Anode and cold air thruster combined air supply cusped magnetic field plasma thruster

A technology of cold air thrust and cusp magnetic field, which is applied in the field of plasma, can solve the problem that it is difficult to effectively generate thrust less than 100 micronewtons, and achieve the effect of continuous adjustable thrust in a wide range, simple system, and high thrust density

Inactive Publication Date: 2018-05-08
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to solve the problem that the existing cusp magnetic field thruster is difficult to effectively

Method used

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  • Anode and cold air thruster combined air supply cusped magnetic field plasma thruster
  • Anode and cold air thruster combined air supply cusped magnetic field plasma thruster

Examples

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Embodiment

[0031] Example: Combined figure 2 Be explained.

[0032] This implementation case provides a micro-level cusped magnetic field plasma thruster with a simple structure, small size, and a thrust that can be continuously varied from 1 μN to 100 μN. It is composed of a miniaturized micro-level tangent magnetic field plasma thruster and a micro-level cold gas thruster that can generate a thrust of less than 10 μN;

[0033] The specific structure of the anode-cold gas thruster gas supply tangential magnetic field plasma thruster is as follows: figure 2 As shown, the overall structure is axisymmetric, including discharge channel 1, magnetic ring 2, first permanent magnet 3, cold air thruster 4, anode 5, magnetic ring heat conducting sheet 6, second permanent magnet 7, housing 8, heating Device 9, heater terminal 10;

[0034] The cold air thruster 4 can directly adopt the size of the existing thruster nozzle, and finally be integrated inside the anode 5 of the tangential magnetic...

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Abstract

The invention provides an anode and cold air thruster combined air supply cusped magnetic field plasma thruster and belongs to the field of the space technology and low-temperature plasma. The plasmathruster is provided for solving the problem that an existing cusped magnetic field thruster can hardly generate the thrust less than 100 micronewtons. The plasma thruster comprises a discharge channel, a magnetic conducting ring, a first permanent magnet, an anode, a magnetic conducting ring heat conducting plate, a second permanent magnet and a shell. The anode is arranged at the bottom of the discharge channel. The two permanent magnets are sequentially arranged between the outer sidewall of the discharge channel and the shell from the bottom of a discharge outlet. The magnetic conducting ring and the magnetic conducting ring heat conducting plate are arranged between the two permanent magnets. A gap is reserved between the two permanent magnets and the outer sidewall of the discharge channel. The plasma thruster further comprises a cold air thruster. The anode is of a hollow structure. The cold air thruster is arranged in an inner cavity of the anode. The cold air thruster can operate independently and is used for generating the micronewton-scale thrust. The discharge channel is a variable cross-section channel. The radium of the channel gradually decreases from the discharge outlet to the bottom. The longitudinal section of the sidewall of the discharge channel is a right trapezoid.

Description

technical field [0001] The invention relates to a cusp magnetic field plasma thruster, in particular to an anode-cold gas thruster combined with a gas supply cusp magnetic field plasma thruster, which belongs to the field of aerospace technology and low-temperature plasma. Background technique [0002] As a new type of space electric propulsion technology, cusped magnetic field plasma has the characteristics of high thrust density, simple system composition, high reliability, long life, easy integration and large-scale continuous adjustment of thrust. It is the future drag-free control satellite. One of the main thrusters. [0003] figure 1 It is a structural schematic diagram of a tangential magnetic field plasma thruster in the prior art, which includes a discharge channel 1, a magnetic conducting ring 2, a first permanent magnet 3, an anode 5, a magnetic conducting ring heat conducting sheet 6, a second permanent magnet 7 and The shell 8, the problem of the magnetic fie...

Claims

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Application Information

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IPC IPC(8): F03H1/00
CPCF03H1/0081
Inventor 刘辉蒋文嘉于达仁崔凯曹希峰曾明
Owner HARBIN INST OF TECH
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