中文摘要：

本文对千瓦级氩电弧加热发动机内的传热与流动进行了数值模拟研究,获得了典型工况下发动机内温度、速度和马赫数以及发动机喷管温度等参数分布。模拟结果表明,工作气体主要是在阴极下游附近以及约束通道内被加热电离,气体在发动机喷管的上游为亚音速流动,经过约束通道后转变为超音速流动。在进气总压一定时,随着弧电流的增加,发动机出口温度和速度均随之增加,但工作气体流量略有下降。

英文摘要：

In this paper,modelling study is performed to reveal the plasma flow and heat transfer characteristics of a kW-class argon arcjet thruster.Computed results are presented concerning the temperature,velocity and Mach number distributions within the thruster nozzle and the temperature distributions inside the nozzle wall under typical operating conditions.Modelling results show that the heating and ionization of the propellant mainly take place near the cathode tip and constrictor region.The flow transits from upstream subsonic regime into downstream supersonic regime with the transonic in the constrictor region.With the increase of arc current,the temperature and velocity at the thruster exit plane increase,while the mass flow rates of working gas at fixed inlet pressure decreases slightly.