The invention discloses a radio frequency ion thruster with a hemispherical discharge chamber, and aims to solve the problems that the energy loss of the inner surface of the discharge chamber is high and the efficiency of the thruster is low due to the fact that an existing radio frequency ion thruster adopts a cylindrical discharge chamber. The thruster comprises a thruster shell, a discharge chamber and a radio frequency antenna are arranged in the thruster shell, and the discharge chamber is of a hemispherical structure; the radio frequency antenna is connected with a radio frequency source; an ion optical system is arranged at the lower end of the discharge chamber and comprises a screen grid electrode and an acceleration grid electrode; one end of the gas inlet pipe is connected with the gas cylinder through the mass flow controller, and the other end of the gas inlet pipe penetrates through the thruster shell and then is connected with the gas distributor; by adopting the hemispherical discharge chamber structure, the inner surface area of the discharge chamber is reduced, the ion energy loss is reduced, and the efficiency of the thruster is improved; different from traditional column-type and disc-type radio frequency antennas, the radio frequency antenna wound on the outer side of the hemispherical discharge chamber is of a special-shaped structure and can be tightly attached to the discharge chamber, and the radio frequency energy coupling efficiency is improved.

    本申请公开了一种半球形放电室射频离子推力器,以解决现有射频离子推力器采用圆柱型放电室存在放电室内表面能量损耗多、推力器的效率低的问题。本申请包括推力器壳体,其内部设有放电室和射频天线,放电室为半球形结构;射频天线连接射频源;放电室下端设有离子光学系统,离子光学系统包括屏栅极和加速栅极;进气管一端通过质量流量控制器连接气瓶,另一端穿过推力器壳体后接气体分配器,工质气体通过气体分配器进入放电室;本申请采用半球形放电室结构,降低了放电室内表面面积,减少离子能量损耗,提高推力器效率;与传统柱型和盘型射频天线不同,缠绕在半球形放电室外侧的射频天线为异型结构,能够与放电室紧密贴合,提高射频能量耦合效率。


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    Title :

    Hemispherical discharge chamber radio frequency ion thruster


    Additional title:

    一种半球形放电室射频离子推力器


    Contributors:
    BAN XIN (author) / MA LONGFEI (author) / FU JIAHAO (author) / HE JIANWU (author)

    Publication date :

    2024-05-10


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

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




    Radio Frequency thruster

    KANG KYUNG CHANG | European Patent Office | 2018

    Free access

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    Syueber, T. J. / American Institute of Aeronautics and Astronautics / Society of Automotive Engineers et al. | British Library Conference Proceedings | 2005


    Discharge chamber optimization of SERT II thruster

    Bechtel, R.T. | Engineering Index Backfile | 1968


    Discharge Chamber Performance of the NEXIS Ion Thruster

    Goebel, Dan / Polk, J. / Sengupta, A. | AIAA | 2004