Plasma Synthetic Jet Actuator Charateristics And Application

High cruise Mach number,high fuel economy,wide working envelope and high radar stealth performance are importance targets for future aircraft.How to improve the aerodynamic performance of aircraft by controling shock state in high-speed flight is a desiderate problem in engineering.Plasma synthetic jet(PSJ)actuator has a simple structure,fast response and a wide frequency band.Its parameters are easy to adjust and aerodynamic actuation intensity is high.With these merits,PSJ actuator is becoming one of the leading edge and a hotspot in the field of solving the negative effects caused by shock wave.However,the working principle of plasma synthetic jet actuator and its flow control mechanism on shock wave are the key scientific problems in the application,which needs to be solved urgently.Aiming at the urgent need of high speed flow field flow control and the above key scientific problems,this paper studies the aerodynamic acutation and active flow control mechanism of plasma synthetic jet actuator in static field,supersonic field and hypersonic field by combining experiment and numerical simulation.In addition,the aerodynamic acutaion limit of the plasma synthetic jet actuator is studied,and the corresponding solutions are proposed.Firstly,by conducting the multi-field coupling simulation method and high-speed phase-lock schlieren method,plasma synthetic jet actuator is studied from discharge to generate aerodynamic actuation,from inside the cavity to outside the cavity under the condition of the whole process of acutation and multiple pulse heat accumulation effect in the temporal and spatial scales.Those researches realized a comprehensive understanding of the actuator characteristics.Secondly,by means of high-speed phase-locked schlieren system and electrical parameter measurement system,the geometrical parameters and discharge parameters which affect the aerodynamic actuation intensity of the plasma synthetic jet actuator are studied in detail.The research shows that the aerodynamic actuation of the plasma synthetic jet actuator has continuous stable actuation stage,critical actuation stage and discontinuous actuation stage under the condition of high frequency and multi-pulse discharge.This provides a reference for setting discharge parameters in actual active flow control.In this paper,an adaptive actuation control scheme is proposed to improve the adaptive range of the actuator.Furthermore,the influence of different parameters on actuation intensity and actuation range is obtained.The results show that the mono-type and the array-type plasma synthetic jet acutators are similar in aerodynamic actuation after pulse discharge,but the shock wave of the array-type actuator will form a "wave front",which provides a possibility for large-scale flow control applications.Then,the plasma synthetic jet actuator is applied to the shock wave/boundary layer flow field.By using the ejection time difference between the blast waves and the synthetic jet of the actuator,the key factor of actuator control shock wave is explored.Coupling experiment with numerical simulation method,the control process of aerodynamic actuation on the external flow field is analyzed synthetically.The blast waves not only have a great influence on the shape of an oblique shock wave induced by the wedge compression corner,but also have an effect on the shear layer.Due to different ejection time and intensity of each blast wave,the shear layer appears as "sea wave" along with the blast waves' propagation.In addition,the position and discharge parameters of the plasma synthetic jet actuator have great influence on its control effect.Finally,the plasma synthetic jet actuator is applied to the hypersonic flow field and its active flow control efficiency is studied.The actuator is applied in two dimensional intel precursor and counterflow device and its control effect on the shock wave and the flow field structure on the scale of time and space is studied.In the meanwhile,the balance process between the actuator's aerodynamic actuation and the outflow field in the case of multi-pulse actuation is analyzed.This paper studies deeply on the basic characteristics of plasma synthetic jet actuator,reveales the constraint of the existence of actuator and gives the corresponding solution,illuminates the dominant factor of the actuator flow control shock wave/boundary layer interference phenomenon.This paper has certain theoretical significance and engineering application value for the plasma synthetic jet actuator application in aerospace,fluid machinery,and other fields.