A Laser-Induced RF Discharge Plasma Thruster

Abstract

The invention discloses a laser-induced radio-frequency discharge plasma thruster, comprising: an outer electrode, an insulating layer, an inner electrode, an outer electrode radio frequency power supply, an inner electrode radio frequency power supply, a transmission shaft and a stepping motor; an outer electrode, an insulating layer and an inner electrode Set up concentrically in turn to form a dual-electrode acceleration system; the outer electrode RF power supply is connected to the outer electrode through the transmission shaft to provide the high-frequency voltage required for acceleration for the outer electrode; the inner electrode RF power supply is connected to the inner electrode through the transmission shaft. Provide the internal electrode with the high-frequency voltage required for acceleration; the stepper motor is connected to the dielectric target through the transmission shaft, driving the dielectric target to rotate at a constant speed; an alternating electric field is formed between the double-electrode acceleration system and the dielectric target; the dielectric target The material generates laser plasma under the action of pulsed laser, and the laser plasma is ejected after being accelerated several times in the alternating electric field. The invention can effectively realize multiple accelerations of laser plasma, and is of great significance to laser plasma propulsion technology.

Description

technical field [0001] The invention belongs to the technical field of lasers, and more specifically relates to a laser-induced radio frequency discharge plasma thruster. Background technique [0002] The development of micro-spacecraft has always been a research hotspot in the aerospace field of various countries in the world. Micro-propulsion technology can be used for attitude adjustment of in-orbit satellites and orbit control of micro-spacecraft. Although in the past, many micro-spacecraft did not have propulsion systems, future micro-spacecraft will require powerful propulsion capabilities to provide a high degree of maneuverability. The current feasibility study of micro-spacecraft shows that for a micro-spacecraft with a mass of less than 100 kg, the propulsion power is less than 100 watts. To achieve greater propulsion power, various potential propulsion systems have been proposed for micro-spacecraft applications, such as ion thrusters, field emission thrusters, p...

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Problems solved by technology

[0004] For the defects of the prior art, the purpose of the present invention is to solve the technical problem of how to improve the ejection velocity of laser plasma

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