The influence of the excitation condition on the aeroengine rotor blade response in fatigue test is studied. Numerical analysis and experiments test results show that in the rigid clamping condition, the relative relationship between the rotor blade clamping and the test device excitation load vector has no significant effect on the first-order natural frequency, mode shape and stress distribution. In the first mode shape vibration condition, the span stress component dominates the surface stress of the blade, the clamping influences the transfer function between excitation and response. There exists a clamping position, in which, minimum excitation energy is required when the vibration amplitude of blade tip reaches certain amount. The conclusion is of great significance to improve the rotor blade fatigue performance evaluation technology.