Supporting device and supporting method for solid rocket engine end face combustion grain

A solid rocket, end face combustion technology, applied in rocket engine devices, machines/engines, jet propulsion devices, etc., can solve the problems of grain sloshing, unsafe, uneven stress on grain surface ventilation, etc., to avoid cracking, improve Stress condition, unique high temperature resistance effect

Active Publication Date: 2020-04-10
西安航科等离子体科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] Aiming at the above problems in the prior art that the grain of the solid rocket motor is easy to sway in the combustion chamber, causing unsafe conditions, and the uneven ventilation on the surface of the grain produces stress, the present invention proposes a supporting device and a support for the solid rocket motor end combustion grain. method, can solve these two problems well, and its specific technical scheme and method are as follows:

Method used

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  • Supporting device and supporting method for solid rocket engine end face combustion grain
  • Supporting device and supporting method for solid rocket engine end face combustion grain

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0035] In this embodiment, the support device used for the solid rocket motor end combustion charge, the bottom support plate 1 and the side support plate 2 are EPDM plates, the inner surface of the side support plate 2 and the outer surface of the charge 3 There is a gap of 0.3mm between them, the cross section of the bottom support plate 1 is fan-shaped, and the thickness of the bottom support plate 1 is 1.3mm, and the supporting surface area of ​​the bottom support plate 1 is 1200mm 2 , the bonding strength of the bottom support plate 1 is 2MPa; the cross section of the side support plate 2 is rectangular, and the length, width and thickness of the side support plate 2 are 100mm, 60mm and 1.5mm respectively; the combustion chamber is cylindrical, and the combustion chamber The diameter of the indoor surface is Ф142.2mm, and the diameter of the outer surface of the grain column 3 is Ф139mm.

[0036] Using the supporting device of this embodiment for the solid rocket motor en...

Embodiment 2

[0041] The difference from Embodiment 1 is that in this embodiment, a gap of 0.2mm is left between the inner surface of the side support plate 2 and the outer surface of the charge 3 in the supporting device for the solid rocket motor end combustion charge. The length, width and thickness of the support plate 2 are 100mm, 60mm and 1.2mm respectively.

[0042] (1) Determine that the proportion of the gap between the combustion inner surface 4 and the outer surface of the grain 3 is 62%, that is Into the formula It is calculated that the number of side support plates 2 installed is 4; the number of bottom support plates 1 installed is 4; where n is the number of side support plates, b is the width of the side support plates, δ is the thickness of the side support plates, and D is The diameter of the inner surface of the combustion chamber, d is the diameter of the outer surface of the grain, is the proportion of the space between the inner surface of the combustion chamber ...

Embodiment 3

[0046] The difference from Embodiment 1 is that this embodiment is used as a supporting device for solid rocket motor end-face combustion charges, and there is a gap of 0.1 mm between the inner surface of the side support plate 2 and the outer wall of the charge 3 . All the other are identical with embodiment 1.

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Abstract

The invention provides a supporting device and a supporting method for a solid rocket engine end face combustion grain, and belongs to the technical field of solid rocket engine manufacturing. The supporting device specifically comprises a combustion chamber and the grain connected in the combustion chamber, and a supporting piece is arranged between the outer surface of the grain and the inner surface of the combustion chamber and comprises a bottom supporting plate and a side supporting plate, wherein the bottom supporting plate is arranged at the head of the grain, the side supporting plateis arranged on the outer side face of the grain, and the bottom supporting plate is not connected with the side supporting plate. By utilization of the supporting device for the solid rocket engine end face combustion grain, integrity of the grain and safety during solid rocket engine running can be guaranteed, meanwhile, the buffering and stress releasing functions are achieved for the grain surface, and the stress situation of the grain can be well improved.

Description

technical field [0001] The invention belongs to the technical field of solid rocket motor manufacturing, and in particular relates to a supporting device and a supporting method for solid rocket motor end-face combustion charges. Background technique [0002] The solid rocket motor is the power device of aerospace vehicles such as rockets and missiles. Its principle is to generate high-temperature gas through the combustion of solid propellants. After the high-temperature gas is ejected through the nozzle, it generates a reaction force to propel the rocket or missile. When the engine is working, its combustion chamber is always in a state of high temperature and high pressure. [0003] When the combustion chamber of the engine is always in a state of high temperature and high pressure, the surface of the grain will also be in a high temperature and high pressure gas environment. Therefore, the surface of the grain exposed to the gas environment will be subject to a large com...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/36
CPCF02K9/36
Inventor 马俊王浩静姚挺陈铭德樊黎君周倩倩黄微波
Owner 西安航科等离子体科技有限公司
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