Investigation of the laboratory model of a thruster with anode layer operating with air and nitrogen-oxygen mixture

Abstract

Ambient air is one of the perspective propellants for the electric thrusters of the low orbit spacecrafts. The results of the comparison of the laboratory model of a thruster with closed electron drift (Hall thruster) performance are presented. The model was originally designed for operation with xenon. The comparison was made for the model performance with xenon, air and nitrogen-oxygen mixture in a ratio of 2 to 1. The current efficiency, the mass utilization efficiency and the power-to-thrust ratio were chosen as the comparison characteristics. The results of the laboratory model ion beam current measurements are also presented.