Manufacturing method of high-temperature resistant fiber wound composite material shell

A technology of winding composite materials and high temperature resistant fibers, which is applied in household components, household appliances, other household appliances, etc., can solve the problems of light weight, high strength, high temperature resistance, harsh flight environment, etc., and achieves low cost and blasting pressure. High and reliable effect

Active Publication Date: 2018-12-21
JIANGSU XINYANG NEW MATERIALS CO LTD
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  • Abstract
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, in the existing technology, the flight environment of new aerospace flight devices is extremely harsh, and its operating temperature continues to increase. However, the heat-resistant temperature of the carbon fiber-wound epoxy resin composite shell manufa

Method used

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Embodiment Construction

[0051] Below the present invention is further described:

[0052] A method for manufacturing a high-temperature-resistant fiber-wound composite shell, comprising the following steps:

[0053] Step 1, prepare the tooling and mold, clean the residue on the molding surface of the mold to avoid scratching the molding surface of the mold, then wipe the mold with a clean cloth dipped in acetone, clean the residue that affects the product, and then dry it; Before using the mold, it is necessary to assemble the mold first, first place the mandrel on the support tooling, and then follow the steps of radial and axial assembly to assemble the mold parts. The assembly sequence is the connecting and fixing flanges at both ends, 32 pieces of module A, 32 One-piece module B and 32-module C are assembled in sequence according to the number and digital model, to avoid the wrong assembly position of each module, and to ensure that the assembled surface is flat, smooth, and free of gaps;

[005...

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Abstract

The invention discloses a manufacturing method of a high-temperature resistant fiber wound composite material shell in the field of monitoring. The manufacturing method comprises the following steps:(1) a tool and a mold are prepared; (2) preparation of a gypsum layer: gypsum powder, polyvinyl alcohol and water are mixed as gypsum according to a weight ratio of 2: (1-2): 1; after uniform mixing,the mixed gypsum is coated on a metal core mold; and an outer molding surface of the core mold is treated to a theoretical inner molding surface of a thermal insulation layer by using a molding surface scraper; (3) a skirt mold is prepared; and (4) a skirt is prepared. The composite material shell produced by the method has the characteristics of low mass, high reliability, low cost, high-temperature resistance and high blasting pressure, and can meet the requirement of normal flying of a novel aerospace aircraft under harsh high-temperature environment; and the manufacturing method can be used for manufacturing the high-temperature resistant fiber wound composite material shell.

Description

technical field [0001] The invention relates to a manufacturing method of a housing, in particular to a manufacturing method of a high-temperature-resistant composite material housing. Background technique [0002] Fiber-reinforced resin-based composites have the characteristics of high specific strength, high specific modulus, stable dimensions, strong designability, and easy large-area integral molding. They have become one of the most important aerospace structural materials after aluminum alloys, titanium alloys and steel. , has been widely used in the aerospace field. With the rapid development of the aerospace industry, the requirements for the weight and high-temperature resistance of structural devices are more stringent. Lightweight, high-strength, high-temperature-resistant composite materials are of great significance for reducing the weight of engines, improving the performance of aircraft, and reducing launch costs. As early as the 1940s, composite material she...

Claims

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Application Information

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IPC IPC(8): B29C70/68B29C70/34B29C70/44B29C70/30B29C33/72B29L31/30
CPCB29C33/72B29C70/30B29C70/342B29C70/44B29C70/68B29C70/681B29C70/683B29L2031/3082
Inventor 杨恒李顺马婷婷李俊
Owner JIANGSU XINYANG NEW MATERIALS CO LTD
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