Aiming at the problem of excessive low-frequency vibration of the rotor caused by the unbalance of the helicopter blade mass and aerodynamic, an active technology of vibration reduction that takes the rotor track as the constraint and only adjusts the blade pitch rods is proposed. This technology uses the least squares identification method to estimate the linear model between the vibration frequency domain component and the displacement of the pitch rod on the basis of the established blade flap-lag-torsion coupling dynamic model, thereby constructing and solving the quadratic performance index function which the rotor track is the constraint and the low-frequency vibration component is control objective. At the same time, the algorithm is implemented with Simulink module, real-time simulation calculation is performed, and the effectiveness of the control result is verified. The results show that the algorithm proposed can reduce the low-frequency vibration of the rotor by more than 80% while constraining the rotor track, and the influence on the lift and torque of the hub center is within 0.3%, and it has no adverse effect on the other dynamic response of the helicopter. Combined with Simulink, the real-time simulation of the model provides an engineering application idea for the adjustment of the helicopter track and dynamic balance.