A lightweight, high-power, particle-rich propellant ignition device

An ignition device, high-power technology, applied in rocket engine devices, jet propulsion devices, machines/engines, etc., can solve the problems of high cost, poor ignition ability, complex design and production, and achieve weight reduction, increase effectiveness and The effect of improving reliability and quality ratio

Active Publication Date: 2022-05-10
XIAN AEROSPACE PROPULSION INST +1
View PDF0 Cites 0 Cited by
  • 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

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • A lightweight, high-power, particle-rich propellant ignition device
  • A lightweight, high-power, particle-rich propellant 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...

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to view more

PUM

No PUM Login to view more

Abstract

The invention discloses a light-weight, high-power, and particle-rich propellant ignition device, which solves the problems of high development and test costs of the existing ignition device, long development period, and easy damage to the thrust chamber caused by the remains of the ignition device after ignition. The ignition device mainly includes an ignition head, an initial charge, a main charge, a shell, a nozzle and a sealing diaphragm. After the ignition head of the ignition device is energized and detonated, the initial charge is ignited, and then the main charge is ignited. The high-temperature gas generated breaks through the sealing diaphragm through the nozzle to produce a continuous and stable flame output rich in hot particles, thereby realizing the engine. Ignition of thrust chamber propellant.

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

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to view more

Application Information

Patent Timeline
no application Login to view more
Patent Type & Authority Patents(China)
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
Who we serve
  • R&D Engineer
  • R&D Manager
  • IP Professional
Why Eureka
  • Industry Leading Data Capabilities
  • Powerful AI technology
  • Patent DNA Extraction
Social media
Try Eureka
PatSnap group products

Browse by: Latest US Patents, China's latest patents, Technical Efficacy Thesaurus, Application Domain, Technology Topic.

© 2024 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap