This paper describes a hollow cathode keeper power supply and an anode power supply for a hall thruster on artificial satellites. In the keeper power supply, it is required that the electric discharge characteristic is excellent and the current control characteristic is stable. In the anode power supply, it is required that the electric discharge characteristic is excellent, the voltage control characteristic is stable and the efficiency is high. We confirm that these electric discharge characteristics are excellent with the experimental models. Furthermore, we confirm these control characteristics are stable for the hollow cathode and the hall thruster made as experimental models. Lastly, it is reported on the condition to suppress the electrical discharge oscillation phenomenon of a hall thruster.
