Retention-type rear cover separation device capable of braking and buffering based on large-impulse collision

A separation device and tail cover technology, which can be used in projectiles, self-propelled bombs, offensive equipment, etc., can solve the problems of complicated separation devices, and achieve the effects of increasing separation reliability, improving buffer efficiency, and improving safety.

Active Publication Date: 2018-03-20
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

These two tail cover separation schemes are to separate the tail cover after the missile body is released from the cylinder. The separation device is complicated. However, the tail cover separation

Method used

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  • Retention-type rear cover separation device capable of braking and buffering based on large-impulse collision
  • Retention-type rear cover separation device capable of braking and buffering based on large-impulse collision
  • Retention-type rear cover separation device capable of braking and buffering based on large-impulse collision

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Embodiment Construction

[0024] The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0025] The present invention provides a stagnation type tail cover separation device based on large impulse collision brake buffer, see attached figure 1 , including: accommodating shell 4, metal shear piece group 5, positioning block 6, force transmission seat 7, positioning pin 8 and limit post 9;

[0026] The overall connection relationship is as follows: see attached figure 2 , the tail cover 2 is installed on the outer circumferential surface of the missile body 1 by the positioning pin 8; the missile body 1 and the tail cover 2 are all installed in the launch tube 3; strip through hole;

[0027] The force transmission seat 7 is a T-shaped structure, and the lower surface of its horizontal part is fitted on the outer circumference of the launch tube 3, and its vertical part passes through the bar-shaped through hole of the launch tube 3 and connect...

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PUM

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Abstract

The invention discloses a retention-type rear cover separation device capable of braking and buffering based on large-impulse collision and belongs to the technical field of missile fire. The retention-type rear cover separation device comprises an accommodating housing, a metal shearing piece group, a positioning block, a force transfer seat and limited posts, wherein a rear cover is mounted on the outer circumferential surface of a missile body; the missile body and the rear cover are mounted in a launch canister; a vertical part on one side of the force transfer seat is opposite to the rearcover, and a horizontal part on the other side of the force transfer seat is opposite to long metal sheets of the metal shearing piece group; the positioning block is mounted on the upper surface ofthe horizontal part of the force transfer seat; one ends of two or more limited posts are mounted in the positioning block, and the other ends of the two or more limited posts penetrate through holesof the metal shearing piece group; and the accommodating housing is a housing with two side surface openings and an end surface opening, and is fixedly connected with the launch canister after being mounted on the positioning block and the metal shearing piece group in a buckling manner. The retention-type rear cover separation device is simple in principle and compact in structure, and can quickly, safely and reliably separate the missile body from the rear cover.

Description

technical field [0001] The invention belongs to the technical field of missile launching, and in particular relates to a retention-type tail cover separation device based on large-impulse collision braking and buffering. Background technique [0002] The missile body is ejected by the high-temperature and high-pressure gas generated by the ejection power device at the bottom of the launch tube. In order to prevent the high-temperature and high-pressure gas from causing harm to the engine and electromechanical equipment at the tail end of the missile during ejection, the tail cover is usually used to protect and bear the force of the missile body. effect. When the missile body is out of the cylinder, the tail cover must be separated in time to make the engine ignite. [0003] At present, there are mainly two tail cover separation schemes: 1) Separate side push method: first, the explosion bolt is unlocked, and the tail cover is separated from the tail end of the missile body...

Claims

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Application Information

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IPC IPC(8): F42B15/36
CPCF42B15/36
Inventor 黄美姜毅
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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