Patent ID: 9089040
Filing Date: 2015-07-21
Classification: B64G,F03H,H05H

Abstract:
1. A Hall thruster comprising: an acceleration channel forming an annular discharge space, ionizing propellant flowing into the discharge space to generate ions, and accelerating and discharging the generated ions; an anode penetrating to the discharge space of the acceleration channel; a distributor having a plurality of holes arranged azimuthally, supplying propellant from the plurality of holes via the anode to the discharge space of the acceleration channel, an amount of the propellant varying according to positions of the plurality of holes, thereby generating a plurality of regions, between adjacent ones of which a mass flow rate of the propellant is different, azimuthally in the discharge space of the acceleration channel, and adjusting, with respect to the mass flow rate of the propellant in the discharge space of the acceleration channel, a differential within a range of 5 to 15% between the mass flow rate of the propellant in a region with a large mass flow rate of the propellant and the mass flow rate of the propellant in a region with a small mass flow rate of the propellant; and a plenum chamber segmented into a plurality of sections azimuthally corresponding to the plurality of regions, respectively, the plenum chamber having a port to which the propellant is injected for each section; and a propellant injecting part for injecting the propellant to the port of the plenum chamber, the propellant injecting part adjusting an injecting amount of the propellant for each section of the plenum chamber, wherein the distributor supplies the propellant injected to the port of the plenum chamber for each section of the plenum chamber, from each one of the plurality of holes, which penetrates to a region corresponding to each section of the plenum chamber through the anode, to the discharge space of the acceleration channel.