Design of Flapping Wing Aircraft based on Crank Chute Mechanism

Qi Li; Yu Cai; Xiansheng Huang; Bin Liu

doi:10.16578/j.issn.1004.2539.2022.06.019

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Design of Flapping Wing Aircraft based on Crank Chute Mechanism

Development·Application | 更新时间：2022-10-04

- Design of Flapping Wing Aircraft based on Crank Chute Mechanism
- Journal of Mechanical Transmission Vol. 46, Issue 6, Pages: 127-133(2022)
- 作者机构：
  
  1.广西大学电气工程学院，广西南宁 530004
- 作者简介：
- 基金信息：
- DOI：10.16578/j.issn.1004.2539.2022.06.019
  CLC：
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李启,蔡毓,黄显升等.基于曲柄滑槽机构的扑翼飞行器设计[J].机械传动,2022,46(06):127-133.

Li Qi,Cai Yu,Huang Xiansheng,et al.Design of Flapping Wing Aircraft based on Crank Chute Mechanism[J].Journal of Mechanical Transmission,2022,46(06):127-133.
李启,蔡毓,黄显升等.基于曲柄滑槽机构的扑翼飞行器设计[J].机械传动,2022,46(06):127-133. DOI： 10.16578/j.issn.1004.2539.2022.06.019.

Li Qi,Cai Yu,Huang Xiansheng,et al.Design of Flapping Wing Aircraft based on Crank Chute Mechanism[J].Journal of Mechanical Transmission,2022,46(06):127-133. DOI： 10.16578/j.issn.1004.2539.2022.06.019.

摘要

针对传统扑翼飞行器机翼拍打存在相位差的问题，设计了一种使用曲柄滑槽机构传动的扑翼飞行器，对其进行建模和仿真分析，制作样机并进行了实际飞行测试。制作的样机质量为26 g，翼展为340 mm，最高拍打频率为17 Hz。对曲柄滑槽机构进行理论分析，推导出该机构的运动学方程；利用SolidWorks软件对曲柄滑槽机构进行运动学仿真分析，研究了不同曲柄长度和不同拍打频率下扑翼飞行器的运动特性，确定了一个合适的曲柄长度；测试了不同电机型号和减速比下扑翼飞行器的功率消耗，确定一组低功耗的动力装置。研究结果表明，曲柄滑槽传动机构能够实现机翼无相差对称拍打，降低升力不平衡对机身的影响；在曲柄长度为4.5 mm时，机翼的上冲程角和下冲程角分别为45°和-15°，扑翼飞行器能够实现在空中稳定飞行。

Abstract

Aiming at the problem of phase lag in flapping wing of traditional flapping wing aircraft，a kind of flapping wing aircraft driven by crank chute mechanism is designed，its modeling and simulation analysis are carried out，the prototype is made and the actual flight test is carried out. The mass of the prototype is 26 g，the wingspan is 340 mm，and the maximum beating frequency is 17 Hz. The crank chute mechanism is analyzed theoretically，and the kinematic equation of the mechanism is deduced； the kinematic simulation analysis of crank chute mechanism is carried out by using the SolidWorks software. The motion characteristics of flapping wing aircraft under different crank length and different flapping frequency are studied，and a suitable crank length is determined； the power consumption of flapping wing aircraft with different motor types and reduction ratios is tested，and a set of low-power power devices is determined. The results show that the crank chute mechanism can eliminate the phase lag between the wings and reduce the influence of lift imbalance on the fuselage； when the crank length is 4.5 mm，the up stroke angle and down stroke angle of the wing are 45° and -15°； the flapping wing aircraft can achieve stable flight in the air.

关键词

扑翼飞行器曲柄滑槽机构相位差运动仿真

Keywords

Flapping wing aircraftCrank chute mechanismPhase lagMotion simulation

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