High-temperature superconducting plasma thruster system having variable temperature ranges and being applied in space

A high-temperature superconducting plasma thruster system, having variable temperature ranges and being applied in space, wherein the high-temperature superconducting plasma thruster system comprises:

• a cathode-anode assembly, a high-temperature superconducting magnet system, a supporting and adjusting platform, a power-and-gas supply and cooling system, and an obtaining control system;
• wherein the cathode-anode assembly is disposed at a center of a ring of the high-temperature superconducting magnet system;
• the cathode-anode assembly and the high-temperature superconducting magnet system are spatially engaged with each other by the supporting and adjusting platform to form a main body of the high-temperature superconducting plasma thruster system;
• the power-and-gas supply and cooling system and the obtaining control system are located outside of the main body of the high-temperature superconducting plasma thruster system and are connected to the cathode-anode assembly and the high-temperature superconducting magnet system;
• the cathode-anode assembly comprises;
• a cathode-anode cooling and heat-exchanging assembly, a cathode-anode pressure-resistant and insulating assembly, and a cathode-anode plasma high-voltage ionization assembly;
• the cathode-anode cooling and heat-exchanging assembly comprises:
• an anode body, a spiral pipe heat-exchanging unit, and a multi-channel inlet-outlet pipe;
• the cathode-anode pressure-resistant and insulating assembly comprises:
• a sleeve-type ceramic and a G10 positioning flange plate;
• the cathode-anode plasma high-voltage ionization assembly comprises:
• a cathode inlet tube, a fixation ring, an inner cavity, a nozzle fixation seat, and a cathode nozzle.