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Hybrid rocket engine igniter

A solid-liquid rocket, igniter technology, applied in rocket engine devices, machines/engines, mechanical equipment, etc., can solve problems such as explosion and rapid engine start, and achieve the goal of improving reliability, improving energy utilization, and reducing heat loss. Effect

Active Publication Date: 2015-07-22
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the decomposition of hydrogen peroxide generates a lot of heat, which may cause an explosion if the temperature is too high
However, hydrogen peroxide does not have enough energy to self-decompose to start the engine quickly

Method used

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  • Hybrid rocket engine igniter
  • Hybrid rocket engine igniter

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Embodiment Construction

[0022] The present invention will be further described below in conjunction with the accompanying drawings.

[0023] The solid-liquid rocket engine igniter of the present invention comprises an igniter threaded ring 1, an igniter box body 2, an igniter 3, and an igniter heat insulation layer 4, which is used for ignition and starting of a solid-liquid rocket engine, and is fixedly mounted on the solid-liquid rocket engine nozzle. On the injection panel 7, it is located between the injection panel 7 and the powder column 8.

[0024] Wherein, the threaded ring 1 of the igniter is an annular structure with an internal thread; the igniter box 2 is an annular structure with an external thread, and an annular groove is opened along the circumference of the outer wall of the igniter box 2 . The igniter box body 2 is nested with the igniter threaded ring 1, is located in the igniter threaded ring 1, and is threadedly connected with the external thread on the igniter box body 2 through...

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PUM

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Abstract

The invention discloses a hybrid rocket engine igniter which comprises an igniter thread ring, an igniter box body, an igniter heat insulation layer and ignition powder. The igniter thread ring is connected with the igniter box body through a large thread, and therefore a cavity structure with inner and outer annular side walls is formed. The containing cavity is filled with the ignition powder which is composed of ignition materials and fuel. The igniter thread ring, the igniter box body and the igniter heat insulation layer are adhesively connected. The inner wall face of the igniter box body and the inner wall face of the igniter heat insulation layer are provided with fire outlet holes. A sealing belt is laid on the inner annular side wall of the igniter box body. It is ensured that the ignition powder is reliably sealed before the igniter works. One end of an igniter lead is provided with an ignition head which produces electric sparks after being powered on, and the other end of the igniter lead is provided with an electric wire. The igniter starts to work after the igniter lead is powered on. The hybrid rocket engine igniter has the advantages that the start energy is high, the energy is released rapidly, the engine ignition delay is short, and the ignition delay time of the improved igniter is shorter than 1s when a large-flow hybrid rocket engine starts.

Description

technical field [0001] The invention belongs to the field of ignition and starting of rocket engines, and specifically relates to an igniter for solid-liquid rocket engines, which is suitable for single ignition of solid-liquid rocket engines, especially for high-altitude ignition and long-time work of solid-liquid rocket engines Solid-liquid rocket motor. Background technique [0002] The solid-liquid rocket motor adopts liquid oxidant and solid fuel, and has the common characteristics of both liquid rocket motor and solid rocket motor in structure. It has good safety, easy thrust adjustment, good environmental protection, good grain stability and low temperature sensitivity. It can be used for sounding rockets, target bombs, tactical missiles, etc. [0003] Igniter technology is one of the key technologies of rocket engines. Liquid rocket engines usually require multiple starts. In addition to self-ignition ignition, the common way is to use multiple pyrotechnic igniters...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/95
Inventor 田辉王鹏飞孙兴亮赵博张源俊
Owner BEIHANG UNIV
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