A multi-stage high-efficiency pulsed plasma thruster

Abstract

The invention discloses a multi-section type high-efficiency pulse plasma thruster, and belongs to the field of micro-nano satellite micro-propulsion. The thruster is mainly composed of a one-sectionanode, a one-section cathode, a two-section anode, a two-section cathode, an insulation section, a trigger electrode, a trigger working medium, an energy storage capacitor set, a propellant, a coatinglayer and an outer shell body; the electrodes of the thruster are divided into two sections, each section of electrodes is provided with a voltage through a respective energy storage capacitor, so that the total energy distributed to different capacitors discharging at different positions are realized, so that a propellant ablation ionization process and a plasma acceleration process are separated, more energy is enabled to be used for the plasma acceleration process, and the whole acceleration efficiency of the thruster can be improved. A small amount of plasma is generated by triggering theworking medium which is triggered through a trigger electrode, the breakdown voltage between one-section electrode is greatly reduced to facilitate the triggering of initial discharge, and then the reliability of the operation of the thruster is further improved; and the thruster is suitable for application occasions of low-power wiener satellites, and meets corresponding task thrust requirements.

Description

Technical field [0001] The invention relates to a multi-section high-efficiency pulse plasma thruster, belonging to the field of micro-nano satellite micro-propulsion. Background technique [0002] In recent years, with the rapid development of aerospace technology, micro-nano satellites have received more and more attention due to their small size, low power consumption, short launch period, light weight, low cost, and functional scalability, and their application prospects are broad. . A large "virtual satellite" is formed by a formation of several micro-nano satellites. Through the cooperative signal processing between the micro-nano satellites, tasks such as earth observation, communication navigation, and target reconnaissance can be completed. Therefore, the mission requirements of the micro-nano satellite and the flight space environment make its propulsion system meet the following requirements: light weight, low power consumption, small size, and accurate thrust. Tradi...

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Problems solved by technology

[0003] In order to solve the problems of the traditional pulse plasma thruster ignition start-up device being prone to failure, insufficient reliability, and low energy conversion efficiency, the invention discloses a multi-stage high-efficiency pulse plasma thruster. The main technical problem to be solved is: to improve the pulse plasma Reliability and Energy Conversion Efficiency of Ignition Device for Body Thruster

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