电弧射流激励器工作特性仿真研究

为了在高超声速飞行器减阻中达到更好的减阻效果，设计了一种电弧射流等离子体激励器。采用有限元法求解非线性多物理方程，对此电弧射流等离子体激励器的工作特性进行了数值模拟，得到了激励器内部的电势、压力、温度和速度分布，综合分析了进气口气体速度、放电电流、激励器管道半径对电势、压力、温度和速度分布的影响。获得了全面的影响规律，通过仿真结果还得到:电弧射流等离子体激励器可产生最高温度为8638 K、最高速度为655 m/s的等离子体射流。当电流20 A，进气速度0.5 m/s，管道半径2.5 mm时，所需功率最小；当电流20 A，入口气体流速5 m/s，管道半径2.5 mm时，出口处平均温度最高；当电流20 A，进口气体速度10 m/s，管道半径2.5 mm时，出口处平均速度最大。并对仿真得到的放电电压进行了实验验证，在等离子体参数相似的情况下，实验结果与仿真结果吻合较好。

Numerical study on the characteristics of an arc jet plasma actuator

An arc jet plasma actuator was designed for drag reduction of hypersonic vehicle to achieve better drag reduction effect. The characteristics of the arc jet plasma actuator were simulated numerically by using the finite element method to solve the nonlinear multiple physical equations, and the distributions of potential, pressure, temperature and velocity inside the actuator were obtained, and the influencing effects of velocity at the inlet, current, radius of the pipe on the distributions of potential, pressure, temperature and velocity were analyzed comprehensively. The comprehensive influence laws are obtained, and the simulation shows that the arc jet plasma actuator can produce a plasma jet with a maximum temperature of 8638 K and a maximum velocity of 655 m/s. The minimum power is required when the inlet gas velocity is the least, the maximum average temperature at the exit is obtained when the plasma current is the largest and the inlet gas velocity is medium. The maximum average speed at the exit is obtained at the largest current and the largest inlet gas velocity. Validation by experiment is also carried out. Comparison between the experimental and simulation results also show good agreement under similar plasma parameters.