Performance of a High Specific Impulse Hall Thruster

摘要: Busek Co. Inc., in a SBIR program sponsored by the NASA Glenn Research Center, designed, and tested nominally 1 kW thruster capable of both single stage two-stage operation. This paper describes results from detailed performance testing using several geometries configurations. Experimental revealed that specific impulses greater than 3000 seconds at moderate applied voltage(s) (<1000 V) is feasible. Measured thrust, efficiency Isp were obtained over range input power propellant mass flowrates providing characterization designs. In configuration, measured thrust was 88 mN sec an 2.3 into discharge. twostage maximum 3300 seconds, also power. The experimental are used to compare contrast Data comparable configurations showed little advantage for this style two Also presented simple analytical model characterize understand thruster(s). model, applicable all sizes types Hall thrusters, useful correlating expressed terms global parameters, primary electron utilization lumped voltage loss. Analysis data show important parameter increasing high Isp.