Abstract: A thermal management system (5) for a magnetoplasmadynamic thruster (10) for a space craft is disclosed. The thermal management system (5) is located between at least one superconducting magnet (120) and a plasma discharge unit (15 and comprises a thermal barrier (40, 60) located adjacent to the plasma discharge unit (15), —a multilayer insulation (70) located between the thermal barrier (40, 60) and the cryostat insulation (80), and a radiation gap (50) located in the thermal barrier (40, 60).

Abstract: A propulsion unit (10) for a spacecraft is described. The propulsion unit (10) comprises a centrally arranged cathode (20), a concentric anode (30), an injection point (60) for injecting a propellant (50) between the central cathode (20) and the concentric anode (30), an acceleration coil system (100) and a vectoring coil system (110) for expelling a plasma plume (75) from a nozzle (115). A plurality of superconducting coils (120, 125) is arranged about the concentric anode (30) for creating a magnetic field (B) between the central cathode (20) and the concentric anode (30) and directing the plasma plume (65) from the nozzle (115).