The invention relates to the technical field of spacecraft propulsion, in particular to a microwave cathode ion thruster which comprises an air inlet pipeline, a microwave power source, a microwave neutralizer, a microwave cathode system, a thruster discharge chamber and a grid system. Wherein the gas inlet pipeline comprises a first gas inlet pipeline communicated with a microwave neutralizer, a second gas inlet pipeline communicated with a microwave cathode system and a third gas inlet pipeline communicated with a thruster discharge chamber; the microwave power supply is respectively connected with the microwave neutralizer and the microwave cathode system; the microwave cathode system is arranged at the input end of the thruster discharge chamber, and the grid system is arranged at the output end of the thruster discharge chamber; and the microwave neutralizer is communicated with the thruster discharge chamber and is close to the output end of the thruster discharge chamber. The ultra-low earth orbit environment gas can be used as a working medium, the service life of the thruster is long, the energy of electron flow can be improved, the energy of primary electrons can be effectively increased, and therefore the plasma ionization degree of the discharge chamber can be improved.

    本申请涉及航天器推进技术领域,具体而言,涉及一种微波阴极离子推力器,包括进气管路、微波电源、微波中和器、微波阴极系统、推力器放电室以及栅极系统,其中:进气管路包括与微波中和器连通的第一进气管路、与微波阴极系统连通的第二进气管路以及与推力器放电室连通的第三进气管路;微波电源分别与微波中和器以及微波阴极系统连接;微波阴极系统设置在推力器放电室的输入端,栅极系统设置在推力器放电室的输出端;微波中和器与推力器放电室连通,靠近推力器放电室的输出端。本申请能够利用超低地球轨道环境气体作为工质,实现较长的推力器寿命,可提高电子流的能量,可使原初电子有效增加能量,从而有利于放电室等离子体电离度的提高。


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    Title :

    Microwave cathode ion thruster


    Additional title:

    一种微波阴极离子推力器


    Contributors:
    WU XIANMING (author) / GENG HAI (author) / WU CHENCHEN (author) / SUN XINFENG (author) / JIA LIANJUN (author) / HE YAQIANG (author) / PU YANXU (author)

    Publication date :

    2023-03-21


    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



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