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Numerical analysis of the plasma flow in an arcjet thruster

Electro-thermal arcjet is extensively used in electrical propulsion. The flow and discharge characteristics in these thrusters vary dramatically. Thus, a relatively accurate understanding of arcjet will facilitate the development of its technique. In this paper, a two-temperature chemical non-equilibrium fluid model is employed to investigate the interior flow of an arcjet thruster with argon as the propellant. Our simulation also includes the cathode and anode in the computational domain as the electric and thermal fields are coupled in the flow and solid structure. In addition, the DSMC method is employed to investigate the downstream flow as well as the plume where the flow is rarefied. It is found that the arc is attached diffusively at 1mm downstream of the constrictor and obvious velocity slip and temperature jump is observed along the anode surface near the thruster exit.