Projectile shell separation structure

A technology for separating structures and rocket shells, which is applied in the field of spacecraft structures, can solve problems such as large separation and separation distances, easy interference problems, and complex separation structures, so as to reduce separation links, prevent interference between structures, and simple separation structures Effect

Active Publication Date: 2014-02-19
BEIJING INST OF ASTRONAUTICAL SYST ENG
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  • Summary
  • Abstract
  • Description
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AI Technical Summary

Problems solved by technology

This separation method has disadvantages such as relatively complicated separation sequence, relatively complicated separation structure, large separation distance, and prone to interference problems.

Method used

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  • Projectile shell separation structure
  • Projectile shell separation structure
  • Projectile shell separation structure

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Embodiment Construction

[0019] The present invention will be further described below in conjunction with accompanying drawing.

[0020] The separation structure of the rocket shell of the present invention is an annular closed structure, such as figure 2 Shown is a partial cross-sectional schematic view of the cutting and separating structure of the present invention. The separation structure of the missile case includes: a separation case 1 , a circumferential shield 2 , an axial shield 3 , a T-shaped shield 4 , a flexible detonating cord assembly 5 and a T-shaped explosion transfer assembly 6 . At the predetermined separation place outside the circumference of the separation shell 1, there are respectively circumferential preset weakening grooves 7, axial preset weakening grooves 8 and T-shaped prefabricated weakening grooves 9, as attached image 3 shown.

[0021] On the upper and lower end faces of the separation case 1 , the flexible detonating cord assembly 5 is installed in the position cor...

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Abstract

The invention discloses a structure for shell separation between missiles and rocket stages, comprising a separation shell (1), a circumferential shield (2), an axial shield (3), and a T-shaped shield (4) , the flexible detonating cord assembly (5) and the T-shaped detonating assembly (6); the circumferential shield (2), the axial shield (3) and the T-shaped shield (4) respectively connect the corresponding detonating cord assembly It is fixed on the inner side of the separation shell (1) to form a continuous and interlinked flexible detonating cord cutting structure in the circumferential and axial directions. The invention arranges flexible detonating cord components in the circumferential and axial ways of the separation shell, and connects them through the T-shaped detonation transmission component, which can combine the two operations of flame exhaust and interstage separation, and cut the cutting shell instantly at the same time The number of petals makes the separation sequence simple, reduces the separation links, and has a simple and reliable structure.

Description

technical field [0001] The invention belongs to the technical field of spacecraft structures, in particular to a structure for shell separation between missiles and rocket stages. Background technique [0002] The shell of the missile refers to the visible external structure of the missile or rocket. It is the main part of the missile body to bear the force and maintain the external contour. The shell is equipped with various components and its brackets. It is generally in the shape of a hollow cylinder or a round table . After the projectile is launched, it is necessary to separate the segments that have completed the task by cutting. Generally, there are two kinds of separation devices: point type and linear type. Compared with the point type separation device, the linear separation device has the advantages of fewer components, simple structure and high reliability. [0003] The separation work before and after the operation of the current rocket two-stage engine includ...

Claims

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Application Information

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IPC IPC(8): F42B15/36
Inventor 孙璟朱长军张晓晖范新中苏晗宋保永卢红立王建忠
Owner BEIJING INST OF ASTRONAUTICAL SYST ENG
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