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Hall thruster cooling bracket

A technology of Hall thruster and heat dissipation bracket, which is applied to thrust reversers, machines/engines, utilizing plasma, etc., can solve the problems of overall Hall thruster, overheating, etc., and achieve the effect of increasing space radiation heat dissipation

Active Publication Date: 2018-09-07
HARBIN INST OF TECH
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  • Summary
  • Abstract
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to solve the overall or local overheating problem of the Hall thruster under high power, and provide a cooling bracket for the Hall thruster

Method used

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  • Hall thruster cooling bracket
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specific Embodiment approach 1

[0021] Specific implementation mode one: the following combination Figure 1 to Figure 4 To illustrate this embodiment, the Hall thruster cooling bracket described in this embodiment can be found in figure 1 As shown, this embodiment adopts an integrated processing method, and a whole piece of material is directly processed to ensure that the overall structure has a small thermal resistance.

[0022] In this embodiment, the material used for the cooling support structure of the Hall thruster is an aluminum alloy with high thermal conductivity and strong anti-sputtering ability. The thermal conductivity of the aluminum alloy is generally 210W / (m·K).

[0023] During the installation and use of the heat dissipation support of this embodiment, the heat dissipation support contacts with other parts at two parts, one is that it acts as a ceramic support, and the ceramic discharge channel is fixed on the discharge channel installation ring surface 4 in the middle; the other is It it...

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Abstract

The heat dissipation bracket of a Hall thruster belongs to the field of Hall thrusters, and the invention aims to solve the problem of overall or partial overheating of a Hall thruster under high power. The invention includes a heat dissipation ring, a radial heat dissipation bottom edge, m heat conduction supporting ribs, a discharge channel installation ring surface and n heat insulation blocks; The radial heat dissipation bottom edge with outward creases, the lower surface of the radial heat dissipation bottom edge is evenly provided with n heat insulation blocks along the circumferential direction, and each heat insulation block is provided with a bottom plate penetrating the radial heat dissipation bottom edge Mounting holes; the discharge channel installation ring surface is coaxially arranged with the heat dissipation ring, and the discharge channel installation ring surface is connected to the inner side wall of the heat dissipation ring through m heat conduction support ribs evenly distributed along the circumferential direction; between two adjacent heat conduction support ribs The radial holes provide space for installing the external excitation coil and the external magnetic shield; the axial distance between the heat conduction support rib and the top of the heat dissipation ring is 1 / 7 to 1 / 5 of the axial height of the heat dissipation ring.

Description

technical field [0001] The invention belongs to the field of Hall thrusters. Background technique [0002] Hall Thruster (Hall Thruster) uses electric energy to ionize the working gas (usually inert gas Xe) to generate plasma, and then uses the electric field formed in the annular channel of the thruster to accelerate the ions out of the channel along the axial direction to obtain power. Electric propulsion. It has the characteristics of simple structure, high specific impulse, high efficiency, long working life, high power density, long service time in orbit, etc. It is suitable for attitude control, orbit correction, orbit transfer, power compensation, position maintenance, Repositioning, off-orbit processing, space exploration and interstellar voyage and other tasks are currently the most widely used and most mature electric propulsion systems in the world. [0003] At present, the high-power, high-thrust Hall thruster is a research hotspot in electric propulsion. Howe...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F03H1/00
CPCF03H1/0031F03H1/0075
Inventor 丁永杰魏立秋李鸿于达仁
Owner HARBIN INST OF TECH
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