Solid rocket engine inner insulation layer forming method

A solid rocket and molding method technology, which is applied in the field of forming a thermal protection inner insulation layer of a solid rocket motor, can solve the problems of multiple energy sources, use requirements and complicated operation processes, cost, etc., and achieve full utilization, reduce production process steps, and increase production capacity. Effect

Active Publication Date: 2018-01-16
HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Since the high-pressure (>0.6MPa) molding of the heat-insulating layer is completed in a complex pressurized oven, the shell needs to be sealed before pressurizat

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0020] The method for forming the inner thermal insulation layer of the solid rocket motor comprises the following steps:

[0021] 1) Preparation before pressurization: brush the adhesive on the inner wall of the shell and dry it, and paste the rubber sleeve 3 of the heat insulation layer (120 mm in length, 50 mm in diameter, and 1 mm in thickness) into the corresponding bonding position of the solid rocket motor shell 2 (Ensure that the insulation layer rubber sleeve 3 is laid flat and without wrinkles);

[0022] 2) Put the air bag 4 filled with air into the casing. Screw the port positioning tooling 1 at both ends of the shell to ensure the distance between the rubber sleeve of the heat insulating layer and the port of the shell, and put the shell into a vacuum container 5 (vacuum oven).

[0023] 3) Pressurization: Start to evacuate the vacuum oven, the air in the airbag 4 expands in the vacuum environment, apply a pressure of 0.1MPa to the rubber sleeve 3 of the heat insul...

Embodiment 2

[0027] The method for forming the inner thermal insulation layer of the solid rocket motor comprises the following steps:

[0028] 1) Preparation before pressurization: After brushing the adhesive on the inner wall of the shell and drying it, paste the rubber sleeve 3 of the heat insulating layer (300mm in length, 100mm in diameter, and 2mm in thickness) into the corresponding bonding position of the solid rocket motor shell 2 ( Ensure that the rubber sleeve 3 of the thermal insulation layer is laid flat and without wrinkles);

[0029] 2) Put the airbag 4 filled with nitrogen into the casing. Screw the port positioning tooling 1 at both ends of the shell to ensure the distance between the rubber sleeve of the heat insulating layer and the port of the shell, and put the shell into the vacuum container 5 (vacuum cylinder).

[0030] 3) Pressurization: start to vacuumize the vacuum cylinder, the nitrogen in the airbag 4 expands in a vacuum environment, apply a pressure of 0.1MPa ...

Embodiment 3

[0034] The method for forming the inner thermal insulation layer of the solid rocket motor comprises the following steps:

[0035] 1) Preparation before pressurization: After brushing the adhesive on the inner wall of the shell and drying it, paste the rubber sleeve 3 of the heat insulating layer (700mm in length, 150mm in diameter, and 3mm in thickness) into the corresponding bonding position of the solid rocket motor shell 2 ( Ensure that the rubber sleeve 3 of the thermal insulation layer is laid flat and without wrinkles);

[0036] 2) Put the air bag 4 filled with air into the casing. Screw the port positioning tooling 1 at both ends of the shell to ensure the distance between the rubber sleeve of the heat insulating layer and the port of the shell, and put the shell into the vacuum cylinder.

[0037] 3) Pressurization: start to evacuate the vacuum cylinder, the air in the airbag 4 expands in a vacuum environment, apply a pressure of 0.1MPa to the rubber sleeve 3 of the h...

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Abstract

A solid rocket engine inner insulation layer forming method comprises the following steps: 1, evenly coating the inner wall of a solid rocket engine casing with an adhesive, drying in air, pasting aninsulation layer rubber sleeve onto a corresponding bonding position on the inner wall of the solid rocket engine casing; 2, putting a gas bag fully filled with a gas into the solid rocket engine casing with the insulation layer rubber sleeve, mounting positioning fixtures on both ends of the solid rocket engine casing, and putting the solid rocket engine casing into a vacuum container; 3, vacuumizing the vacuum container for expansion of air in the gas bag under vacuum conditions so as to apply 0.1MPa pressure to the insulation layer rubber sleeve pasted on the inner wall of the solid rocketengine casing to complete solidification of the adhesive so as to complete pasting forming of the insulation layer rubber sleeve and the solid rocket engine casing; and 4, taking the solid rocket engine casing out of the vacuum container, removing the positioning fixtures on the both ends of the solid rocket engine casing, and taking the gas bag out. According to the method, a gas bag pressurizingmedium is changed from a high-pressure compressed gas to an ordinary pressure gas, production energy consumption is reduced, the sealing treatment process on the casing in the adiabatic process is omitted, and production operation difficulty is effectively reduced.

Description

technical field [0001] The invention relates to a method for forming an inner thermal insulation layer for thermal protection of a solid rocket motor. Background technique [0002] The traditional airbag pressurization process used for forming the thermal insulation layer in the solid rocket motor uses raw rubber for the thermal insulation layer, and uses a complex pressurized oven device to complete the flow molding and cross-linking curing process under the high pressure (>0.6MPa) of the airbag . Since the raw rubber of the thermal insulation layer is directly flow-formed in the engine casing, it has the disadvantages that the thickness is not easy to control, and the surface appearance is prone to flaws. The thermal insulation layer is first cured by molding and other means, and then the cured thermal insulation layer is pasted into the shell to complete the thermal insulation layer—the bonding and molding of the shell has gradually become the dominant airbag pressuri...

Claims

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Application Information

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IPC IPC(8): B29C65/48
Inventor 郑光虎付翔聂松李月常董自萍彭琴罗宏伟
Owner HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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