Prototype Development of a 130 W class Hall Thruster for Small Satellites

Small satellites with a mass below 300 kg are actively utilized in various space missions such as Earth observation and space exploration. In recent years, mega-constellations composed of small satellites in low Earth orbit (LEO) have played a key role in enabling space-based internet services such as Starlink and OneWeb. For coordinated operations, satellites require precise relative position control and orbit maintenance, which necessitate a propulsion system capable of providing sufficient delta-v (Δv). A Hall thruster is considered a promising electric thruster for space missions such as station-keeping and orbit transfer maneuvers due to its high specific impulse and high thrust-to-power ratio. In this study, a prototype of a 130 W class Hall thruster was designed and fabricated for small satellite applications. Based on low-power Hall thruster scaling laws, the channel mean diameter (26 mm), channel width (6.3 mm), anode mass flow rate (0.5 mg/s), and target thrust (7.7 mN) were determined. In the design process, thermal expansion was taken into account and the magnetic field configuration was determined based on the channel geometry and ionization length. In addition, the uniformity of propellant flow was also evaluated by analyzing the influence of the anode baffle and orifice size on the flow distribution in the azimuthal direction. In this presentation, the design parameters and discharge characteristics of the prototype Hall thruster will be presented in detail.