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High-pressure intensity and mass-flow liquid oxygen kerosene engine plasma ignition device

A plasma and ignition device technology, which is applied in the directions of combustion ignition, incandescent ignition, combustion method, etc., can solve the problems of inability to integrate and low degree of automation of plasma igniters, achieve simple and reliable feedback adjustment circuit, and improve ignition reliability. and service life, the effect of small size

Active Publication Date: 2018-06-22
XIAN AEROSPACE PROPULSION INST
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, conventional plasma igniters cannot operate under high chamber pressure conditions, and the degree of integration and automation is not high. There are shortcomings and deficiencies in terms of onboard assembly, portability, and reliability.

Method used

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  • High-pressure intensity and mass-flow liquid oxygen kerosene engine plasma ignition device

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Embodiment Construction

[0036] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments.

[0037] combine figure 1 It can be seen that the present invention includes a gas bottle 1, a plasma torch 3, a drive module 6, a measurement and control module 7, and a battery 9; the gas bottle 1 has a volume of 3L, an operating pressure of 25MPa, and is equipped with a one-way filling valve 10. When the air pressure outside the filling valve is higher than the air pressure in the gas cylinder 1, the gas cylinder 1 can be inflated. The gas outlet of the gas cylinder 1 communicates with the gas inlet 32 ​​of the plasma torch 3 through the high-pressure solenoid valve and the gas supply pipeline 4. No power supply is required when the power is on and off, and the mass is 0.2kg; the gas supply pipeline 4 is a conventional high-pressure metal pipe with a diameter of 3 mm; the plasma torch 3 can work under a room pressure environment of 20 MPa, an...

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Abstract

The invention relates to non-hypergolic propellant rocket engine ignition devices, in particular to a high-pressure intensity and mass-flow liquid oxygen kerosene engine plasma ignition device. The high-pressure intensity and mass-flow liquid oxygen kerosene engine plasma ignition device comprises an air source, a plasma torch, a power module and a control unit. An outlet of the air source communicates with an air inlet of the plasma torch through a high-pressure electromagnet and an air supply pipeline. The control unit comprises a drive module and a measuring and controlling module. The output end of the drive module is connected with an electrical signal input end of the plasma torch through a cable and is used for providing electrical signals for driving the plasma torch. The measuringand controlling module is connected with the high-pressure electromagnetic valve, the drive module and the power module and used for controlling opening and closing of the high-pressure electromagnetic valve and the drive module according to an external control instruction and feeding back the temperature of the power module and output electrical signal parameters of the drive module. The power module is used for supplying power to the electromagnetic valve.

Description

technical field [0001] The invention relates to an ignition device for a non-spontaneous propellant rocket engine, in particular to a plasma ignition device for a liquid oxygen kerosene engine with high pressure and high flow rate. Background technique [0002] At present, the ignition devices of non-pyrophoric propellants are mostly electric squibs, igniters, and spark plugs. Electric squib and igniter ignition, poor safety, difficult to achieve multiple starts, ordinary spark plugs have low ignition energy and general ignition reliability. In order to achieve multiple starts of non-spontaneous propellant rocket engines and improve ignition reliability, plasma ignition technology is an effective way. However, conventional plasma igniters cannot operate under high chamber pressure conditions, and the degree of integration and automation is not high. There are shortcomings and deficiencies in terms of onboard assembly, portability, and reliability. Contents of the inventio...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23Q7/00F23Q7/22
CPCF23Q7/00F23Q7/22
Inventor 王飞王妍贾桂友狄江李斌郑军旗韩先伟
Owner XIAN AEROSPACE PROPULSION INST
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