Design and Optimization of Bionic Wings Based on Leading-edge Angle for Flapping-Wing Micro Air Vehicle

The Flapping-Wing Micro Air Vehicle, imitating the flight of birds or insects, is a new type of aircraft with broad application value. Since its flying principle is quite different from that of traditional aircraft, the efficient design of the bionic wing is the core of whether the flapping-wing micro air vehicle can have good flight performance. To achieve better flight performance, this paper analyzes the flapping mechanism based on aerodynamics, optimizes the design of the flapping mechanism of the flying robot, and improves the energy utilization rate and lift of the air vehicle. With the goal of optimizing the bionic wing, many bionic wings are completed, controlling the variables except the leading edge, to carry out the lift test, hoping to obtain the relationship between the leading-edge angle and the lift. To finish the experiment with accurate results, this paper designs a micro-bionic flapping-wing optimization design platform to verify the different wings' lift effects. Through the experiments done on the platform, a wing design scheme is found, which has the best lift performance under current conditions, and the platform can carry out flap experiments conveniently, efficiently, and accurately. Besides, the experimental result clearly shows the trend of the wing lift with the leading-edge angle, which provides an important reference for further optimization design, and has a high Reference value. Future research will concentrate on the other variables of the bionic wing design to achieve more lift.