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

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...

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 generate thrust less than 100 micronewtons, and provides an anode-cold air thruster combined with gas supply cusp magnetic field plasma thruster

Images