Curing method for large-thickness fiber-reinforced epoxy resin matrix composite material

A technology of epoxy resin and composite materials, which is applied in the field of composite material parts, can solve the problems of long curing period, difficult and complicated optimization, low thermal conductivity and other problems of large thickness composite materials, and achieve the reduction of microcracks and stress concentration, and low voids Efficiency, uniform internal quality

Active Publication Date: 2015-11-25
COMAC +2
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The manufacture of large-thickness composite parts usually has the following problems: due to the low thermal conductivity of polymer materials, the curing cycle of large-thickness composites is longer
[0003] In order to optimize the curing method of large-thickness wallboard and obtain qualified composite parts, relevant scholars have done a lot of research. However, due to the low thermal conductivity, anisotropy and curing exothermic characteristics of epoxy resin-based composite materials, making It becomes difficult and complex to optimize in ordinary solidification regimes using theoretically derived methods
S.R.White et al. (White, S.R.in'Proc.ICCM-9', UniersityofZaragoza, SpainandWoodheadPublishingCo., Cambirdge, 1993, Vol.3, pp.622-629) then adopts the "step-by-step curing" method that includes multiple insulation steps The curing process was optimized for ultra-thick composite parts, and it was found that the internal quality of the parts after curing was greatly improved, but the disadvantage of this method is that the cycle is too long, which is more than 6-10 times that of the ordinary cycle
In addition, some manufacturing processes of ultra-thick parts have also been reported, but most of these processes require new types of process equipment, and are not very practical in actual production

Method used

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  • Curing method for large-thickness fiber-reinforced epoxy resin matrix composite material
  • Curing method for large-thickness fiber-reinforced epoxy resin matrix composite material

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0029] On the flat steel mold, the carbon fiber reinforced epoxy resin-based prepreg with a size of 500×500mm is paved, and the paving is completed when the thickness reaches 16mm. Lay the isolation film, air felt and vacuum bag on the prepreg, and stick the vacuum bag on the mold with high temperature resistant adhesive tape, use the vacuum device to draw out the gas in the vacuum bag, and maintain the negative pressure state, when the vacuum bag After the vacuum degree stabilizes, the packaging of the prepreg is completed. Place the encapsulated prepreg in an autoclave, and set the pressure of the autoclave to 0.5MPa. First, in the temperature rise step from room temperature to 90°C, the temperature rises to 90°C at a rate of 2°C / min. Raise the temperature up to 180°C at a rate of 0.1°C / min in the temperature rise step from 90 to 180°C, and keep the temperature at a rate of 2°C / min for 120 minutes and then drop it below 23°C, take out the prepreg to obtain a composite materi...

Embodiment 2

[0031] On the curved aluminum mold, lay carbon fiber plain weave fabric, and when the thickness reaches 60mm, the laying is completed. After heat setting, epoxy resin is injected into the laid fabric by using resin vacuum introduction technology, and after packaging, the fabric is placed in an oven. In the oven, the heating rate is first raised to 90°C at a rate of 0.3°C / min. Use a heating rate of 1°C / min to rise to 110°C, then use a heating rate of 1.5°C / min to rise to 120°C, and keep at this temperature for 120 minutes, then drop to 100°C at a rate of 0.3°C / min, and then use When the speed of 2°C / min is reduced to below 23°C, composite parts with qualified quality can be obtained.

Embodiment 3

[0033] On the composite material mold, the aramid fiber-reinforced epoxy resin-based prepreg with a diameter of 1200 mm is paved, and the paving is completed when the thickness reaches 80 mm. Lay the isolation film, air felt and vacuum bag on the prepreg, and stick the vacuum bag on the mold with high temperature resistant adhesive tape, use the vacuum device to draw out the gas in the vacuum bag, and maintain the negative pressure state, when the vacuum bag After the vacuum degree stabilizes, the packaging of the prepreg is completed. Place the packaged prepreg in an autoclave, set the pressure of the autoclave to 0.9MPa, first raise the temperature to 80°C at a rate of 0.1°C / min, and then increase the rate of temperature to 80°C at a rate of 0.5°C / min. 100°C, then rise to 120°C at a rate of 1°C / min, and keep at this temperature for 60 minutes, then drop to 100°C at a rate of 0.1°C / min, and then drop to 23°C at a rate of 0.5°C / min Next, the prepreg is taken out to obtain a c...

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Abstract

The invention discloses a curing method for a superlarge-thickness fiber-reinforced epoxy resin matrix composite material and a composite material workpiece manufactured according to the method. Compared with a common constant-speed temperature-rising curing method, the stepped curing method for the superlarge-thickness thermosetting resin matrix composite material has the advantages that the degree of asynchronous curing of the interior of the superlarge-thickness composite material can be greatly lowered, and the temperature uniformity in the curing process of the large-thickness composite material is improved. The curing method is suitable for manufacturing large-thickness composite material parts in fields such as the aviation field, the aerospace field, the building field, the wind power field, the naval ship field, the automobile field and the electronic field.

Description

technical field [0001] The present invention relates to a method of curing a large thickness fiber reinforced epoxy resin based composite material and a composite material article manufactured according to said method. technical background [0002] In the process of manufacturing large and complex composite parts, it is necessary to optimize the curing method of large thickness parts. The manufacture of large-thickness composite parts usually has the following problems: due to the low thermal conductivity of polymer materials, the curing cycle of large-thickness composites is longer. During the heating and curing process, there are temperature hysteresis and temperature overshoots inside, which will cause uneven temperature on the thickness gradient and asynchronous curing, which will eventually lead to uneven internal residual stress, fiber volume content and mechanical properties of the part. In extreme cases, excessive temperatures can cause material degradation, carboni...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C70/42B29C70/44B29C35/02B29C70/54B29K63/00B29K105/08B29K105/12
Inventor 杨洋谢中亚刘卫平袁协尧余木火潘利剑朱姝刘宇婷
Owner COMAC
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