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Ignition device for small solid rocket engine

A technology of solid rockets and ignition devices, which is applied in the direction of rocket motor devices, machines/engines, jet propulsion devices, etc., can solve problems such as poor safety performance and blockage of nozzles by solid ejecta, and achieve reduced packaging difficulty and ignition safety performance Good, the effect of reducing the difficulty of the process

Pending Publication Date: 2020-06-19
宁波天擎航天科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The invention provides an ignition device for a small solid rocket motor, which aims to solve the problem that the small solid rocket motor ignition device in the prior art is easy to generate solid ejection to block the nozzle and has poor safety performance when ignited

Method used

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  • Ignition device for small solid rocket engine
  • Ignition device for small solid rocket engine
  • Ignition device for small solid rocket engine

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Embodiment Construction

[0025] 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 embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.

[0026] The small solid rocket motor ignition device provided by the embodiment of the present invention uses the electric squib to ignite the ignition powder, and after the ignition powder is ignited, the propellant grain is ignited through the nozzle. When the small solid rocket motor ignition device is ignited, it can ignite and propel The small solid rocket motor igniter will not produce solid jets when it is ignited, so as to prevent the solid jets from clogging the nozzle of the engine, so that the ignition safety performance is good; and there is no need to pack the ignition powder inside the ...

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Abstract

The invention is suitable for the technical field of small solid rocket engines, and provides an ignition device for a small solid rocket engine. The ignition device comprises a shell, a top cover, anelectric detonator, ignition powder and a nozzle, wherein the shell is arranged in a propellant grain and provided with inner holes distributed in the length direction of the shell; the top cover isconnected with one end of the shell, and mounting holes communicating with the inner holes are formed in the top cover; the electric detonator is arranged in the mounting holes, and the ignition powder is arranged in the inner holes; and the nozzle is connected with the other end of the shell and is provided with spray holes communicating with the inner holes. According to the ignition device forthe small solid rocket engine, solid ejecta cannot be generated during ignition, so that the solid ejecta are prevented from blocking a spray pipe of the engine, and the ignition safety performance isgood.

Description

technical field [0001] The invention relates to the technical field of small solid rocket motors, in particular to an ignition device for small solid rocket motors. Background technique [0002] At present, the small solid rocket motor with the head fully loaded needs to be provided with an igniter for igniting the propellant grain, while the usual igniter uses a plastic cartridge wrapped with igniting powder. When the igniter is ignited, the igniter passes through the ignition point The gunpowder detonates the plastic cartridge to ignite the propellant grain, which powers the engine. [0003] In the prior art, when a small solid rocket motor is ignited, after the ignition powder of the igniter is ignited, solid ejecta will be produced after the plastic cartridge of the igniter is detonated, and when the solid ejecta is ejected from the nozzle of the engine It is easy to block the nozzle of the engine and cause an explosion, and the safety performance is poor. Contents of...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/95F02K9/32
CPCF02K9/95F02K9/32
Inventor 杨敬贤李海涛杨威王彬平李东张汉秀张海涛
Owner 宁波天擎航天科技有限公司