Magnetohydrodynamic modelling of a plasma thruster engine for small satellites.

In this study, a magnetohydrodynamics simulation of a plasma propulsion system for small satellites was studied and modelled using COMSOL Multiphysics and SOLIDWORKS software. This research aimed to study the operating process of a plasma propulsion system for small satellites. A PPS-1350 Hall Thruster with a 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 form 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, magnetic fields, fluid flow and plasma modules. The results were validated by comparing them with PPS-1350 experimental data. The study found that the simulation results tend to be lower than those obtained in the experiments. With a 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 the 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 systems. [ABSTRACT FROM AUTHOR]