Abstract: An experimental study is conducted to investigate UAV attitude instability caused by heavy vibrations of single-rotor UAV airborne equipment. Suitable measurement points are selected, and the vibration signals under two working conditions of gimbal take-off and flight are collected to obtain the time-domain response and power spectrum density of the gimbal. Integrated with the dynamics model of the vibration damping system, the vibration damping scheme of the UAV gimbal is proposed, and the field flight test of the UAV shows the vibration time domain response and power spectrum density are significantly reduced after vibration damping. The vibration damping scheme serves as an effective basis for the design of UAV vibration damping.