Ignition process for narrow channel hall thruster

A narrow channel Hall thruster, comprising:

• a thruster body comprising a magnetic circuit;
• an annular discharge channel formed within the magnetic circuit, the annular discharge channel having a first extremity having a first channel width, and a second extremity, downstream from the first extremity and having a second channel width, the second channel width being 3 mm or less, and the first channel width being greater than the second channel width;
• an annular anode positioned in the annular discharge channel;
• a cathode positioned externally to the annular discharge channel, and configured for electron emission;
• a first power supply configured to apply a positive potential to the annular anode relative to the thruster body and the cathode, such that a plasma discharge can be generated in gases within the annular discharge channel;
• and
• a second power supply configured to apply a negative potential to the cathode, relative to the thruster body and the annular anode,
• wherein the second power supply is configured to reduce the negative potential applied to the cathode, when a current supplied by the first power supply exceeds a predetermined level.