Hall thruster with double magnetic screens

A technology of Hall thruster and magnetic shield, which is applied in the direction of thrust reverser, machine/engine, and utilization of plasma, and can solve the problems of electron-wall interaction, wall energy deposition, thermal instability energy, loss, etc., to avoid Discharge thermal instability, electronic current suppression, robustness and longevity assurance effects

Active Publication Date: 2020-06-02
HARBIN INST OF TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] In order to solve the problem of thermal instability and energy loss caused by the frequent interaction between electrons and the wall in the channel of the existing Hall thruster, the present invention provides a Hall thruster with double magnetic shields. The double ma...

Method used

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Embodiment approach

[0017] combined with Figure 1 to Figure 2 Illustrate the specific embodiment of the present invention: the Hall thruster of a kind of double magnetic screen of the present invention, as figure 1 As shown, it includes inner magnetic pole 1, inner excitation coil 2, inner magnetic shield 3, additional coil 4, bottom plate 5, ceramic channel 6, additional magnetic shield 7, gas distributor 8, fixing nut 9, ceramic gasket 10, anode 11 , the outer magnetic shield 12, the outer excitation coil 13 and the outer magnetic pole 14, the base plate 5 is a circular plate shape, the center of the circular plate shape is provided with a column, and four cylinders are evenly distributed on the circumference of the base plate 5; the ring-shaped The additional coil 4 is set on the bottom of the column of the base plate 5, the inner magnetic shield 3 is set on the column of the base plate 5 and is located above the additional coil 4, the inner excitation coil 2 is wound on the column of the bas...

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Abstract

The invention discloses a Hall thruster with double magnetic screens, and belongs to the technical field of Hall thrusters. The Hall thruster solves the problems that in an existing Hall thruster channel, due to the fact that electrons and the wall face interact frequently, energy deposition of the wall face is caused, and heat instability and energy loss are caused. According to the Hall thruster, an additional magnetic screen is additionally arranged on a traditional Hall thruster to form a double-magnetic-screen structure, the double magnetic screens are used for carrying out secondary short circuit on a magnetic field close to the wall face, and therefore magnetic lines of force are guided not to penetrate through the channel and an anode any more, the energy deposition problem of theelectrons on the wall face is reduced, and the electron current is controlled. The double magnetic screens are used for solving the energy deposition problem of the electrons in the channel on the wall face, and the problems of discharge heat instability of the thruster and performance loss caused by energy loss are avoided. Meanwhile, the electron current is restrained, and the current utilization rate is increased. In addition, the thickness of the additional magnetic screen and insulation between an inner magnetic screen and the anode are guaranteed, the robustness and the service life of the additional magnetic screen are guaranteed, and the Hall thruster can effectively work for a long time.

Description

technical field [0001] The invention relates to a Hall thruster with double magnetic screens, belonging to the technical field of Hall thrusters. Background technique [0002] With the continuous development of the aerospace industry, higher requirements are put forward for the life and performance of the Hall thruster. One of the important factors affecting the discharge life and performance of the Hall thruster is the energy deposition on the wall. The higher the energy deposition, the easier it is to transfer heat to the magnetic circuit, which will cause thermal instability and also mean greater energy loss. A factor that affects performance is the current utilization rate, which directly affects the discharge efficiency of the thruster. For the Hall thruster, the current utilization rate pursues higher ion current and lower electron current. The wall energy deposition is caused by the interaction between the plasma and the discharge channel, and the interaction between...

Claims

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Application Information

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IPC IPC(8): F03H1/00
CPCF03H1/0087
Inventor 丁永杰李鸿魏立秋于达仁
Owner HARBIN INST OF TECH
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