Two-dimensional modelling of a kW-class argon arcjet

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.