Journal
PLASMA SOURCES SCIENCE & TECHNOLOGY
Volume 31, Issue 7, Pages -Publisher
IOP Publishing Ltd
DOI: 10.1088/1361-6595/ac7904
Keywords
air-breathing electric propulsion; plasma modelling; Monte Carlo simulation; very low earth orbit simulator; air-fed Hall thruster; atmospheric propellant
Categories
Funding
- European Union [870 436]
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This paper characterizes the HT5k Hall thruster in different operating conditions and proposes a 0D-hybrid model for atmospheric propellant fed Hall thruster discharges. The calibrated model comparison against experimental data shows a mean absolute error of 3.7% in thrust and 7.6% in discharge power.
As part of on-going efforts in advancing air-breathing electric propulsion, the HT5k Hall thruster was characterized in six operating conditions, ranging from 5 mg s(-1) to 7 mg s(-1) of 0.56N(2) + 0.44O(2) mass flow rate and 225 V to 300 V of discharge voltage. The cathode was operated with N-2 at mass flow rates between 0.5 mg s(-1) and 0.7 mg s(-1). This paper presents a 0D-hybrid model for atmospheric propellant fed Hall thruster discharges. Verified performance ranged between 30 mN to 120 mN in thrust, 1.2 kW to 5.2 kW in discharge power, and 8% to 18% in anodic efficiency. Calibrated model comparison against experimental data resulted in a mean absolute error of 3.7% in thrust and 7.6% in discharge power.
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