Xウィング型羽ばたきUAVの推力発生機構のモデリング

抄録

frequencies of left and right wings independently. In the present study, we identified a mathematical model of the thrust generation through a series of experiments using the actual aircraft, aiming at the development a flight control system. The input is taken as the duty ratio of the PWM signal to the motor, and the output is the thrust from the flapping wing. We conducted a flight simulation by using the identified model to investigate the reproducibility of the airspeed of the UAV in the hovering flight mode, where the degree of freedom of the aircraft is restricted in a vertical axis.