The Performance and Wear Characterization of a High-Power High-Isp NASA Hall Thruster

Abstract

The performance of a 50-kilowatt-class Hall thruster designed for high voltage operation was measured using both xenon and krypton propellants. The thruster was operated at discharge powers ranging from 4-46 kW on xenon and 5-65 kW on krypton. The device produced thrust ranging from 0.3 to 2.1 N at discharge voltages between 200 and 1050 V. Maximum anode specific impulses of 3370 and 4940 sec. were demonstrated at discharge voltages of 600 V on xenon and 1050 V on krypton, respectively. The peak anode efficiencies were 72% at 600 V on xenon and 68% at 1050 V on krypton. In addition to performance testing the thruster was operated on krypton at 700 V and 53 A to characterize the thruster wear. The observed wear characteristics of the thruster were compared to previous xenon Hall thruster wear results.