Abstract: To suppress the noise from the blade-tip vortex interactions(BVI) of the helicopter rotor, plasma synthetic jets（PSJs）were used as an active flow control method to weaken the intensity of the blade tip vortex. Firstly, the jet characteristics of the PSJ actuator at different loading voltage parameters (amplitude, frequency, duty cycle) were investigated. Then, the scheme of plasma synthetic jets to control the blade tip vortex was designed through simulation. The effects of blade tip vortex weakening in situations with various numbers and positions of PSJ and different sizes of jet holes were examined. According to the optimal flow control scheme from simulation design, the vertical jets were arranged near the leading edge of the end surface of the blade tip model. Then the test was carried out in the low-speed wind tunnel. Besides, the suppression effects of the plasma synthetic jet and continuous jet on the vortex strength of the blade tip were compared. Eventually, the mechanism of the suppression of the blade tip vortex was analyzed. The results show that the PSJ can effectively inhibit the development of the hovering blade tip vortex, and it is more effective than the continuous jet. Only a few jets need to be arranged on the leading edge near the lower edge part of the blade tip surface to obtain better results.