A high-temperature superconducting plasma thruster system, having variable temperature ranges and being applied in space, is provided. The high-temperature superconducting plasma thruster system includes: 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. 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 thruster system; the power-and-gas supply and cooling system and the obtaining control system are located outside of the main body of the thruster system and are connected to the cathode-anode assembly and the high-temperature superconducting magnet system.


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    Title :

    HIGH-TEMPERATURE SUPERCONDUCTING PLASMA THRUSTER SYSTEM HAVING VARIABLE TEMPERATURE RANGES AND BEING APPLIED IN SPACE


    Contributors:
    ZHENG JINXING (author) / LIU HAIYANG (author) / ZHU XIAOLIANG (author) / LU YUDONG (author) / LI MING (author) / DU YIFAN (author) / ZHU LEI (author) / TANG ZHUOYAO (author)

    Publication date :

    2024-07-11


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    H05H Plasmatechnik , PLASMA TECHNIQUE / B64G Raumfahrt , COSMONAUTICS / F03H PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR , Erzeugung von Vortriebskraft [Schub] nach dem Prinzip des Rückstoßes, soweit nicht anderweitig vorgesehen




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