Numerical and Experimental Study of a 1-kW Hydrazine Engineering Design Model Arcjet Thruster

Abstract

AbstractNumerical and experimental study of a 1-kW hydrazine engineering design model arcjet thruster with simulated hydrazine reaction products as propellant was performed. A two-dimensional numerical model incorporating the effects of viscous dissipation, Lorentz force, ohmic heating, heat conduction, radiation loss, and pressure work was developed to model the plasma processes inside the arcjet nozzle. The flow field and heat-transfer characteristics inside the arcjet nozzle obtained from the numerical study are discussed. The effects of the electrical conductivity and the anode wall temperature on arcjet performance prediction are also discussed. Experimental tests of the engineering design model arcjet thruster with simulated hydrazine reaction products as propellant were carried out with a mass flow rate range of 20–32 mg/s and an arc current range of 8–10 A. Over the mass flow rate and arc current ranges tested in the experiment, the specific impulse of the arcjet was in the range 479–528 s, and th...