Abstract
In Hall Effect Thrusters (HETs), calculating thrust from several of input parameters is a critical work. In both government and industry, instead of expensive experimental test set-ups, numerical approach is adopted for various reasons. However, electron dynamics and other effects in a HET must be analyzed in detail to reach a fully consistent result. To determine the correct HET for a satellite during the initial sizing phase, a modified thrust equation is constructed to compute thrust value for different discharge voltages and anode mass flow rates. To achieve that aim, first, thrust equation with correction factor is derived by taking into consideration the literature data. Then, that equation is validated with experimental work. Finally, the compatibility with commercial HETs is monitored.
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