Solid-liquid rocket engine igniter and head wire-outgoing method thereof

A solid-liquid rocket and igniter technology, which is applied to rocket engine devices, machines/engines, mechanical equipment, etc., can solve the problems of small installation cable space for flight engines, troublesome wiring of igniter leads, and increased negative mass of engines, etc., to achieve The effect of avoiding wiring on the outer wall, reducing negative mass, and improving energy utilization

Active Publication Date: 2015-07-29
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In the flight engine, the electrical equipment is generally at the head of the engine, and the throat outlet method is adopted. The igniter is too long, the ignition reliability is reduced, and the negative mass of the engine is increas

Method used

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  • Solid-liquid rocket engine igniter and head wire-outgoing method thereof

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Embodiment Construction

[0030] Below in conjunction with accompanying drawing, the present invention will be further described

[0031] The solid-liquid rocket engine igniter of the present invention comprises an igniter threaded ring 1, an igniter box body 2, and an ignition powder 3, is used for ignition and starting of the solid-liquid rocket engine, and is fixedly installed on the injection panel 5 of the solid-liquid rocket engine. It is located between the injection panel 5 and the grain column 6 .

[0032] 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 the internal thread on the igniter threade...

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PUM

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Abstract

The invention discloses a solid-liquid rocket engine igniter and a head wire-outgoing method thereof, wherein the igniter comprises an igniter box body, an igniter thread ring, and an ignition powder. The igniter box body is threaded to the igniter thread ring, is sealed by a sealing ring, with an annular cavity for filling the ignition powder being formed therein. The head wire-outgoing method of the solid-liquid rocket engine igniter comprises the following steps: employing an igniter sealing head for being threaded to an igniter adaptation sleeve; and threading the igniter adaptation sleeve to an injection panel; inserting one end of an igniter lead wire into an ignition material of the ignition powder; leading out the lead wire from an ignition hole of the igniter box body; and leading the lead wire outside the engine through a wire hole of the igniter box body, an inner hole of the igniter adaptation sleeve, and the igniter sealing head. The solid-liquid rocket engine igniter has the advantage of reasonable in structure; and the head wire-outgoing method thereof has the advantages of greatly reducing the length of the igniter lead wire, avoiding the breakage of the igniter lead wire after the igniter is working, reducing the wiring difficulty of the igniter, and increasing the reliability of the igniter.

Description

technical field [0001] The invention relates to a rocket engine igniter, and proposes a brand-new outlet method for the lead wire of the solid-liquid rocket engine igniter, which is suitable for the ignition of the solid-liquid rocket engine, especially for high-altitude ignition of the solid-liquid rocket engine. 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 or to have an additional ignition system th...

Claims

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Application Information

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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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