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Ignition circuit for micro pulse plasma thruster

A technology of pulsed plasma and ignition circuit, applied in the direction of using plasma, thrust reverser, machine/engine, etc., can solve the problems of unadjustable charging voltage, poor anti-interference ability, complex ignition circuit, etc., and reduce the occurrence of false ignition. frequency, avoid the fluctuation of charging voltage, and reduce the frequency of leakage ignition

Active Publication Date: 2018-02-23
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

[0010] The invention aims at technical problems such as poor reliability of the ignition circuit, poor anti-interference ability, non-adjustable charging voltage, non-adjustable ignition energy and insufficient utilization, power consumption in the system during standby, relatively complicated ignition circuit, and inflexible ignition trigger mode. , designed an application with good reliability, strong anti-interference ability, adjustable charging voltage, adjustable ignition energy and full utilization, no power consumption in the standby system, simple ignition circuit, and relatively flexible ignition trigger mode. Ignition circuit for micro-pulse plasma thruster

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Embodiment Construction

[0031] In order to make the object, technical solution and advantages of the present invention clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and specific implementation methods. It should be understood that the specific embodiments described here are only used to explain the present invention, and do not limit the protection scope of the present invention.

[0032] It should be noted that when an element is referred to as being “fixed on”, “disposed on” or “installed on” another element, it may be directly on the other element or there may be an intervening element. When an element is considered to be "connected" to another element, it may be directly connected to the other element or there may be an intervening element at the same time; the specific way that one element is fixedly connected to another element can be realized through existing technologies, and will not be discussed here. To repeat it agai...

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Abstract

The invention provides an ignition circuit for a micro pulse plasma thruster. The ignition circuit comprises an ignition power supply unit, an ignition control unit, an ignition start unit, a voltageadjusting unit and a sparking plug. The ignition circuit has great reliability, strong anti-interference capacity, adjustable charging voltage and ignition energy and full utilization; electricity consumption is free when the system is at a standby state; and the ignition circuit is simple and an ignition triggering way is relatively flexible.

Description

technical field [0001] The invention relates to an ignition control circuit for a micro-pulse plasma thruster. Background technique [0002] At present, the rapid development of satellite systems along the network and miniaturization makes it necessary to develop micro-electric thrusters that can meet the high-precision attitude control requirements of micro-nano satellites, and have the characteristics of light weight, small size, and low power consumption. Micro-Pulsed Plasma Thruster (μPPT) is a kind of pulsed plasma thruster (Pulsed Plasma Thruster, PPT). Usually, the PPT whose system mass is less than 1kg is called μPPT. Its mass, volume and work The average consumption is at least an order of magnitude lower than that of PPT. In addition to the advantages of traditional PPT, such as high thrust density, high specific impulse, small and precise thrust, high control precision, simple structure, and high reliability, μPPT also has the advantages of low power consumption,...

Claims

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Application Information

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IPC IPC(8): F03H1/00
CPCF03H1/0006F03H1/0087
Inventor 何兆福吴建军何振程玉强黄强张宇李健欧阳
Owner NAT UNIV OF DEFENSE TECH
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