Electro-chemical hybrid power space thruster

Abstract

The invention discloses an electro-chemical hybrid power space thruster which comprises a shell, an insulating heat-insulating sleeve, a spring, a low-voltage cathode, an electronic control solid propellant, a low-voltage anode, an insulating plate, a high-voltage anode, an electric propulsion propellant, a high-voltage cathode, an insulating sleeve and a fixed contact pin. The electronic control solid propellant is used for replacing a traditional solid chemical propellant, and multiple times of ignition and flameout of the solid propellant and thrust adjusting operation are achieved. A traditional solid chemical thruster is improved, the traditional solid chemical thruster and a pulse plasma thruster are integrated into a set of electro-chemical hybrid poewr space thruster, and the requirements for large thrust and high specific impulse of space propulsion are met; and when the thruster combusts the electronic control solid propellant to work, products generated by combustion can be accelerated by the action of an electric field between the high-voltage anode and the high-voltage cathode, and thrust and specific impulse during electrochemical propulsion are increased.

Description

technical field [0001] The invention relates to the technical field of aerospace propulsion, in particular to an electro-chemical hybrid space thruster. Background technique [0002] With the rapid development of the aerospace industry, especially the sharp increase of commercial launch missions and the expansion of space exploration missions, new requirements have been put forward for space propulsion technology to realize operations such as vehicle orbit change, attitude adjustment and formation flight. Traditional chemical propulsion technology and electric propulsion technology are the mainstream of current space propulsion technology. The outstanding feature of traditional chemical propulsion technology is that it can provide large thrust, but due to the properties of the propellant, it is difficult to achieve multiple starts and adjustable thrust operations, and the specific impulse of the propellant is low (the highest specific impulse is about 450s). Using tradition...

AI Technical Summary

Problems solved by technology

[0003] The present invention proposes an electrochemical-chemical hybrid space thruster aiming at the current situation that it is difficult to simultaneously meet the requirements of high specific impulse and large thrust in the existing propulsion technology

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