Diagnostic and modelling investigation on the ion acceleration and plasma throttling effects in a dual- emitter hollow cathode micro-thruster

Hollow cathode discharges are widely used as neutralizers for the electric propulsion systems and recently developed into micro-thrusters for the small satellites. In this work, a dual emitter hollow cathode thruster is developed, which can be operated in two different modes-the neutralizer mode and the micro-thruster mode. For characterizing this kind of new device, the Langmuir probe, Faraday probe, and retarding potential analyzer are used to determine the electron temperature, electron density, ion flux, and ion energy distribution function. The operating parameters, including the thrust, and specific impulse, are also measured. A two-dimensional self-consistent extended fluid model is employed to calculate the spatial distribution of plasma parameters and the fluid field of electrons in the region around the emitters. By comparing the diagnostic and modelling results, it is found that the change in the electric field and ionization zone is the essential reason for the different performances of the device in the neutralizer and micro-thruster modes. Variation in the electric field leads to an ion acceleration effect in the micro-thruster mode; moving of the ionization zone raises the plasma pressure in the orifice region of the hollow cathode, and thus leads to enhanced plasma throttling and gas expanding effects. By analyzing the above mechanisms, the possible methods for improving this kind of hollow cathode micro-thruster are discussed. (c) 2021 Chinese Society of Aeronautics and Astronautics. Production and hosting by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/).