This paper investigates the flying mechanism based on the second mode ring vibration. The flapping mechanism has a pair of curved wings attached near the neighboring nodal points. The flying mechanism can attain a lift by the difference in drag forces generated by the up and down motions of the wings, which is dependent upon the shape and size of wings and the amplitude of flapping motions. When the wing span angle is slightly less than 90 degrees, the flying mechanism subject to external rotation has the capability of stable self-attitude control. When the wing span angle is larger than 90 degrees, the flying mechanism gets unstable, losing the capability of self-attitude control. The lift force is simulated numerically and verified by experiment using a lift force measuring device. The self-attitude control effect is also simulated and verified by experiment using an angle measuring device.
