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Method for manufacturing carbon fiber reinforced resin matrix composite structure

A composite material and resin-based technology, which is applied in the field of preparation of carbon fiber reinforced resin-based composite material structural parts, can solve the problems of inability to use a prepreg-autoclave molding process, restrict the wide application of composite materials, and achieve good application prospects. , The effect of reducing material cost and improving interlaminar fracture toughness

Inactive Publication Date: 2011-06-29
CHENGDU AIRCRAFT INDUSTRY GROUP +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the above method cannot be used for the prepreg-autoclave molding process commonly used in aircraft composite components, which restricts the wide application of composite materials in the aviation field.

Method used

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  • Method for manufacturing carbon fiber reinforced resin matrix composite structure
  • Method for manufacturing carbon fiber reinforced resin matrix composite structure
  • Method for manufacturing carbon fiber reinforced resin matrix composite structure

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0024] Carbon fiber (Toray T300-1K, Japan) is impregnated with epoxy resin (Kunshan Yubo Resin Factory, FW-77 type), and the pultrusion process (such as figure 1 As shown) to prepare carbon fibers with a diameter of 0.3mm, where the glue tank temperature is 36°C, the mold temperature is 89°C, and the pultrusion speed is 0.18m / min.

[0025] figure 2 For the process flow diagram of ultrasound-assisted implantation, refer to figure 2 As shown, the above-mentioned micro-diameter carbon fiber rod is cut into a fixed-length rod with a length of 6mm, and is evenly implanted into the foam carrier according to the volume fraction of 3.14%; the foam carrier implanted with the micro-diameter carbon fiber rod is placed on the composite material prepreg blank surface( figure 2 As shown in a), micro-diameter carbon fiber rods are vertically implanted into the laminated structure by ultrasonic-assisted equipment as [0] 24 5224 high-temperature epoxy resin-based domestic carbon fiber U3...

Embodiment 2

[0028] Carbon fiber (Toray T300-1K, Japan) was impregnated with bismaleimide resin (QC-130), and a micro-diameter carbon fiber rod with a diameter of 0.3 mm was prepared by pultrusion. The temperature of the glue tank was 95 ° C, and the mold temperature was 180 ° C. The pultrusion speed is 0.18m / min; the above-mentioned micro-diameter carbon fiber rod is cut into a fixed-length rod with a length of 5mm by a self-made numerical control implanter, and is evenly implanted into the foam carrier at a volume fraction of 0.44%; the micro-diameter carbon fiber rod is implanted The foam carrier is placed on the upper surface of the composite prepreg blank, and the micro-diameter carbon fiber rods are vertically implanted into the laminate structure by ultrasonic equipment as[0] 24 The 5224 high-temperature epoxy resin-based domestic carbon fiber U3160 prepreg, remove the foam, and obtain the resin-based composite material blank reinforced by the micro-diameter carbon fiber rod.

[002...

Embodiment 3

[0031] Carbon fiber (Toray T300-3K, Japan) is impregnated with epoxy resin (Kunshan Yubo Resin Factory FW-125 type), and a micro-diameter carbon fiber rod with a diameter of 0.5 mm is prepared by pultrusion. The temperature of the glue tank is 36 °C and the mold temperature is 129 °C. ℃, the pultrusion speed is 0.18m / min.

[0032] Cut the above-mentioned micro-diameter carbon fiber rod into a fixed-length rod with a length of 3 mm using a self-made numerical control implanter, and implant it into the foam carrier evenly at a volume fraction of 1.23%; place the foam carrier implanted with the micro-diameter carbon fiber rod on the composite material prepreg On the upper surface of the blank, the fixed-length micro-diameter carbon fiber rods are vertically implanted into the laminated structure by ultrasonic equipment as [0 2 / 90 / 0 2 / 90 / 0 2 / 90 / 0 3 ] S The HT7 / 5429 bismaleimide unidirectional carbon fiber prepreg is removed from the foam to obtain a resin-based composite bl...

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Abstract

The invention relates to a method for manufacturing a carbon fiber reinforced resin matrix composite structure, which comprises the following steps: (1) utilizing a pulling and extruding forming technique to prepare a micro-diameter carbon fiber rod with the diameter of 0.3mm-0.5mm; (2) using a numerical control embedded machine to implant the carbon fiber into a foam carrier according to a designed direction and distribution density; (3) guiding the micro-diameter carbon fiber rod from the foam carrier into a resin base composite material pre-soaking material blank by using an ultrasonic auxiliary implanting device, wherein the volume ratio of carbon fiber rod to resin base composite material is 0.44%-3.14%; and (4) after removing foams, co-curing the micro-diameter carbon fiber rod with a prepreg piece, so as to acquire a multi-directional enhanced resin base composite material co-curing component. By using the method, all sub-layers of the composite material having the layered structure are fixedly combined along the direction vertical to a paving layer. Compared with the composite material having no multi-directional enhanced layered structure, the interlayer fracture toughness of the multi-directional enhanced composite material having the layered structure is obviously increased, thereby improving the interlayer property.

Description

technical field [0001] The invention relates to a preparation method of a carbon fiber-reinforced resin-based composite material structural part reinforced by a micro-diameter carbon fiber rod. Background technique [0002] Carbon fiber reinforced resin matrix composites have high specific strength and specific modulus, and are more and more widely used in the aerospace field. The laminated components based on carbon fiber reinforced resin matrix composite materials are widely used in the design and manufacture of various aviation aircraft due to their light weight, high strength and structural design. With the continuous development of my country's aviation industry, composite materials are used in aircraft fuselages. The proportion of structural materials is also increasing. [0003] The laminated structure based on carbon fiber reinforced resin matrix composites has good in-plane mechanical properties and designability, but the low interlaminar strength and interlaminar f...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C70/44B29C70/52B29K63/00B29K77/00
Inventor 文友谊文琼华窦作勇陈雯娜肖军
Owner CHENGDU AIRCRAFT INDUSTRY GROUP
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