Dynamic model of Flapping Wing Micro-Aerial-Vehicle

In allusion to design and estimate of flapping flight control, this paper presents the dynamic characteristic of Flapping-wing Micro Aerial Vehicle, and researches the problem of modeling and simulating the dynamic model with Matlab / Simulink. The unsteady instantaneous aerodynamics associated with flapping flight is estimated through improved strip theory, and the aerodynamic characteristic of fuselage and tails has been studied by wind tunnel experiment. Simulation on the proposed model demonstrate that the flight process can be simulated preferably and can manifest the character of flapping flight in evidence. We compare the simulation result with the flight-test data and analyse the angular orientation of flapping flight, then give a primary attitude control strategy and test the efficiency of control system by adding disperse gust to the simulation, the result demonstrate that control system can minish external gust effect on the FMAV in evidence. An analysis has also been made of the fuselage motion of an FMAV resulting from wing flapping and compared it with flight-test data. It is suggested that this motion may reduce the efficiency of task equipment (such as minisize vidicon) and the thrust produced by wings, some techniques should be adopted for eliminating dithering.