Replaceable sputtering-resistant vacuum cavity for electric thruster ignition test and assembly method

Abstract

The invention discloses a replaceable sputtering-resistant vacuum cavity for an electric thruster ignition test and an assembly method. The replaceable sputtering-resistant vacuum cavity comprises a vacuum cavity body, sputtering-resistant protection plates, channel steels and a water inlet and outlet pipeline; n sputtering-resistant protection plates are circumferentially and uniformly distributed and spliced to form a structure with an n-sided cross section, the sputtering-resistant protection plates are fixedly connected with the inner wall of the vacuum cavity through channel steel, and the inner wall of the vacuum cavity is a cambered surface. Grooves are machined in the end faces, facing the vacuum cavity, of the steel channels. A cavity formed by closing the grooves and the inner wall of the vacuum cavity is used as a cold water pipeline; the vacuum cavity is provided with a through hole on a wall surface, one end of the water inlet and outlet pipeline is communicated with the cold water flow channel through the through hole in the wall surface of the vacuum cavity, and the other end of the water inlet and outlet pipeline is connected with an external cold water circulationsystem. The replaceable sputtering-resistant heat dissipation device has the advantages of being simple in structure, low in manufacturing cost, low in reliability risk, easy to maintain and the like.

Description

technical field [0001] The invention relates to a replaceable sputtering-resistant vacuum cavity and an assembly method for ignition tests of electric thrusters, belonging to the technical field of vacuum tests. Background technique [0002] In order to increase the specific impulse of the propulsion system of artificial spacecraft, thereby reducing the weight of the spacecraft and improving the life of the spacecraft, the concept of electric propulsion has been proposed. Electric propulsion is a propulsion technology in which a spacecraft uses electrical energy converted into kinetic energy of the propellant. Compared with chemical propulsion technology, electric propulsion is not limited by the chemical energy of the propellant. It mainly relies on electric energy to provide energy for the propellant, which is free from the limitation of chemical energy. Therefore, by increasing the energy provided to the propellant per unit mass, it is possible to produce Much greater ex...

AI Technical Summary

Problems solved by technology

[0007] The technical problem of the present invention is: to overcome the deficiencies of the prior art, and to propose a replaceable sputter-resistant vacuum cavity and assembly method for the ignition test of the electric thruster, which solves the problem of the traditional "birdcage" heat sink. Problems such as complex system structure, high production cost, and long production time

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