Abstract
This paper presents the results of comparison of characteristics of a laboratory model of a single-stage anode layer thruster operating with krypton and xenon. The laboratory model was optimized for xenon operation. The studies were carried out at a flow rate of the propellant and discharge voltage, which provide approximately equal calculated thrust on krypton and xenon. The thrust was estimated using the ion current of the beam measurements data. The thrust generated by the thruster was estimated by the ion current of the beam. The ion beam current was measured using a Faraday cylinder. The discharge power ranged from 800 to 1200 W, with a discharge voltage of 250 V. The current-voltage characteristics are presented, as well as the dependences of the ion current on the discharge voltage for several krypton and xenon flow rates. The coefficients of mass utilization, current efficiency and thrust to power ratio are compared.
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