Pulse laser plasma electricity hybrid micro-propulsion unit and method

Abstract

The invention discloses a plasma laser plasma electricity hybrid micro-propulsion unit which comprises a pulse laser ablation device, a propellant supply device and a plasma accelerating device, wherein the pulse laser ablation device irradiates a propellant supplied by the propellant supply device to generate high-speed plasma; and the plasma accelerating device is used for accelerating the high-speed plasma again. The invention also provides a pulse laser plasma electricity hybrid micro-propulsion method which comprises the following steps of: generating high-temperature and high-speed plasma through the high-frequency pulse laser ablation propellant; and accelerating the high-temperature and high-speed plasma through an electric field or magnetic field. According to the invention, a pushing force with high specific impulse and high thrust-to-power ratio can be provided for a mini satellite.

Description

technical field [0001] The invention relates to the field of plasma propulsion, in particular to a pulse laser plasma electric hybrid micro propulsion device and method. Background technique [0002] The rapid development of micro-satellites makes it necessary to study micro-propulsion technology with high efficiency, light weight, low power consumption, small thrust and micro-impulse. At present, the main researched micropropulsion technologies such as pulsed plasma propulsion (PPT) and Hall propulsion (SPT) have their own advantages and disadvantages. At present, the ionization degree of the PPT propulsion method is low, and most particles cannot be directly accelerated by the electromagnetic field. The propulsion efficiency is very low, less than 10%, and the propulsion power ratio is not high. The propellant used in Hall propulsion (SPT) is usually xenon gas, which has high specific impulse and high thrust power ratio; the disadvantage is that the steel cylinder for sto...

AI Technical Summary

Problems solved by technology

At present, the ionization degree of the PPT propulsion method is low, most of the particles cannot be directly accelerated by the electromagnetic field, the propulsion efficiency is very low, less than 10%, and the propulsion power ratio is not high

The propellant used in Hall propulsion (SPT) is usually xenon gas, which has high specific impulse and high thrust power ratio; the disadvantage is that the cylinder for storing gas accounts for more than half of the dry weight of the system, resulting in large mass and volume, and the structure complex, low payload rate, and also limited by cathode launcher life, difficult to use on tiny satellites

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