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采用基于电子束电离的磁流体力学(MHD)控制系统,对高超声速流场附面层,以及非设计状态下的高超声速进气道流场的磁流体控制进行了深入研究.控制方程为低磁雷诺数Navier-Stokes方程,采用等离子体动力学模型与电子束模型模拟空气电离过程.研究结果表明:①电子束电离能有效提高流场的电导率,增强磁场对流场的控制效率;②基于电子束诱导电离的MHD控制系统能有效地控制高超声速流场的附面层,但其控制效率跟电子束能量大小相关;③基于电子束诱导电离的MHD控制系统能有效地改变非设计状态下高超声速飞行器的斜激波结构,使进气道重新满足Shock-on-lip(SOL)条件,但进气道的总压恢复系数以及流量将会降低.
The magnetohydrodynamics (MHD) control system based on electron beam ionization is used to study the control of the magnetohydrodynamics in hypersonic flow field and the non-designed hypersonic inlet flow field. The governing equation is low Magnetic Reynolds number Navier-Stokes equation was used to simulate air ionization process with plasma dynamics model and electron beam model.The results show that: (1) Electron beam ionization can effectively improve the conductivity of the flow field and enhance the control efficiency of the magnetic field on the flow field; The MHD control system based on electron beam induced ionization can effectively control the surface layer of hypersonic flow field, but its control efficiency is related to the energy of electron beam. The MHD control system based on electron beam induced ionization can effectively change the non-design state Under the oblique shock structure of the hypersonic vehicle, the inlet meets the condition of Shock-on-lip (SOL) again, but the total pressure recovery factor of the inlet and the flow rate will be reduced.