Performance of a low power Hall effect thruster with several gaseous propellants
Thomas F. Munro-O’Brien, Charles N. Ryan
Abstract
There is a growing need to consider alternative propellants for operation in Hall thrusters, away from the conventional legacy of using xenon. This is particularly the case for small Hall thrusters; which are growing exponentially in their use, whilst needing to be operational on inexpensive propellants. Alternative propellants include condensable propellants (i.e., zinc and iodine), or other gaseous propellants (krypton, argon, and nitrogen (N2)) - which are the focus here. A low power (nominally 100 W) miniature magnetically shielded Hall thruster has been designed and manufactured, based upon standard scaling laws, and with specific considerations for operation with the use of alternative gaseous propellants. The thruster, designated the MaSHEKT-100, was designed to be a low power magnetically shielded thruster to operate on krypton. Here the thruster has subsequently been operated on xenon, krypton, argon, and diatomic nitrogen successfully, with an unstable operation with neon. The thruster is operated at discharge powers of between 30 - 810 W. Using a pendulum thrust balance, the thruster performance was measured across a wide range of flow rates, magnetic field strengths, and anode discharge voltages. The performance measured for different propellants had peak thrusts of 12.6 mN, 6.9 mN, 6.6 mN and 5.7 mN, anode efficiencies up to 26.3%, 15.2%, 9.6% and 5.4%, and specific impulses up to 2160 s, 1730 s, 1390 s, and 1000 s, for xenon, krypton, argon, and diatomic nitrogen respectively. This dataset and the following analysis provides one of the few times a comprehensive selection of alternative gaseous propellants have been tested within the same thruster and compared directly with unchanged geometry or set-up.