Design and aerodynamic analysis of a flapping-wing micro aerial vehicle

This paper presents the design and aerodynamic performance of a planar membrane wing as shape airfoil for the micro aerial vehicle. This simulation calculates the average lift force, L ¯ as the criteria weight of the flapping wing (weight must be lower than 8.78 g), to make one ultra-light, small size flapping wing MAV. In here two phases are discussed. First, the 3D aerodynamic calculation and flow field simulation of a planar membrane wing as shape airfoil for a MAV were studied. Analyzing the flapping wing under different frequencies and angles of attack, investigates the pressure distribution, the airfoil-tip vortex and the up-wash situation of the air flow. Second is to average lift force, L ¯ 8.78 g for designing weight limit of the MAV. The specifications of flapping wing MAV are 8 g gross weight, the 15 cm wingspan, and 5 cm chord length. In this vehicle, we employed the concept of four-bar linkage to design a flapping mechanism which simulates the flapping motion of a bird. The angles of upstroke and downstroke can be varied in the design. The total flapping angle is 73°. The flapping frequency of wing is 25.58 Hz. The power source comes from motor with a Li–H battery. A simple flight test was carried out and the result of the flight is going well. The actual flight distance is approximately 8 m, and the primary goal is achieved. By the way, we found the rigidity of tail wing is crucial and should be enhanced to prevent the flapping-wing MAV will be unable to revise if the MAV in a crooked condition and it will cause a crash.