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Solid rocket engine combustion chamber shell adiabatic layer forming method

A technology of solid rockets and molding methods, which is applied to household components, household appliances, and other household appliances. It can solve the problems of raw film patch distortion and unsmooth exhaust, achieve uniform thickness, improve consistency, and heat-insulate the production process. Optimized effect

Active Publication Date: 2019-04-12
HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In order to solve the problems existing in the prior art, the present invention provides a method for forming the heat insulation layer of the solid rocket motor combustion chamber shell, which utilizes the inner support tension of the heat insulation layer prefabricated part itself and the good isolation gap with the inner wall of the combustion chamber shell, Effectively solve the problems of twisting of the raw film patch and unsmooth exhaust, and improve the bonding reliability of the interface between the heat insulating layer and the shell

Method used

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  • Solid rocket engine combustion chamber shell adiabatic layer forming method
  • Solid rocket engine combustion chamber shell adiabatic layer forming method
  • Solid rocket engine combustion chamber shell adiabatic layer forming method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0041] Prepare the thermal insulation layer of the combustor shell of the small solid rocket motor with large length-to-diameter ratio according to the following steps:

[0042] Step 1: If figure 1 As shown, the insulation layer prefabricated part of EPDM rubber composite material is prepared by winding molding process, the length of the working surface of the winding mold core 1 (the length of the heat insulation layer preform) is set to 1000 mm, and the outer diameter of the winding molding core 1 is is 109.7mm (calculated by the following formula, α is 0.92, and the outer diameter of the prefabricated part of the heat insulation layer is 92% of the inner diameter of the shell):

[0043]

[0044] Among them, D MX is the outer diameter of the mold core, D KT is the inner diameter of the shell, d is the thickness of the insulation layer, K is the shrinkage rate of different rubber composite materials in different molding processes (the shrinkage rate of EPDM rubber compo...

Embodiment 2

[0051] Prepare the thermal insulation layer of the combustor shell of the small solid rocket motor with large length-to-diameter ratio according to the following steps:

[0052] Step 1: If image 3 As shown, the HALF mold 6 is used for the compression molding process to prepare the thermal insulation layer prefabricated part of the EPDM composite material. The outer diameter of the mold core 7 is 108.6mm (calculated by the following formula, α is 0.92, and the outer diameter of the prefabricated part of the heat insulation layer is 92% of the inner diameter of the shell):

[0053]

[0054] Among them, D MX is the outer diameter of the mold core, D KT is the inner diameter of the shell, d is the thickness of the heat insulation layer, K is the shrinkage rate of different rubber composite materials in different molding processes (the shrinkage rate of EPDM rubber composite materials in the molding process is K = 2%), and α corresponds to the prefabricated part of the heat ins...

Embodiment 3

[0061] Prepare the thermal insulation layer of the combustor shell of the small solid rocket motor with large length-to-diameter ratio according to the following steps:

[0062] Step 1: If figure 1 As shown, the insulation layer prefabricated part of EPDM rubber composite material is prepared by winding molding process, the length of the working surface of the winding mold core 1 (the length of the heat insulation layer preform) is set to 1000 mm, and the outer diameter of the winding molding core 1 is is 113.4mm (calculated by the following formula, α is 0.95, and the outer diameter of the prefabricated part of the heat insulation layer is 95% of the inner diameter of the shell):

[0063]

[0064] Among them, D MX is the outer diameter of the mold core, D KT is the inner diameter of the shell, d is the thickness of the insulation layer, K is the shrinkage rate of different rubber composite materials in different molding processes (the shrinkage rate of EPDM rubber compo...

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Abstract

The invention relates to a solid rocket engine combustion chamber shell adiabatic layer forming method, and belongs to the field of adiabatic layer forming technologies. The solid rocket engine combustion chamber shell adiabatic layer forming method comprises the steps that according to the design structure of an engine combustion chamber shell, an adiabatic layer prefabricated part which is not completely vulcanized is prepared, and the outer diameter of the adiabatic layer prefabricated part which is not completely vulcanized is less than the inner diameter of the engine combustion chamber shell; the adiabatic layer prefabricated part which is not completely vulcanized is bonded to the inner wall of the engine combustion chamber shell through a heat vulcanization adhesive; and hot pressing vulcanization is conducted, and thus the engine combustion chamber shell with an adiabatic layer is obtained. Through internal support tension of the adiabatic layer prefabricated part and a good isolation gap between the adiabatic layer prefabricated part and the inner wall of the combustion chamber shell, the problems of sheet pasting warp and unsmooth exhaust of sheet rubber are effectivelysolved, and bonding reliability of the interface of the adiabatic layer and the shell is improved.

Description

technical field [0001] The invention relates to a heat insulating layer forming process of a solid rocket motor, in particular to a process for forming a heat insulating layer in a combustion chamber of a small solid rocket motor with a large length-to-diameter ratio, and belongs to the field of heat insulating layer forming technology. Background technique [0002] At present, the methods for manufacturing the inner insulation layer of solid rocket motors mainly include airbag pressurization molding, mold pressurization molding, vulcanization tank hot press molding process, etc. For large aspect ratios (such as figure 2 As far as the thermal insulation layer is formed in the combustion chamber of the small solid rocket motor with L / D≥7), only airbag pressure forming and vulcanization tank hot pressing forming processes are feasible. However, it is difficult to discharge the gas between the heat insulation layer and the shell in the hot press molding process of the vulcaniz...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C35/02B29C35/00
CPCB29C35/002B29C35/02B29L2031/749
Inventor 李洋詹穹孙笑然王江彭正贵程靖萱伍政陈亚格彭琴
Owner HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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