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A Wire Burst Enhanced Microcapillary Pulsed Plasma Thruster

A technology of pulsed plasma and microcapillary, which is applied in the direction of using plasma, thrust reverser, machine/engine, etc., can solve the problems of complicated external trigger system, limit the life of spark plug, and small output element impulse, so as to expand the output range , Reduce the volume of the device and enhance the effect of the output element impulse

Active Publication Date: 2021-06-04
XI AN JIAOTONG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0003] Existing micro-pulse plasma thrusters usually require semiconductor spark plugs to be triggered by surface discharge, and the external trigger system is complicated, and problems such as carbon deposition will limit the life of the spark plug, thereby affecting the short life of the system; in addition, the existing pulse plasma propulsion technology has output The unit impulse is small, the range is narrow, the total impulse is low and the efficiency is low, etc.

Method used

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  • A Wire Burst Enhanced Microcapillary Pulsed Plasma Thruster

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Embodiment Construction

[0024] The present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0025] Please refer to figure 1 , the wire burst enhanced microcapillary pulsed plasma thruster includes:

[0026] anode nozzle 1;

[0027] A capillary cavity 2, the capillary cavity 2 is installed on one side of the anode nozzle 1;

[0028] a trigger electrode 3, the trigger electrode 3 is arranged on the capillary cavity 2;

[0029] A cathode base 4, the cathode base 4 is installed on the side of the capillary cavity 2 away from the anode nozzle 1, and a central hole is opened in the center of the cathode base 4;

[0030] A metal wire 7 , one end of the metal wire 7 passes through the middle hole and extends into the capillary cavity 2 .

[0031] Both ends of the capillary cavity 2 are provided with internal threads, and the anode nozzle 1 and the cathode base 4 are provided with external threads. The anode nozzle 1, the capillary cavity 2 and the...

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Abstract

The invention provides a metal wire explosion-enhanced microcapillary pulse plasma thruster. The wire explosion-enhanced microcapillary pulsed plasma thruster includes an anode nozzle; a capillary cavity, the capillary cavity is installed on one side of the anode nozzle; a trigger electrode, the trigger electrode is arranged in the capillary cavity On the body; the cathode base, the cathode base is installed on the side of the capillary cavity away from the anode nozzle, and the center of the cathode base is provided with a middle hole; the metal wire, one end of the metal wire through the mesopore and extend into the capillary lumen. The metal wire explosion-enhanced microcapillary pulse plasma thruster provided by the invention has the advantages of small size and wide range of output element impulse.

Description

technical field [0001] The invention relates to the technical field of micro electric thrusters, in particular to a metal wire explosion-enhanced microcapillary pulse plasma thruster. Background technique [0002] The pulsed plasma thruster is based on the discharge of the spark plug to generate plasma, which causes the discharge of the main energy storage capacitor to form an arc to ablate the surface of the propellant, and the vaporized and decomposed propellant is ejected under the action of electromagnetic force and aerodynamic force to generate thrust pulses plasma device. Pulsed plasma thrusters are mainly used for micro-nano-satellite rotation elimination, orbit positioning (orbit insertion), long-term on-orbit (orbit maintenance), orbit and position adjustment, attitude control, formation flight, and orbit unloading. With the continuous development of aerospace technology, electric propulsion technology has increasingly become one of the symbols to measure the advan...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F03H1/00
CPCF03H1/0087
Inventor 王亚楠韩若愚任林渊丁卫东
Owner XI AN JIAOTONG UNIV
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