A replaceable sputtering-resistant vacuum chamber and assembly method for ignition test of electric thruster

Abstract

A replaceable sputtering-resistant vacuum cavity and assembly method for electric thruster ignition test, comprising: a vacuum cavity, a sputtering-resistant protection plate, channel steel, and water inlet and outlet pipes. The n sputtering-resistant protective plates are spliced ​​evenly in the circumferential direction to form an n-sided structure in cross section. The sputtering-resistant protective plates are fixedly connected to the inner wall of the vacuum chamber through channel steel, and the inner wall of the vacuum chamber is an arc surface. The end surface of the channel steel facing the vacuum cavity is processed with grooves. The cavity formed by the groove and the inner wall of the vacuum chamber is used as a cold water pipeline; the wall of the vacuum chamber is provided with a through hole, and one end of the water inlet and outlet pipe is connected to the cold water flow through the through hole on the wall of the vacuum chamber, and the water inlet and outlet pipe The other end is connected to the external cold water circulation system. The invention provides a replaceable sputtering-resistant heat sink, which has the advantages of simple structure, low manufacturing cost, low reliability risk, simple maintenance and the like.

Description

Technical field[0001]The present invention relates to an alternative splash-resistant vacuum cavity and assembly method for electrically thrust ignition test, belonging to the field of vacuum test technology.Background technique[0002]In order to improve the propheticity of the artificial spacecraft, reduce the weight of the spacecraft, improve the life of the spacecraft, and people put forward the concept of electricity promotion. Electricity Promotion is a promotion technique for the kinetic energy converted into propellant using electrical energy. Compared to chemical propulsion technology, electricity advancement is not limited by the chemical solution, mainly by electrical energy to provide energy to the propellant, get rid of chemical restrictions, so it is possible to produce by increasing the energy supplied to unit quality propellant. Multi-exhaust velocity or comparative propulsion is larger than chemical. Therefore, the electric propulsion system can save propellants to im...

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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