PARAMETERS OF THE ST-40M HALL-EFFECT THRUSTER IN ITS OPERATION ON XENON AND KRYPTON
Keywords:
Hal-effect thruster, propellant, xenon, krypton, thrust, specific impulse.Abstract
This article presents the results of an experimental study of the parameters of the ST-40M Hall-effect thruster developed by SETS (Space Electric Propulsion Systems) in its operation on xenon and krypton. Electric propulsion systems based on Hall-effect thrusters have found wide application due to their high performance and relative simplicity of design and operation compared to other types of propulsion systems. Traditionally, xenon is used as propellant in Hall-effect thrusters. It is an inert gas with a low ionization energy and a high atomic mass, which makes it possible to achieve a high performance of the electric propulsion system while maintaining operational simplicity. However, the high cost of xenon significantly affects the overall expenses during the testing and operation of the thruster and the propulsion system. Therefore, research is underway on the use of alternative propellants that could reduce operating costs while maintaining the thruster performance at an acceptable level. The most promising alternative to xenon is considered to be krypton. It has a lower cost and ensures operational simplicity, but its higher ionization energy negatively affects the thruster efficiency. The goal of this work was to compare the main parameters of the thruster operating on xenon and krypton under identical conditions. Experimental tests were carried out in a vacuum chamber at discharge voltages ranging from 250 to 500 V and propellant mass flow rates from 1 to 1.78 mg/s for xenon and from 1 to 1.6 mg/s for krypton. A comparative analysis of the thruster parameters in its operation on xenon and krypton at a mass flow rate of 1 mg/s showed that the use of krypton leads to a deterioration in thruster performance. The anode thrust and specific impulse decreased by 25 %–37 %, while the anode efficiency dropped by 15 %–24 %.
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