Axisymmetric air inlet structure of Hall thruster

A Hall thruster and air intake structure technology, which is applied in the field of aerospace electric propulsion, can solve the problems of asymmetric discharge influence, asymmetric distribution, etc., and achieve the effect of reducing weight, releasing occupied space, and reducing axial size and length

Active Publication Date: 2022-04-29
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0010] The purpose of the present invention is to solve the problem that the working medium gas of the Hall thruster is asymmetrically distributed when it enters the discharge channel, which causes the influence of asymmetric discharge, and proposes an axisymmetric intake structure of the Hall thruster

Method used

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  • Axisymmetric air inlet structure of Hall thruster
  • Axisymmetric air inlet structure of Hall thruster
  • Axisymmetric air inlet structure of Hall thruster

Examples

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specific Embodiment approach 1

[0067] Specific implementation mode one: combine Figure 2 to Figure 4 Describe this embodiment, the axisymmetric intake structure of the Hall thruster described in this embodiment, the intake structure includes an intake pipe 1, a radial buffer chamber 3, an axial buffer chamber 4 and a gas injection structure 5 ;

[0068] The radial buffer chamber 3 includes a radial buffer chamber sink 31 , a radial buffer chamber cover plate 32 and a No. 1 air outlet 33 ;

[0069] A disk-shaped radial buffer chamber sinking groove 31 is provided at the center of the lower part of the magnetic pole bottom plate 12 of the Hall thruster, and the radial buffer chamber cover plate 32 is covered on the radial buffering gas path sinking groove 31, and the contact edge seam welding and sealing to form a complete radial buffer chamber 3, the inlet pipe 1 is vertically connected to the center of the cover plate 32 of the radial buffer chamber, and the working medium gas enters the radial buffer gas...

specific Embodiment approach 2

[0079] Embodiment 2: This embodiment further defines the axisymmetric intake structure of the Hall thruster described in Embodiment 1. In this embodiment, the axial buffer chamber 4 also includes a sealing ring 43;

[0080] Two annular grooves are provided at the bottom of the discharge channel 6, and the two annular grooves are respectively provided on both sides of the sinking groove 42 of the No. 2 axial buffer chamber. The sealing ring 43 is embedded in the two annular grooves. The sealing ring 43 is used for The junction of the second axial buffer chamber sinker 42 and the first axial buffer chamber sinker 41 is sealed.

[0081] In this embodiment, the structure also includes a mortise and tenon structure,

[0082] The No. 1 axial buffer chamber sinker 41 on the top of the magnetic pole bottom plate 12 , the No. 2 axial buffer chamber sinker 42 on the discharge channel 6 and the sealing ring 43 are connected together by a mortise and tenon structure.

specific Embodiment approach 3

[0083] Embodiment 3: This embodiment further defines the axisymmetric intake structure of the Hall thruster described in Embodiment 1. In this embodiment, the structure also includes a split air passage 2;

[0084] The split gas path 2 includes a round block, a split gas path sink 21 and a split gas path cover plate 22;

[0085] The round block is placed on the central position of the disk-shaped radial buffer chamber sinking groove 31, and a diversion air path sinking groove 21 is set in the center of the round block, and the split flow gas path sinking groove 21 communicates with the radial buffer chamber sinking groove 31;

[0086] The remaining part of the round block except for the diversion air channel sinking groove 21 is called a bump, and a gap matching the bump is provided on the radial buffer chamber cover plate 32, and a split flow is formed between every two adjacent gaps. Gas path cover plate 22;

[0087] The split air path cover plate 22 and the radial buffer c...

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Abstract

The invention discloses an axisymmetric air inlet structure of a Hall thruster, relates to the field of spaceflight electric propulsion, and aims to solve the problem that working medium gas is asymmetrically distributed when entering a discharge channel, so that the influence of asymmetrical discharge is caused. A radial buffer chamber sinking groove is formed in the center of the lower portion of a magnetic pole bottom plate of the Hall thruster, and a radial buffer chamber cover plate covers the radial buffer air channel sinking groove to form a closed radial buffer chamber. The top of the magnetic pole bottom plate and the bottom of the discharge channel are provided with a first axial buffer chamber sinking groove and a second axial buffer chamber sinking groove respectively, and a closed axial buffer chamber is formed by combining a sealing ring and a mortise and tenon joint structure. Constructing a gas injection structure at the bottom of the discharge channel; communicating air holes which are uniformly distributed in the circumferential direction are formed in the bottom of the magnetic pole bottom plate and the bottom of the discharge channel to communicate the radial buffer chamber, the axial buffer chamber and the gas injection structure; working medium gas sequentially passes through the gas inlet pipe, the radial buffer chamber, the axial buffer chamber and the gas injection structure and is finally injected into the discharge channel in an axial symmetry mode. The device is used for injecting gas into the discharge channel in an axial symmetry mode.

Description

technical field [0001] The invention relates to the technical field of aerospace electric propulsion. Background technique [0002] The Hall thruster is an electric thruster that uses orthogonal electromagnetic fields to ionize the atomic working fluid, accelerate the generated ions, and convert electrical energy into ion kinetic energy. It has the advantages of simple structure, high specific impulse, high efficiency, and high reliability. It is suitable for It is currently one of the most mature electric propulsion devices used in the world for attitude control, position maintenance, and deep space exploration of various spacecraft. [0003] When the Hall thruster is working, the working gas needs to be injected into the discharge channel to maintain the discharge process in the thruster channel. The ideal state of injecting the working medium gas into the discharge channel is axisymmetric state, so as to realize the stable discharge of the thruster, reduce the discharge ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F03H1/00
CPCF03H1/0081F03H1/0006
Inventor 于达仁李鸿丁明浩
Owner HARBIN INST OF TECH
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