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Method for integrally forming low-cost composite material large cabin

A composite material and molding method technology, which is applied in the field of integrated molding of low-cost composite large cabins, can solve the problems of high cost of large composite cabins, and achieve the effects of good product strength and rigidity, light weight, and good overall compactness.

Active Publication Date: 2019-12-13
长春长光宇航复合材料有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to solve the high cost problem of the existing composite material large cabin, and provide a low-cost composite material large cabin integral molding method

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0020] A low-cost composite material large cabin integral molding method, including the following steps:

[0021] S1: Preparation of large-scale metal molds: A female mold for the outer surface profile of the product is processed by machining;

[0022] S2: Apply elastic glue on the female mold for sealing treatment. After the elastic glue is cured, place 3K carbon cloth, and place the outer skin of normal temperature curing epoxy resin prepreg on the carbon cloth. The thickness of the outer skin is 2mm- 3mm;

[0023] S3: Use a vacuum bag to evacuate the laid outer skin or pressurize it in a hot autoclave, and the pressure is 0.1-0.3MPa;

[0024] S4: Put it into a curing oven or autoclave for heating after pressurizing, heating temperature / time is 80℃ / 4h, curing and forming;

[0025] S5: Position the installation position of the metal embedded part according to the drawing on the outer skin, and bond the metal embedded part to the outer skin, and at the same time position the hat-shaped...

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Abstract

The invention discloses a method for integrally forming a low-cost composite material large cabin, and belongs to the field of composite material large cabins. The method comprises the steps of manufacturing a large metal die, sealing the die, forming the outer skin, vacuumizing and curing, forming a cap-shaped reinforcing rib, vacuumizing and curing again, forming the inner skin, vacuumizing andcuring for the third time, demolding and finishing. The method overcomes the defects that a mode of splicing into a whole after sectional forming or a traditional metal framework type square cabin structure is complex in process and weak in mechanical property at the splicing positions, and an integrally formed cabin body is better in air tightness and durability and lighter in weight; and meanwhile, by using a rigid polyurethane foam as a filling material, the integrally formed cabin body is better in thermal insulation performance and higher in functionality, so that the higher performance requirements of a military and civil dual-use large cabin are better met.

Description

Technical field [0001] The invention relates to the field of large-scale composite cabins, in particular to a method for integral molding of large-scale composite cabins with low cost. Background technique [0002] The composite material large cabin is mainly used in the process of vehicle parking and motor transportation; used to load on-board equipment and provide necessary environmental conditions for the equipment; provide environmental protection and survival guarantee during use. There are high requirements for the appearance quality, water tightness, and driving test of the thermal insulation cabin. The composite material large cabin can be stored for a long time in an environment with an ambient temperature of 0℃~+40℃ and a relative humidity of not more than 98% (25℃). The accumulated days of abnormal storage environment allowed to occur each year does not exceed 30 days. Due to the difficulty of the integrated molding process for large composite cabins, most of them cur...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C70/68B29C70/44B29C70/54B29C35/02
CPCB29C35/02B29C70/44B29C70/54B29C70/68B29C70/681
Inventor 邹志伟迟贺曹延君秦闯林再文
Owner 长春长光宇航复合材料有限公司
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