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Pulsed plasma thruster based on electrothermal-electromagnetic hybrid accelerating

A pulsed plasma and electromagnetic mixing technology, applied in the field of plasma, can solve the problems of low utilization rate of working medium, low specific impulse parameters of thrusters, inability to satisfy thrusters at the same time, etc., achieving less moving parts, small size, and improved energy The effect of utilization efficiency

Active Publication Date: 2017-08-18
XI AN JIAOTONG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, under the electrothermal acceleration mechanism, the specific impulse parameters of the thruster are low, and the utilization rate of the working medium is low, which cannot meet the requirements of the micro satellite for the high specific impulse and high efficiency output parameters of the thruster.

Method used

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  • Pulsed plasma thruster based on electrothermal-electromagnetic hybrid accelerating
  • Pulsed plasma thruster based on electrothermal-electromagnetic hybrid accelerating

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Embodiment Construction

[0020] In one embodiment, combined with figure 1 , figure 2 , the disclosure discloses a pulsed plasma thruster based on electrothermal electromagnetic hybrid acceleration,

[0021] The thruster includes: a power processing unit, a trigger, a trigger circuit, a main discharge circuit, a capillary discharge cavity, a coaxial accelerating electrode and a semiconductor spark plug; the power processing unit supplies power to the main discharge circuit;

[0022] The main discharge circuit is used to apply a high voltage between the anode and the cathode of the thruster before the thruster is ignited, so that the radial and axial electric fields are distributed inside the capillary discharge cavity;

[0023] The trigger circuit outputs high-voltage pulses to the trigger;

[0024] Under the action of the pulse high voltage output by the trigger circuit, the trigger generates surface flashover and releases initially charged particles, and the initially charged particles enter the c...

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Abstract

The invention relates to a pulsed plasma thruster based on electrothermal-electromagnetic hybrid accelerating. The pulsed plasma thruster based on electrothermal-electromagnetic hybrid accelerating comprises a power processing unit, a micro pulse forming network, a trigger, a trigger circuit, a main discharge circuit, a capillary discharge cavity, a cathode nozzle, an anode base, a rodlike anode and a backflow shell. Owing to the ingenious structural design, the pulsed plasma thruster can achieve electrothermal and electromagnetic accelerating effects simultaneously, and can play a good accelerating effect on neutral elements and charged elements produced by ablation. In a small energy state, the problem of low thruster efficiency can be improved significantly, and the pulsed plasma thruster is suitable for low power micro satellite applications.

Description

technical field [0001] The disclosure belongs to the field of discharge plasma, in particular to a pulse plasma thruster based on electrothermal electromagnetic hybrid acceleration. Background technique [0002] Microsatellites have the advantages of low cost, short development cycle, strong expansion capability, and flexible launch methods, and can be networked to complete the functions of a single large space vehicle, which can greatly reduce costs and risks. [0003] Most of the microsatellites launched in the early stage do not have propulsion modules due to technical difficulties and lack of relevant mission requirements. months to a year or so. However, with the demand for longer life of micro-satellites or more complex tasks (networking, precise observation, scientific experiments, etc.), the requirements for the life of micro-satellites in orbit are 3-5 years. Therefore, a higher total impulse requirement is put forward for the propulsion module carried by the micr...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F03H1/00
CPCF03H1/0006F03H1/0087
Inventor 丁卫东王亚楠程乐闫家启李志闯申赛康
Owner XI AN JIAOTONG UNIV
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