New Concept Promotion Technology Improved Design And Experimental Study Of Corona Discharge Lift

Corona discharge lifter is a kind of actuator which can directly convert electric energy into thrust.Because of its structural characteristics,it is called asymmetric capacitor thruster.As a propulsion system,it has the advantages of high thrust power ratio,no exhaust emission,low noise,simple structure and low cost.The ion wind generated during its operation can also be used for air flow transportation,electrostatic precipitation,mass transfer and heat transfer,etc.However,weak thrust and low efficiency seriously limit the application of act as a propulsion system,so it is of great significance to improve the thrust and efficiency of act.Firstly,based on the model that the reaction force of the ion wind is the source of the thrust of the electric drift machine,the ion wind is divided into different regions according to the thermodynamic properties and the thermodynamic process of the ion wind in different regions is assumed to establish the thermodynamic model of the ion wind,and the relationship between the ideal mechanical efficiency of the ion wind and the temperature is derived.The mechanical efficiency of ionic wind is qualitatively and quantitatively analyzed by comparing with previous data.The results show that the thermodynamic model of ionic wind is reasonable.Finally,based on the ion wind thermodynamic model,the guiding design suggestions for improving the propulsion efficiency of the electrostatic precipitator are given.Secondly,the first attempt is not to change the discharge mode,and the linear wing structure electric floater is used to lift the thrust.The results show that the linear wing structure electric floater can not improve the propulsion performance obviously.The maximum static pressure of the ion wind is obtained by considering the static field in the acceleration region,and then the upper limit of the electrostatic thrust density of the electric floater is obtained.It is found that the conclusion is reasonable by comparing with the previous data.Finally,the thermodynamic model can supplement the conditions ignored in the hypothesis,and the thermodynamic model is more suitable for the study of the factors restricting the upper limit of the ionic wind performance.Third,based on the analysis of ion aerothermal model and reaction thrust model,the conclusion is that there is upper limit of thrust efficiency and thrust density of the electric floater.Therefore,the design idea is to design the electric floater with high propulsion performance limit,and then make the actual propulsion performance close to the upper-limit of propulsion performance by technical means.The DCT is divided into three modes:static electricity,combustion and electromagnetic excitation according to the plasma generation mode.The theoretical electrostatic propulsion performance of DCT is analyzed.Finally,the propulsion performance of dual potential DCT and Asymmetric Capacitor Thruster with the same size is studied experimentally.The results show that the propulsion performance of dual potential DCT is still better than ACT.The results show that the combustion mode can greatly improve the propulsion performance of DCT by increasing the plasma density between electrodes.However,the combustion instability leads to the decrease of the applicability of the combustion mode.Finally,the thermal mechanical model of ion wind is explored and supplemented.The momentum asymmetry model is used to explain the feasibility of using single fluid model to approximate the thrust performance of the electric floater under corona discharge condition.Based on the new conditions,the conclusion of the theoretical model of ion drift is correct.