The operation of a low-power cylindrical Hall thruster with zinc as the propellant

Abstract

There is a strong interest to develop electric propulsion systems that utilize alternative propellants to xenon, both forsmaller platforms with tighter budget, mass, and volume constraints, or for larger satellites that may otherwise depletethe world market resource. This is leading to the development of high performance electric propulsion systems, forexample Hall Effect Thrusters, which can operate on alternative propellants. Hall Thrusters (HTs) have been shownto function with a wide range of propellants including xenon, krypton, iodine, and more exotic propellants such aszinc, magnesium and bismuth. Their relatively simple annular topology makes them well suited to miniaturisation,however reduced component size has implications for the strength of the magnetic field, erosion of the channel, andthe level of heating present. The Cylindrical Hall Thruster (CHT) was proposed to address these issues, using arecessed annular channel to reduce the surface-to-volume ratio and a cusp magnetic field to contain the electrons. Acollaborative project between the University of Southampton and OHB Sweden has begun to characterise a low-powerCHT using firstly Krypton, and then to compare the performance to when using zinc as the propellant.The paper presents the results of the characterisation of the CHT-100 thruster using krypton, and development of thethruster for operating with zinc. The design of the CHT-100 is described, and also the setup of the test campaign usedto evaluate the thruster performance, with a pendulum thrust balance used to accurately record the thrust producedand therefore efficiency. Results from operating the CHT-100 on krypton are discussed.The in depth characterization of a propellant delivery system using zinc as the propellant are described. This involvesthermal analysis of the system,Further, the design of a low power (100 – 200 W) Hall Effect Thruster is discussed. The design process is described,including validation that it is capable of operating on alternative propellants. The manufactured thruster is illustratedand the magnetic field demonstrated to be that which is required.

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