CN111073276A - Composite material with high mechanical property and preparation method thereof - Google Patents
Composite material with high mechanical property and preparation method thereof Download PDFInfo
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- CN111073276A CN111073276A CN201911314070.3A CN201911314070A CN111073276A CN 111073276 A CN111073276 A CN 111073276A CN 201911314070 A CN201911314070 A CN 201911314070A CN 111073276 A CN111073276 A CN 111073276A
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- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08L—COMPOSITIONS OF MACROMOLECULAR COMPOUNDS
- C08L77/00—Compositions of polyamides obtained by reactions forming a carboxylic amide link in the main chain; Compositions of derivatives of such polymers
- C08L77/06—Polyamides derived from polyamines and polycarboxylic acids
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
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- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08J—WORKING-UP; GENERAL PROCESSES OF COMPOUNDING; AFTER-TREATMENT NOT COVERED BY SUBCLASSES C08B, C08C, C08F, C08G or C08H
- C08J5/00—Manufacture of articles or shaped materials containing macromolecular substances
- C08J5/04—Reinforcing macromolecular compounds with loose or coherent fibrous material
- C08J5/0405—Reinforcing macromolecular compounds with loose or coherent fibrous material with inorganic fibres
- C08J5/042—Reinforcing macromolecular compounds with loose or coherent fibrous material with inorganic fibres with carbon fibres
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- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08J—WORKING-UP; GENERAL PROCESSES OF COMPOUNDING; AFTER-TREATMENT NOT COVERED BY SUBCLASSES C08B, C08C, C08F, C08G or C08H
- C08J2377/00—Characterised by the use of polyamides obtained by reactions forming a carboxylic amide link in the main chain; Derivatives of such polymers
- C08J2377/06—Polyamides derived from polyamines and polycarboxylic acids
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- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08J—WORKING-UP; GENERAL PROCESSES OF COMPOUNDING; AFTER-TREATMENT NOT COVERED BY SUBCLASSES C08B, C08C, C08F, C08G or C08H
- C08J2433/00—Characterised by the use of homopolymers or copolymers of compounds having one or more unsaturated aliphatic radicals, each having only one carbon-to-carbon double bond, and only one being terminated by only one carboxyl radical, or of salts, anhydrides, esters, amides, imides, or nitriles thereof; Derivatives of such polymers
- C08J2433/04—Characterised by the use of homopolymers or copolymers of compounds having one or more unsaturated aliphatic radicals, each having only one carbon-to-carbon double bond, and only one being terminated by only one carboxyl radical, or of salts, anhydrides, esters, amides, imides, or nitriles thereof; Derivatives of such polymers esters
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- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08J—WORKING-UP; GENERAL PROCESSES OF COMPOUNDING; AFTER-TREATMENT NOT COVERED BY SUBCLASSES C08B, C08C, C08F, C08G or C08H
- C08J2451/00—Characterised by the use of graft polymers in which the grafted component is obtained by reactions only involving carbon-to-carbon unsaturated bonds; Derivatives of such polymers
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Organic Chemistry (AREA)
- Health & Medical Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Medicinal Chemistry (AREA)
- Polymers & Plastics (AREA)
- Manufacturing & Machinery (AREA)
- Materials Engineering (AREA)
- Inorganic Chemistry (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Reinforced Plastic Materials (AREA)
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Abstract
The invention belongs to the field of composite materials, and discloses a composite material which comprises the following components: 30-70 parts of polyphthalamide, 15-35 parts of carbon fiber, 2-10 parts of compatilizer, 0.1-2 parts of coupling agent, 0.3-2 parts of lubricant and 0.1-0.8 part of antioxidant. The invention also discloses a preparation method of the composite material, which comprises the following steps: (1) weighing the components according to the proportion, and mixing the components except the carbon fiber to obtain a premix; (2) and putting the premix and the carbon fiber into an extrusion device, and carrying out melt extrusion and cooling to obtain the composite material. The composite material has good mechanical properties and can be applied to the field of aerospace.
Description
Technical Field
The invention belongs to the field of composite materials, and particularly relates to a composite material with high mechanical property and a preparation method thereof.
Background
The carbon fiber composite reinforced material is one of the most advanced composite materials at present, and can give consideration to the performances of carbon fiber and a matrix, so that the carbon fiber composite reinforced material becomes an engineering structure material with more excellent comprehensive performance and a functional material with special performance. The carbon fiber composite reinforced material is widely used as a structural material and a high-temperature-resistant ablation-resistant material due to the characteristics of light weight, high strength, high temperature resistance, corrosion resistance, excellent thermodynamic performance and the like. Carbon fiber composites are also used in a variety of applications, such as aircraft and high-speed train braking systems, civil aircraft and automotive composite structural members, high-performance carbon fiber bearings, large blades of wind power generators, sports equipment, and the like, due to their high specific strength and specific modulus.
Therefore, research, development and application of carbon fiber composite materials have become a system engineering in multiple disciplinary fields, and the development status of carbon fiber composite materials becomes an important sign of the development level of material science.
Although the carbon fiber composite material has been developed, the mechanical properties (mechanical properties) of the existing carbon fiber composite material still have shortcomings in high-end technological fields such as aerospace, medical instruments and the like, and cannot completely meet the actual needs.
It is therefore desirable to provide a composite material with good mechanical properties.
Disclosure of Invention
The present invention is directed to solving at least one of the problems of the prior art described above. Therefore, the invention provides a composite material with high mechanical property and a preparation method thereof.
A composite material comprising the following components:
the polyphthalamide is sufficiently dried before use.
Preferably, the diameter of the carbon fiber is 5-15 μm, and the length of the carbon fiber is 3-6 mm.
Preferably, the compatibilizer is at least one selected from modified polyacrylate, epoxy resin, and maleic anhydride graft. The compatibilizer is also called a compatibilizer, and refers to an aid which promotes incompatible two polymers to be combined together by virtue of intermolecular bonding force, so as to obtain a stable blend.
More preferably, the compatibilizer is a maleic anhydride graft. The maleic anhydride graft compatilizer has high polarity and reactivity by introducing strong polar reactive groups, and can greatly improve the compatibility of the composite material and the dispersibility of the filler, thereby improving the mechanical strength of the composite material.
Preferably, the coupling agent is selected from at least one of a silane coupling agent, a chromium complex coupling agent, or a titanate coupling agent. The coupling agent in the composite material can react with certain groups on the surface of the reinforcing material and also react with matrix resin to form an interface layer between the reinforcing material and the resin matrix, and the interface layer can transfer stress, so that the bonding strength between the reinforcing material and the resin is enhanced, the performance of the composite material is improved, other media can be prevented from permeating into the interface, the interface state is improved, and the aging resistance, the stress resistance and the electrical insulation performance of a product are facilitated.
More preferably, the coupling agent is a silane coupling agent.
Preferably, the lubricant is selected from at least one of silane polymers, fatty acid salts, fatty acid amides, stearic acid, oleamide, vinyl bis-stearamide, pentaerythritol stearate or polyolefin wax. The lubricant promotes the melting of each component, effectively improves the fluidity of the composite material melt, reduces the friction between the composite material melt and processing machinery in the processing process, has better rubber mold effect and shortens the injection molding period of the composite material.
Preferably, the antioxidant is selected from at least one of hindered phenol, hindered amine, thioether or phosphite antioxidant. The antioxidant includes, but is not limited to, antioxidant 1010, antioxidant 1098, antioxidant 168, antioxidant 3114, antioxidant 619 or antioxidant DSTP. The antioxidant is used for improving the thermal decomposition resistance of the composite material so as to prevent the composite material from aging.
A method of making a composite material comprising the steps of:
(1) weighing the components according to the proportion, and mixing the components except the carbon fiber to obtain a premix;
(2) and putting the premix and the carbon fiber into an extrusion device, and carrying out melt extrusion and cooling to obtain the composite material.
Preferably, the temperature of the melt extrusion in step (2) is 260-330 ℃.
More preferably, the melt extrusion temperature is: the temperature of the first zone is 260-280 ℃, the temperature of the second zone is 270-320 ℃, the temperature of the third zone is 270-320 ℃, the temperature of the fourth zone is 270-325 ℃, the temperature of the fifth zone is 265-300 ℃, the temperature of the sixth zone is 265-310 ℃, the temperature of the seventh zone is 260-300 ℃, the temperature of the eighth zone is 260-290 ℃, the temperature of the ninth zone is 265-300 ℃ and the temperature of the head is 280-330 ℃.
Preferably, the rotation speed of the host of the extrusion device in the step (2) is 300-450 r/min.
Preferably, the feeding frequency of the extrusion device in the step (2) is 4-10 Hz.
Preferably, the screw diameter of the extrusion device in the step (2) is 55-65mm, and the screw length-diameter ratio is (40-46): 1.
the composite material is applied to the field of aerospace, and can be particularly used for manufacturing wings of unmanned planes or helicopters.
An airfoil comprising the composite. The mechanical property of wing is good, can be used to high strength load unmanned aerial vehicle.
Compared with the prior art, the invention has the following beneficial effects:
(1) the composite material prepared by the invention has good mechanical property, the tensile strength can reach 242MPa, the bending strength can reach 328MPa, and the composite material is suitable for manufacturing equipment in the field of aviation.
(2) The composite material prepared by the invention has smooth surface and no fiber floating phenomenon, and shows that the adopted preparation method can achieve good plasticizing effect and shearing effect and can realize better fusion of all components in the composite material.
(3) The composite material prepared by the invention has low saturated water absorption (not higher than 1.5 percent) and good water resistance.
Detailed Description
In order to make the technical solutions of the present invention more apparent to those skilled in the art, the following examples are given for illustration. It should be noted that the following examples are not intended to limit the scope of the claimed invention.
Example 1
A composite material comprising the following components:
wherein the polyphthalamide is HTN502 of DuPont, U.S. and is dried at 120 deg.C for 4 hr before use; the carbon fibers had a diameter of 5 μm and a length of 6mm, and were purchased from Tolli corporation of Japan; the compatilizer is modified polyacrylate (Guangdong Haohui new material Co., Ltd., model: HU 280); the coupling agent is a silane coupling agent (Nanjing eosin chemical industry group Co., Ltd., model: KH-560); the lubricant is pentaerythritol stearate (Italian hair base Co., Ltd., type: PETS-AP); the antioxidant is Irgafos 1098/Irgafos 168 (BASF chemical Co., Ltd.).
The preparation method of the composite material comprises the following steps:
(1) weighing the materials according to the component proportion, and putting the other materials except the carbon fiber into a mixer for mixing to obtain a premix;
(2) and adding the premix into a double-screw extruder from a main feeding port and a carbon fiber side feeding port, performing melt extrusion, cooling and then granulating to obtain the composite material.
Wherein the main machine rotating speed of the double-screw extruder (Nanjing Ruiya extrusion equipment Co., Ltd., model: TSE-65) is 350r/min, the feeding frequency is 6Hz, the screw diameter is 65mm, and the screw length-diameter ratio is 44: 1.
the temperature of the twin-screw extruder was set as follows: the temperature in the first zone is 280 ℃, the temperature in the second zone is 300 ℃, the temperature in the third zone is 300 ℃, the temperature in the fourth zone is 300 ℃, the temperature in the fifth zone is 295 ℃, the temperature in the sixth zone is 290 ℃, the temperature in the seventh zone is 280 ℃, the temperature in the eighth zone is 270 ℃, the temperature in the ninth zone is 280 ℃ and the temperature in the head is 300 ℃.
Example 2
A composite material comprising the following components:
wherein the polyphthalamide is HTN502 of DuPont, U.S. and is dried at 120 deg.C for 4 hr before use; the carbon fibers had a diameter of 5 μm and a length of 6mm, and were purchased from Tolli corporation of Japan; the compatilizer is maleic anhydride graft (Guangzhou Corne chemical Co., Ltd., type: HS 2-002A); the coupling agent is a silane coupling agent (Nanjing eosin chemical industry group Co., Ltd., model: KH-560); the lubricant is silicone resin; the antioxidant is antioxidant 1010 (BASF chemical Co., Ltd.).
The preparation method of the composite material comprises the following steps:
(1) weighing the materials according to the component proportion, and putting the other materials except the carbon fiber into a mixer for mixing to obtain a premix;
(2) and adding the premix into a double-screw extruder from a main feeding port and a carbon fiber side feeding port, performing melt extrusion, cooling and then granulating to obtain the composite material.
Wherein the main machine rotating speed of the double-screw extruder (Nanjing Ruiya extrusion equipment Co., Ltd., model: TSE-65) is 300r/min, the feeding frequency is 10Hz, the diameter of the screw is 60mm, and the length-diameter ratio of the screw is 40: 1.
the temperature of the twin-screw extruder was set as follows: the temperature of the first zone is 300 ℃, the temperature of the second zone is 320 ℃, the temperature of the third zone is 320 ℃, the temperature of the fourth zone is 315 ℃, the temperature of the fifth zone is 300 ℃, the temperature of the sixth zone is 310 ℃, the temperature of the seventh zone is 300 ℃, the temperature of the eighth zone is 290 ℃, the temperature of the ninth zone is 300 ℃ and the temperature of the head is 320 ℃.
Example 3
A composite material comprising the following components:
wherein the polyphthalamide is HTN502 of DuPont, U.S. and is dried at 120 deg.C for 4 hr before use; the carbon fibers had a diameter of 5 μm and a length of 6mm, and were purchased from Tolli corporation of Japan; the compatilizer is maleic anhydride graft (Guangzhou Corne chemical Co., Ltd., type: HS 2-002A); the coupling agent is titanate coupling agent (Nanjing eosin chemical industry group Co., Ltd., model: NDZ-109); the lubricant is pentaerythritol stearate (Italian hair base Co., Ltd., type: PETS-AP); the antioxidant is antioxidant 1098 (BASF CHEMICAL CO., LTD.).
The preparation method of the composite material comprises the following steps:
(1) weighing the materials according to the component proportion, and putting the other materials except the carbon fiber into a mixer for mixing to obtain a premix;
(2) and adding the premix into a double-screw extruder from a main feeding port and a carbon fiber side feeding port, performing melt extrusion, cooling and then granulating to obtain the composite material.
Wherein the main machine rotating speed of the double-screw extruder (Nanjing Ruiya extrusion equipment Co., Ltd., model: TSE-65) is 400r/min, the feeding frequency is 10Hz, the diameter of the screw is 55mm, the length-diameter ratio of the screw is 45: 1.
the temperature of the twin-screw extruder was set as follows: the first zone temperature is 260 ℃, the second zone temperature is 280 ℃, the third zone temperature is 280 ℃, the fourth zone temperature is 280 ℃, the fifth zone temperature is 270 ℃, the sixth zone temperature is 265 ℃, the seventh zone temperature is 270 ℃, the eighth zone temperature is 265 ℃, the ninth zone temperature is 260 ℃ and the head temperature is 280 ℃.
Comparative example 1
Compared with the example 1, the raw materials of the components and the preparation method in the comparative example 1 are the same, and the difference is that the dosage ratio of the components specifically comprises the following components:
comparative example 2
Compared with the example 1, the raw materials of the components and the preparation method in the comparative example 2 are the same, and the difference is that the dosage ratio of the components specifically comprises the following components:
comparative example 3
Compared with example 1, the components and preparation method used in comparative example 3 are substantially the same, except that: the twin-screw extruder (Kekuilong (Nanjing) machinery, Inc., type: CTE-35) had a screw diameter of 35mm, a screw length-diameter ratio of 40: 1.
comparative example 4
Compared with example 1, the components and preparation method used in comparative example 4 are substantially the same, except that: the twin-screw extruder (Nanjing Haisi extrusion Equipment Co., Ltd., type: SHJ-65) had a screw diameter of 65mm, a screw length-diameter ratio of 32: 1.
product effectiveness testing
The surface properties and mechanical properties of the composites prepared in examples 1-3 and comparative examples 1-4 were measured, and the results are shown in Table 1:
TABLE 1
As shown in Table 1, the composite materials obtained in examples 1 to 3 had better mechanical properties (tensile strength, flexural modulus and notched Izod impact strength), lower saturated water absorption and better water resistance, and had smooth surfaces without fiber floating. And although the strength of the comparative example 2 is high, the surface of the product is easy to warp due to the fact that the carbon fiber content is high, and the wing is easy to break when rotating at a high speed, so that the wing is not suitable for the wing of the unmanned aerial vehicle. Therefore, the composite material disclosed by the invention has good performance, can be suitable for the field of aviation or aerospace, and is currently applied to production and manufacturing of high-strength load-carrying unmanned aerial vehicle wings.
Claims (10)
1. A composite material, comprising the following components:
2. the composite material according to claim 1, wherein the carbon fibers have a diameter of 5-15 μm and a length of 3-6 mm.
3. The composite material of claim 1, wherein the compatibilizer is selected from at least one of a modified polyacrylate, an epoxy resin, or a maleic anhydride graft.
4. The composite material of claim 1, wherein the coupling agent is selected from at least one of a silane coupling agent, a chromium complex coupling agent, or a titanate coupling agent.
5. A method of preparing a composite material according to any one of claims 1 to 4, comprising the steps of:
(1) weighing the components according to the proportion, and mixing the components except the carbon fiber to obtain a premix;
(2) and putting the premix and the carbon fiber into an extrusion device, and carrying out melt extrusion and cooling to obtain the composite material.
6. The method as claimed in claim 5, wherein the temperature of the melt extrusion in the step (2) is 260-330 ℃.
7. The method as claimed in claim 5, wherein the rotation speed of the main body of the extrusion apparatus in step (2) is 300-450 r/min.
8. The method according to claim 5, wherein the screw diameter of the extrusion device in the step (2) is 55-65mm, and the screw length-diameter ratio is (40-46): 1.
9. use of the composite material according to any one of claims 1 to 4 in the field of aerospace.
10. An airfoil comprising the composite material of any one of claims 1 to 4.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201911314070.3A CN111073276A (en) | 2019-12-19 | 2019-12-19 | Composite material with high mechanical property and preparation method thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201911314070.3A CN111073276A (en) | 2019-12-19 | 2019-12-19 | Composite material with high mechanical property and preparation method thereof |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH07179753A (en) * | 1993-12-24 | 1995-07-18 | Calp Corp | Complex resin composition |
| CN102382454A (en) * | 2011-10-19 | 2012-03-21 | 深圳市科聚新材料有限公司 | High-strength antistatic heat-conductive PPA (Polyphthalamide) material and preparation method of same |
| CN104744926A (en) * | 2013-12-30 | 2015-07-01 | 上海杰事杰新材料(集团)股份有限公司 | High wear resistant and high self-lubrication continuous long fiber reinforced high temperature resistant nylon composite material and preparation method thereof |
-
2019
- 2019-12-19 CN CN201911314070.3A patent/CN111073276A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH07179753A (en) * | 1993-12-24 | 1995-07-18 | Calp Corp | Complex resin composition |
| CN102382454A (en) * | 2011-10-19 | 2012-03-21 | 深圳市科聚新材料有限公司 | High-strength antistatic heat-conductive PPA (Polyphthalamide) material and preparation method of same |
| CN104744926A (en) * | 2013-12-30 | 2015-07-01 | 上海杰事杰新材料(集团)股份有限公司 | High wear resistant and high self-lubrication continuous long fiber reinforced high temperature resistant nylon composite material and preparation method thereof |
Non-Patent Citations (4)
| Title |
|---|
| 于守武 肖淑娟 赵晋津: "《高分子材料改性 原理及技术》", 31 May 2015, 知识产权出版社 * |
| 卞军: "《塑料成型原理及工艺》", 31 August 2015, 西南交通大学出版社 * |
| 周惠久: "《新材料辞典》", 31 December 1996, 上海科学技术文献出版社 * |
| 齐贵亮: "《塑料改性配方工艺速查360例》", 31 January 2016, 文化发展出版社 * |
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