CN111605223A - High-performance carbon fiber composite material based on discontinuous fiber structure and preparation method thereof - Google Patents
High-performance carbon fiber composite material based on discontinuous fiber structure and preparation method thereof Download PDFInfo
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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
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- 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
- B29C70/345—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 matched moulds
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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
- B29C70/06—Fibrous reinforcements only
- B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
- B29C70/12—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of short length, e.g. in the form of a mat
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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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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
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Abstract
The invention belongs to the technical field of composite materials, and particularly relates to a high-performance carbon fiber composite material based on a discontinuous fiber structure. The carbon fiber prepreg selected for the composite material is mechanically cut to obtain a non-continuous fiber structure, the included angle between the incision direction and the fiber direction during cutting is alpha, and alpha is less than 5 degrees and less than 25 degrees. Compared with the traditional notch structure, the notch structure of the discontinuous fiber is adjusted, so that the tensile strength, the tensile modulus and the energy absorption performance of the carbon fiber composite material based on the discontinuous fiber structure are improved, and meanwhile, the carbon fiber composite material based on the discontinuous fiber structure still has good pseudo-ductility and formability of a complex geometric structure. The preparation method of the composite material is simple to operate and convenient for industrial production.
Description
Technical Field
The invention belongs to the technical field of composite materials, and particularly relates to a high-performance carbon fiber composite material based on a discontinuous fiber structure.
Background
The new material industry is one of the strategic emerging industries of the country and determines the equipment development level of one country, so the "first generation materials and first generation equipment". Advanced countries such as Europe and America attach great importance to the development of new materials, and specific development plans are proposed, such as German industry 4.0, national nanotechnology plan and material genome plan in the United states. The carbon fiber composite material (CFRP) is used as a novel military and civil dual-purpose material, and is an important guarantee for realizing the development of industries such as aerospace equipment lightweight, accelerated building, energy, traffic and the like.
However, the mutual exclusion of strength and toughness of the conventional carbon fiber composite material is one of the important problems which have long plagued the design field. Although CFRP has the advantages of light weight, high strength, high modulus, etc., its brittle nature and weak residual strength limit its application expansion to some extent. For example, a slight impact causes a localized structural damage inside the CFRP, which, while intact in appearance, is susceptible to brittle fracture under loads that are far below the design load without significant damage warning. To ensure safety, the maximum allowable stress for CFRP tends to be a greater safety factor than other, more ductile materials. This design limitation not only does not fully exploit the performance advantages of CFRP, but also makes it unsuitable for applications where load conditions are not easily predictable.
Therefore, the material design concept capable of simultaneously enhancing toughness is a long-standing challenge in studying high-performance CFRP, namely how to make CFRP have a nonlinear progressive failure process similar to that of a metal material so that the CFRP has a significant failure early warning phenomenon before final failure, that is, making CFRP change from a brittle failure mode to a pseudo-ductile failure mode, and generating pseudo-ductile strain before CFRP failure fracture, so as to achieve toughness, as shown in fig. 1.
A quick and direct method of increasing the ductility of carbon fiber reinforced composites is to mix other fibers with better ductility with carbon fibers to form a hybrid composite. That is, the matrix contains two or more types of reinforcing fibers, i.e., low elongation fibers (LE) and high elongation fibers (HE). Wherein the LE fibers are generally broken first and the HE fibers continue to bear in the event the former is broken. The most common hybrid composite structures are in three forms, inter-layer hybrid lay-up, intra-layer hybrid weave, intra-layer fiber mixing, as shown in fig. 2. Generally, carbon fibers belong to LE. After the carbon fiber and other HEs are mixed to prepare the fiber mixed composite material, when the material is failed in stretching, the carbon fiber is firstly broken, and the HE continues to bear external force until the carbon fiber is broken after being broken. Taking the carbon fiber-glass fiber hybrid composite material as an example, different hybrid composite structures have significant effects on the mechanical properties of the material, and the failure modes occurring when the material fails are also different, as shown in fig. 3. In recent years, due to the continuous development of an ultrathin carbon fiber prepreg process, excellent mechanical properties of the ultrathin carbon fiber prepreg are reported, and due to the low energy release rate of the ultrathin carbon fiber prepreg, the composite material can delay the final failure of the composite material by inhibiting delamination failure and overall fracture, so that the ultrathin carbon fiber prepreg has higher allowable design strain. However, the current ultrathin carbon fiber prepreg still cannot meet the comprehensive requirements on the strength and toughness of materials in certain fields, such as aerospace, automobile, energy and other industries.
On the other hand, the discontinuous carbon fiber reinforced composite material is prepared by preparing the traditional continuous fiber prepreg into the oriented discontinuous carbon fiber prepreg by a mechanical high-frequency cutting method and curing the oriented discontinuous carbon fiber prepreg. The discontinuous fiber structure improves the material molding flowability and improves the failure characteristic and the energy absorption characteristic of the composite material. As shown in FIG. 4, the weak structural strength of the continuous carbon fiber reinforced composite material, which has no carbon fiber distribution but resin aggregation, is liable to occur at the position of the structural discontinuity, while the weak structural strength of the discontinuous carbon fiber reinforced composite material is remarkably improved (A new compression-molding processing using interfacial polymerization strands, I.Taketa, T.Okabe, A.Kitano.composites: Part A39 (2008) 1884-1890). As can be seen from the stress-strain curve of the discontinuous carbon fiber Reinforced metal composite in FIG. 5, the discontinuous carbon fiber Reinforced composite exhibits a non-linear failure characteristic (underfence of fiber length on the tensebehlavor of fiber metals with discrete requirements for information. Jua Xue, Wen-Xue Wang, et al. journal of Reinforced Plastics and Composites, July 6,2015). However, in all of the conventional non-continuous fiber structures, slits perpendicular to the fiber direction are introduced into the prepreg, and as shown in fig. 6a, the strength of the material is weakened, and therefore, the slits are easily broken at a low load level, and the high strength characteristics of the carbon fibers cannot be fully developed. As shown in FIG. 7, the tensile Strength of the current non-continuous chopped carbon fiber prepreg (UASC) laminate is about 400MPa, which is significantly reduced compared to the tensile Strength of the conventional continuous carbon fiber reinforced laminate of about 800MPa (Strength improvement in unidentional aligned chlorinated laminates with interfacial coating Tougening. I. Taketa, T.Okabe, A.Kitano.Compounds: Part A40 (2009) 1174-.
The invention aims at the mutual exclusion problem of the strength and the toughness of the CFRP, develops the research of the high-performance pseudo-ductility carbon fiber composite material based on the excellent performance of the discontinuous fiber structure in the process of improving the damage capacity of the material, and provides a novel discontinuous fiber reinforced structure and a laying structure. Compared with the existing discontinuous carbon fiber composite material, the high-performance carbon fiber composite material based on the discontinuous fiber structure provided by the invention has the advantages that the strength is obviously improved, the high-strength characteristic of carbon fiber is better exerted, and meanwhile, the high-performance carbon fiber composite material has a better energy absorption characteristic.
Disclosure of Invention
The invention aims to overcome the defects of the prior art, and designs a novel discontinuous fiber reinforced structure in view of the important practical requirements of the industries such as aerospace, automobiles and energy sources on carbon fiber composite materials and the problems in the research on high-performance pseudo-ductile carbon fiber composite materials at the present stage. By improving the non-continuous fiber reinforced structure, the effect of non-continuous fibers on the aspects of improving the damage capacity and the flowability of the material can be fully excavated, the pseudo-ductility of the ultrathin carbon fiber prepreg laminated plate and the formability of a complex geometric structure are further improved, the reinforcing effect of carbon fibers is better kept, the high-strength characteristic of the carbon fibers is reflected, the energy absorption performance of the material is improved, and the high-performance carbon fiber composite material based on the non-continuous fiber structure is finally obtained.
The invention also aims to provide a preparation method of the high-performance carbon fiber composite material based on the discontinuous fiber structure.
The invention provides a high-performance carbon fiber composite material based on a discontinuous fiber structure, wherein a carbon fiber prepreg selected for the composite material is mechanically cut to obtain the discontinuous fiber structure, the included angle between the incision direction and the fiber direction during cutting is alpha, the included angle is 5 degrees < alpha <25 degrees, all incisions are linear, and the carbon fiber prepreg is cut through.
Further, the cuts cut the entire carbon fiber prepreg. At this point, each cut is continuous, which may be referred to as a continuous cut.
Further, the length of the incisions in the direction perpendicular to the fibers is d, 2mm < d <15mm, and the incisions in the same direction are staggered.
Furthermore, all the notches are parallel to each other and are in a one-way staggered distribution structure. In this case, the slits are arranged in a step-like manner when viewed in the slit direction, and may be referred to as step slits. Or, a part of the incisions and the fiber direction deflect an angle alpha leftwards, the other part of the incisions and the fiber direction deflect an angle alpha rightwards, and the incisions in the same direction are distributed in a staggered manner to form a bidirectional staggered distribution structure. At this time, the incision exhibits two angular changes as viewed from the fiber direction, and may be referred to as a double angle incision.
Furthermore, the carbon fiber composite material is also mixed with glass fibers, and the mode of mixing the carbon fibers and the glass fibers in the carbon fiber composite material is interlayer mixed laying or in-layer mixed weaving.
The invention also provides a preparation method of the high-performance carbon fiber composite material based on the discontinuous fiber structure, which comprises the following steps:
firstly, guiding a cutting design drawing into a computer according to design requirements, and cutting the carbon fiber prepreg through a numerical control cutting bed;
secondly, laying carbon fiber prepreg on the lower die surface according to a design structure;
covering an upper die, sealing the die, and vacuumizing the die;
and fourthly, completing high-temperature forming according to the designed forming process, opening the mould, and taking out the composite material to obtain the high-performance carbon fiber composite material based on the discontinuous fiber structure.
Further, the carbon fiber prepreg used in the first step needs to be left at 25 ℃. + -. 2 ℃ for 10 hours or more for softening adjustment.
Furthermore, in the second step, the mold needs to be cleaned first, and the isolation plastic films and the release paper on the two side surfaces of the prepreg are removed when the carbon fiber prepreg is laid.
Further, in the second step, when the carbon fiber prepreg is laid, the carbon fiber prepreg and the glass fiber prepreg are laid in sequence according to a designed carbon fiber-glass fiber hybrid composite structure, or a woven product formed by weaving the carbon fiber prepreg and the glass fiber prepreg is laid. When the carbon fiber prepreg and the glass fiber prepreg are laid firstly and then, the carbon fiber and the glass fiber are mixed and laid in an interlayer mode; when a woven product of carbon fiber prepreg and glass fiber prepreg is laid, the carbon fiber and the glass fiber are woven in an in-layer mixed manner.
Further, in the third step, before the mold is sealed, the suction felt is laid on the surface of the upper mold. The operation of sealing the mold includes: sticking a sealing adhesive tape along the edge of the mould; and laying the vacuum bag film on the adhesive absorption felt, gradually removing the isolation paper of the sealing adhesive tape, and tightly attaching the vacuum bag film to the sealing adhesive tape.
When the discontinuous fiber structure receives external force, when the external force is small, the material does not deform or deforms very little under the reinforcing action of the chopped fibers; with the increase of the external force, the strength of the material matrix is lower than that of the chopped fibers, the material matrix is obviously deformed at the cut of the chopped fibers, and the positions of the chopped fibers are deviated along with the matrix. Due to the staggered distribution of the notches, the composite material shows obvious extension characteristics in the fiber direction. The energy generated by partial external force can be absorbed in the process, the material damage capacity is improved, and meanwhile, the composite material fluidity is improved due to the deviation of the chopped fibers along with the matrix. Traditional discontinuous fiber structure because the incision is perpendicular with the fibre direction, on the fibre direction, can bear tensile fibre suddenly and reduce on incision department and the perpendicular plane of fibre direction for combined material obviously reduces at the biggest bearing capacity of incision department, has weakened combined material's intensity, appears the incision easily under lower load level and destroys, can not the high strength characteristic of full play carbon fiber.
The notch of the composite material forms an included angle alpha with the fiber direction, so that the number of fibers capable of bearing tensile force on the plane of the notch perpendicular to the fiber direction is reduced in the fiber direction, although the number of fibers capable of bearing tensile force on a plurality of continuous planes is reduced, the maximum bearing capacity of the composite material at the whole notch is reduced, the load level when the notch is damaged is improved, and the high-strength characteristic of the carbon fibers is exerted best. Meanwhile, the maximum bearing capacity of the composite material at the notch is improved compared with the maximum bearing capacity of the traditional discontinuous fiber composite material at the notch, so that the energy absorption performance of the composite material is correspondingly improved.
In addition, the laminated plate based on the carbon fiber composite material with the non-continuous fiber structure still has good pseudo-ductility and formability with a complex geometry.
The invention not only provides a novel discontinuous fiber reinforced structure on the basis of theoretical analysis, but also researches the influence rule of the discontinuous fiber structure parameters on the mechanical properties such as material strength, modulus, energy absorption characteristic, pseudo-ductility and the like.
Through stress analysis of the discontinuous structure notch, failure of a base material at the notch is approximately calculated according to a laminated plate and an elastoplasticity theory, and the influence of a notch angle alpha (5 degrees < alpha <25 degrees) and a size parameter d (2mm < d <15mm) on material strength is preliminarily estimated. By adopting an orthogonal experiment method, the material performance parameters (tensile strength and tensile modulus) of the discontinuous fiber reinforced single-layer board with different structural parameters (alpha and d) are obtained, so that the inclination angle of the notch and the size parameter of the chopped fiber are optimally designed, and the influence rule of the parameters on the mechanical property of the laminated board material is analyzed.
The beneficial effects of the invention include:
1. by adjusting the direction and arrangement of the cuts of the discontinuous fibers, the tensile strength, tensile modulus and energy absorption performance of the discontinuous carbon fiber composite material are improved.
2. The carbon fiber composite material based on the discontinuous fiber structure still has good pseudo-ductility and formability of a complex geometric structure.
3. The preparation method of the composite material is simple to operate and convenient for industrial production.
Drawings
FIG. 1 is a schematic diagram of pseudo-ductility of a carbon fiber composite;
fig. 2 is a graph of three main hybrid composite structures of the hybrid composite: (a) interlayer mixed laying, (b) layer mixed weaving, (c) layer fiber mixing;
fig. 3 is a schematic view of a failure mode and a stress-strain curve of a carbon fiber-glass fiber hybrid composite material: (a) overall fracture, (b) layered fracture, (c) carbon fiber multiple fracture, (d) carbon fiber multiple fracture and layered fracture;
FIG. 4 is a structural comparison of a T-shaped plate formed by continuous carbon fibers and discontinuous carbon fibers: (a) a continuous carbon fiber reinforced composite, (b) a discontinuous fiber reinforced composite;
fig. 5 is a schematic structural diagram and a nonlinear failure curve of a discontinuous carbon fiber reinforced metal composite material: (a) a schematic structural diagram, (b) a non-linear failure curve;
FIG. 6 is a schematic diagram of the cutting pattern of fibers in a non-continuous fiber composite: (a) the method comprises the following steps of (a) traditional staggered distribution notches perpendicular to the fiber direction, (b) unidirectional staggered distribution notches deflected by a small angle with the fiber direction, and (c) bidirectional staggered distribution notches deflected by a small angle with the fiber direction, wherein l is the length of a cut fiber in the fiber direction, d is the length of a notch in the direction perpendicular to the fiber direction, and alpha is an included angle formed by the notches and the fiber direction in a deflected mode (0 degrees < alpha <90 degrees);
FIG. 7 is a comparison of tensile strength and tensile modulus of three laminates of a sheet-shaped plastic film SMC, a non-continuous chopped carbon fiber prepreg UACS and a conventional continuous carbon fiber;
FIG. 8 is a graph illustrating the effect of different thicknesses of non-continuous carbon fiber layers on the pseudo-ductility of a carbon fiber-glass fiber hybrid laminate in example 3 of the present invention;
FIG. 9 is a graph showing a comparison of mechanical properties of a carbon fiber composite material laminate having a discontinuous fiber structure with different notch structures according to example 4 of the present invention: (a) tensile modulus, (b) tensile strength;
FIG. 10 is a graph comparing the energy absorption characteristics of carbon fiber composite laminates having different cut structures and discontinuous fiber structures laid in different ways according to example 5 of the present invention.
Detailed Description
In order to more clearly illustrate the technical solutions of the present invention, the following description is given with reference to specific embodiments and accompanying drawings, and it is obvious that the embodiments in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other embodiments can be obtained according to these embodiments without any creative effort.
Example 1
In the embodiment, carbon fiber composite materials with non-continuous fiber structures with different parameters alpha are prepared. The specific content comprises the following steps:
step one, taking out qualified carbon fiber prepreg from a refrigerator according to experimental requirements, and placing the carbon fiber prepreg at the room temperature of 25 +/-2 ℃ for more than 10 hours for softening adjustment; according to design requirements, guiding a cutting design drawing into a computer, and cutting the carbon fiber prepreg through a numerical control cutting bed; wherein each cut cuts the whole carbon fiber prepreg, and the parameter alpha is shown in table 1;
secondly, cleaning the surface of the mould, and wiping the outer surfaces of the upper mould and the lower mould with alcohol; laying carbon fiber prepreg on the lower die surface according to a design structure, laying the carbon fiber prepreg in a unidirectional mode, laying 8 layers, and removing the isolation plastic films and release paper on the surfaces of the two sides of the prepreg when each layer is laid;
thirdly, removing the prepreg release paper on the outermost layer, and covering an upper die; paving a glue absorption felt on the surface of an upper die, and sticking a sealing adhesive tape along the edge of the die; laying the prepared vacuum bag film on a glue absorption felt, gradually removing the isolation paper of the sealant strip, tightly attaching the vacuum bag film to the sealant strip, and connecting a vacuum suction nozzle;
and fourthly, completing high-temperature forming according to the designed forming process, opening the mold, and taking out the composite material to obtain the carbon fiber composite material based on the discontinuous fiber structure.
TABLE 1
| Numbering | a1 | a2 | a3 | a4 | a5 | a6 | a7 | a8 |
| α/° | 5 | 8 | 11 | 14 | 17 | 20 | 23 | 25 |
After performance tests, the carbon fiber composite material has the best tensile property when the alpha is 11 degrees.
Example 2
In the embodiment, carbon fiber composite materials with non-continuous fiber structures with different parameters d are prepared. The specific content comprises the following steps:
step one, taking out qualified carbon fiber prepreg from a refrigerator according to experimental requirements, and placing the carbon fiber prepreg at the room temperature of 25 +/-2 ℃ for more than 10 hours for softening adjustment; according to design requirements, guiding a cutting design drawing into a computer, and cutting the carbon fiber prepreg through a numerical control cutting bed; wherein the directions and the distributions of the cuts are respectively two cuts in fig. 6b and fig. 6c, the parameters d of the two cuts are respectively shown in table 2, alpha is 11.3 degrees, and the obtained carbon fiber composite material is respectively marked as a step cut and a double-angle cut;
secondly, cleaning the surface of the mould, and wiping the outer surfaces of the upper mould and the lower mould with alcohol; laying carbon fiber prepregs on the lower die surface according to a design structure, repeatedly laying 8 layers of carbon fiber prepregs at an angle of 0 degree and 90 degrees in the length direction, repeatedly laying 8 layers of carbon fiber prepregs at an angle of 90 degrees and 0 degrees in the length direction (the laying mode is marked as 0/90), and removing the isolation plastic films and release paper on the surfaces of the two sides of each layer of carbon fiber prepregs;
thirdly, removing the prepreg release paper on the outermost layer, and covering an upper die; paving a glue absorption felt on the surface of an upper die, and sticking a sealing adhesive tape along the edge of the die; laying the prepared vacuum bag film on a glue absorption felt, gradually removing the isolation paper of the sealant strip, tightly attaching the vacuum bag film to the sealant strip, and connecting a vacuum suction nozzle;
and fourthly, completing high-temperature forming according to the designed forming process, opening the mold, and taking out the composite material to obtain the carbon fiber composite material based on the discontinuous fiber structure.
The first to fourth steps were repeated, wherein in the first step, the carbon fiber prepreg was cut entirely by each cut, and the parameter d was as shown in table 2, and α was 11.3 °. And obtaining the carbon fiber composite material based on the discontinuous fiber structure, and marking the carbon fiber composite material as a continuous notch.
TABLE 2
After performance tests, the smaller d is, the better the tensile property of the carbon fiber composite material is. In consideration of the difficulty of the processing technology, the d can be 5mm in practical production.
Example 3
In the embodiment, the discontinuous carbon fiber-glass fiber hybrid composite material with different carbon fiber layer numbers is prepared, and the mechanical property of the composite material is researched. The carbon fiber prepreg is a commercially available carbon fiber epoxy resin prepreg, and the glass fiber prepreg is a commercially available glass fiber epoxy resin prepreg. The thickness of each layer of carbon fiber prepreg is 0.03mm, and the thickness of each layer of glass fiber prepreg is 0.15 mm. The preparation process comprises the following steps:
step one, taking out qualified carbon fiber prepreg from a refrigerator according to experimental requirements, and placing the carbon fiber prepreg at the room temperature of 25 +/-2 ℃ for more than 10 hours for softening adjustment; according to design requirements, guiding a cutting design drawing into a computer, and cutting the carbon fiber prepreg through a numerical control cutting bed;
secondly, cleaning the surface of the mould, and wiping the outer surfaces of the upper mould and the lower mould with alcohol; laying two layers of glass fiber prepregs on the surface of a lower die according to a designed structure, laying one or three layers of carbon fiber prepregs in the same direction, and laying two layers of glass fiber prepregs at last, wherein each layer of the glass fiber prepregs is laid, and isolating plastic films and release paper on the surfaces of the two sides of each prepreg are removed;
thirdly, removing the prepreg release paper on the outermost layer, and covering an upper die; paving a glue absorption felt on the surface of an upper die, and sticking a sealing adhesive tape along the edge of the die; laying the prepared vacuum bag film on a glue absorption felt, gradually removing the isolation paper of the sealant strip, tightly attaching the vacuum bag film to the sealant strip, and connecting a vacuum suction nozzle;
and fourthly, completing high-temperature forming according to a designed forming process, opening the mould, and taking out the composite material to obtain the carbon fiber composite material G2/C1/G2 paved with a layer of carbon fiber prepreg or the carbon fiber composite material G2/C3/G2 paved with three layers of carbon fiber prepreg.
The carbon fiber composite material G2/C1/G2 and the carbon fiber composite material G2/C3/G2 are respectively subjected to a plurality of tensile property tests, and the stress-strain curves of the carbon fiber composite material G3578/C1/G2 and the carbon fiber composite material G2/C3/G2 are shown in FIG. 8. As can be seen from fig. 8, the carbon fiber composite material has good pseudo-extensibility, and the proof stress of the carbon fiber composite material is slightly increased as the thickness of the carbon fiber layer of the discontinuous fiber structure is increased.
Example 4
In this example, carbon fiber composite materials with different notch structures were prepared, and mechanical properties thereof were analyzed and compared. Wherein the carbon fiber prepreg is an epoxy resin prepreg of a carbon fiber commercially available.
Firstly, two isotropic carbon fiber composite materials based on a discontinuous fiber structure are prepared, and the preparation method specifically comprises the following steps:
step one, taking out qualified carbon fiber prepreg from a refrigerator according to experimental requirements, and placing the carbon fiber prepreg at the room temperature of 25 +/-2 ℃ for more than 10 hours for softening adjustment; according to design requirements, guiding a cutting design drawing into a computer, and cutting the carbon fiber prepreg through a numerical control cutting bed; wherein, the directions and the distributions of the cuts are respectively two in fig. 6b and fig. 6c, and the parameters d, l and alpha of the two are the same, and the obtained carbon fiber composite material is respectively marked as a step cut and a double-angle cut;
secondly, cleaning the surface of the mould, and wiping the outer surfaces of the upper mould and the lower mould with alcohol; according to a design structure, carbon fiber prepreg is arranged on the surface of a lower die, the fiber directions of the carbon fibers are respectively laid according to eight directions with the same included angle, finally the carbon fiber prepreg is made to be isotropic, and each layer of the insulation plastic film and release paper on the surfaces of the two sides of the prepreg are removed;
thirdly, removing the prepreg release paper on the outermost layer, and covering an upper die; paving a glue absorption felt on the surface of an upper die, and sticking a sealing adhesive tape along the edge of the die; laying the prepared vacuum bag film on a glue absorption felt, gradually removing the isolation paper of the sealant strip, tightly attaching the vacuum bag film to the sealant strip, and connecting a vacuum suction nozzle;
and fourthly, completing high-temperature forming according to the designed forming process, opening the mold, and taking out the composite material to obtain the carbon fiber composite material based on the discontinuous fiber structure.
Then, the prepared isotropic carbon fiber composite material based on the discontinuous fiber structure specifically comprises the following steps:
step one, taking out qualified carbon fiber prepreg from a refrigerator according to experimental requirements, and placing the carbon fiber prepreg at the room temperature of 25 +/-2 ℃ for more than 10 hours for softening adjustment; according to design requirements, guiding a cutting design drawing into a computer, and cutting the carbon fiber prepreg through a numerical control cutting bed; wherein each cut cuts off the whole carbon fiber prepreg, and the parameter alpha of the cut is the same as that of the step cut and the double-angle cut samples prepared before;
secondly, cleaning the surface of the mould, and wiping the outer surfaces of the upper mould and the lower mould with alcohol; according to a design structure, carbon fiber prepreg is arranged on the surface of a lower die, the fiber directions of the carbon fibers are respectively laid according to eight directions with the same included angle, finally the carbon fiber prepreg is made to be isotropic, and each layer of the insulation plastic film and release paper on the surfaces of the two sides of the prepreg are removed;
thirdly, removing the prepreg release paper on the outermost layer, and covering an upper die; paving a glue absorption felt on the surface of an upper die, and sticking a sealing adhesive tape along the edge of the die; laying the prepared vacuum bag film on a glue absorption felt, gradually removing the isolation paper of the sealant strip, tightly attaching the vacuum bag film to the sealant strip, and connecting a vacuum suction nozzle;
and fourthly, completing high-temperature forming according to the designed forming process, opening the mold, and taking out the composite material to obtain the carbon fiber composite material based on the discontinuous fiber structure.
Finally, the carbon fiber composite material based on the continuous fiber structure is prepared, and the method specifically comprises the following steps:
step one, taking out qualified carbon fiber prepreg from a refrigerator according to experimental requirements, and placing the carbon fiber prepreg at the room temperature of 25 +/-2 ℃ for more than 10 hours for softening adjustment;
secondly, cleaning the surface of the mould, and wiping the outer surfaces of the upper mould and the lower mould with alcohol; according to a design structure, carbon fiber prepreg is arranged on the surface of a lower die, the fiber directions of the carbon fibers are respectively laid according to eight directions with the same included angle, finally the carbon fiber prepreg is made to be isotropic, and each layer of the insulation plastic film and release paper on the surfaces of the two sides of the prepreg are removed;
thirdly, removing the prepreg release paper on the outermost layer, and covering an upper die; paving a glue absorption felt on the surface of an upper die, and sticking a sealing adhesive tape along the edge of the die; laying the prepared vacuum bag film on a glue absorption felt, gradually removing the isolation paper of the sealant strip, tightly attaching the vacuum bag film to the sealant strip, and connecting a vacuum suction nozzle;
and fourthly, completing high-temperature forming according to a designed forming process, opening the mould, and taking out the composite material to obtain the carbon fiber composite material based on the continuous fiber structure, wherein the carbon fiber composite material is marked as continuous fibers.
The carbon fiber composite continuous fiber, the carbon fiber composite continuous notch, the carbon fiber composite step notch and the carbon fiber composite double-angle notch are respectively subjected to a plurality of tensile property tests, and a comparison graph of the tensile modulus and the tensile strength of different samples is shown in fig. 9. As can be seen from fig. 9a, under the same other conditions, the tensile modulus of the carbon fiber composite material having the discontinuous fiber structure with different notch structures is slightly lower than that of the carbon fiber composite material having the continuous fiber structure, and the tensile modulus of the carbon fiber composite material having the discontinuous fiber structure with the double-angle notch is very close to that of the carbon fiber composite material having the continuous fiber structure. As can be seen from fig. 9b, when other conditions are the same, the tensile strength of the carbon fiber composite material with the discontinuous fiber structure having different notch structures is significantly lower than that of the carbon fiber composite material with the continuous fiber structure, but has a significant advantage over the conventional tensile strength (about 400MPa, see fig. 7) of the carbon fiber composite material with the discontinuous fiber structure having vertical notches, and the tensile strength of the carbon fiber composite material with the discontinuous fiber structure having double-corner notches almost reaches 500 MPa. Therefore, the carbon fiber composite material based on the discontinuous fiber structure better reflects the high strength characteristic of the carbon fiber.
Example 5
The embodiment prepares the discontinuous carbon fiber composite materials with different carbon fiber laying modes, and researches the energy absorption performance of the discontinuous carbon fiber composite materials. Wherein the carbon fiber prepreg is an epoxy resin prepreg of a carbon fiber commercially available.
Firstly, two isotropic carbon fiber composite materials based on a discontinuous fiber structure are prepared, and the specific preparation process comprises the following steps:
step one, taking out qualified carbon fiber prepreg from a refrigerator according to experimental requirements, and placing the carbon fiber prepreg at the room temperature of 25 +/-2 ℃ for more than 10 hours for softening adjustment; according to design requirements, guiding a cutting design drawing into a computer, and cutting the carbon fiber prepreg through a numerical control cutting bed; wherein, the directions and the distributions of the cuts are respectively two in fig. 6b and fig. 6c, and the parameters d, l and alpha of the two are the same, and the obtained carbon fiber composite material is respectively marked as a step cut and a double-angle cut;
secondly, cleaning the surface of the mould, and wiping the outer surfaces of the upper mould and the lower mould with alcohol; laying carbon fiber prepregs on the lower die surface according to a design structure, repeatedly laying 8 layers of carbon fiber prepregs at an angle of 0 degree and 90 degrees in the length direction, repeatedly laying 8 layers of carbon fiber prepregs at an angle of 90 degrees and 0 degrees in the length direction (the laying mode is marked as 0/90), and removing the isolation plastic films and release paper on the surfaces of the two sides of each layer of carbon fiber prepregs;
thirdly, removing the prepreg release paper on the outermost layer, and covering an upper die; paving a glue absorption felt on the surface of an upper die, and sticking a sealing adhesive tape along the edge of the die; laying the prepared vacuum bag film on a glue absorption felt, gradually removing the isolation paper of the sealant strip, tightly attaching the vacuum bag film to the sealant strip, and connecting a vacuum suction nozzle;
and fourthly, completing high-temperature forming according to the designed forming process, opening the mold, and taking out the composite material to obtain the carbon fiber composite material based on the discontinuous fiber structure.
And repeating the first step to the fourth step, wherein in the second step, 8 layers of carbon fiber prepregs are repeatedly laid at 90 degrees and 0 degrees in the length direction, and then 8 layers of carbon fiber prepregs are repeatedly laid at 0 degrees and 90 degrees in the length direction (the laying mode is marked as 90/0).
Then, the carbon fiber composite material based on the continuous fiber structure is prepared, and the method specifically comprises the following steps:
step one, taking out qualified carbon fiber prepreg from a refrigerator according to experimental requirements, and placing the carbon fiber prepreg at the room temperature of 25 +/-2 ℃ for more than 10 hours for softening adjustment;
secondly, cleaning the surface of the mould, and wiping the outer surfaces of the upper mould and the lower mould with alcohol; laying carbon fiber prepregs on the lower die surface according to a design structure, repeatedly laying 8 layers of carbon fiber prepregs at an angle of 0 degree and 90 degrees in the length direction, repeatedly laying 8 layers of carbon fiber prepregs at an angle of 90 degrees and 0 degrees in the length direction (the laying mode is marked as 0/90), and removing the isolation plastic films and release paper on the surfaces of the two sides of each layer of carbon fiber prepregs;
thirdly, removing the prepreg release paper on the outermost layer, and covering an upper die; paving a glue absorption felt on the surface of an upper die, and sticking a sealing adhesive tape along the edge of the die; laying the prepared vacuum bag film on a glue absorption felt, gradually removing the isolation paper of the sealant strip, tightly attaching the vacuum bag film to the sealant strip, and connecting a vacuum suction nozzle;
and fourthly, completing high-temperature forming according to a designed forming process, opening the mould, and taking out the composite material to obtain the carbon fiber composite material based on the continuous fiber structure, wherein the carbon fiber composite material is marked as continuous fibers.
And repeating the first step to the fourth step, wherein in the second step, 8 layers of carbon fiber prepregs are repeatedly laid at 90 degrees and 0 degrees in the length direction, and then 8 layers of carbon fiber prepregs are repeatedly laid at 0 degrees and 90 degrees in the length direction (the laying mode is marked as 90/0).
The carbon fiber composite continuous fibers, the carbon fiber composite stepped cuts and the carbon fiber composite double-angle cuts in different laying modes are respectively subjected to multiple energy absorption performance tests, and a comparison graph of the energy absorption performance of different samples is shown in fig. 10. As can be seen from fig. 10, under the same other conditions, the energy absorption performance of the carbon fiber composite material with the discontinuous fiber structure having the laying method of 0/90 is slightly improved compared with the energy absorption performance of the carbon fiber composite material with the continuous fiber structure, and the energy absorption performance of the carbon fiber composite material with the discontinuous fiber structure having the laying method of 90/0 is significantly improved compared with the energy absorption performance of the carbon fiber composite material with the continuous fiber structure. Therefore, the carbon fiber composite material based on the discontinuous fiber structure has higher energy absorption property.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. The utility model provides a high performance carbon-fibre composite based on discontinuous fiber structure which characterized in that, carbon-fibre prepreg that carbon-fibre composite chooseed for use obtains discontinuous fiber structure through mechanical cutting, and the contained angle between incision direction and the fibre direction during cutting is alpha, and 5 < alpha <25 >, and all incisions are the rectilinearly, and cut through carbon-fibre prepreg.
2. The high performance carbon fiber composite material based on the discontinuous fiber structure according to claim 1, wherein the incisions cut off the carbon fiber prepreg in its entirety.
3. The high-performance carbon fiber composite material based on the discontinuous fiber structure is characterized in that the length of the cuts in the direction perpendicular to the fiber direction is d, 2mm < d <15mm, and the cuts in the same direction are distributed in a staggered manner.
4. The high-performance carbon fiber composite material based on the discontinuous fiber structure is characterized in that all the cuts are parallel to each other and are in a unidirectional staggered distribution structure; or, a part of the incisions and the fiber direction deflect an angle alpha leftwards, the other part of the incisions and the fiber direction deflect an angle alpha rightwards, and the incisions in the same direction are distributed in a staggered manner to form a bidirectional staggered distribution structure.
5. The high-performance carbon fiber composite material based on the discontinuous fiber structure is characterized in that glass fibers are also mixed in the carbon fiber composite material, and the manner of mixing the carbon fibers and the glass fibers in the carbon fiber composite material is interlayer mixed laying or interlayer mixed weaving.
6. A method for preparing a high-performance carbon fiber composite material based on a discontinuous fiber structure according to any one of claims 1 to 5, characterized in that the method comprises the following steps:
firstly, guiding a cutting design drawing into a computer according to design requirements, and cutting the carbon fiber prepreg through a numerical control cutting bed;
secondly, laying carbon fiber prepreg on the lower die surface according to a design structure;
covering an upper die, sealing the die, and vacuumizing the die;
and fourthly, completing high-temperature forming according to the designed forming process, opening the mould, and taking out the composite material to obtain the high-performance carbon fiber composite material based on the discontinuous fiber structure.
7. The production method according to claim 6, wherein the carbon fiber prepreg used in the first step is subjected to softening adjustment at 25 ℃ ± 2 ℃ for 10 hours or more.
8. The method according to claim 6, wherein in the second step, the mold is cleaned, and the release plastic film and the release paper on the two side surfaces of the carbon fiber prepreg are removed when the carbon fiber prepreg is laid.
9. The manufacturing method according to claim 6, wherein in the second step, when the carbon fiber prepreg is laid, the carbon fiber prepreg and the glass fiber prepreg are laid in sequence according to a designed carbon fiber-glass fiber hybrid composite structure, or a woven product obtained by weaving the carbon fiber prepreg and the glass fiber prepreg is laid.
10. The method for preparing the rubber mold as claimed in claim 6, wherein in the third step, a suction felt is laid on the surface of the upper mold before the mold is sealed; the operation of sealing the mold includes: sticking a sealing adhesive tape along the edge of the mould; and laying the vacuum bag film on the adhesive absorption felt, gradually removing the isolation paper of the sealing adhesive tape, and tightly attaching the vacuum bag film to the sealing adhesive tape.
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