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Redundant electric explosion valve

An electric explosion valve and redundant technology, applied in the aerospace field, can solve problems such as unproposed solutions, and achieve the effect of improving the reliability of the action

Inactive Publication Date: 2018-06-15
BEIJING INST OF ASTRONAUTICAL SYST ENG +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] In view of the above-mentioned problem of improving the reliability of the electric explosion valve action and realizing the internal discharge of explosive gas, no effective solution has been proposed so far.

Method used

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  • Redundant electric explosion valve
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  • Redundant electric explosion valve

Examples

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Effect test

Embodiment 1

[0025] Such as figure 1 As shown, one of the valve body structures of the redundant electric explosion valve in this embodiment mainly includes: an igniter 1, a housing 2, a cutter 3, a breaking piece 4, a baffle plate 5, an adapter nozzle 6, and a piston assembly 7, Wherein the piston assembly 7 includes retaining ring 8, O-ring 9, nut 10, cup 11, piston rod 12; igniter 1, baffle plate 5, nut 10, cup 11, retaining ring 8, O-ring 9, cutting Knife 3 is arranged on the same end of housing 2 successively according to the order from outside to inside, and housing 2 is provided with the housing taper that forms interference fit with cutter 3 inside, when cutter 3 and described housing taper When fitting, the base of the cutter 3, that is, the end of the cutter 3 close to the piston assembly 7 forms a sealed cavity structure together with the igniter 1 and the housing 2. When the igniter 1 detonates, the detonation gas passes through the baffle 5 A hole is provided into the sealed ...

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Abstract

The invention discloses a redundant electric explosion valve. The redundant electric explosion valve comprises a shell (2), and a through connection nozzle (6) is arranged on the shell (2), wherein one end of the through connection nozzle (6) positioned in the shell (2) is sealed by a cutting element (4), and two identical electric explosion valve structures are arranged in the shell. According tothe redundant electric explosion valve, a dual-gas-path structure of a double-electric-explosion tube is adopted, so that the redundancy in the true sense is realized, then the operation reliabilityof the electric explosion valve in the flying process is improved, so that the technical effects of reducing the number of products on the rocket and installing structure are reduced; in addition, theelectric explosion valve is of an explosive substance internal-discharge structure, so that the technical effect of solving the problem that an explosive product contaminates other components in an arrow after explosion of an existing electric explosion valve is solved, and the technical purposes that the reliability of action of the electric explosion valve is improved, and explosion gas is discharged inside the valve body are realized.

Description

technical field [0001] The present application relates to the field of aerospace technology, in particular to a redundant electric explosion valve. Background technique [0002] Electric detonation valve (including igniter) is an important stand-alone unit of the pressurized conveying system of the launch vehicle, which is used to supplement the pressure of the storage tank. Before the igniter works, the electric explosion valve seals the high-pressure gas in the gas cylinder. When the igniter detonates according to the system timing according to the electrical signal during the flight, the valve opens to connect the upstream and downstream, and the high-pressure gas in the gas cylinder realizes the discharge of the storage tank. Make up pressure. [0003] As a one-time product, the electric detonation valve should be detonated normally in time sequence during the rocket flight, and its detonation process cannot be verified by the ground test, which is an untestable item, s...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F16K17/40F16K31/122F16K31/02
CPCF16K17/403F16K31/02F16K31/122
Inventor 李娟娟王细波崔景芝曹荣刘春姐孙海鹏王剑中黄哲黄栩余武江王堃
Owner BEIJING INST OF ASTRONAUTICAL SYST ENG
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