KR101747109B1

KR101747109B1 - Complex carbon materials

Info

Publication number: KR101747109B1
Application number: KR1020160028929A
Authority: KR
Inventors: 박경래; 박동원; 신승우
Original assignee: 윈엔윈(주)
Priority date: 2016-03-10
Filing date: 2016-03-10
Publication date: 2017-06-14

Abstract

Carbon composite material is provided. The carbon composite material is produced by laminating the carbon fibers impregnated in the epoxy according to an embodiment of the present invention so that the thickness of the body is made to have a certain thickness. The body is formed by sequentially forming the first carbon layer, the core layer and the second carbon layer And the core layer is made of a bubble reinforced plastic having a thickness corresponding to a ratio of 0.2 to 0.6 with respect to the total thickness of the flesh.

Description

COMPLEX CARBON MATERIALS

The present invention relates to a carbon composite material, and more particularly, to a carbon composite material which comprises a synthetic foam core between carbon layers located on both sides in a process of forming a carbon material for use as a material for a bicycle frame, To thereby provide a carbon composite material which can be advantageous in terms of weight, strength, elasticity, cost, and the like.

Because of its low weight and strong strength, carbon is used as a material for a variety of products, including aircraft, automobiles, wind power generators, bicycles and archery.

Bicycle frames are made of steel, aluminum, titanium, carbon and so on. Among them, bicycles made of carbon frames are popular because carbon frames are light in weight and strong in strength.

On the other hand, the archery is generally made of a carbon material whose handle portion is made of metal or wood, and the wings to which both ends of the demonstration are connected are advantageous in terms of strength and elasticity.

However, bicycle frames and archery wings made of carbon material have a very good advantage in terms of mechanical properties such as weight, strength, and elasticity. However, since carbon fibers used in molding processes of bicycle frames and archery wings are very expensive, It is disadvantageous in that the unit price of the apparatus becomes expensive.

Therefore, it is possible to reduce the amount of carbon contained in the frame, and reduce the rigidity, the torsional rigidity, the shock absorption, and the vibration damping, as compared with the entire carbon frame of the same weight, And durability, and it is required to reduce the burden in terms of cost.

1. Japanese Patent Publication No. 4903881 (Mar. 28, 2012) 2. Registration of utility model in Japan Registered Utility Model No. 3137942 (November 21, 2007)

SUMMARY OF THE INVENTION The present invention has been made to solve the above-described problems of the conventional art, and it is an object of the present invention to provide a carbon material used for manufacturing bicycle frames, archery wings, etc., Carbon composite material which can exert more excellent effects and reduce the cost burden.

The present invention configured to achieve the above-described object is as follows. That is, the carbon composite material according to the present invention is a carbon composite material which is produced by laminating carbon fibers impregnated in epoxy to have a predetermined thickness of the body, wherein the body comprises a first carbon layer, a core layer and a second carbon layer , Wherein the core layer has a thickness corresponding to a ratio of 0.2 to 0.6 based on the total thickness of the flesh, comprising 50 to 70% by weight of the resin, 10 to 30% by weight of the filler and 20 to 30% by weight of the resin content Wherein the filler is made of foamed glass bubbles or ash having a specific gravity of 0.2 to 0.42 and has a specific gravity of 0.15 to 0.19 and a specific gravity of 0.02 to 0.25 produced by foaming the ultrafine hollow spheres or the thermoplastic resin. 0.03 < / RTI >
In the structure according to the present invention as described above, the first carbon layer and the second carbon layer may be formed to have the same thickness.
In the structure according to the present invention, the first carbon layer and the second carbon layer are formed by weaving in the UD method in parallel with the axial direction on the inner peripheral surface and the outer peripheral surface of the core layer on the basis of the core layer in the molding process of the first and second carbon layers The carbon prepreg is placed on the inner circumferential surface of the core layer and positioned on the inner circumferential surface of the carbon prepreg woven in the UD system and on the outer circumferential surface of the core layer. The outer circumferential surface of the carbon prepreg woven in the UD system is woven The carbon prepreg may be formed in a state in which it is positioned.
Meanwhile, in the structure according to the present invention, the body may be formed into a pipe shape having a circular section and a predetermined length.
In addition, in the structure according to the present invention, the body may be formed into an archery wing having a shape in which the core layer is thinned from one side to the other side in the longitudinal direction.
In addition, in the structure according to the present invention, the body may be formed into a plate shape.

According to an embodiment of the present invention, it is possible to provide a bicycle frame, an archery wing, and the like in which all of the materials used in the production process are not made of carbon, but have rigidity, torsional rigidity, shock absorption, vibration damping and durability And the like.

In addition, since the amount of carbon contained in the bicycle frame, the archery wing, and the like is reduced, the cost burden on both the bicycle manufacturer and the consumer can be reduced.

It should be understood that the effects of the present invention are not limited to the above effects and include all effects that can be deduced from the detailed description of the present invention or the configuration of the invention described in the claims.

1 is a cross-sectional view of a carbon tube according to an embodiment of the present invention;
2 is a view showing an arrangement of a carbon prepreg for improving torsion according to an embodiment of the present invention;
3 is a view illustrating a process of manufacturing a carbon composite material according to an embodiment of the present invention.
4 is an enlarged photograph of a filler according to an embodiment of the present invention;
5 is a graph showing a result of testing rigidity of a carbon composite material according to an embodiment of the present invention.
6 is a view showing a result of testing torsional rigidity of a carbon composite material according to an embodiment of the present invention.
7 is a view showing a result of testing impact absorption and vibration damping performance of a carbon composite material according to an embodiment of the present invention.
FIG. 8 is a table showing the contents of the core layer included in the carbon composite material according to an embodiment of the present invention, and shows the actual laminate according to the table. FIG.
9 is a view showing a result of the strength test according to the condition shown in Fig.
10 is a view showing the result of comparing strengths of S-Core laminate and All Carbon Laminate at specific strength values among the strength test results of FIG. 9. FIG.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, the present invention will be described with reference to the accompanying drawings. The present invention may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein.

In order to clearly illustrate the present invention, parts not related to the description are omitted, and similar parts are denoted by like reference characters throughout the specification.

Throughout the specification, when a part is referred to as being "connected" to another part, it includes not only "directly connected" but also "indirectly connected" .

Also, when a part is referred to as "comprising ", it means that it can include other components as well, without excluding other components unless specifically stated otherwise.

Hereinafter, embodiments of the present invention will be described in detail with reference to the accompanying drawings.

1 is a cross-sectional view of a carbon tube according to an embodiment of the present invention.

The carbon composite material 100 according to an embodiment of the present invention may include a first carbon layer 110, a core layer 120, and a second carbon layer 130.

As shown in FIG. 1, the carbon composite material 100 may be formed into a pipe shape for manufacturing a bicycle frame, or may be formed into a plate shape for manufacturing an archery wing.

Hereinafter, an embodiment in which the carbon composite material 100 is formed into a pipe shape will be described.

The first carbon layer 110 is formed by laminating a plurality of carbon prepregs in a mandrel so as to have a predetermined thickness, and curing (thermoforming at 120 ° C for one hour) by applying heat to the carbon prepregs (Removing and separating the first carbon layer 110 wound on the mandrel).

For reference, the release agent may be applied to the surface of the mandrel so as to facilitate the demoulding of the first carbon layer 110 from the mandrel.

Further, in order to improve the twist, a plurality of carbon prepregs can be cut so that the woven patterns are respectively arranged at predetermined angles (for example, 0 deg., 45 deg.).

The arrangement of the carbon prepreg for improving the torsion will be described later with reference to Fig.

The core layer 120 may include a resin paper coated with a synthetic foam (S-foam), and the S-foam may be formed by using a resin, a curing agent, a filler, .

In one embodiment of the S-foam blend, the resin may be used in an amount of 50 to 70 wt% of BPA Epoxy EEW 100 to 250, and the curing agent may be 20 to 30 wt% of Amidoamine and Tetraethylenepentamine (TEPA) based curing agent .

The filler may be a glass bubble having a specific gravity of 0.2 to 0.42 in an amount of 10 to 30 wt%, and the defoaming agent may be added in a small amount depending on the amount of resin, hardener and filler used.

For reference, glass bubble is a high strength and low specific gravity additive made of Soda-lime-borosilicate glass which is resistant to moisture and chemically stable. It is used for thermoplastic, SMC, BMC, structural foam, Elastomer and the like.

Various fillers can be used as another embodiment of the above-described S-foam blend.

For example, a micro hollow sphere having a specific gravity of 0.15 to 0.19 or a micro balloon having a specific gravity of 0.02 to 0.03 produced by foaming a thermoplastic resin can be used, which is produced by foaming an ash.

The S-foam blended using the above materials can be made of resin paper. Resin paper is a release paper coated with a special release agent, which can be manufactured by coating a certain thickness of S-foam and then wrapping the release vinyl in roll form.

The resin paper using the S-foam manufactured as described above can be used as the core layer 120. After being stored at 4 to 10 DEG C, the resin paper is cut to a predetermined length by a necessary amount and wound on the first carbon layer 110 .

Meanwhile, the second carbon layer 130 may be wound to a predetermined thickness on the core layer 120 wound on the first carbon layer 110.

The second carbon layer 130 may also be formed by laminating a plurality of carbon prepregs in the same manner as the first carbon layer 110 and curing the mixture by applying heat. In order to improve the torsion, a plurality of carbon pre- Can be cut to be arranged at predetermined angles (e.g., 0 deg., 45 deg.), Respectively.

The first carbon layer 110, the core layer 120, and the second carbon layer 130 may form a body of the carbon composite material 100 having a pipe shape with a predetermined thickness.

In the process of forming the body of the carbon composite material 100 according to the embodiment of the present invention, the first carbon layer 110 and the second carbon layer 130 are formed by laminating carbon fibers impregnated with epoxy in a predetermined thickness The core layer 120 between the first carbon layer 110 and the second carbon layer 130 thus formed has a thickness of 0.2 to 0.6 times the thickness of the body constituting the carbon composite material 100. [ Of the thickness of the substrate.

If the thickness of the body of the carbon composite material 100 is 3 mm as shown in FIG. 1, the first carbon layer 110 and the second carbon layer are 0.6 mm each, and the core layer 120 is And may have a thickness of 1.8 mm. When the carbon composite material 100 having a thickness of 3 mm is manufactured, the first carbon layer 110 and the second carbon layer may each be formed to have a thickness of 1.2 mm and the core layer 120 may have a thickness of 0.6 mm .

In addition, the carbon composite material 100 can be constituted of the first carbon layer 110, the core layer 120, and the second carbon layer 130 at a predetermined weight.

The used weight of the first carbon layer 110, the core layer 120 and the second carbon layer 130 is 45: 10: 45 to 10: 80: 10. &Lt; / RTI >

The strength, torsional rigidity, shock absorption, and vibration damping performance according to the thickness and the weight ratio of the core layer 120 included in the carbon composite material 100 will be described later with reference to FIG. 5 to FIG.

FIG. 2 is a view showing the arrangement of a carbon prepreg for torsional improvement according to an embodiment of the present invention.

The carbon composite material 100 may be laminated in order of the first carbon layer 110, the core layer 120 and the second carbon layer 130. The first carbon layer 110 and the second carbon layer 130 may be laminated in this order. It can be seen that a plurality of carbon prepregs are stacked and wound.
The first carbon layer 110 and the second carbon layer 130 are formed on the core layer 120 in the forming process of the first and second carbon layers 110 and 130, 120, a UD-woven carbon prepreg is disposed in parallel with the axial direction.
The outer circumferential surface of the carbon prepreg, which is located on the inner circumferential surface of the core layer 120 and is woven in the UD method, and the outer circumferential surface of the carbon prepreg, which is located on the outer circumferential surface of the core layer 120, A carbon prepreg is located.
As described above, a plurality of carbon prepregs included in the first carbon layer 110 and the second carbon layer 130 are cut so that the linear pattern woven is arranged at 0 ° and ± 45 °, As shown in FIG.
The carbon composite material 100 of FIG. 2 can be manufactured in the form of a pipe having a predetermined length, which is circular in cross section of the body for manufacturing a bicycle frame.
The body composing the carbon composite material 100 may be formed into an archery wing having a shape in which the thickness of the core layer 120 becomes thinner from one side to the other side in the longitudinal direction, May be formed in the form of a plate.

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As shown in Fig. 2, the twist can be improved by arranging the woven patterns of the plurality of carbon prepregs at predetermined angles, respectively.

3 is a view illustrating a process of manufacturing a carbon composite material according to an embodiment of the present invention.

3 is a process for manufacturing a pipe material for a bicycle frame using a carbon composite material.

First, S-foam is blended using a resin, a curing agent, a filler and a defoaming agent (S301).

Here, the resin may be used in an amount of 50 to 70 wt% of BPA Epoxy EEW 100 to 250, and amidoamine and tetraethylenepentamine (TEPA) type curing agent may be used in 20 to 30 wt% of the resin content.

The filler may be used in a content of 10 to 30 wt% with a glass bubble having a specific gravity of 0.2 to 0.42. The defoaming agent may be added in a small amount depending on the amount of resin, hardener and filler used.

As a reference, in addition to glass bubbles as a filler, a microballoon having a specific gravity of 0.15 to 0.19 or a micro balloon of a specific gravity of 0.02 to 0.03 produced by foaming a thermoplastic resin was prepared by foaming an ash Can be used

After S301, the core layer 120 including the resin paper is formed using the combined S-foam, and cut to a predetermined length (S302).

The resin paper is a release paper wound with a release agent coated thereon. The release paper can be prepared by coating S-foam blended in S301 with a certain thickness and then wrapping it in roll form to cover the release vinyl, and it can be stored at 4-10 ° C .

After S302, the first carbon layer 110 is formed into a predetermined thickness (S303).

Here, the first carbon layer 110 is formed by laminating a plurality of carbon prepregs on a mandrel so as to have a predetermined thickness, and curing the carbon prepregs by applying heat thereto, and then demolding the mandrels, wherein a plurality of carbon prepregs are patterned at predetermined angles Can be cut to be placed.

After S303, the core layer 120 cut in S302 is wound on the first carbon layer 110 to a predetermined thickness (S304).

At this time, the vinyl covered on the core layer 120 may be removed to be spread on the bottom without bending, and then rolled from the top of the first carbon layer 110.

After step S304, if the core layer 120 is wound on the first carbon layer 110, the second carbon layer 130 may be wound on the first carbon layer 130 to a predetermined thickness to produce a carbon tube including the core layer 120 S305).

Here, the second carbon layer 130 can be formed by laminating a plurality of carbon prepregs (the woven patterns are arranged at predetermined angles, respectively) and curing by heating, and the second carbon layer 130 is wound And then cured by heating at 120 DEG C for 1 hour.

In the tube manufacturing process of FIG. 3, the thickness of the core layer 120 may be a thickness corresponding to a ratio of 0.2 to 0.6 as compared to the total thickness. The weight of the first carbon layer 110, the core layer 120, and the second carbon layer 130 may be 45:10:45 to 10:80:10, respectively.

After S305, the carbon tube is cut to match the length to be used as a bicycle frame, and the cut surface is sanded (S306).

4 is an enlarged view of a filler according to an embodiment of the present invention.

Fig. 4 (a) is a glass bubble, which can contribute to weight saving, dimensional stability improvement, process improvement, and overall cost reduction of the carbon composite material.

Also, as shown in FIG. 4 (a), the glass bubble can have a fine hollow glass spherical shape, which can provide various advantages that the glass bubble does not have any irregular mineral filler.

For example, due to the ball-bearing effect of the glass bubble, a large amount of filler can be filled without fear of flowability unlike other fillers. When the same volume is added due to the perfect spherical shape of the glass bubble, The viscosity increase of the contrasting resin can be minimized.

In addition, glass bubbles can reduce warpage and shrinkage, thereby improving dimensional stability, and at the same time, can reduce overall product cost.

4 (b) is a fly ash which can be used as a filler instead of a glass bubble.

It can have a spherical shape similar to a glass bubble, and can provide similar advantages as the glass bubble described above.

FIG. 5 is a graph showing a result of testing rigidity of a carbon composite material according to an embodiment of the present invention.

5, a whole carbon laminate (hereinafter, referred to as an "all carbon laminate") having the same weight as a laminate (hereinafter referred to as "S-core laminate") including a core layer 120 according to an embodiment of the present invention, And the compressive strengths were compared.

5, the S-core laminate has a thickness of the first carbon layer 110, the core layer 120, and the second carbon layer 130 of 0.5 to 0.6: 1: 0.5 to 0.6 The thickness of 3 mm may have a thickness of 0.8 t, 1.4 t and 0.8 t, respectively.

On the other hand, All Carbon Laminate at the same weight can be divided into 0.8t, 0.7t and 0.8t thickness.

That is, the carbon layer having the thickness of 0.7t of All Carbon Laminate can be replaced with the core layer 120 having the thickness of 1.4t of S-Core Laminate at the same weight.

5, it can be seen that the S-core laminate according to an embodiment of the present invention is about 50% higher than the all carbon laminate.

6 is a result of testing the torsional rigidity of a carbon composite material according to an embodiment of the present invention.

The test environment is the same as in FIG. 5, and it can be seen that the S-core laminate according to an embodiment of the present invention is higher by about 40 to 50% than the all carbon laminate in the torsional stiffness.

Torsional stiffness and flexural rigidity of about 40 to 50% or more means that the torsional stiffness and the flexural rigidity are stronger than that of carbon having the same weight. Therefore, the carbon composite material according to one embodiment of the present invention is used to manufacture a carbon tube In this case, it is possible to make a light and durable bicycle frame by using small-diameter carbon pipe.

FIG. 7 is a graph illustrating a test result of impact absorption and vibration damping performance of a carbon composite material according to an embodiment of the present invention.

The test environment is the same as in FIG. 5, and it can be seen that the S-Core laminate according to one embodiment of the present invention exerts superior performance to shock absorption and vibration damping as compared with the all carbon laminate.

Therefore, when the carbon composite material according to the embodiment of the present invention is manufactured, it is possible to provide a more stable and comfortable ride feeling than the general aluminum frame as well as the general carbon frame.

8 and 10 are the results of testing the strength characteristics of the carbon composite material according to the content of the core layer 120 according to an embodiment of the present invention.

FIG. 8 is a table showing the contents of the core layer 120 included in the carbon composite material according to an embodiment of the present invention, and shows the actual laminate according to the table.

The proportion of the core layer 120 in the laminate is 0 (All Carbon), 20%, 40%, 50% and 70%, and the weight is all the same as 55 g as shown in the table.

For reference, it can be seen that the total thickness increases as the ratio of the core layer 120 increases.

Fig. 9 shows the results of the strength test according to the conditions shown in Fig.

When the ratio of the core layer 120 is 50%, it can be confirmed that the strength is the maximum.

For reference, it can be seen that as the ratio of the core layer 120 increases, the strength also increases, but when the ratio of the core layer 120 is 70%, the strength decreases.

However, even when the ratio of the core layer 120 is 70%, it can be confirmed that it still has higher strength than All Carbon Laminate.

FIG. 10 is a result of comparing strengths of S-Core laminate and All Carbon Laminate at specific strength values among the strength test results of FIG.

10 shows the comparison of the strength of the All Carbon Laminate when the ratio of the core layer 120 is 50% and the strength of the core layer 120 is 50%. When the ratio of the core layer 120 is 50% While for All Carbon Laminate it is 98 kgf.

In other words, the strength of the S-core laminate is twice as high as that of the all carbon laminate.

For reference, the strength of the S-core laminate can be improved more than that of the all-carbon laminate due to the structural form in the tube state.

11 is a test result comparing vibration of an S-Core Laminate and an All Carbon Laminate according to an embodiment of the present invention.

In Fig. 11, vibration damping effects through vibration were compared using a vibrator of the same force.

11, it can be confirmed that the vibration damping effect of the S-core laminate is superior to that of the all carbon laminate.

12 is a test result of a comparison of impact absorption between an S-core laminate and an all carbon laminate according to an embodiment of the present invention.

In Fig. 12, the impact was compared by dropping a 130 g weight steel bar from a height of 1 m.

As shown in FIG. 12, it can be seen that the impact absorption of the S-core laminate is superior to that of the all carbon laminate.

As can be seen from the above test results, the core layer 120 has a specific gravity which is as low as one-half of that of the carbon prepreg, and has excellent strength properties, so that the bending strength and torsional strength of the carbon tube can be effectively increased.

In addition, the core layer 120 may exhibit shock absorption and vibration damping performance of the S-core laminate due to excellent impact resistance and vibration damping performance.

It will be understood by those skilled in the art that the foregoing description of the present invention is for illustrative purposes only and that those of ordinary skill in the art can readily understand that various changes and modifications may be made without departing from the spirit or essential characteristics of the present invention. will be.

It is therefore to be understood that the above-described embodiments are illustrative in all aspects and not restrictive.

For example, each component described as a single entity may be distributed and implemented, and components described as being distributed may also be implemented in a combined form.

The scope of the present invention is defined by the appended claims, and all changes or modifications derived from the meaning and scope of the claims and their equivalents should be construed as being included within the scope of the present invention.

100: Tubular carbon composite material
110: first carbon layer
120: core layer
130: second carbon layer

Claims

A carbon composite material laminated with carbon fibers impregnated with epoxy to have a thickness of a predetermined thickness,
Wherein the body is formed in order of a first carbon layer, a core layer and a second carbon layer,
Wherein the core layer has a thickness corresponding to a ratio of 0.2 to 0.6 based on the total thickness of the flesh, a curing agent corresponding to 50 to 70 wt% of a resin, 10 to 30 wt% of a filler, and 20 to 30 wt% Reinforced plastic molded from a mixture obtained by mixing the above-
Wherein the filler is composed of ultrafine particle hollow spheres having a specific gravity of 0.15 to 0.19 or a superfine particle plastic hollow spheres having a specific gravity of 0.02 to 0.03 produced by foaming a thermoplastic resin produced by foaming a glass bubble or an ash having a specific gravity of 0.2 to 0.42. .

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The carbon composite material according to claim 1, wherein the first carbon layer and the second carbon layer have the same thickness.

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The method as claimed in claim 1 or 3, wherein the first and second carbon layers are formed on the inner and outer circumferential surfaces of the core layer with respect to the core layer in the molding process of the first and second carbon layers, A carbon prepreg which is woven in a side-by-side UD system and is positioned on the inner circumferential surface of the core layer and is disposed on an inner circumferential surface of a carbon prepreg woven in a UD system and an outer circumferential surface of a carbon prepreg Wherein the carbon prepreg is woven in a plain weave manner.

The carbon composite material according to claim 5, wherein the body is formed into a pipe having a circular cross section and a predetermined length.

[6] The carbon composite material according to claim 5, wherein the body is formed into an archery wing having a thickness of the core layer thinner from one side to the other side in the longitudinal direction.

The carbon composite material according to claim 5, wherein the body is formed in the shape of a plate.