CN1491972A - Processfor preparing carbon fiber reinforced resin base composite material with controllable thermal expansion coefficient - Google Patents
Processfor preparing carbon fiber reinforced resin base composite material with controllable thermal expansion coefficient Download PDFInfo
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- CN1491972A CN1491972A CNA03125313XA CN03125313A CN1491972A CN 1491972 A CN1491972 A CN 1491972A CN A03125313X A CNA03125313X A CN A03125313XA CN 03125313 A CN03125313 A CN 03125313A CN 1491972 A CN1491972 A CN 1491972A
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- carbon fiber
- matrix material
- thermal expansion
- expansion coefficient
- thermal expansivity
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Abstract
The present invention provides the preparation process of carbon fiber reinforced resin composite material with controllable thermal expansion coefficient. The method is based on the carbon fiber with the features of high strength, high modulus and low density and the important characteristic of possessing negative thermal expansion coefficient in the direction of 0 deg. By means of controlling the angle of carbon fiber layer and the fiber content in the composite material, the present invention reaches the aim of controlling the thermal expansion coefficient of the composite material in some direction and prepares carbon fiber reinforced composite resin material with low thermal expansion coefficient approaching zero.
Description
Technical field
The present invention relates to a kind of preparation method of low thermal coefficient of expansion carbon fiber enhancement resin base composite material, specifically, reach the method for control matrix material thermal expansivity purpose by adjusting volume content, fiber lay down layer direction and the fibre shape of carbon fiber in the matrix material.
Technical background
There are a lot of product requirements in wide temperature range, to work at aerospace field,, especially requiring to have thermostability to a certain degree under the high-accuracy situation for these structured materials of having relatively high expectations.This just needs to select the material of low-expansion high strength, high rigidity.At electronics, appliance field, many precise parts require material thermal expansivity under the use temperature in 100 ℃ little, reach 10
-6/ ℃ the order of magnitude.For example, be used in the light bridge bar on the laser apparatus, under the situation that satisfies strength of materials requirement, thermal expansivity requires to reach 10
-7/ ℃; The high-precision antenna tamper also requires strength of materials height, thermal expansivity little.Carbon-fibre composite makes its requirement that can not only satisfy aerospace, electronics and appliance field physical and mechanical properties, and can satisfy the requirement of its thermal expansivity with its superior heat-stability energy, good designability.
Carbon fiber has a lot of good performances, and except that many outstanding features such as have intensity height, modulus height, density is low, thermal conductivity is high, frictional coefficient is little, also have and on 0 ° of direction of fiber, be negative thermal expansivity, and the little characteristics of thermal expansivity.Be used for Resins, epoxy, resol and the unsaturated polyester resin three big interchangeable heat thermosetting resins of matrix material, the Resins, epoxy over-all properties is best, and mechanical property is good, and linear expansivity is also very little, is generally 6 * 10
-5/ ℃.And the coefficient of expansion of carbon fiber has anisotropy, and thermal expansivity is with vertically thermal expansivity is different on 0 ° of direction, and 0 ° of direction is for negative, vertically for just.
Someone has studied glass fibre and the carbon fiber hybrid unidirectional fibre strengthens the performance resins based composites, investigated thermal expansivity with hybrid ratio, mix the rule that interface number and shop layer sequential scheduling parameter change, obtain the unidirectional hybrid composite of zero thermal expansion by adjusting hybrid ratio.
Summary of the invention
The preparation method who the purpose of this invention is to provide the carbon fiber enhancement resin base composite material of may command thermal expansivity,
The preparation method of the carbon fiber enhancement resin base composite material of may command thermal expansivity of the present invention is by adjusting content, fiber lay down layer angle and the fibre shape of carbon fiber, thermal expansivity on a certain direction of matrix material is controlled, and the preparation thermal expansivity is near zero high performance composite.
Carbon fiber volume content is in 40%～70% scope in the described matrix material.
The form of carbon fiber comprises continuous carbon fibre, chopped carbon fiber, carbon fiber preform in the described matrix material.
When described matrix material used continuous carbon fibre, the braiding of carbon fiber or shop layer angle changed in 0～90 ° of direction.
The resin matrix of matrix material uses high performance Resins, epoxy among the present invention, and thermal expansivity is 10
-5/ ℃.Carbon fiber adopts mold pressing, hand to stick with paste or the winding shaping process preparation on resin matrix, and carbon fiber volume content is controlled at 40%～70%.
When using chopped carbon fiber, the orientation of carbon fiber is uncontrollable.By adjusting the volume content of carbon fiber, can produce thermal expansivity and reach 10
-6/ ℃ matrix material.
When using continuous carbon fibre, at first adjust the content of carbon fiber.Under the certain situation of content, the angle [alpha] (see figure 2) of controlling fiber, the direction of arrow coefficient of expansion among adjustable reduction condensation material Fig. 1.The matrix material thermal expansivity of making has reached 10
-7/ ℃.
The present invention uses the carbon fiber of different shapes such as continuous carbon fibre, chopped carbon fiber, carbon fiber preform, by volume content, the carbon fiber shop layer angle of adjusting carbon fiber, thermal expansivity on a certain direction of matrix material is controlled, prepared thermal expansivity near zero high performance composite.
Description of drawings
The carbon fiber enhancement resin base composite material synoptic diagram of Fig. 1 may command thermal expansivity
The distribution synoptic diagram of Fig. 2 carbon fiber in matrix material
The direction of arrow is the direction of the control matrix material coefficient of expansion among the figure, α be fiber and controlling party to angle
Embodiment
Further specify characteristics of the present invention below by embodiment:
Embodiment 1
Carbon fiber is toray company's T-300 a polyacrylonitrile-radical continuous long carbon fiber, and thermal expansivity is-0.6 * 10-5/ ℃ on 0 ° of direction, and Resins, epoxy is bisphenol A-type (Xinhua Resin Factory, Shanghai's production).It is long that the carbon fiber weak point is cut to 5mm, and mold pressing prepares condensation material.When the volume content of carbon fiber was 65%, the thermal expansivity of matrix material was 2.5 * 10-6/ ℃.
Embodiment 2
Carbon fiber is toray company's T-300 a polyacrylonitrile-radical continuous long carbon fiber, and thermal expansivity is-0.6 * 10 on 0 ° of direction
-6/ ℃, Resins, epoxy is bisphenol A-type, (Xinhua Resin Factory, Shanghai's production).Adopt mould pressing process to prepare matrix material.Keeping the volume content of carbon fiber constant, is 65%.By different lay angle [alpha] lay down fibre.
When α was 0 °, direction of arrow thermal expansivity minimum had reached 2.1 * 10
-7℃;
When α was 45 °, direction of arrow thermal expansivity was 9.3 * 10
-7℃;
When α was 90 °, direction of arrow thermal expansivity was 8.6 * 10 to the maximum
-6℃.
Claims (4)
1, the preparation method of the carbon fiber enhancement resin base composite material of may command thermal expansivity, it is characterized in that this method is by adjusting volume content, fiber lay down layer angle and the fibre shape of the carbon fiber in the matrix material, thermal expansivity on a certain direction of matrix material is controlled, and the preparation thermal expansivity is near zero low thermal coefficient of expansion carbon-fibre composite.
2,, it is characterized in that the volumn concentration of carbon fiber in the described matrix material is controlled in 40%～70% scope according to the method for claim 1.
3,, it is characterized in that the form of carbon fiber in the described matrix material comprises continuous carbon fibre, chopped carbon fiber, carbon fiber preform according to the method for claim 1.
4,, it is characterized in that described matrix material uses continuously according to the method for claim 1
During carbon fiber, the braiding of carbon fiber or shop layer angle change in 0～90 ° of scope.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 03125313 CN1233704C (en) | 2003-08-22 | 2003-08-22 | Processfor preparing carbon fiber reinforced resin base composite material with controllable thermal expansion coefficient |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 03125313 CN1233704C (en) | 2003-08-22 | 2003-08-22 | Processfor preparing carbon fiber reinforced resin base composite material with controllable thermal expansion coefficient |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1491972A true CN1491972A (en) | 2004-04-28 |
| CN1233704C CN1233704C (en) | 2005-12-28 |
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ID=34239597
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 03125313 Expired - Fee Related CN1233704C (en) | 2003-08-22 | 2003-08-22 | Processfor preparing carbon fiber reinforced resin base composite material with controllable thermal expansion coefficient |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1233704C (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108461925A (en) * | 2018-03-15 | 2018-08-28 | 浙江大学 | A kind of list covering grid reinforcement backing strip high-precision reflector |
| CN111538131A (en) * | 2020-06-04 | 2020-08-14 | 中国科学院长春光学精密机械与物理研究所 | Axial heat-dissipation truss supporting mechanism for space optical camera |
-
2003
- 2003-08-22 CN CN 03125313 patent/CN1233704C/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108461925A (en) * | 2018-03-15 | 2018-08-28 | 浙江大学 | A kind of list covering grid reinforcement backing strip high-precision reflector |
| CN111538131A (en) * | 2020-06-04 | 2020-08-14 | 中国科学院长春光学精密机械与物理研究所 | Axial heat-dissipation truss supporting mechanism for space optical camera |
Also Published As
| Publication number | Publication date |
|---|---|
| CN1233704C (en) | 2005-12-28 |
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Granted publication date: 20051228 Termination date: 20130822 |