence of stiffness distribution and shape of a Flapping Wing Rotor （FWR） on aerodynamic lift and efficiency is significantly different from that of the traditional insect like Flapping Wing （FW） in vertical take-off and landing and hovering. An experimental study was carried out to evaluate the effect of stiffness and wingtip shape of the FWR on its aerodynamic lift and efficiency in hovering. Based on a conventional rectangular shape， 12 wing test samples with different structural configurations and wingtip sweep angles were made， and were compared with a sample of dragonfly-like wing shape. Effect of spanwise and chordwise stiffness， wing tip stiffness and wing tip shape on motion， aerodynamic lift and efficiency of flapping wing rotor measured and analyzed through experimental tests. The test results show that chordwise stiffness and wingtip shape have significant effect on the FWR motion. An optimal spanwise and chordwise stiffness distribution to support the membrane skin and a dragonfly-like wingtip shape can increase the FWR aerodynamic lift and efficiency significantly. An FWR test model of 30.1 g was used in the study as an example. With an input voltage of 3.4 V， the test sample that was finally evolved into an optimal bionic wing produced an average lift （49.6 g）， which is 74% higher than the original rectangular wing， and the lift efficiency is increased from 3.5 g/W to 5.9 g/W. This research is of great significance to improving the aerodynamic performance of FWR-MAVs.
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