Integral forming method for engine composite shell and spray pipe

A technology of composite materials and molding methods, which is applied to other household appliances, household appliances, household components, etc., can solve the problems of large negative weight, long cycle, complicated manufacturing and assembly process, etc., to improve the quality ratio, improve the use performance, eliminate The effect of the assembly process

Active Publication Date: 2017-01-04
湖北三江航天江北机械工程有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] Filament-wound engine casings can effectively reduce the negative weight of the engine casing, which is the main development direction of the engine casing in the future. However, the conventional filament-wound engine casings are usually connected to the metal flange on the nozzle through the rear head. The negative weight is still relatively large, which reduces the mass ratio of the solid rocket motor, thus greatly affecting the performance of the solid rocket motor, and the manufacturing and assembly process is complicated and the cycle is long

Method used

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  • Integral forming method for engine composite shell and spray pipe
  • Integral forming method for engine composite shell and spray pipe
  • Integral forming method for engine composite shell and spray pipe

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Experimental program
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Embodiment 1

[0028] 1) Form the nozzle 6, the front joint 1, the front skirt 3, the rear skirt 5, the water-soluble quartz sand mandrel 7 and the mandrel 8 respectively, wherein: the outer surface of the water-soluble quartz sand mandrel 7 and the engine composite material shell The internal profile is consistent, and the nozzle 6 includes a converging section 61, a backing 62, a throat lining 63, a diffusing section 64 and a nozzle housing 65;

[0029] In this embodiment, the water-soluble quartz sand mandrel 7 is prepared with a quartz sand mixed adhesive according to the weight ratio of quartz sand, polyvinyl alcohol and water in a ratio of 100:4:8, and is cured to obtain the water-soluble quartz sand mandrel 7; the front joint 1 The material of nozzle housing 65 is aluminum alloy forging material or titanium alloy forging material; the throat liner 63 of nozzle 6 is made of C / C composite material, and the convergent section 61, diffusion section 64, back of nozzle 6 The materials used ...

Embodiment 2

[0039] 1) Form the nozzle 6, the front joint 1, the front skirt 3, the rear skirt 5, the water-soluble quartz sand mandrel 7 and the mandrel 8 respectively, wherein: the outer surface of the water-soluble quartz sand mandrel 7 and the engine composite material shell The internal profile is consistent, and the nozzle 6 includes a converging section 61, a backing 62, a throat lining 63, a diffusing section 64 and a nozzle casing 65;

[0040] In this embodiment, the water-soluble quartz sand mandrel 7 is prepared with a quartz sand mixed adhesive according to the weight ratio of quartz sand, polyvinyl alcohol and water in a ratio of 100:5:8, and is solidified to obtain the water-soluble quartz sand mandrel 7; the front joint 1 The material of nozzle housing 65 is aluminum alloy forging material or titanium alloy forging material; the throat liner 63 of nozzle 6 is made of C / C composite material, and the convergent section 61, diffusion section 64, back of nozzle 6 The materials u...

Embodiment 3

[0050] 1) Form the nozzle 6, the front joint 1, the front skirt 3, the rear skirt 5, the water-soluble quartz sand mandrel 7 and the mandrel 8 respectively, wherein: the outer surface of the water-soluble quartz sand mandrel 7 and the engine composite material shell The internal profile is consistent, and the nozzle 6 includes a converging section 61, a backing 62, a throat lining 63, a diffusing section 64 and a nozzle housing 65;

[0051] In this embodiment, the water-soluble quartz sand mandrel 7 is prepared with a quartz sand mixed adhesive according to the weight ratio of quartz sand, polyvinyl alcohol and water in a ratio of 100:3:8, and is solidified to obtain the water-soluble quartz sand mandrel 7; the front joint 1 The material of nozzle housing 65 is aluminum alloy forging material or titanium alloy forging material; the throat liner 63 of nozzle 6 is made of C / C composite material, and the convergent section 61, diffusion section 64, back of nozzle 6 The materials ...

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PUM

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Abstract

The invention discloses an integral forming method for an engine composite shell and a spray pipe. The integral forming method refers to the process of rapidly and efficiently combining the spray pipe and the engine composite shell into a whole. The engine composite shell comprises a shell main body part and a front connector connected to the front end of the shell main body part. An engine shell and spray pipe flange connecting structure in the prior art is omitted. After assembled in place, a spray pipe assembly is formed together with the engine composite shell in a winding and curing mode. Metal components such as a rear connector, a connecting piece and the like are omitted. The mass ratio of an engine can be increased effectively. Meanwhile, the assembling procedure of the engine composite shell and the spray pipe is omitted, and the assembling and manufacturing period of the engine composite shell and the spray pipe is effectively shortened.

Description

technical field [0001] The invention belongs to the technical field of rocket engine casing molding, and in particular relates to an integral molding method for an engine composite material casing and a nozzle. Background technique [0002] The development of high-quality ratio solid motors is the development goal of solid propulsion technology. The negative mass of the rocket motor will reduce the carrying capacity of the rocket, and the effect will be greater the higher the stage. [0003] Filament-wound engine casings can effectively reduce the negative weight of the engine casing, which is the main development direction of the engine casing in the future. However, the conventional filament-wound engine casings are usually connected to the metal flange on the nozzle through the rear head. The negative weight is still large, which reduces the mass ratio of the solid rocket motor, thereby greatly affecting the performance of the solid rocket motor, and the manufacturing an...

Claims

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Application Information

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IPC IPC(8): B29D99/00C04B26/04C04B14/06
CPCB29D99/006C04B26/04C04B14/06
Inventor 余峰李天明卓艾宝王明坤廖东初敬生
Owner 湖北三江航天江北机械工程有限公司
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