Magnetohydrodynamic Modeling of Plasma Thruster Engine for Small Satellites

In this study, a magnetohydrodynamics simulation of the plasma propulsion
system for small satellites was studied and modeled by using COMSOL Multiphysics
and SOLIDWORKS software. This research aimed to study the operating process of
the plasma propulsion system for small satellites. The PPS-1350 Hall Thruster with
xenon propellant was used as the prototype model. The propulsion system injects
electrically neutral xenon gas through the propellant feeder (Anode) into the discharge
chamber to generate positively charged xenon plasma and generate thrust. In this
study, a plasma propulsion system model was simulated. This study contained 4
modules consisting of Electrostatics module, Magnetic Fields module, Fluid Flow
module and Plasma module. The results were validated by comparing with the PPS-
1350 experimental data. The study found that the simulation results tend to be lower
than those obtained in the experiments. With xenon mass flow rate of 2.31-3.7 mg/s,
the thrust was found to be around 41-66 mN. When compared to the experimental
results at the same mass flow rate, thrust was found to be around 46-80 mN. Overall,
the deviation between the simulation and actual operating data were found to be
within 20% despite some model simplifications and limited access to actual operating
data and internal dimensions. Given that the prediction is on the conservative side, it
can still be said that the simulation model of PPS-1350 Hall Thruster is reasonably
accurate and acceptable. The results of this study will be used as knowledge for
further analysis of plasma propulsion system.