Title: Design and implementation of low-power low-cost quasi steady-state magnetoplasmadynamic propulsion using Ar-He and N₂-He gas mixtures

Authors: C.A. Barry Stoute

Addresses: Department of Earth and Space Science and Engineering, Lassonde Engineering, York University, Toronto, Ontario, M3J1P3, Canada

Abstract: Current miniature plasma propulsion technologies use ion or Hall propulsion to provide thrust for miniature satellites. The problem with ion and Hall thrusters is the low thrust-to-power ratio (30 mN/kW-50 mN/kW), and it is not enough for high-speed manoeuvres in deep-space missions. Alternatively, magnetoplasmadynamic propulsion provides higher thrust to miniature satellites than ion thrusters without the increase in mass. Magnetoplasmadynamic propulsion is a technology that the plasma is accelerated electromagnetically. This research investigates the design and performance of a low-cost magnetoplasmadynamic thruster built for micro and nanosatellites. Gas mixtures are tested in this research to observe any improvement in the overall performance. The gases used in the thruster are pure helium, nitrogen and argon; with gas mixtures of 50% helium - 50% nitrogen and 50% helium - 50% argon. The specific impulse, impulse bit, thrust efficiency and thrust-weight ratios of 50% helium - 50% nitrogen are 801 seconds, 6.29 μN·s, 19.8% and 15.72 mN/kg, respectively.

Keywords: magnetoplasmadynamics; MPD; propulsion; electric; space; astronautics; plasma.

DOI: 10.1504/IJASSE.2021.114118

International Journal of Aerospace System Science and Engineering, 2021 Vol.1 No.1, pp.20 - 34

Received: 24 Sep 2016
Accepted: 15 Mar 2017
Published online: 09 Apr 2021 *