Design and Motion Simulation of Dragonfly-like Wings

Abstract

In order to study the bionic dragonfly wings, based on the existing structure of the plane single crank double rocker mechanism, a mechanism similar to the crank slider double rocker rod is used, and SOLIDWORKS is used to model and design it. In the design of the bionic dragonfly wing, ANSYS is used to perform static and modal finite element analysis on the determined mathematical model of the wing. We determine through static force analysis that the maximum principal stresses of the front and rear wings are 73.78MPa and 90.87MPa, respectively. Its position is the rear side of the wing root of the airfoil, where it is necessary to appropriately increase the thickness to improve the strength of the wing. At the same time, the first-order natural frequencies of the front wing and rear wing of the bionic dragonfly are also analyzed to be 15.97 Hz and 16.56 Hz, respectively. Finally, ADAMS is used to simulate the motion of the designed flapping wing mechanism, and the maximum flapping angle is 70 degrees, the upper flapping angle of the front and rear wings are about 33 degrees, and the lower flapping angle is about 37 degrees. The main stage of the flapping-wing generating lift accounts for about 53 % of the whole process, indicating that the designed flapping-wing mechanism moves smoothly and stably, meets the design requirements of the imitation dragonfly flapping-wing aircraft, and satisfies that the phase difference between the front wing and the rear wing is 90 degrees. Compared with traditional Unmanned Aerial Vehicles (UAVs), the bionic dragonfly UAV has high flexibility, compact structure, low noise and stable operation, which provides an important parameter basis for the design of advanced bionic aircraft, and is of great significance for its practical application.