Laser-induced radio-frequency discharge plasma thruster

Abstract

The invention discloses a laser-induced radio-frequency discharge plasma thruster which comprises an outer electrode, an insulating layer, an inner electrode, an outer electrode radio-frequency powersupply, an inner electrode radio-frequency power supply, a transmission shaft and a stepping motor; the outer electrode, the insulating layer and the inner electrode are coaxially arranged in sequenceto form a double-electrode acceleration system; the outer electrode radio-frequency power supply is connected with the outer electrode through the transmission shaft and provides high-frequency voltage required by acceleration for the outer electrode; the inner electrode radio-frequency power supply is connected with the inner electrode through the transmission shaft and provides high-frequency voltage required by acceleration for the inner electrode; the stepping motor is connected with a medium target material through the transmission shaft and drives the medium target material to rotate ata constant speed; an alternating electric field is formed between the double-electrode acceleration system and the medium target material; and the medium target material generates laser plasmas underthe action of pulse laser, and the laser plasmas are sprayed out after being accelerated for multiple times in the alternating electric field. According to the laser-induced radio-frequency dischargeplasma thruster, multiple acceleration to the laser plasma can be effectively realized to play great significance to the 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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