Preliminary Experimental Characterization of a Microwave Discharge Cusped Field Thruster

Abstract

The cusped field thruster has become a candidate thruster in next-generation space science missions due to its low complexity and potential long life over a wide range of thrust conditions. However, the reduction of propellant utilization and, as a result, the total performance degradation has emerged in works on cusped field thruster downscaling. In this work, a coaxial resonator is utilized to feed the microwave (MW) into the near-anode region of the cusped field thruster, which contributes to ionization at a relatively low mass flow rate. With a LaB6 thermionic emission cathode, the thruster can operate in two modes: MW excited mode and the MW-DC mixed mode. The results show that the thruster can operate with a minimum mass flow rate minimum of 0.004\xa0mg/s and achieves a continuously adjustable thrust from 1.9\xa0μN to 30.8\xa0μN. The performance variation characteristics over the three control parameters (anode voltage, mass flow rate, and MW power) are considered. Additionally, a plume plasma diagnosis is performed with a Faraday probe and a retarding potential analyzer to analyze the discharge performance and plasma characteristics with different operating conditions. •An MW-DC combined discharge is achieved in a blend mode.•An efficient microwave plasma generator, CTLR, is creatively applied on an electric propulsion device.•Thrust which fulfills the primary application demands of the GW observation mission is achieved.