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Rubber-based thermal insulation layer patching method

A thermal insulation layer and rubber-based technology, which is applied in the field of solid rocket motor thermal insulation layer manufacturing, can solve the problems of inconvenient operation, long construction period of thermal insulation layer materials, high labor intensity, etc., and achieve long service life, good elasticity, and accelerated drying speed Effect

Active Publication Date: 2015-10-07
HUBEI SANJIANG AEROSPACE JIANGHE CHEM TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The invention provides a patching method for a rubber-based thermal insulation layer, which solves the problem of long construction period, high labor intensity, and inconvenient operation for solid rocket motors with diameters ranging from φ100mm to φ1400mm and using nitrile, EPDM rubber, etc. as substrates for thermal insulation layer materials. At the same time, it can meet the production requirements of the thermal insulation layer in the charge combustion chamber of the solid rocket motor with small front and rear openings and large length.

Method used

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Examples

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Embodiment 1

[0029] Such as figure 2 As shown, a solid rocket motor has a diameter of 220 mm and a length of 1600 mm. The inner wall is integrally pasted with a 4 mm thick heat insulating layer, and the heat insulating material used is nitrile rubber as the base heat insulating material;

[0030] 1) Preparatory steps: clean the inner surface of the engine housing with ethyl acetate solvent; manufacture the straight section heat insulation layer green sheet of the engine according to the design thickness requirements, the length of the green sheet is 1600mm, the width is 660mm, and the thickness is 4mm;

[0031] Manufacture rubber airbags, the specific material is silicone rubber, under the internal pressure of 0.1MPa, the outer diameter of rubber airbags is designed to be φ180mm, and the length is 1580mm;

[0032] 2) Glue brushing step: evenly brush the adhesive BM-1 inside the engine casing, the thickness of the adhesive film is 27μm-45μm, and let it dry for 2 hours;

[0033] 3) Laminat...

Embodiment 2

[0039] Such as figure 2 As shown, a solid rocket motor has a diameter of 220 mm and a length of 1600 mm. The inner wall is integrally pasted with a 4 mm thick heat insulating layer, and the heat insulating material used is nitrile rubber as the base heat insulating material;

[0040]1) Preparatory steps: Clean the inner surface of the engine shell with ethyl acetate solvent; manufacture the straight section heat insulation layer green sheet of the engine according to the design thickness requirement of 4mm, the length of the green sheet is 1600mm, the width is 660mm, and the thickness is 4mm;

[0041] Manufacture rubber airbags, the specific material is silicone rubber, under the internal pressure of 0.1MPa, the outer diameter of rubber airbags is designed to be φ180mm, and the length is 1580mm;

[0042] 2) Glue brushing step: evenly brush the adhesive BM-1 inside the engine housing, the thickness of the adhesive film is 27 μm ~ 45 μm, let it dry for 3 hours, evenly brush the...

Embodiment 3

[0049] Such as figure 2 As shown, a solid rocket motor has a diameter of 220 mm and a length of 1600 mm. The inner wall is integrally pasted with a 4 mm thick heat insulating layer, and the heat insulating material used is nitrile rubber as the base heat insulating material;

[0050] 1) Preparatory steps: Clean the inner surface of the engine shell with ethyl acetate solvent; manufacture the straight section heat insulation layer green sheet of the engine according to the design thickness requirement of 4mm, the length of the green sheet is 1600mm, the width is 660mm, and the thickness is 4mm;

[0051] Manufacture rubber airbags, under the internal pressure of 0.1MPa, the outer diameter of rubber airbags is designed to be φ180mm, and the length is 1580mm;

[0052] 2) Glue brushing step: evenly paint the adhesive BM-1 inside the engine housing, the thickness of the adhesive film is 27 μm to 45 μm, the heating temperature is 60°C, and the time is 1h. The thickness of the film ...

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Abstract

A rubber-based thermal insulation layer patching method belongs to the solid rocket motor thermal insulation layer manufacturing method, and solves the problems of long construction period, high labor intensity, inconvenient operation and the like of a solid rocket motor with the diameter Phi of Phi 100mm-1400mm, using nitrile, EPDM rubber and other materials as a thermal insulation layer material; at the same time is able to meet production requirements of a thermal insulation layer material of a charging combustion chamber of a solid rocket motor with small front and back opening sizes and large length. The method includes a preliminary step, a gluing step, a patching step, a hot prepressing step, a fault detection step and a curing step. The method is successfully applied to multiple products, the thermal insulation layer fully meets the design requirements; process cycle is reduced by 67%, labor productivity is increased by at least 1 time, lower labor cost is reduced by at least 50%, raw material cost can be reduced by 15%; the operating environment is significantly improved, and a guarantee is provided for the prevention of occupational diseases.

Description

technical field [0001] The invention belongs to a method for manufacturing a heat-insulating layer of a solid rocket motor, and in particular relates to a patching method for a rubber-based heat-insulating layer. Background technique [0002] The insulation layer structure is an important part of the solid rocket motor charge combustion chamber, which can prevent the casing from reaching temperatures that endanger the structure. [0003] Publication No. CN1451020 is titled "Method for Insulating the Housing of Solid Propellant Rocket Motor", "Research on Forming Technology of Thermal Insulation Layer of Combustion Chamber of Small Solid Rocket Motor" (Aerospace Materials and Technology 2002.01), "Research on Integral Molding Technology of Rear Head" (Aerospace Manufacturing Technology 2006.03), and "Integral Molded Head Heat Insulation Layer and Artificial Debonding Layer Manufacturing Technology" (Aerospace Materials Technology 1996.02) all involve the method of pastin...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C65/52B29C65/18B29C65/82
Inventor 朱稼麟崔瑞禧何宜丰李方朔宋考生祝世杰宋铭赵碧娟徐晋阳周乐意
Owner HUBEI SANJIANG AEROSPACE JIANGHE CHEM TECH
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