CN113524718B - Mould pressing preparation method of large-thickness carbon fiber reinforced resin matrix composite material - Google Patents
Mould pressing preparation method of large-thickness carbon fiber reinforced resin matrix composite material Download PDFInfo
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- CN113524718B CN113524718B CN202110674285.7A CN202110674285A CN113524718B CN 113524718 B CN113524718 B CN 113524718B CN 202110674285 A CN202110674285 A CN 202110674285A CN 113524718 B CN113524718 B CN 113524718B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Moulding By Coating Moulds (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The invention discloses a die pressing preparation method of a large-thickness carbon fiber reinforced resin matrix composite material, which comprises the following steps: 1) Preparing a prepreg: processing carbon fiber cloth and resin to prepare prepreg cloth; 2) Pre-soaking cloth laying: cutting the prepreg cloth into a designed shape, and then layering in a tool; 3) Vacuumizing treatment: carrying out intermittent vacuum-pumping treatment in the process of laying the prepreg cloth; 4) Die pressing and curing: after the layering is finished, closing the die of the tool and putting the die in a flat vulcanizing machine for pressurizing and curing; 5) And (3) post-treatment: and (4) obtaining a large-thickness carbon fiber reinforced resin matrix composite product through machining treatment. The mould pressing preparation method of the large-thickness carbon fiber reinforced resin matrix composite material can be used for mould pressing at one time, and the preparation efficiency is high.
Description
Technical Field
The invention relates to the technical field of composite material preparation, in particular to a mould pressing preparation method of a large-thickness carbon fiber reinforced resin matrix composite material.
Background
With the continuous development of science and technology, the space carrier rocket needs to greatly increase the carrying distance to meet the requirements of technological progress. The improvement of the thrust-weight ratio of the carrier rocket, the improvement of the effective load and the development of the engine with the super-large diameter are the necessary ways for improving the carrying technology. The novel material can be developed to replace the metal material of the original spacecraft, so that the structural mass of the spacecraft is effectively reduced, the effective load of the spacecraft is improved, and the carrying distance is greatly increased.
The carbon fiber reinforced resin matrix composite belongs to an advanced composite and has the characteristics of high specific strength, high specific rigidity, good fatigue resistance, good shock absorption and the like. Moreover, the local optimization of the material performance is realized through the layer design, the strength, the rigidity and various special requirements can be met, which is incomparable with the traditional metal material with strong performance uniformity.
The main preparation technology of the carbon fiber reinforced resin matrix composite material is a vacuum-autoclave technology, and the technology is suitable for preparing thin-wall composite materials. However, when the technology is used for preparing a large-thickness composite material, the defects of internal delamination, rich grease, pores and the like of a product can occur.
Disclosure of Invention
The invention aims to overcome the defects of the background technology and provide a mould pressing preparation method of a large-thickness carbon fiber reinforced resin matrix composite material, the preparation method can be used for mould pressing formation at one time, and the preparation efficiency is high.
In order to realize the aim, the invention provides a mould pressing preparation method of a large-thickness carbon fiber reinforced resin matrix composite, which comprises the following steps:
1) Preparing a prepreg: processing carbon fiber cloth and resin to prepare prepreg cloth;
2) Pre-soaking cloth laying: cutting the prepreg cloth into a designed shape, and then layering in a tool;
3) Vacuumizing treatment: carrying out intermittent vacuum-pumping treatment in the process of laying the prepreg cloth;
4) Die pressing and curing: after the layering is finished, closing the die of the tool and putting the die in a flat vulcanizing machine for pressurizing and curing;
5) And (3) post-treatment: and (4) obtaining a large-thickness carbon fiber reinforced resin matrix composite product through machining treatment.
Further, in the step 1), the carbon fiber cloth is selected from plain cloth and/or unidirectional cloth; the resin is selected from epoxy resins.
Further, in the step 1), the resin content of the prepreg is 30-50%.
Further, in the step 2), a continuous coating and layering mode and a non-continuous parallel layering mode are adopted for layering.
Furthermore, the continuous coating and layering mode is that the upper layer, the lower layer and any side surface are layered by continuous pre-impregnated cloth, and the rest part is non-continuous parallel layering; the non-continuous parallel laying mode is that the prepreg cloth is parallel laid, and the prepreg cloth between each layer is discontinuous.
Further, in the step 2), the ratio of the thickness of the prepreg cloth laying layer to the thickness of the large-thickness carbon fiber reinforced resin matrix composite product is 1:0.8 to 0.9.
Further, in the step 3), the intermittent vacuum-pumping treatment is to pump vacuum once every 30-40 layers of pre-impregnated cloth is paved.
Further, in the step 3), the vacuum pressure of the intermittent vacuum-pumping treatment is less than or equal to-0.09 MPa, and the pressure is maintained for 30-60 min.
Further, in the step 4), the pressure of the pressurization curing is 10-15 MPa, the temperature is 160-180 ℃, and the heat preservation time is 2-3 h.
And further, in the step 5), quality inspection is carried out before machining treatment, and machining treatment is carried out after product inspection is passed to obtain a large-thickness carbon fiber reinforced resin matrix composite product with a designed shape.
Furthermore, the thickness of the large-thickness carbon fiber reinforced resin matrix composite material is 60-100 mm.
Compared with the prior art, the invention has the following advantages:
firstly, the large-thickness carbon fiber reinforced resin matrix composite material is prepared by groping the flat vulcanization mould pressing technology, and the prepared composite material has the characteristics of high specific strength, high specific rigidity, good fatigue resistance, good shock absorption and the like.
Secondly, the mould pressing preparation method of the large-thickness carbon fiber reinforced resin matrix composite material can realize one-step mould pressing by continuously adjusting the process parameters, and has high preparation efficiency.
Thirdly, the die pressing preparation method of the large-thickness carbon fiber reinforced resin matrix composite can realize net size forming of structural parts with complex shapes of all composite materials by changing the inner profile of the tool, greatly reduce raw materials and improve production and preparation efficiency.
Detailed Description
The following describes the embodiments of the present invention in detail with reference to the embodiments, but they are not intended to limit the present invention and are only examples. While the advantages of the invention will be apparent and readily appreciated by the description.
The invention discloses a die pressing preparation method of a large-thickness carbon fiber reinforced resin matrix composite material, which comprises the following steps:
1) Preparing a prepreg: processing carbon fiber cloth and resin to prepare prepreg cloth; the carbon fiber cloth is selected from plain cloth and/or unidirectional cloth; the resin is selected from epoxy resin, and the resin content of the prepreg cloth is 30-50%.
2) Pre-soaking cloth laying: cutting the prepreg cloth into a designed shape, and then layering in a tool; laying layers by adopting a continuous coating and laying mode and a non-continuous parallel laying mode, wherein the continuous coating and laying mode is that an upper layer, a lower layer and any side surface are laid by continuous pre-impregnated cloth, and the rest part is a non-continuous parallel laying layer; the non-continuous parallel laying mode is that the prepreg cloth is parallel laid, and the prepreg cloth between each layer is discontinuous. The ratio of the thickness of the prepreg cloth laying layer to the thickness of the large-thickness carbon fiber reinforced resin matrix composite product is 1:0.8 to 0.9.
3) Vacuumizing treatment: carrying out intermittent vacuum-pumping treatment in the process of laying the prepreg cloth; the intermittent vacuum-pumping treatment is to pump vacuum once for 30-40 layers of pre-impregnated cloth, wherein the vacuum pressure is less than or equal to-0.09 MPa, and the pressure is maintained for 30-60 min.
4) Die pressing and curing: after the layering is finished, closing the die of the tool and putting the die in a flat vulcanizing machine for pressurizing and curing; the pressure of the pressurization and solidification is 10-15 MPa, the temperature is 160-180 ℃, and the heat preservation time is 2-3 h.
5) And (3) post-treatment: and (3) carrying out quality inspection on the material after mould pressing and curing, wherein the quality inspection comprises strength test and internal quality inspection, and then carrying out machining treatment to obtain the large-thickness carbon fiber reinforced resin matrix composite product with the designed shape.
Example 1
The mould pressing preparation method of the large-thickness carbon fiber reinforced resin matrix composite material comprises the following steps:
(1) Processing carbon fiber cloth and resin into prepreg cloth, and selecting carbon fiber plain cloth and unidirectional cloth with the resin content of 30 percent; (2) The plain cloth adopts continuous coating and lays layers, the unidirectional cloth adopts non-continuous bag parallel laying layers, and the proportion of the thickness of the laying layers of the prepreg cloth to the thickness of the required composite material is 1:0.8; (3) Vacuumizing once every 30 layers of carbon fiber prepreg cloth are laid, ensuring that the prepreg cloth is smooth in laying and free of air bubbles, keeping the vacuum pressure less than-0.09 MPa, and keeping the pressure for 30min; (4) After layering is finished, closing the tooling, putting the tooling in a flat vulcanizing machine for pressurizing and curing, wherein in the whole process, the pressure range is controlled at 10MPa, the temperature range is controlled at 160 ℃, and the heat is preserved for 2 hours; (5) And (3) carrying out strength test and internal quality inspection on the performance of the large-thickness composite material prepared by die pressing.
The tensile strength of the composite material prepared by the embodiment is 25MPa, and the internal quality has no defects such as layering and pores.
Example 2
The mould pressing preparation method of the large-thickness carbon fiber reinforced resin matrix composite material comprises the following steps:
(1) Processing carbon fiber cloth and resin to prepare prepreg cloth, and selecting carbon fiber unidirectional cloth with the resin content of 30%; (2) The unidirectional cloth adopts non-continuous bags to spread layers in parallel, and the ratio of the thickness of the spread layers of the pre-soaked cloth to the thickness of the required composite material product is 1:0.8; (3) Vacuumizing once every 30 layers of carbon fiber prepreg cloth are laid, ensuring that the prepreg cloth is smooth in laying and free of air bubbles, keeping the vacuum pressure less than-0.09 MPa, and keeping the pressure for 30min; (4) After the layering is finished, closing the die of the tool, putting the die in a flat vulcanizing machine for pressurizing and curing, wherein in the whole process, the pressure range is controlled to be 10MPa, the temperature range is controlled to be 160 ℃, and the temperature is kept for 2h; (5) And (3) carrying out strength test and internal quality inspection on the performance of the large-thickness composite material prepared by die pressing, and carrying out machining treatment to obtain a large-thickness carbon fiber reinforced resin matrix composite material product with a designed shape.
The tensile strength of the composite material prepared by the embodiment is 20MPa, and the internal quality has no defects such as layering and pores.
Example 3
The mould pressing preparation method of the large-thickness carbon fiber reinforced resin matrix composite material comprises the following steps:
(1) Processing carbon fiber cloth and resin into prepreg cloth, and selecting carbon fiber plain cloth with the resin content of 30 percent; (2) The plain cloth adopts non-continuous bags to spread layers in parallel, and the proportion of the thickness of the spread layers of the pre-impregnated cloth to the thickness of the required composite material product is 1:0.8; (3) Vacuumizing once every 30 layers of carbon fiber prepreg cloth are laid, ensuring that the prepreg cloth is smooth in laying and free of air bubbles, keeping the vacuum pressure less than-0.09 MPa, and keeping the pressure for 30min; (4) After the layering is finished, closing the die of the tool, putting the die in a flat vulcanizing machine for pressurizing and curing, wherein in the whole process, the pressure range is controlled to be 10MPa, the temperature range is controlled to be 160 ℃, and the temperature is kept for 2h; (5) And (3) carrying out strength test and internal quality inspection on the performance of the large-thickness composite material prepared by die pressing, and carrying out machining treatment to obtain a large-thickness carbon fiber reinforced resin matrix composite material product with a designed shape.
The tensile strength of the composite material prepared by the embodiment is 15MPa, and the internal quality has no defects such as layering and pores.
Example 4
The mould pressing preparation method of the large-thickness carbon fiber reinforced resin matrix composite material comprises the following steps:
(1) Processing carbon fiber cloth and resin into prepreg cloth, and selecting carbon fiber plain cloth and unidirectional cloth with the resin content of 50%; (2) Plain cloth adopts continuous cladding to spread the layer, and unidirectional cloth adopts the parallel layer of spreading of discontinuous package, and the proportion of prepreg cloth layer thickness and required combined material product thickness is 1:0.8; (3) Vacuumizing once every 30 layers of carbon fiber prepreg cloth are laid, ensuring that the prepreg cloth is smooth in laying and free of air bubbles, keeping the vacuum pressure less than-0.09 MPa, and keeping the pressure for 30min; (4) After layering is finished, closing the tooling, putting the tooling in a flat vulcanizing machine for pressurizing and curing, wherein in the whole process, the pressure range is controlled at 10MPa, the temperature range is controlled at 160 ℃, and the heat is preserved for 2 hours; (5) And (3) carrying out strength test and internal quality inspection on the performance of the large-thickness composite material prepared by die pressing, and carrying out machining treatment to obtain a large-thickness carbon fiber reinforced resin matrix composite material product with a designed shape.
The tensile strength of the composite material prepared by the embodiment is 20MPa, and the internal quality has no defects such as layering and pores.
Example 5
The mould pressing preparation method of the large-thickness carbon fiber reinforced resin matrix composite material comprises the following steps:
(1) Processing carbon fiber cloth and resin into prepreg cloth, and selecting carbon fiber plain cloth and unidirectional cloth with the resin content of 30 percent; (2) Plain cloth adopts continuous cladding to spread the layer, and unidirectional cloth adopts the parallel layer of spreading of discontinuous package, and the proportion of prepreg cloth layer thickness and required combined material product thickness is 1:0.9; (3) Vacuumizing once every 30 layers of carbon fiber prepreg cloth are laid, ensuring that the prepreg cloth is smooth in laying and free of air bubbles, keeping the vacuum pressure less than-0.09 MPa, and keeping the pressure for 30min; (4) After the layering is finished, closing the die of the tool, putting the die in a flat vulcanizing machine for pressurizing and curing, wherein in the whole process, the pressure range is controlled to be 10MPa, the temperature range is controlled to be 160 ℃, and the temperature is kept for 2h; (5) And (3) carrying out strength test and internal quality inspection on the performance of the large-thickness composite material prepared by die pressing, and carrying out machining treatment to obtain a large-thickness carbon fiber reinforced resin matrix composite material product with a designed shape.
The tensile strength of the composite material prepared by the embodiment is 23MPa, and the internal quality has no defects such as layering and pores.
Example 6
The mould pressing preparation method of the large-thickness carbon fiber reinforced resin matrix composite material comprises the following steps:
(1) Processing carbon fiber cloth and resin to prepare prepreg cloth, and selecting carbon fiber plain cloth and unidirectional cloth with the resin content of 30%; (2) The plain cloth adopts continuous coating and lays layers, the unidirectional cloth adopts non-continuous bag parallel laying layers, and the proportion of the thickness of the laying layers of the prepreg cloth to the thickness of the required composite material product is 1:0.8; (3) Vacuumizing once every 30 layers of carbon fiber prepreg cloth are laid, ensuring that the prepreg cloth is smooth in laying and free of air bubbles, keeping the vacuum pressure less than-0.09 MPa, and keeping the pressure for 60min; (4) After layering is finished, closing the tooling, putting the tooling in a flat vulcanizing machine for pressurizing and curing, wherein in the whole process, the pressure range is controlled at 10MPa, the temperature range is controlled at 160 ℃, and the heat is preserved for 2 hours; (5) And (3) carrying out strength test and internal quality inspection on the performance of the large-thickness composite material prepared by die pressing, and carrying out machining treatment to obtain a large-thickness carbon fiber reinforced resin matrix composite material product with a designed shape.
The tensile strength of the composite material prepared by the embodiment is 28MPa, and the internal quality has no defects such as layering and pores.
Example 7
The mould pressing preparation method of the large-thickness carbon fiber reinforced resin matrix composite material comprises the following steps:
(1) Processing carbon fiber cloth and resin into prepreg cloth, and selecting carbon fiber plain cloth and unidirectional cloth with the resin content of 30 percent; (2) The plain cloth adopts continuous coating and lays layers, the unidirectional cloth adopts non-continuous bag parallel laying layers, and the proportion of the thickness of the laying layers of the prepreg cloth to the thickness of the required composite material product is 1:0.8; (3) Vacuumizing once every 30 layers of carbon fiber prepreg cloth are laid, ensuring that the prepreg cloth is smooth in laying and free of air bubbles, keeping the vacuum pressure less than-0.09 MPa, and keeping the pressure for 60min; (4) After the layering is finished, closing the die of the tool, putting the die in a flat vulcanizing machine for pressurizing and curing, wherein in the whole process, the pressure range is controlled to be 15MPa, the temperature range is controlled to be 180 ℃, and the temperature is kept for 3h; (5) And (3) carrying out strength test and internal quality inspection on the performance of the large-thickness composite material prepared by die pressing, and carrying out machining treatment to obtain a large-thickness carbon fiber reinforced resin matrix composite material product with a designed shape.
The tensile strength of the composite material prepared by the embodiment is 27MPa, and the internal quality has no defects such as layering and pores.
The above description is only an embodiment of the present invention, and it should be noted that any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the protection scope of the present invention, and the rest that is not described in detail is the prior art.
Claims (4)
1. A mould pressing preparation method of a large-thickness carbon fiber reinforced resin matrix composite material is characterized by comprising the following steps: the method comprises the following steps:
1) Preparing a prepreg cloth: processing carbon fiber cloth and resin to prepare prepreg cloth; the resin is selected from epoxy resins; the resin content of the prepreg is 30-50%;
2) Laying prepreg cloth: cutting the prepreg cloth into a designed shape, and then layering in a tool; layering is carried out in a continuous coating layering mode and a non-continuous parallel layering mode; the continuous coating and layering mode is that the upper layer, the lower layer and any side surface are layered by continuous pre-impregnated cloth, and the rest part is non-continuous parallel layering; the non-continuous parallel layering mode is that the prepreg cloth is parallel layering, and the prepreg cloth between each two layers is not continuous;
3) Vacuumizing treatment: carrying out intermittent vacuum-pumping treatment in the process of laying the prepreg cloth; the intermittent vacuum-pumping treatment is to pump vacuum once when laying 30-40 layers of pre-impregnated cloth; the vacuum pressure of the intermittent vacuum pumping treatment is less than or equal to-0.09 MPa, and the pressure is maintained for 30-60 min;
4) Die pressing and curing: after the layering is finished, closing the die of the tool and putting the die in a flat vulcanizing machine for pressurizing and curing; the pressure of the pressurization and solidification is 10-15 MPa, the temperature is 160-180 ℃, and the heat preservation time is 2-3 h;
5) And (3) post-treatment: and (4) obtaining a large-thickness carbon fiber reinforced resin matrix composite product through machining treatment.
2. The mould pressing preparation method of the large-thickness carbon fiber reinforced resin matrix composite material as claimed in claim 1, characterized in that: in the step 1), the carbon fiber cloth is selected from plain cloth and/or unidirectional cloth.
3. The die pressing preparation method of the large-thickness carbon fiber reinforced resin matrix composite material as claimed in claim 1, wherein the method comprises the following steps: in the step 2), the ratio of the thickness of the prepreg cloth laying layer to the thickness of the large-thickness carbon fiber reinforced resin matrix composite product is 1:0.8 to 0.9.
4. The die pressing preparation method of the large-thickness carbon fiber reinforced resin matrix composite material as claimed in claim 1, wherein the method comprises the following steps: and in the step 5), quality inspection is carried out before machining treatment, and machining treatment is carried out after the product is qualified through inspection to obtain a large-thickness carbon fiber reinforced resin matrix composite product with a designed shape.
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| CN110509629A (en) * | 2019-08-30 | 2019-11-29 | 北京航空航天大学 | A kind of carbon fiber-carbon nanotube intertexture laminated composite and preparation method thereof |
| CN111746000A (en) * | 2020-06-16 | 2020-10-09 | 上海复合材料科技有限公司 | Edge strip slender composite material wing surface and forming method thereof |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102514206B (en) * | 2011-12-07 | 2014-02-05 | 长春工业大学 | Production method of phenol formaldehyde epoxy vinyl ester resin/carbon fiber composite material |
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2021
- 2021-06-17 CN CN202110674285.7A patent/CN113524718B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4786343A (en) * | 1985-05-10 | 1988-11-22 | The Boeing Company | Method of making delamination resistant composites |
| CN102152502A (en) * | 2010-12-07 | 2011-08-17 | 沈阳航空航天大学 | Preparation method of high-intensity composite material grid structure |
| CN109228547A (en) * | 2018-10-24 | 2019-01-18 | 株洲时代新材料科技股份有限公司 | Fiber ply angles, the drawing and extruding section bar of reinforcing material |
| CN110509629A (en) * | 2019-08-30 | 2019-11-29 | 北京航空航天大学 | A kind of carbon fiber-carbon nanotube intertexture laminated composite and preparation method thereof |
| CN111746000A (en) * | 2020-06-16 | 2020-10-09 | 上海复合材料科技有限公司 | Edge strip slender composite material wing surface and forming method thereof |
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