Solid pulse plasma thruster with high propellant utilization rate and working method

Abstract

The invention discloses a solid pulse plasma thruster with high propellant utilization rate and a working method, and belongs to the technical field of aerospace propulsion of micro-satellites. The solid pulse plasma thruster with high propellant utilization rate comprises a constant-force spring, an upper insulating plate for fixing a propellant, a semiconductor spark plug, a permanent magnet for increasing impulse bit, a cathode plate, a permanent magnet for increasing specific impulse, an anode plate, a high-voltage power supply, a main spark-gap capacitor, a diode, a lower insulating plate for fixing the propellant and a solid propellant; gas storage cavities for reducing the forward movement speed of neutral gas are respectively formed in the cathode plate and the anode plate; the distance between the cathode plate and the anode plate is increased on the rear sides of the gas storage cavities; tail ends, which are close to a nozzle, of the cathode plate and the anode plate are parallel to each other; the permanent magnet for increasing the impulse bit is added in the direction which is opposite to the direction of a self-inductance magnetic field; and the permanent magnet for increasing the specific impulse is added in the direction which is the same as the direction of the self-inductance magnetic field. The propellant utilization rate of the solid pulse plasma thruster can be increased. The solid pulse plasma thruster has the advantage of low cost, and is suitable for being used as a main thruster of a micro-nano satellite or an adjusting device of various large satellites.

Description

technical field [0001] The invention relates to a solid pulse plasma thruster and a working method, belonging to the technical field of microsatellite space propulsion. Background technique [0002] Low cost, short development cycle, flexible launch and low payload are the main advantages of microsatellites. At present, microsatellites have been widely used in the fields of communication, remote sensing, earth observation and space experiments. In recent years, the development of micro-satellites at home and abroad is very rapid, and the number of space launches shows an overall increasing trend. Since microsatellites are limited by total power, mass, and volume, their propulsion systems need to have the characteristics of light weight, low power consumption, small size, long life, and precise thrust. Electric propulsion technology has the advantages of small thrust, high specific impulse, and controllable thrust, and is very suitable as a propulsion technology for microsat...

AI Technical Summary

Problems solved by technology

But the current solid pulse plasma thruster has been criticized due to its extremely low working efficiency (usually less than 10%)

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