The rotor dynamic structure of a helicopter presents a high value of strategic development. As the vibration caused by rotor operation negatively impacts flying performance, the exploration of rotor vibration control methods is perceived as vital to the improvement of helicopter performance. Regarding the key frontier problem, the principle of active vibration control is scrutinized with the cause of fuselage vibration by rotor and the frequency characteristics of vibration considered. Then, the overall framework of helicopter active vibration control is described. The control methods are divided into frequency-domain and time-domain control on the basis of the periodic property of helicopter vibration. The higher harmonic control method, robust method, and intelligent method are reviewed and summarized, coupled with the related test results. Furthermore, vibration transfer suppression technology is briefly introduced, and active vibration control tests conducted home and abroad are reviewed. By summarizing the shortcomings of vibration control methods, the future research directions for active control methods are suggested: robust adaptive control for stable flight states, intelligent self-learning control for full flight states, and the design of integrated active control systems for performance improvement should be conducted.