A Hall thruster with lightweight integrated anode

Abstract

The invention discloses a Hall thruster adopting a lightweight integrated anode. The Hall thruster comprises a bottom plate, wherein an inner magnetic core wound with an inner magnetic coil is configured at the centre of the bottom plate; a plurality of outer magnetic cores wound with outer magnetic coils are configured at the periphery of the bottom plate; the lightweight integrated anode is arranged between the inner magnetic core and the outer magnetic cores; a protective cover is arranged outside the anode; and the protective cover and the anode are insulated and supported by ceramic. An inner ceramic ring and an outer ceramic ring are arranged at the outlet of the lightweight integrated anode, and the inner ceramic ring and the outer ceramic ring are compacted by the outer edge of the inner magnetic core and a front panel separately; and all the parts are installed on the bottom plate, and an insulation sleeve sleeves the gas pipe of the lightweight integrated anode. According to the Hall thruster disclosed by the invention, an integrated anode structure is adopted, and the flowing and distribution characteristics of a gas are improved, so that the thruster is better in ionization effect, better in performance, lower in thermal load, higher in the capacity of resisting to severe mechanical environments, more compact in structure, smaller in size, and lighter in weight.

Description

technical field [0001] The invention relates to a Hall thruster, in particular to a Hall thruster using a lightweight integrated anode. Background technique [0002] Hall thrusters have been widely used in various spacecraft such as satellites and deep space probes. Although the traditional Hall thruster has the advantages of high thrust density, high thrust power ratio and high reliability, it also has a series of problems: [0003] (1) Performance advantages such as specific impulse and efficiency are not obvious; [0004] (2) The volume and weight have reached the limit according to the design idea of ​​the traditional Hall thruster, and there is no room for further optimization; [0005] (3) The ceramic discharge chamber with a large surface-to-volume ratio is used, and the mechanical strength is not high. Therefore, when it is applied to a spacecraft with strict mechanical environment requirements, vibration reduction measures must be considered, thereby increasing th...

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Problems solved by technology

[0003] (1) Performance advantages such as specific impulse and efficiency are not obvious;

[0004] (2) The volume and weight have reached the limit according to the design idea of ​​the traditional Hall thruster, and there is no room for further optimization;

[0005] (3) The ceramic discharge chamber with a large surface-to-volume ratio is used, and its mechanical strength is not high. Therefore, when it is applied to a spacecraft that has strict requirements on the mechanical environment, vibration reduction measures must be considered, thereby increasing the complexity of star installation and affecting the installation and positioning. precision;

[0006] (4) When the thruster is working, it passively dissipates heat, and the heat generation and dissipation depend on the natural balance, which makes it take a long time for the thruster to reach thermal equilibrium (steady state operation), usually about several hours;

[0007] (5) The traditional anode structure of its configuration is still lacking in gas uniformity and buffer characteristics, and should be further optimized and improved

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