An arc thruster anode structure

Abstract

An arc thruster anode structure, comprising: a contraction section, a core section, a first expansion section, and a second expansion section; all of them are conductors, all of which are cylindrical in shape, and are sequentially coaxial and serially sealed and connected. Inside the constricted segment, there is a conical constricted first channel; inside the core segment, there are conically constricted second channels, cylindrical channels, and conically expanded third channels; inside the dilated segment, there is a conically dilated fourth channel; inside the dilated segment There is a fifth channel with conical expansion. The first channel, the second channel, the cylindrical channel, the third channel, the fourth channel and the fifth channel are coaxially connected in series to form the inner wall of the anode. There are heat-absorbing channels inside the contracting section, the core section, the first expanding section and the second expanding section, and the outer surface has a radiation heat dissipation coating; the gas propellant flows along the heat-absorbing channel, and enters after absorbing heat from the wall of the heat-absorbing channel. arc discharge zone. The invention can reduce the processing difficulty and raw material cost of the anode, improve the performance of the thruster, reduce the quality of the anode, and is beneficial to the engineering application of satellites.

Description

technical field [0001] The invention relates to an arc discharge device, in particular to an arc thruster anode suitable for a satellite propulsion system. Background technique [0002] The anode is the key component of the arc thruster, and its function is to participate in the arc discharge and double as the nozzle of the thruster. The anode generally has a shrink-expanded inner surface. The core area involved in arc discharge is mainly the throat and its upstream and downstream areas. This area has high temperature and arc attachment, and is prone to inner wall ablation and thermal creep. Limit the life of the arc thruster. For satellite engineering applications, the existing technology generally adopts the integral anode made of tungsten alloy, which has the following shortcomings: [0003] 1) It is difficult to process. The core area near the throat of the integral anode is located inside the anode, which is difficult for machining tools to reach. [0004] 2) The co...

AI Technical Summary

Problems solved by technology

The core area near the throat of the integral anode is located inside the anode, which is difficult for machining tools to reach

[0004] 2) High cost of raw materials

A large section of tungsten alloy bar is required, and the material cost is high, especially when using rhenium-containing tungsten alloy, the material cost is higher

[0005] 3) Restrict thruster performance

It is difficult to arrange regenerative cooling channels and expand the outer surface area inside the anode, which is not conducive to enhancing the heat dissipation of the anode and restricts the performance of the thruster

[0006] 4) Not conducive to weight loss

Tungsten alloy has a high density, resulting in a large anode mass

[0007] Therefore, the existing technology is not conducive to the engineering application of satellites

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