CN112454943A - Carbon fiber aramid fiber composite material and integrated forming preparation method thereof - Google Patents
Carbon fiber aramid fiber composite material and integrated forming preparation method thereof Download PDFInfo
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- CN112454943A CN112454943A CN202011235479.9A CN202011235479A CN112454943A CN 112454943 A CN112454943 A CN 112454943A CN 202011235479 A CN202011235479 A CN 202011235479A CN 112454943 A CN112454943 A CN 112454943A
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- carbon fiber
- epoxy resin
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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
- B29C70/342—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 using isostatic pressure
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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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- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08L—COMPOSITIONS OF MACROMOLECULAR COMPOUNDS
- C08L83/00—Compositions of macromolecular compounds obtained by reactions forming in the main chain of the macromolecule a linkage containing silicon with or without sulfur, nitrogen, oxygen or carbon only; Compositions of derivatives of such polymers
- C08L83/04—Polysiloxanes
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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
- C08L2205/00—Polymer mixtures characterised by other features
- C08L2205/03—Polymer mixtures characterised by other features containing three or more polymers in a blend
- C08L2205/035—Polymer mixtures characterised by other features containing three or more polymers in a blend containing four or more polymers in a blend
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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
- C08L2205/00—Polymer mixtures characterised by other features
- C08L2205/14—Polymer mixtures characterised by other features containing polymeric additives characterised by shape
- C08L2205/16—Fibres; Fibrils
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- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Health & Medical Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Medicinal Chemistry (AREA)
- Polymers & Plastics (AREA)
- Organic Chemistry (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
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Abstract
The invention discloses a carbon fiber aramid fiber composite material, wherein an epoxy resin and a curing agent are coated on the surface of carbon fiber cloth to obtain a carbon fiber-epoxy resin layer, an epoxy resin and a curing agent are coated on the surface of aramid fiber cloth to obtain an aramid fiber-epoxy resin layer, and the aramid fiber-epoxy resin layer is laid on the carbon fiber-epoxy resin layer and is heated and cured to obtain a carbon fiber aramid fiber composite material product. The invention adopts an integrated molding process method of a stainless steel or aluminum alloy outer mold and an elastic polymer material inner mold on the basis of the design and preparation of the novel carbon fiber composite material, and the obtained carbon fiber aramid fiber composite material has the advantages of good surface uniformity, no layering, high surface flatness and no obvious bubbles and pores.
Description
Technical Field
The invention relates to the field of carbon fiber composite materials, in particular to a carbon fiber aramid fiber composite material and an integrated forming preparation method thereof.
Background
The carbon fiber material has a plurality of excellent performances such as light weight, high specific strength, high specific modulus, high temperature resistance, small thermal expansion coefficient, high fatigue resistance, good chemical stability and the like, is widely applied to a plurality of fields such as military use, civil use and the like, and is a high and new technology fiber material which is mainly encouraged to be preferentially developed at the present stage in China. However, the carbon fiber structural member product obtained by using the thermosetting resin-based composite material with carbon fibers as the reinforcement through common production and processing processes such as compression molding and the like is prone to have many external defects, such as poor surface uniformity, easy delamination, uneven surface, bubbles and pores.
At present, carbon fiber structural parts, such as the structural forming technology of unmanned aerial vehicle wings, mostly adopt the mode of multiple forming and splicing forming, use two halves mould to splice after well done, can be difficult to avoid producing the fracture after impacting easily at seam crossing. In view of the above-mentioned circumstances, it is necessary to provide a new carbon fiber composite material and an integrated molding process to solve the deficiencies in the prior art.
Disclosure of Invention
The purpose of the invention is as follows: aiming at the defects and defects of the prior art, the invention provides a carbon fiber aramid fiber composite material and an integral forming preparation method thereof, and on the basis of the design and preparation of a novel carbon fiber composite material, an integral forming process method of a stainless steel or aluminum alloy outer mold and an elastic high polymer material inner mold is adopted, so that the obtained carbon fiber aramid fiber composite material has the advantages of good surface uniformity, no layering, high surface flatness and no obvious bubbles and pores.
The technical scheme is as follows: the invention relates to a carbon fiber aramid fiber composite material, which is characterized in that: coating epoxy resin and a curing agent on the surface of the carbon fiber cloth to obtain a carbon fiber-epoxy resin layer, coating the epoxy resin and the curing agent on the surface of the aramid fiber cloth to obtain an aramid fiber-epoxy resin layer, and laying the aramid fiber-epoxy resin layer on the carbon fiber-epoxy resin layer for heating and curing to obtain the carbon fiber aramid fiber composite material product.
Wherein the K number of the carbon fiber is 1K-3K.
Wherein, the aramid fiber is full para-aramid copolymer fiber.
Wherein, the epoxy resin is liquid epoxy resin glue.
Wherein, the curing agent is polybutadiene latex.
The integrated forming preparation method of the carbon fiber aramid fiber composite material is characterized by comprising the following steps of: the method comprises the following steps:
(1) shearing the carbon fiber cloth to a preset size, and uniformly coating a mixture of epoxy resin and a curing agent with a mass ratio of 1.8-2.2: 1 on the surface of the carbon fiber cloth to obtain a carbon fiber-epoxy resin layer; the mass ratio of the mixture of the epoxy resin and the curing agent to the carbon fiber cloth is 0.7-2.2: 1; the curing time of the epoxy resin is 12-24 h; preferably, the mass ratio of the epoxy resin to the curing agent is 2: 1;
(2) shearing the aramid fiber cloth to a preset size, and uniformly coating a mixture of epoxy resin and a curing agent with a mass ratio of 1.8-2.2: 1 on the surface of the aramid fiber cloth to obtain an aramid fiber-epoxy resin layer; the mass ratio of the mixture of the epoxy resin and the curing agent to the aramid fiber cloth is 0.7-2.0: 1; the curing time of the epoxy resin is 12-24 h; preferably, the mass ratio of the epoxy resin to the curing agent is 2: 1;
(3) placing the carbon fiber-epoxy resin layer and the aramid fiber-epoxy resin layer into a mold, and injecting a liquid polymer elastic material into the hollow part between the mold and the carbon fiber; heating and curing in a vacuum environment;
(4) and demolding to obtain the carbon fiber aramid fiber composite material product.
Wherein, the molding is carried out by combining a stainless steel or aluminum alloy outer mold and a liquid polymer elastic material inner mold. The melting point of the die is not lower than 600 ℃, so that the die is not deformed in a long-time high-temperature environment.
Wherein, the liquid polymer elastic material in the step (3) is any two of polydimethylsiloxane, dibenzoyl peroxide and di-tert-butyl peroxy hexane.
Wherein the vacuum degree of the vacuum environment is more than or equal to 102Pa。
Wherein the curing temperature of the heating curing is 80-120 ℃, and the curing time is 1-5 h. Preferably, the curing temperature is 90-110 ℃, and the curing time is 2-4 h.
Has the advantages that: compared with the prior art, the invention has the following remarkable advantages: the invention adopts an integrated molding process method of a stainless steel or aluminum alloy outer mold and an elastic high polymer material inner mold on the basis of the design and preparation of the novel carbon fiber composite material. The obtained carbon fiber aramid fiber composite material has good surface uniformity, no layering, high surface flatness and no obvious bubbles and pores, and solves the problems that the bonding force at the joint is not tight enough and the joint is easy to break under the action of external force caused by the traditional carbon fiber multi-splicing process. The invention has the other characteristic that the structure is formed in one step, the elastic material in the structure formed in one step has a supporting function, and can be taken out from the structure after the process is finished, so that the elastic material can be easily demoulded, and the structure has a good effect on manufacturing of parts of unmanned aerial vehicle wings, other fields and the like.
Drawings
FIG. 1 is a surface perspective view of a carbon fiber aramid fiber composite material of the present invention.
Detailed Description
The technical solution of the present invention is further described with reference to the accompanying drawings and the detailed description.
According to the carbon fiber-aramid fiber composite material, the surface of carbon fiber cloth is coated with epoxy resin and a curing agent to obtain a carbon fiber-epoxy resin layer, the surface of aramid fiber cloth is coated with epoxy resin and a curing agent to obtain an aramid fiber-epoxy resin layer, and the aramid fiber-epoxy resin layer is laid on the carbon fiber-epoxy resin layer and is heated and cured to obtain a carbon fiber-aramid fiber composite material product. Wherein the K number of the carbon fiber is 1K-3K; the aramid fiber is full para-aramid copolymer fiber; the epoxy resin is liquid epoxy resin glue; the curing agent is polybutadiene latex.
The integral forming preparation method of the carbon fiber aramid fiber composite material comprises the following steps:
(1) shearing the carbon fiber cloth to a preset size, and uniformly coating a mixture of epoxy resin and a curing agent with a mass ratio of 1.8-2.2: 1 on the surface of the carbon fiber cloth to obtain a carbon fiber-epoxy resin layer; the mass ratio of the mixture of the epoxy resin and the curing agent to the carbon fiber cloth is 0.7-2.2: 1; the curing time of the epoxy resin is 12-24 h; preferably, the mass ratio of the epoxy resin to the curing agent is 2: 1;
(2) shearing the aramid fiber cloth to a preset size, and uniformly coating a mixture of epoxy resin and a curing agent with a mass ratio of 1.8-2.2: 1 on the surface of the aramid fiber cloth to obtain an aramid fiber-epoxy resin layer; the mass ratio of the mixture of the epoxy resin and the curing agent to the aramid fiber cloth is 0.7-2.0: 1; the curing time of the epoxy resin is 12-24 h; preferably, the mass ratio of the epoxy resin to the curing agent is 2: 1;
(3) placing the carbon fiber-epoxy resin layer and the aramid fiber-epoxy resin layer into a mold, and injecting a liquid polymer elastic material into the hollow part between the mold and the carbon fiber; heating and curing in a vacuum environment; the liquid polymer elastic material is any two of polydimethylsiloxane, dibenzoyl peroxide and di-tert-butyl peroxy hexane; the vacuum degree of the vacuum environment is more than or equal to 102Pa; the curing temperature of heating curing is 80-120 ℃, and the curing time is 1-5 h; preferably, the curing temperature is 90-110 ℃, and the curing time is 2-4 h;
(4) and demolding to obtain the carbon fiber aramid fiber composite material product.
Wherein, the molding is carried out by combining a stainless steel or aluminum alloy outer mold and a liquid polymer elastic material inner mold. The melting point of the die is not lower than 600 ℃, so that the die is not deformed in a long-time high-temperature environment.
Example (b):
the integrated forming preparation method of the carbon fiber aramid fiber composite material for the aileron of the unmanned aerial vehicle comprises the following steps:
(1) shearing the carbon fiber cloth to a preset size, and uniformly coating a mixture of epoxy resin and a curing agent with a mass ratio of 2:1 on the surface of the carbon fiber cloth to obtain a carbon fiber-epoxy resin layer; the mass ratio of the mixture of the epoxy resin and the curing agent to the carbon fiber cloth is 1: 1.
(2) Shearing the aramid fiber cloth to a preset size, and uniformly coating a mixture of epoxy resin and a curing agent in a mass ratio of 2:1 on the surface of the aramid fiber cloth to obtain an aramid fiber-epoxy resin layer; the mass ratio of the mixture of the epoxy resin and the curing agent to the aramid fiber cloth is 1.5: 1.
(3) The aramid fiber-epoxy resin layer is laid on the carbon fiber-epoxy resin layer and is placed into an unmanned aerial vehicle aileron mould after being flattened, the redundant material part is cut off along the edge of the mould, and then the upper half mould and the lower half mould are aligned and fixed firmly; and injecting a liquid high-molecular elastic material into the mold, and closing the mold.
Putting the integral structure into a vacuum bag, then inserting a vacuum tube and sealing the vacuum tube by using vacuum mud; continuously vacuumizing and heating at 90 ℃ for 4h by a vacuum pump connected with a vacuum tube; and separating the mold from the carbon fiber finished product to obtain the carbon fiber unmanned aerial vehicle aileron. And heating for curing.
(4) And (4) obtaining an unmanned aerial vehicle aileron product made of the carbon fiber aramid fiber composite material after demoulding.
The surface morphology (magnification of 500 times and scale of 100 mu m) of the aileron product prepared in the embodiment is observed by an inverted metallographic microscope of Leica DMi 8A in germany, and it can be seen from fig. 1 that the surface morphology uniformity of the composite material is good, the carbon fiber filaments are not obviously exposed, the surface flatness is high, and no obvious bubbles and pores exist.
Claims (10)
1. A carbon fiber aramid fiber composite material is characterized in that: coating epoxy resin and a curing agent on the surface of the carbon fiber cloth to obtain a carbon fiber-epoxy resin layer, coating the epoxy resin and the curing agent on the surface of the aramid fiber cloth to obtain an aramid fiber-epoxy resin layer, and laying the aramid fiber-epoxy resin layer on the carbon fiber-epoxy resin layer for heating and curing to obtain the carbon fiber aramid fiber composite material product.
2. A carbon fiber aramid fiber composite material as claimed in claim 1 wherein: the K number of the carbon fiber is 1K-3K.
3. A carbon fiber aramid fiber composite material as claimed in claim 1 wherein: the aramid fiber is full para-aramid copolymer fiber.
4. A carbon fiber aramid fiber composite material as claimed in claim 1 wherein: the epoxy resin is liquid epoxy resin glue.
5. A carbon fiber aramid fiber composite material as claimed in claim 1 wherein: the curing agent is polybutadiene latex.
6. A process for the integral formation of a carbon fibre-aramid fibre composite material as claimed in any one of claims 1 to 4, characterised in that: the method comprises the following steps:
(1) shearing the carbon fiber cloth to a preset size, and uniformly coating a mixture of epoxy resin and a curing agent with a mass ratio of 1.8-2.2: 1 on the surface of the carbon fiber cloth to obtain a carbon fiber-epoxy resin layer; the mass ratio of the mixture of the epoxy resin and the curing agent to the carbon fiber cloth is 0.7-2.2: 1;
(2) shearing the aramid fiber cloth to a preset size, and uniformly coating a mixture of epoxy resin and a curing agent with a mass ratio of 1.8-2.2: 1 on the surface of the aramid fiber cloth to obtain an aramid fiber-epoxy resin layer; the mass ratio of the mixture of the epoxy resin and the curing agent to the aramid fiber cloth is 0.7-2.0: 1;
(3) placing the carbon fiber-epoxy resin layer and the aramid fiber-epoxy resin layer into a mold, and injecting a liquid polymer elastic material into the hollow part between the mold and the carbon fiber; heating and curing in a vacuum environment;
(4) and demolding to obtain the carbon fiber aramid fiber composite material product.
7. The method of integrally forming a carbon fiber-aramid fiber composite material as claimed in claim 6, wherein: the molding is carried out by combining a stainless steel or aluminum alloy outer mold with a liquid polymer elastic material inner mold.
8. The method of integrally forming a carbon fiber-aramid fiber composite material as claimed in claim 6, wherein: the liquid polymer elastic material in the step (3) is any two of polydimethylsiloxane, dibenzoyl peroxide and di-tert-butyl peroxy hexane.
9. The method of integrally forming a carbon fiber-aramid fiber composite material as claimed in claim 6, wherein: the vacuum degree of the vacuum environment is more than or equal to 102Pa。
10. The method of integrally forming a carbon fiber-aramid fiber composite material as claimed in claim 6, wherein: the curing temperature of the heating curing is 80-120 ℃, and the curing time is 1-5 h.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011235479.9A CN112454943A (en) | 2020-11-06 | 2020-11-06 | Carbon fiber aramid fiber composite material and integrated forming preparation method thereof |
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| CN202011235479.9A CN112454943A (en) | 2020-11-06 | 2020-11-06 | Carbon fiber aramid fiber composite material and integrated forming preparation method thereof |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CH430163A (en) * | 1963-04-22 | 1967-02-15 | Haenle Eugen | Process for the production of bending and torsion-resistant shell components in the form of aircraft wings, fuselages, fan blades or the like from glass fiber reinforced plastic |
| CN104626605A (en) * | 2014-12-16 | 2015-05-20 | 西安爱生技术集团公司 | Composite material wing integral molding technological method and composite material wing integral molding tool |
| CN205150216U (en) * | 2015-11-24 | 2016-04-13 | 中国航天时代电子公司 | Unmanned aerial vehicle's foam presss from both sides core wing |
| CN108891040A (en) * | 2018-06-21 | 2018-11-27 | 西安爱生技术集团公司 | A kind of small and medium size unmanned aerial vehicles composite horizontal empennage manufacturing method |
| CN208558492U (en) * | 2018-03-15 | 2019-03-01 | 浙江大学 | Comprehensive zero expansion composite material laminate in plane |
| CN110193955A (en) * | 2019-07-03 | 2019-09-03 | 西安爱生技术集团公司 | A kind of small and medium size unmanned aerial vehicles composite material outer wing technological forming method |
-
2020
- 2020-11-06 CN CN202011235479.9A patent/CN112454943A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CH430163A (en) * | 1963-04-22 | 1967-02-15 | Haenle Eugen | Process for the production of bending and torsion-resistant shell components in the form of aircraft wings, fuselages, fan blades or the like from glass fiber reinforced plastic |
| CN104626605A (en) * | 2014-12-16 | 2015-05-20 | 西安爱生技术集团公司 | Composite material wing integral molding technological method and composite material wing integral molding tool |
| CN205150216U (en) * | 2015-11-24 | 2016-04-13 | 中国航天时代电子公司 | Unmanned aerial vehicle's foam presss from both sides core wing |
| CN208558492U (en) * | 2018-03-15 | 2019-03-01 | 浙江大学 | Comprehensive zero expansion composite material laminate in plane |
| CN108891040A (en) * | 2018-06-21 | 2018-11-27 | 西安爱生技术集团公司 | A kind of small and medium size unmanned aerial vehicles composite horizontal empennage manufacturing method |
| CN110193955A (en) * | 2019-07-03 | 2019-09-03 | 西安爱生技术集团公司 | A kind of small and medium size unmanned aerial vehicles composite material outer wing technological forming method |
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