Abstract: Control algorithm is a key factor to improve the performance for reducing helicopter vibration. In this paper， according to the multi-frequency characteristics of helicopter vibration， both the response separator and controller are constructed utilizing the adaptive notch filter to establish the adaptive dual-notch control of helicopter structural response. The response separator separates each frequency component from the error response to update the control input of each harmonic independently in time domain. Utilizing a dynamic similarity model of helicopter airframe， simulations and experimental studies of the proposed adaptive dual-notch control algorithm are carried out. The results show that the adaptive dual-notch control algorithm has good control performance and faster convergence rate under the multi-frequency excitations， and it can enhance the robustness of active vibration control system by increasing the critical convergence step size.