A system comprising (i) 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 solenoidal coil for generating a radial direction magnetic field in the acceleration channel; and a distributor having a plurality of holes (13, 13a, 13b) arranged azimuthally, supplying propellant from the plurality of holes (13, 13a, 13b) 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 (13, 13a, 13b), 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 (ii) a coil power source connected to the solenoidal coil; characterized in that the system is configured to adjust, with respect to the mass flow rate of the propellant in the discharge space of the acceleration channel, a normalized 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 to operate with a magnetic flux density between 42 mT and 64 mT. (i) 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 solenoidal coil for generating a radial direction magnetic field in the acceleration channel; and a distributor having a plurality of holes (13, 13a, 13b) arranged azimuthally, supplying propellant from the plurality of holes (13, 13a, 13b) 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 (13, 13a, 13b), 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 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 solenoidal coil for generating a radial direction magnetic field in the acceleration channel; and a distributor having a plurality of holes (13, 13a, 13b) arranged azimuthally, supplying propellant from the plurality of holes (13, 13a, 13b) 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 (13, 13a, 13b), 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 (ii) a coil power source connected to the solenoidal coil;