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Vacuum arc propeller based on multi-anode structure

A multi-anode and thruster technology, which is applied in the direction of thrust reverser, machine/engine, and plasma utilization, can solve the problems of increasing the mass and volume of the thruster, unfavorable vacuum arc thruster application, increasing the mass and volume of the thruster, etc. , to improve propulsion performance, achieve long-gap vacuum breakdown, and reduce radial diffusion

Active Publication Date: 2019-03-29
BEIJING JIAOTONG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, the application of an external magnetic field will increase the mass and volume of the thruster, which is not conducive to the application of vacuum arc thrusters
[0005] Therefore, it is necessary to design a vacuum arc thruster, which can avoid the problem of increasing the mass and volume of the thruster caused by the introduction of a magnetic field while realizing the confinement of the plasma plume outside the thruster

Method used

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  • Vacuum arc propeller based on multi-anode structure
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  • Vacuum arc propeller based on multi-anode structure

Examples

Experimental program
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Effect test

Embodiment 1

[0058] An embodiment of the present invention provides a vacuum arc thruster based on a multi-anode structure, which improves the propulsion performance of the vacuum arc thruster through a unique anode structure setting and a vacuum gap breakdown discharge mechanism.

[0059] A vacuum arc thruster based on a multi-anode structure provided by an embodiment of the present invention adopts a vacuum gap breakdown discharge mechanism. The discharge mechanism is field-induced electron emission near the cathode caused by a strong electric field. The explosion, the generated plasma is generally called metal plasma, which is mainly composed of metal ions and electrons.

[0060] A schematic structural diagram of a vacuum arc thruster based on a multi-anode structure provided by an embodiment of the present invention is as follows figure 1 As shown, the vacuum arc thruster is a coaxial electrode structure, including: a cathode structure 1, a multi-anode structure (2, 3) and an insulatin...

Embodiment 2

[0089] This embodiment provides an experimental system of a vacuum arc thruster based on a multi-anode structure, and performs experimental verification of the vacuum arc thruster proposed by the present invention. The realization structure of the experimental system is as follows figure 2 As shown, the specific contents may include the following:

[0090] An application system of a vacuum arc thruster based on a multi-anode structure includes: a pulse power supply, a vacuum discharge device and a diagnosis system.

[0091] Pulse power supplies use energy storage capacitors as the energy source for discharge. Before discharging, the energy storage capacitor C is charged to a specific voltage. When the switch SG is closed, the voltage of the capacitor C starts to be applied to both ends of the electrodes through the current limiting resistor R1 and the inductor L. Therefore, a discharge occurs due to breakdown of the vacuum gap. The diode D connected in series with the circ...

Embodiment 3

[0116] This embodiment provides a vacuum arc thruster based on a multi-anode structure, and compares the influence of the distance between the cathode structure and the remote anode (abbreviated as D) on the discharge characteristics of the multi-anode electrode structure. The specific comparison results are as follows:

[0117] Under the same voltage, when D is 100mm, 80mm, 60mm, and 40mm respectively, according to the value of D and the time when the inter-electrode voltage drops to the arc voltage, the propagation velocity of the plasma can be calculated as: 6.38km / s, 6.24km / s, 6.22km / s, 6.02km / s.

[0118] According to the electric field simulation, when D is 100mm, 80mm, 60mm, and 40mm respectively, the initial positions of the cathode structure from the A area are: 25.64mm, 25.81mm, 23.48mm, and 18mm, respectively. Assuming that the velocity of the metal plasma remains constant during propagation, the durations of T1 are: 4.02 μs, 4.14 μs, 3.95 μs, and 2.96 μs, respective...

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Abstract

The embodiment of the invention provides a vacuum arc propeller based on a multi-anode structure. The vacuum arc propeller comprises a cathode structure, the multi-anode structure and an insulating part, wherein the cathode structure is externally connected with negative high pressure, and the multi-anode structure is grounded; the cathode structure is a tapered cylindrical structure and is used for generating metal plasma; the multi-anode structure comprises a first anode and a second anode; the first anode is in the shape of a spray nozzle, and is externally coated with an insulating medium;the second anode is annular, and is arranged on a position, which is spaced with the cathode structure by a preset distance; and a cone central axis of the first anode, a cone central axis of the second anode and a cone central axis of the cathode structure are superposed. The multi-anode structure can realize long-gap vacuum breakdown, so that vacuum metal arc is formed; and the insulating partis cylindrical, is coated outside the cathode structure, and is embedded into the first anode for insulating and mechanically fixing the cathode structure and the first anode. The vacuum arc propellerdisclosed by the invention can realize plasma radial diffusion, so that propelling performance of the vacuum arc propeller is improved.

Description

technical field [0001] The invention relates to the technical field of vacuum arc thrusters, in particular to a vacuum arc thruster based on a multi-anode structure. Background technique [0002] VAT (Vacuum arc thruster, vacuum arc thruster) has the characteristics of small mass, small volume, and simple structure, and is widely used in the technical field of micro-satellite thrusters. The rapid development of micro-satellite technology puts forward higher requirements in terms of propulsion; therefore, it is of great significance to optimize the propulsion effect of vacuum arc thrusters. [0003] The key factor determining the propulsion effect of a vacuum arc thruster is its plasma generation characteristics, which are largely affected by the electrode structure parameters. In 2015, some researchers studied the design of low-power vacuum arc thrusters with conical contraction, and found that changing the shape of the axial cross-section of the cathode will affect the dis...

Claims

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Application Information

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IPC IPC(8): F03H1/00
CPCF03H1/0087
Inventor 崔伟胜刘文正高永杰
Owner BEIJING JIAOTONG UNIV
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