Abstract: The vibration characteristics and fatigue test methods of an aero-engine rotor blade were studied. The first three order bending vibration frequencies of the blade were obtained by theoretical calculation and experimental verification, and the relationship between the stress of the blade and the natural frequency and amplitude of the blade was obtained under the first order bending vibration mode. The results show that the theoretical and measured vibration characteristics of the structure were consistent, and the vibration stress and amplitude of the test piece obeyed the linear variation law, which indicated that the proposed test method was effective and could provide fatigue performance data support for the development of the rotor blade.