Large-area microcavity discharge plasma microthruster with magnetic field control type liquid working medium

Abstract

The magnetic field control type liquid-phase working medium large-area microcavity discharge plasma micro-thruster, the propellant working medium feeding mechanism diffuses the liquid propellant in the liquid propellant storage tank into the discharge microcavity, and the discharge microcavity is composed of A hole with different diameters runs through the metal sheet and the insulating dielectric, and the insulating dielectric is sandwiched between two adjacent metal sheets, and the adjacent two metal sheets form an electrode pair; the metal sheet at the end of the discharge microcavity and the insulating dielectric form a pull Farr nozzle, where the insulating dielectric forms the constriction and divergence of the Rafal nozzle, and the anode metal sheet forms the throat of the Rafal nozzle, which forms an electrode with the cathode metal sheet located at the exit of the divergent section of the Rafal nozzle Yes; at least one electrode pair is set on the horizontal section of the Rafal nozzle, the external power supply module provides periodic AC or DC high-voltage pulse voltage, and is connected to each electrode pair with a wire, and the ring-shaped permanent magnet is set in the above discharge microcavity outside of the pipe wall.

Description

technical field [0001] The invention relates to a large-area micro-cavity discharge plasma space micro-propulsion based on magnetic field modulation, which is especially suitable for micro-propulsion systems with high integration, low power consumption, precise impulse, and high specific impulse for space micro-spacecraft work needs. Background technique [0002] The urgent need for micro-propulsion technology for space miniaturized platforms stems from the vigorous development of micro-nano satellites in this century. After entering the 21st century, micro-nano satellite networking technology has developed rapidly and become increasingly mature, which enables micro-nano satellites to perform the functions of traditional large satellites while having the advantages of short cycle, low risk, flexible launch methods, and strong scalability . Due to the small size, light weight and small moment of inertia of the micro-nano satellite, the thrust required for satellite orbit an...

AI Technical Summary

Problems solved by technology

[0005] The technical problem of the present invention is: to overcome the bottlenecks of traditional micro-cavity discharge plasma micro-thrusters such as low specific impulse, low energy efficiency, and low propulsion control precision, and propose a large-area micro-cavity discharge plasma based on magnetic field modulation Body micro propulsion, through the comprehensive regulation of various external control conditions and the optimal configuration of various new components to achieve high specific impulse, long life and high control precision micro-nano satellite propulsion

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