Abstract
An efficiency breakdown analysis is derived including energy efficiency, propellant utilization efficiency and beam efficiency and correlates the thruster performance with plasma parameters. The methodology can be applied to a partially ionized and multiply-charged discharge plasma. Additionally, a semi-empirical scaling model is introduced, utilizing a novel database of low-power Hall Effect Thrusters to predict performance across various power levels. These models are used to analyze the Halo thruster performance, providing insights into ionization, acceleration, and loss mechanisms. The findings indicate specific performance losses due to plasma-wall interactions, low ionization rate and low mass utilization efficiency and highlight the need to improve the Halo’s magnetic field design to enhance thruster performance.