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基于三路舵机驱动的扑翼飞行模型气动特性研究
引用本文:张钰,吕鹏,张俭,陈志敏.基于三路舵机驱动的扑翼飞行模型气动特性研究[J].实验力学,2012,27(3):281-287.
作者姓名:张钰  吕鹏  张俭  陈志敏
作者单位:1. 航天科工集团六院41所,内蒙古呼和浩特,010010
2. 西北工业大学航空学院,陕西西安,710072
摘    要:扑动而形成非定常气动现象是扑翼飞行过程中产生高升力的主要原因。本文以Ellington实验的鹰蛾翅膀为原形,设计扑翼实验及数值计算模型。通过压差传感器对翅膀模型上翼面固定位置进行测压,分析前缘涡的产生及脱落情况(考虑动压效应)。测量上下翼面固定位置处的压差,揭示扑翼飞行中产生高升力的主要原因。利用烟风洞观察扑翼模型周围流场结构及特殊涡产生变化情况。另外,根据Ellington提供的升力关系式估算了扑翼模型在一个周期内的平均升力。最后,基于三维欧拉方程对扑翼飞行气动特性进行数值模拟,计算结果与实验吻合良好。

关 键 词:扑翼  压差传感器  烟风洞  数值模拟

On the Aerodynamic Performance of Flapping Wing Model Based on Three Steering Gears
ZHANG Yu , LV Peng , ZHANG Jian , CHEN Zhi-min.On the Aerodynamic Performance of Flapping Wing Model Based on Three Steering Gears[J].Journal of Experimental Mechanics,2012,27(3):281-287.
Authors:ZHANG Yu  LV Peng  ZHANG Jian  CHEN Zhi-min
Institution:The 41st Research Institute, The 6th Academy of China Aerospace Science And Industry Corporation, Hohhot 010010, China;School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China;The 41st Research Institute, The 6th Academy of China Aerospace Science And Industry Corporation, Hohhot 010010, China;School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China
Abstract:The unsteady aerodynamic phenomenon caused by flapping is the main factor to provide high lift for flapping flight. Taking hawkmoth's wing from Ellington experiment as the original model, authors designed the model for flapping wing experiment and numerical simulation. The pressure measurement on the upper flapping wing surface was operated at some special positions by pressure difference transducer to analyze the leading edge vortex (LEV) generation and shedding (considering the dynamic pressure effect). Then, the pressure difference on upper and lower flapping wing surfaces were measured at some special positions through the same pressure difference transducer to explore the main factor of high lift production. The flow structure and vortices developments were also observed in the low speed smoke wind tunnel. The mean lift of the flapping robot in a flapping cycle was estimated according to the lift estimation equation from Ellington. Finally, based on 3D Euler equations, the numerical simulation of this flapping robot is conducted to explore its aerodynamic performance. Numerical simulation results show a reasonable agreement with experimental results.
Keywords:flapping wing  pressure difference transducer  smoke wind tunnel  numerical simulation
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