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.