Bipolar multi-mode micro-cathode arc thruster

Abstract

The invention discloses a bipolar multi-mode micro-cathode arc thruster. The bipolar multi-mode micro-cathode arc thruster is characterized by comprising an insulating cylindrical shell (1), an insulating plate (2), a coaxial anode (3), a hollow coaxial insulating member (4), an annular cathode (5), an annular anode (6), an annular insulating member (7), an electromagnetic coil (8) and a permanentmagnet (9). The double-anode structure of the bipolar multi-mode micro-cathode arc thruster has two anode structures with different configurations, namely the coaxial anode and the annular anode, andthe coaxial anode and the annular anode can be switched to run along with the change of the operating life of the thruster, so that the working states of the two modes in the life period of the thruster are achieved.

Description

technical field [0001] The invention belongs to the field of electric propulsion plasma applications, in particular to a two-stage multi-mode micro-cathode arc thruster applied to space propulsion tasks of micro- and nano-satellites. Background technique [0002] Electric propulsion is a kind of advanced propulsion method that uses electric energy to directly heat the propellant or ionizes and accelerates the propellant to obtain propulsion power. It has high specific impulse, thrust and efficiency. It has broad application prospects in space missions such as space navigation and interstellar navigation. Micro-Cathode Arc Thruster (μCAT for short) is a small-thrust electromagnetic micro-thruster specially designed for CubeSat. The specific impulse (2000-3000s) can be widely used in the attitude adjustment and orbit keeping tasks of small satellites such as micro, nano and cube satellites. [0003] The currently known micro-cathode arc thrusters have problems such as the de...

AI Technical Summary

Problems solved by technology

[0003] The currently known micro-cathode arc thrusters have problems such as performance parameters decrease after long-term ignition, discharge erosion and failure at the end of life.

The main reason is that the discharge mode of the thruster is single. After a long time of ignition, the degree of erosion of the discharge surface and the wall surface will change greatly, but the discharge mode cannot be adjusted accordingly, which will lead to performance degradation or failure of the thruster.

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