Foamed reinforced composite material structure vacuum co-injection integral forming method

A composite material, vacuum injection technology, applied in the field of composite materials, can solve the problems of looseness or air bubbles, easy to produce dry spots, complicated penetration, etc., to ensure stability, avoid the bonding process, and simplify the process operation.

Active Publication Date: 2014-01-08
AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

For foam-reinforced structural composite materials, the existing process technology has complicated r

Method used

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  • Foamed reinforced composite material structure vacuum co-injection integral forming method
  • Foamed reinforced composite material structure vacuum co-injection integral forming method
  • Foamed reinforced composite material structure vacuum co-injection integral forming method

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Embodiment Construction

[0029] The present invention will be further described below through specific embodiments and accompanying drawings.

[0030] figure 1 It is a structural schematic diagram of the foam reinforced composite material of the present invention, which includes an upper skin 1 , a reinforcement 2 (that is, a reinforcing rib), a foam interlayer 3 and a lower skin 4 . The steps of the vacuum co-injection integral molding method of the material are as follows: figure 2 As shown, a single-sided mold with a frame is used to form the lower skin by vacuum injection, and the foam interlayer and reinforced prefabricated parts are directly laid on the lower skin without demoulding, and then the upper skin prefabricated parts are laid, and after vacuum sealing The injection resin is integrally molded, and the product can be obtained after demoulding after curing. The upper skin and the lower skin referred to in the present invention can also be called inner skin and outer skin respectively. ...

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Abstract

The invention belongs to the field of composite materials, and relates to a foamed reinforced composite material structure vacuum co-injection integral forming method. The formed interlayer structure comprises an upper skin, a lower skin, reinforcing ribs, and a foamed interlayer. According to the invention, a single-sided mold with a frame is adopted; the lower skin is formed by vacuum injection; the part is not de-molded, and the foamed interlayer and a rib reinforcing material precast are directly paved on the lower skin; an upper skin reinforcing material precast is paved; vacuum sealing is carried out, and resin is injected, such that integral forming is realized; and curing and de-molding are carried out, and a product can be obtained. With the method provided by the invention, foamed reinforced composite material structure net-size integral forming can be realized. No edge-trimming processing is needed, scrap rate is low, and production efficiency is high. Therefore, the method is suitable for large-scale productions.

Description

technical field [0001] The invention relates to the technical field of composite materials, in particular to a vacuum co-injection overall molding method for a foam-reinforced composite material structure. Background technique [0002] Foam-reinforced composite structure is a typical structural form of composite materials in many fields. The skin plays the role of ensuring the shape and load-bearing. The foam has the functions of impact resistance, lightening weight and supporting the skin. Improve the effectiveness of structural rigidity. The traditional molding process method is to use prepregs to form under pressure in an autoclave. Generally, the skin and reinforcement are cured first and then glued or reinforced with the foam, and the foam and skin are co-cured. However, the prepreg-autoclave molding process has the disadvantages of high prepreg processing, storage and autoclave curing costs, and cannot be mass-produced on a large scale. [0003] The vacuum injection ...

Claims

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Application Information

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IPC IPC(8): B29C70/44
CPCB29C70/443B29C70/542
Inventor 张涛王国勇王召娣
Owner AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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