Experimental Study of the Flapping Parameters on the MAV Aerodynamic Performance in Hovering Flight

In this research, the flapping amplitude effect and flexible shell on the MAV (Micro Air Vehicle) aerodynamic performance in hovering flight are experimentally investigated. For this purpose, a flapping membrane wing mechanism and an experimental measurement setup for measuring generated thrust were designed and constructed. In these tests, for two wings with different flexibility, generated thrust and power usage were measured in the range of flapping frequency and amplitude. In general, flapping wing generated thrust increases with raising flapping amplitude. Values of the propulsion force are different for these two wings.