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Light, high-power and particle-rich gunpowder ignition device

An ignition device and high-power technology, applied in the direction of rocket engine devices, jet propulsion devices, machines/engines, etc., can solve the problems of poor ignition capability, high cost, complicated design and production, etc., to increase effectiveness and reliability, Effects of weight reduction and mass ratio improvement

Active Publication Date: 2021-05-28
XIAN AEROSPACE PROPULSION INST +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] Among them, the existing spontaneous combustion liquid ignition device and torch ignition device all have the problems of complicated design and manufacture and high cost
[0006] However, due to the large mass of the existing solid powder ignition device, and the lack of ignition particles contained in it, the ignition ability is poor. After ignition, the shell of the ignition device will fall off and damage the thrust chamber. At the same time, its structure is relatively complicated, and the cost of development and testing is relatively high.

Method used

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  • Light, high-power and particle-rich gunpowder ignition device
  • Light, high-power and particle-rich gunpowder ignition device

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0037] figure 1 A structure of an ignition device is disclosed, including an ignition head 3 (including an ignition lead 8), an initial charge 4, a main charge 6, a casing, a nozzle 2 and a sealing diaphragm 1;

[0038] One end of the shell is an ignition port, and a sealing diaphragm 1 is installed at the ignition port;

[0039] A nozzle 2, an initial charge 4 and a main charge 6 are sequentially arranged in the shell from the ignition port inward;

[0040] The ignition head 3 is arranged inside the starting charge 4, and its ignition lead wire 8 is drawn out of the shell;

[0041] The nozzle pipe 2 is provided with a nozzle hole 9 along the center; the diameter of the nozzle hole 9 gradually increases from the ignition port to the inside. The method in this embodiment is to form a straight hole near the nozzle hole of the sealing diaphragm, and the nozzle hole near the initial charge is trumpet-shaped, and the largest end of the trumpet shape is close to the described prim...

Embodiment 2

[0050] figure 2 The structure of another ignition device is disclosed, including an ignition head 3 (including an ignition lead 8), an initial charge 4, a main charge 6, a shell, a nozzle 2 and a sealing diaphragm 1;

[0051] One end of the shell is an ignition port, and a sealing diaphragm 1 is installed at the ignition port;

[0052] A nozzle 2, an initial charge 4 and a main charge 6 are sequentially arranged in the shell from the ignition port inward;

[0053] The ignition head 3 is arranged inside the starting charge 4, and its ignition lead wire 8 is drawn out of the shell;

[0054] The nozzle pipe 2 is provided with a nozzle hole 9 along the center; the diameter of the nozzle hole 9 gradually increases from the ignition port to the inside. The method in this embodiment is to form a straight hole near the nozzle hole of the sealing diaphragm, and the nozzle hole near the initial charge is trumpet-shaped, and the largest end of the trumpet shape is close to the initial...

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Abstract

The invention discloses a light, high-power and particle-rich gunpowder ignition device, and solves the problems that an existing ignition device is high in development and test cost and long in development period, and a thrust chamber is prone to being damaged by remains of the ignition device after ignition. The ignition device mainly comprises an ignition head, a starting charge, a main charge, a shell, a spray pipe, a sealing membrane and the like. After the ignition head of the ignition device is powered on and detonated, the starting charge is ignited, then the main charge is ignited, generated high-temperature fuel gas breaks through the sealing diaphragm through the spray pipe, continuous and stable flame output rich in hot particles is generated, and therefore ignition of propellant in a thrust chamber of an engine is achieved.

Description

technical field [0001] The invention relates to a propellant ignition device for a non-spontaneous combustion bicomponent propellant rocket engine, especially a propellant ignition device based on light weight, high power and rich particles, which can be used for non-spontaneous combustion bicomponent propellant Agent rocket engine ignition technology field. Background technique [0002] As a non-toxic and non-polluting propellant combination for launch vehicles, liquid oxygen kerosene has the characteristics of high specific impulse performance, low cost, and convenient use and maintenance, and has been widely used in the new generation of launch vehicles. The liquid oxygen kerosene bicomponent propellant is a non-spontaneous propellant, which needs to provide an initial ignition heat source to make it ignite and burn, and then rely on the heat released by its own combustion to maintain the combustion process of the propellant. [0003] Liquid rocket motors using non-pyrop...

Claims

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Application Information

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IPC IPC(8): F02K9/95F02K9/08
CPCF02K9/95F02K9/08
Inventor 李应强刘上杨安民王元和高凤川张建刚刘铭李永锋常鹏高耸松
Owner XIAN AEROSPACE PROPULSION INST
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