Far-field plume characterization of a low-power cylindrical Hall thruster Articles uri icon

publication date

  • July 2024

start page

  • 1

end page

  • 17

issue

  • 4

volume

  • 136

International Standard Serial Number (ISSN)

  • 0021-8979

Electronic International Standard Serial Number (EISSN)

  • 1089-7550

abstract

  • A fully cylindrical Hall thruster prototype was tested in the power range of 30-300W with the objective of understanding the behavior of the discharge as a function of input parameters. Various operating conditions were compared, including two magnetic field configurations, a set of propellant mass flow rates, and a range of discharge voltages. Plasma properties were measured in the plume, with a Langmuir probe, a retarding potential analyzer, and a Faraday cup. The experimental results showed that the mass flow rate strongly affects the ionization and, consequently, other related properties such as the plasma density, currents, and propellant utilization. The discharge voltage also appeared to influence the ion energy and propellant utilization. The performance accessible from the measured magnitudes is assessed, resulting in a maximum thrust efficiency of about 18% at 0.35 mg s-1 and 168 W.

subjects

  • Aeronautics

keywords

  • polytropic process; electric propulsion; propellants; hall effect thruster; faraday cup; plasma diagnostics; plasma dynamics; plasma properties and parameters; plasma sheaths; fluid flows