Structural Design and Analysis of Small Flapping Wing Aircraft Based on the Crank Slider Mechanism  

作　　者：Minghui Ma Fengli Liu Yongping Hao 

机构地区：[1]School of Mechanical Engineering,Shenyang Ligong University,Shengyang 110159,China [2]Liaoning Provincial Key Laboratory of Advanced Manufacturing Technology and Equipment,Shengyang 110159,China

出　　处：《Journal of Electronic Research and Application》2023年第1期25-31,共7页电子研究与应用

摘　　要：In this project,the miniaturization of the aircraft was realized under the premise of strong maneuverability,high concealability,and driving a certain load,and the flight mode and structural characteristics of birds were imitated.A small bionic flapping wing aircraft was built.The flapping of the wing was realized by the crank slider mechanism,and the sizes of each part were calculated according to the bionics formula.The wingspan was 360.37 mm,the body width was 22 mm,the body length was 300 mm,the wing area was 0.05 m^(2),the flapping amplitude was 71°.ADAMS software was used to simulate the dynamics of the designed aircraft,and the variation of flapping amplitude and angular velocity during the movement of the aircraft was obtained,which verified the feasibility of the mechanism.The prototype aircraft was made for flight test,and the designed bionic flapping wing aircraft achieved the expected effect.It provides a theoretical basis and data support for the design and manufacture of small flapping wing aircraft.

关 键 词：Flapping wing aircraft Structural design Dynamic simulation 

分 类 号：V21[航空宇航科学与技术—航空宇航推进理论与工程]