Radiation heat dissipation device for multistage cusped magnetic field plasma thruster

Abstract

The invention relates to a radiation heat dissipation device, in particular to a radiation heat dissipation device for a multistage cusped magnetic field plasma thruster. The radiation heat dissipation device for the multistage cusped magnetic field plasma thruster aims to solve the problems that due to the high anode temperature of the multistage cusped magnetic field plasma thruster, the high temperature of an outlet and the high temperature of the magnetic separatrix caused by particle collisions on the ceramic inner wall, heating carried out on the channel inner wall and the anode of the thruster is sharply enhanced within a short period, magnetism of a permanent magnet is seriously affected by heat conduction, and the thruster is poor in operation stability and reliability and short in service life. The radiation heat dissipation device for the multistage cusped magnetic field plasma thruster comprises a heat dissipation cylinder, a heat dissipation plate, two heat dissipation conical cylinders and two heat dissipaters, wherein a thruster shell is arranged between the two heat dissipation conical cylinders, the upper portion and the lower portion of the thruster shell are sleeved with the two heat dissipaters respectively, the heat dissipation plate is installed on the thruster shell in a sleeved mode and located between the two hear dissipaters, and the closed end of the heat dissipation cylinder is fixedly connected with the thruster shell. The radiation heat dissipation device is used for the multistage cusped magnetic field plasma thruster.

Description

technical field [0001] The invention relates to a radiation heat dissipation device, in particular to a radiation heat dissipation device for a multi-stage cusp magnetic field plasma thruster. Background technique [0002] The multi-stage cusp magnetic field plasma thruster is a new type of electric propulsion concept emerging in the world. The interior of the thruster is surrounded by multi-stage permanent magnets. The ceramic channel is surrounded by two adjacent permanent magnets with opposite polarities. Under the action of the cathode, the electrons released by the cathode are bound to move in a helical line along the magnetic force line and conduct to the anode through collision to form a discharge circuit. The ions produced by the ionized xenon atoms of the electrons are accelerated and ejected under the action of the axial electric field to generate thrust. . Compared with other electric propulsion devices, the tangential magnetic field plasma thruster has the advan...

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Problems solved by technology

[0004] The present invention is to solve the problem that the anode temperature of the multi-stage tangential magnetic field plasma thruster is relatively high, and the high temperature at the outlet and the high temperature at the magnetic interface caused by the collision of the ceramic inner wall cause short heating of the inner wall of the thruster channel and the anode. The time increases sharply, and these heat conductions have seriously affected the magnetism of the permanent magnet, as well as the problems of poor working stability and reliability of the thruster and short service life, and then provide a radiation cooling device for a multi-stage tangential magnetic field plasma thruster

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