Abstract: A Hall thruster for use with a condensable propellant including a plasma accelerator including an anode for providing plasma discharge, a distributor for distributing the condensable propellant in a liquid or vaporized state, and an electric circuit including a cathode for emitting electrons attracted to the anode and for neutralizing ion flux emitted from the plasma accelerator. A condensable propellant feed system includes a storage vessel for storing the condensable propellant and providing liquid condensable propellant at a controlled pressure. A condensable propellant flow controller includes a pressure reducing device for controlling the flow rate of the liquid condensable propellant. A vaporizer at or above the vaporization temperature of the liquid condensable propellant vaporizes the liquid condensable propellant at a predetermined vaporization rate and flow rate.