CN114058323A - Interlayer toughening composite material and preparation method thereof - Google Patents
Interlayer toughening composite material and preparation method thereof Download PDFInfo
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- CN114058323A CN114058323A CN202111323554.1A CN202111323554A CN114058323A CN 114058323 A CN114058323 A CN 114058323A CN 202111323554 A CN202111323554 A CN 202111323554A CN 114058323 A CN114058323 A CN 114058323A
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- C—CHEMISTRY; METALLURGY
- C09—DYES; PAINTS; POLISHES; NATURAL RESINS; ADHESIVES; COMPOSITIONS NOT OTHERWISE PROVIDED FOR; APPLICATIONS OF MATERIALS NOT OTHERWISE PROVIDED FOR
- C09J—ADHESIVES; NON-MECHANICAL ASPECTS OF ADHESIVE PROCESSES IN GENERAL; ADHESIVE PROCESSES NOT PROVIDED FOR ELSEWHERE; USE OF MATERIALS AS ADHESIVES
- C09J177/00—Adhesives based on polyamides obtained by reactions forming a carboxylic amide link in the main chain; Adhesives based on derivatives of such polymers
- C09J177/10—Polyamides derived from aromatically bound amino and carboxyl groups of amino carboxylic acids or of polyamines and polycarboxylic acids
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- C09—DYES; PAINTS; POLISHES; NATURAL RESINS; ADHESIVES; COMPOSITIONS NOT OTHERWISE PROVIDED FOR; APPLICATIONS OF MATERIALS NOT OTHERWISE PROVIDED FOR
- C09D—COATING COMPOSITIONS, e.g. PAINTS, VARNISHES OR LACQUERS; FILLING PASTES; CHEMICAL PAINT OR INK REMOVERS; INKS; CORRECTING FLUIDS; WOODSTAINS; PASTES OR SOLIDS FOR COLOURING OR PRINTING; USE OF MATERIALS THEREFOR
- C09D163/00—Coating compositions based on epoxy resins; Coating compositions based on derivatives of epoxy resins
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- C—CHEMISTRY; METALLURGY
- C09—DYES; PAINTS; POLISHES; NATURAL RESINS; ADHESIVES; COMPOSITIONS NOT OTHERWISE PROVIDED FOR; APPLICATIONS OF MATERIALS NOT OTHERWISE PROVIDED FOR
- C09D—COATING COMPOSITIONS, e.g. PAINTS, VARNISHES OR LACQUERS; FILLING PASTES; CHEMICAL PAINT OR INK REMOVERS; INKS; CORRECTING FLUIDS; WOODSTAINS; PASTES OR SOLIDS FOR COLOURING OR PRINTING; USE OF MATERIALS THEREFOR
- C09D7/00—Features of coating compositions, not provided for in group C09D5/00; Processes for incorporating ingredients in coating compositions
- C09D7/40—Additives
- C09D7/60—Additives non-macromolecular
- C09D7/61—Additives non-macromolecular inorganic
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- C—CHEMISTRY; METALLURGY
- C09—DYES; PAINTS; POLISHES; NATURAL RESINS; ADHESIVES; COMPOSITIONS NOT OTHERWISE PROVIDED FOR; APPLICATIONS OF MATERIALS NOT OTHERWISE PROVIDED FOR
- C09J—ADHESIVES; NON-MECHANICAL ASPECTS OF ADHESIVE PROCESSES IN GENERAL; ADHESIVE PROCESSES NOT PROVIDED FOR ELSEWHERE; USE OF MATERIALS AS ADHESIVES
- C09J11/00—Features of adhesives not provided for in group C09J9/00, e.g. additives
- C09J11/02—Non-macromolecular additives
- C09J11/04—Non-macromolecular additives inorganic
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Abstract
The invention discloses an interlayer toughening composite material and a preparation method thereof, wherein the composite material comprises a resin-carbon nano tube precoat formed by coating a carbon nano tube-acetone-resin mixture on an interlayer toughening surface and a resin-aramid pulp dreg-curing agent adhesive layer formed by coating an aramid pulp dreg-resin-curing agent mixture on the resin-carbon nano tube precoat. The invention has the beneficial effects that: holes or dents can be formed on the surface by polishing the interlayer toughening surface, the contact area between the interlayer toughening surface and resin can be increased, and the carbon nano tubes and the resin flow into the holes or the dents to achieve the toughening effect; the aramid pulp-resin-curing agent mixture is coated on the resin-carbon nano tube precoating layer, and the curing agent and the resin in the resin-carbon nano tube precoating layer are subjected to chemical reaction, so that the bonding performance is improved.
Description
[ technical field ] A method for producing a semiconductor device
The invention relates to the technical field of interlayer toughening, in particular to an interlayer toughening composite material and a preparation method thereof.
[ background of the invention ]
With the increasingly wide application of composite materials, the requirements on the material performance research are more and more intensive. Research shows that although the composite material structure has the advantages of high specific rigidity, high specific strength and the like, the brittle composite material structure is easy to generate fine layering in the machining process, and meanwhile, the fiber fracture and other failures are caused. The mechanical parts have weak links, so that the mechanical property of the structure is obviously reduced, and the safety of the structure is greatly threatened.
In order to integrally improve the performance of the composite material structure, the mechanical property of the composite material thin-wall structure can be improved by introducing a patch reinforcing method, which is a simple and effective method. However, the introduction of patches is still limited by a weak bonding interface. If the bonding interface is weak, the patch and the structure are easy to separate, so that the patch cannot continuously exert the reinforcing function. Therefore, it is necessary to provide a toughening method for effectively strengthening the bonding interface from the viewpoint of toughening the bonding interface, so as to improve the strengthening effect of the patch on the thin-wall structure of the composite material.
[ summary of the invention ]
The invention discloses an interlayer toughening composite material and a preparation method thereof, which can solve the technical problems related to the background technology.
In order to achieve the purpose, the technical scheme of the invention is as follows:
a preparation method of an interlayer toughening composite material comprises the following steps:
s1, preparing an aramid pulp meal-resin-curing agent mixture, which specifically comprises:
s11, taking a certain amount of aramid pulp and acetone, and fully stirring for 10-30 minutes to form an aramid pulp-acetone mixture;
s12, adding resin into the aramid pulp-acetone mixture, and fully stirring for 10-30 minutes to form the aramid pulp-acetone-resin mixture;
s13, after acetone is completely volatilized, forming an aramid pulp dreg-resin mixture;
s14, adding a curing agent into the aramid pulp meal-resin mixture, and properly stirring for 2-10 minutes to form the aramid pulp meal-resin-curing agent mixture;
s2, preparing a carbon nanotube-acetone-resin mixture, which specifically comprises:
s21, taking a certain amount of carbon nano tube and acetone, and properly stirring for 2-10 minutes to form a carbon nano tube-acetone mixture;
s22, adding resin into the carbon nano tube-acetone mixture, and stirring the mixture properly to form a carbon nano tube-acetone-resin mixture;
s3 preparing a bonding interface, specifically comprising:
s31, coating the carbon nano tube-acetone-resin mixture on the interlayer toughening surface to form a resin-carbon nano tube precoat;
and S32, coating the aramid pulp dreg-resin-curing agent mixture on the resin-carbon nano tube precoating layer to form an aramid pulp dreg-resin-curing agent adhesive layer.
As a preferred improvement of the present invention: in step S11, the mass ratio of the aramid pulp to the acetone is at least 1: 1.
as a preferred improvement of the present invention: in step S12, the mass ratio of acetone to epoxy resin is 4: 1.
as a preferred improvement of the present invention: in step S13, the volatilization time is not less than 12 days.
As a preferred improvement of the present invention: in step S21, the mass ratio of the carbon nanotubes to acetone is at least 1: 1.
as a preferred improvement of the present invention: in step S22, the mass ratio of the resin to the carbon nanotube-acetone mixture is 1: 4.
as a preferred improvement of the present invention: in step S21, the modulus of the carbon nanotube is 1TPa, and the tensile strength is 50-200 GPa.
As a preferred improvement of the present invention: in steps S11 and S21, aramid pulp and acetone and carbon nanotube particles and acetone are stirred by a mechanical stirrer.
The invention also provides an interlayer toughening composite material prepared by the preparation method of the interlayer toughening composite material, which comprises a resin-carbon nanotube precoat formed by coating a carbon nanotube-acetone-resin mixture on an interlayer toughening surface and a resin-aramid pulp dreg-curing agent adhesive layer formed by coating an aramid pulp dreg-resin-curing agent mixture on the resin-carbon nanotube precoat.
As a preferred improvement of the present invention: the interlayer toughened surface is polished prior to coating the carbon nanotube-acetone-resin mixture to form holes or indentations that increase the contact area of the surface with the resin.
The invention has the following beneficial effects:
(1) the interlaminar toughening composite material prepared by the method can obviously improve the bending load resistance, can effectively solve the problem of bonding of a reinforced patch and an original structure, improves the problem of patch falling caused by the traditional bonding, and greatly improves the overall performance of a structure with defects;
(2) holes or dents can be formed on the surface by polishing the interlayer toughening surface, the contact area between the interlayer toughening surface and resin can be increased, and the carbon nano tubes and the resin flow into the holes or the dents to achieve the toughening effect;
(3) the aramid pulp-resin-curing agent mixture is coated on the resin-carbon nano tube precoating layer, and the curing agent and the resin in the resin-carbon nano tube precoating layer are subjected to chemical reaction, so that the bonding performance is improved.
[ description of the drawings ]
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the description of the embodiments are briefly introduced below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without inventive efforts, wherein:
FIG. 1 is a schematic structural view of a toughening structure provided by the present invention;
FIG. 2 is a schematic structural view of a toughening structure having a resin-curing agent bonding interface according to the present invention;
FIG. 3 is a schematic structural diagram of a toughening structure with a resin-carbon nanotube-curing agent bonding interface according to the present invention;
FIG. 4 is a schematic structural diagram of a toughening structure with a resin-aramid pulp meal-curing agent bonding interface according to the present invention;
FIG. 5 is a schematic structural view of a toughened structure having an interlayer toughened composite of the present invention;
FIG. 6 is a schematic diagram of a test structure of an Instron 5982 universal testing machine of the invention on a toughening structure;
FIG. 7 is a comparison of bending load versus displacement curves for the present invention;
FIG. 8 is a graph illustrating the bending failure process of the present invention;
FIG. 9 is a comparison graph of bending load versus displacement curves for different bond patches of the present invention for impact on bending performance of an open CFRP thin-walled structure;
FIG. 10 is a comparison of bending load versus displacement curves for all cases of the present invention;
FIG. 11 is a graph showing a comparison of maximum bending loads for all cases of the present invention;
in the figure, 1, a thin-wall structure to be reinforced; 2. a patch structure; 3. bonding the interface; 4. a resin-curing agent bonding interface; 5. a resin-carbon nanotube-curing agent bonding interface; 6. a first resin-aramid pulp meal-curing agent bonding interface; 7. interlaminar toughening of the composite; 71. a resin-carbon nanotube precoat; 72. and a second resin-aramid pulp-curing agent bonding interface.
[ detailed description ] embodiments
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the following embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that all the directional indicators (such as up, down, left, right, front, and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the movement situation, etc. in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indicator is changed accordingly.
In addition, the descriptions related to "first", "second", etc. in the present invention are only for descriptive purposes and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "connected," "secured," and the like are to be construed broadly, and for example, "secured" may be a fixed connection, a removable connection, or an integral part; can be mechanically or electrically connected; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In addition, the technical solutions in the embodiments of the present invention may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination of technical solutions should not be considered to exist, and is not within the protection scope of the present invention.
The invention provides a preparation method of an interlayer toughening composite material, which comprises the following steps:
s1, preparing an aramid pulp-resin-curing agent mixture;
s11, taking a certain amount of aramid pulp and acetone, and fully stirring for 10-30 minutes to form an aramid pulp-acetone mixture;
specifically, during aramid pulp meal and acetone mixture: the more the acetone content is, the more the aramid pulp meal is favorably uniformly dispersed in the epoxy resin at the back, and the mass ratio of the aramid pulp meal to the acetone is at least 1: 1.
s12, adding resin into the aramid pulp-acetone mixture, and fully stirring for 10-30 minutes to form the aramid pulp-acetone-resin mixture;
specifically, the mass ratio of acetone to epoxy resin is 4: 1.
s13, after the acetone is completely volatilized, forming an aramid pulp dreg-resin mixture;
specifically, the volatilization time is not less than 12 days.
S14, adding a curing agent into the aramid pulp meal-resin mixture, and properly stirring for 2-10 minutes to form the aramid pulp meal-resin-curing agent mixture;
specifically, the mass ratio of the curing agent to the aramid pulp meal-resin mixture is 1: 5.
it is further noted that due to the volatilization of toxic liquids, the entire indoor operation is performed in a fume hood environment. Firstly, in order to uniformly disperse aramid pulp into epoxy resin, aramid pulp is soaked in an acetone solution and mixed. Then, fully stirring the aramid pulp meal and the acetone by using a mechanical stirrer at the maximum rotation speed of 11500rpm to obtain an even aramid pulp meal-acetone mixture. Epoxy resin without curing agent was mixed with acetone based on a certain ratio (80 vol.% acetone to 20 vol.% epoxy resin was used in the present invention). And (3) stirring the aramid pulp, the acetone and the epoxy resin by using the mechanical stirrer again. Then, the uniform aramid pulp-acetone-epoxy resin mixture is placed in a drying oven at a certain temperature to accelerate the full volatilization of acetone. The purpose of volatilizing the acetone is to reduce the effect of acetone on the curing of the epoxy resin. After acetone is completely volatilized, the residual mixture solution only contains epoxy resin and evenly distributed aramid pulp meal. And finally, adding a curing agent into the aramid pulp meal-epoxy resin mixture in a certain proportion, and then properly stirring by using a small wood stick to ensure that the curing agent is uniformly distributed in the mixture as much as possible to form the aramid pulp meal-epoxy resin-curing agent mixture.
S2, preparing a carbon nanotube-acetone-resin mixture, which specifically comprises:
s21, taking a certain amount of carbon nano tube and acetone, and stirring the mixture properly to form a carbon nano tube-acetone mixture;
the more the acetone content is, the more the carbon nano tube is favorably and uniformly dispersed in the following epoxy resin, and the mass ratio of the carbon nano tube to the acetone is at least 1: 1.
specifically, the mass ratio of the carbon nano tube micro-nano to the acetone is as follows: . The modulus of the carbon nano tube is 1TPa, and the tensile strength is 50-200GPa
S22, adding resin into the carbon nano tube-acetone mixture, and properly stirring for 2-10 minutes to form a carbon nano tube-acetone-resin mixture;
specifically, the mass ratio of acetone to epoxy resin is 4: 1.
s3 preparing a bonding interface, specifically comprising:
s31, coating the carbon nano tube-acetone-resin mixture on the interlayer toughening surface to form a resin-carbon nano tube precoat;
and S32, coating the aramid pulp dreg-resin-curing agent mixture on the resin-carbon nano tube precoating layer to form an aramid pulp dreg-resin-curing agent adhesive layer.
It should be further noted that, in the embodiment of the present invention, the resin is an epoxy resin. When the carbon nanotube-acetone-resin mixture is prepared, the epoxy resin has high viscosity and is low in fluidity. The surface treatment of the resin precoat layer is mainly used for reducing the viscosity (improving the flowability) of the epoxy resin, promoting the epoxy resin to easily flow into micro dents and micro holes on the toughening surface and improving the contact area. To achieve this, a small amount of epoxy resin without added curing agent can be added using a large amount of acetone, which also dilutes and wets the resin. Since the size of the carbon nanotubes is very small and smaller than the size of the micro-pits and micro-cavities on the surface of the structure, a small amount of carbon nanotubes may be added to the mixed solution of the resin and acetone. The carbon nano tube flows into the micro-dents and the micro-holes along with the diluted resin, so that the toughening effect of the resin is achieved. Compared with the surface treatment of the resin precoat layer, the surface treatment technology of the carbon nanotube resin precoat layer has higher bonding performance on two structures. Before the surface treatment technology of the carbon nanotube resin precoat layer is implemented, the surfaces of the thin-wall structure to be reinforced and the patch structure can be polished by sand paper, so that more cavities or dents are generated on the surfaces, and the contact area between the surfaces and the resin is increased. The polished structure surface is then cleaned with an acetone solution to remove fine dirt, such as dust and oil, remaining on the surface. Then, the thin-wall structure and the patch structure to be reinforced are immersed in the resin-acetone mixed solution without the curing agent. After a few minutes, the thin-wall structure and the patch structure to be reinforced are taken out and placed aside for the acetone to be completely volatilized. At this point, an acetone-free and very thin resin-carbon nanotube precoat layer remains on the surface of the thin-walled structure and patch structure to be reinforced.
The invention also provides an interlayer toughening composite material prepared by the preparation method, which comprises a resin-carbon nano tube precoat formed by coating the carbon nano tube-acetone-resin mixture on the interlayer toughening surface and a resin-aramid pulp dreg-curing agent adhesive layer formed by coating the aramid pulp dreg-resin-curing agent mixture on the resin-carbon nano tube precoat. It should be noted that the interlayer toughening surface includes the surface of the thin-wall structure to be reinforced and the patch structure.
It is further noted that the interlayer toughened surface is polished prior to coating with the carbon nanotube-acetone-resin mixture to form holes or indentations that increase the contact area of the surface with the resin.
Because the curing agent has diffusion effect in the resin, the resin in the resin-carbon nano tube precoating layer remained on the surface of the thin-wall structure to be reinforced and the patch structure can react with the diffused curing agent, after the thin-wall structure and the patch structure are bonded, a certain pressure is given to ensure the thinness of the interface, and the curing is finished within two weeks.
The interlayer toughened composite material and the preparation method thereof provided by the invention are explained in detail by specific examples.
As shown in fig. 1, a toughening structure includes a to-be-reinforced thin-wall structure 1, a patch structure 2, and a bonding interface 3 sandwiched between the to-be-reinforced thin-wall structure 1 and the patch structure 2. With reference to fig. 2 to 5, the toughening structure shown in fig. 2 includes a thin-wall structure 1 to be reinforced, a patch structure 2, and a resin-curing agent bonding interface 4; the toughening structure shown in fig. 3 includes a thin-wall structure 1 to be reinforced, a patch structure 2, and a resin-carbon nanotube-curing agent bonding interface 5; the toughening structure shown in fig. 4 comprises a thin-wall structure 1 to be reinforced, a patch structure 2 and a resin-aramid pulp meal-curing agent bonding interface 6; the toughening structure shown in fig. 5 comprises a thin-wall structure 1 to be reinforced, a patch structure 2 and an interlayer toughening composite material 7, specifically, the interlayer toughening composite material 7 comprises a resin-carbon nanotube precoating layer 71 coated on the thin-wall structure 1 to be reinforced and the patch structure 2 and a second resin + aramid pulp meal + curing agent bonding interface 72 arranged between the two layers.
It is noted that the toughening structures shown in fig. 2 to 4 serve as comparative examples of the toughening structure shown in fig. 5 to which the toughened composite material provided by the present invention is applied. As shown in fig. 2, the resin-curing agent bonding interface 3 was used as a control without any reinforcing additives. In fig. 3 and 4, a small amount of micro-nano carbon tubes and micro-nano aramid pulp are respectively added to the bonding interface, so that the resin toughening effect is achieved, but the interface bonding force between the resin and the composite material cannot be improved. Therefore, the invention provides a bonding interface which is shown in fig. 5 and adopts the interlayer toughening material 6, and the interface introduces a carbon nano tube resin precoat surface treatment technology on the basis of a second resin + aramid pulp and a curing agent bonding interface 72, namely, a resin-carbon nano tube precoat layer 71 is precoated on the surface of the toughening structure, so that the contact area of the resin and the surface of the composite material and the toughness of the precoated resin can be improved.
Three-point bending tests were performed on the four toughened structures by an Instron 5982 universal tester to evaluate the mechanical properties of the structures. As shown in fig. 6, the experimental test was performed at a certain loading rate, and the loading was stopped after the toughening structure was broken.
Fig. 7 and 8 investigate the reinforcing effect of the adhesive patch (i.e. patch structure) on the open-pored composite thin-walled structure (i.e. thin-walled structure to be reinforced). By comparing the full panel without reinforcement to the apertured panel, it is demonstrated that the introduction of mechanical apertures substantially reduces the bending stiffness and strength of the structure, with a reduction in the peak bending load of up to 49.26%. When the patch is introduced into the perforated plate, the initial rigidity of the structure is obviously improved and even far higher than that of the whole plate; but the highest bending load of the structure is still reduced by 14.48%. While the aperture plate/aperture patch with a pure resin interface had a slight drop in peak load, it was much higher than the aperture plate without the patch reinforcement. The introduction of the bonding patch also shows that the bonding patch has obvious reinforcing effect on the perforated plate and can improve the initial failure strength of the perforated composite material thin-wall structure. Therefore, an in-depth analysis of the mechanical behavior of apertured plates reinforced with patches will be performed. By analysis it can be concluded: as long as the bending load does not reach the bending load corresponding to the initial degumming and the bending load corresponding to the complete interface degumming, the whole structure can continuously bear, which is the first layer protection for the open-pore composite material thin-wall structure; while the bending deformation resistance of the open cell structure itself is a second layer of protection. Therefore, the adhesive capacity of the adhesive interface should be improved as much as possible, and the interface is delayed from debonding, so that the patch can play a longer role.
The reinforcing effect of the adhesive patch structure on the thin-wall structure to be reinforced of the open-pore composite material is mainly embodied in the first half stage of bending, so that the influence of different adhesive patches on the bending performance of the open-pore CFRP thin-wall structure is researched, as shown in FIG. 9. The bending rigidity corresponding to the carbon nano tube interface and the aramid pulp meal interface is similar to that corresponding to the pure resin interface, but the highest bending load is obviously improved. This is because the introduction of the additive increases the toughness of the resin, improves the interfacial adhesion properties, and thus increases the time for the patch to provide the bending resistance. Compared with a carbon nano tube interface, the aramid pulp has higher maximum bending load corresponding to the interface, which is mainly attributed to that the aramid pulp with multiple layers has more effective fiber bridging, and the size factor makes the interface thicker than the carbon nano tube interface. By observing the bending behavior corresponding to the aramid pulp-RPC carbon nanotube interface, the aramid pulp-RPC carbon nanotube interface not only shows the highest structural rigidity, but also has the highest bending load. This demonstrates that the RPC carbon nanotube surface treatment can effectively improve the adhesion of the resin to the open-pore thin-walled structure surface. The RPC carbon nanotube surface treatment and aramid pulp-meal interfacial toughening play a role of a patch as much as possible.
Fig. 10 and 11 compare the bending load-displacement curves and the maximum bending load for all cases. As shown in fig. 10, the shaded area provides additional bending load for the adhesive patch, which also means that more energy absorption is provided, making up for the reduced energy absorption of the mechanical openings. In terms of maximum bending load (as shown in fig. 11), the pure resin interface corresponds to a maximum bending load that is 68.55% higher than the maximum bending load for an apertured plate that has not been reinforced with a patch, but 14.48% lower than the maximum bending load for a full plate. When the carbon nanotubes are used to toughen the bonded interface, the maximum bending load of the apertured plate 103.65% can be increased and also be 3.34% higher than the corresponding maximum bending load of the full plate. However, the maximum bending load corresponding to the aramid pulp meal interface is increased by 177.89%, and is simultaneously higher than the maximum bending load corresponding to the whole plate by 41.00%. Most obviously, aramid pulp-RPC carbon nanotube interface shows the highest structural reinforcement characteristic, and the maximum bending load of the lifting reaches 207.21%, and is 55.88% higher than the maximum bending load corresponding to the whole plate. Through the comparison, the patch reinforcement can make up performance reduction caused by opening under the condition of combining an advanced bonding interface toughening technology, and even can enable the residual bending resistance performance of the opening thin-wall structure to be far higher than that of a complete plate. In the design of the adhesive interface, the performance of the adhesive interface should be improved as much as possible, otherwise the mechanical properties of the open-pore thin-wall structure after the patch is degummed can be reduced to the situation of non-enhancement, as shown in fig. 10.
The carbon nanotube aramid pulp is toughened between the layers by the bean pulp, so that the problem of bonding of a reinforced patch and an original structure is effectively solved, the problem of patch falling caused by traditional bonding is solved, and the overall performance of a structure with defects is greatly improved.
The invention has the following beneficial effects:
(1) the interlaminar toughening composite material prepared by the method can obviously improve the bending load resistance, can effectively solve the problem of bonding of a reinforced patch and an original structure, improves the problem of patch falling caused by the traditional bonding, and greatly improves the overall performance of a structure with defects;
(2) holes or dents can be formed on the surface by polishing the interlayer toughening surface, the contact area between the interlayer toughening surface and resin can be increased, and the carbon nano tubes and the resin flow into the holes or the dents to achieve the toughening effect;
(3) the aramid pulp-resin-curing agent mixture is coated on the resin-carbon nano tube precoating layer, and the curing agent and the resin in the resin-carbon nano tube precoating layer are subjected to chemical reaction, so that the bonding performance is improved.
While embodiments of the invention have been disclosed above, it is not limited to the applications set forth in the specification and the embodiments, which are fully applicable to various fields of endeavor for which the invention pertains, and further modifications may readily be made by those skilled in the art, it being understood that the invention is not limited to the details shown and described herein without departing from the general concept defined by the appended claims and their equivalents.
Claims (10)
1. A preparation method of an interlayer toughening composite material is characterized by comprising the following steps: the preparation method comprises the following steps:
s1, preparing an aramid pulp meal-resin-curing agent mixture, which specifically comprises:
s11, taking a certain amount of aramid pulp and acetone, and fully stirring for 10-30 minutes to form an aramid pulp-acetone mixture;
s12, adding resin into the aramid pulp-acetone mixture, and fully stirring for 10-30 minutes to form the aramid pulp-acetone-resin mixture;
s13, after acetone is completely volatilized, forming an aramid pulp dreg-resin mixture;
s14, adding a curing agent into the aramid pulp meal-resin mixture, and properly stirring for 2-10 minutes to form the aramid pulp meal-resin-curing agent mixture;
s2, preparing a carbon nanotube-acetone-resin mixture, which specifically comprises:
s21, taking a certain amount of carbon nano tube and acetone, and properly stirring for 2-10 minutes to form a carbon nano tube-acetone mixture;
s22, adding resin into the carbon nano tube-acetone mixture, and stirring the mixture properly to form a carbon nano tube-acetone-resin mixture;
s3 preparing a bonding interface, specifically comprising:
s31, coating the carbon nano tube-acetone-resin mixture on the interlayer toughening surface to form a resin-carbon nano tube precoat;
and S32, coating the aramid pulp dreg-resin-curing agent mixture on the resin-carbon nano tube precoating layer to form an aramid pulp dreg-resin-curing agent adhesive layer.
2. The method of claim 1, wherein the method comprises the steps of: in step S11, the mass ratio of the aramid pulp to the acetone is at least 1: 1.
3. the method of claim 2, wherein the method comprises the steps of: in step S12, the mass ratio of acetone to epoxy resin is 4: 1.
4. a method of preparing an interlaminar toughened composite material as claimed in claim 1 or 3, wherein: in step S13, the volatilization time is not less than 12 days.
5. The method of claim 1, wherein the method comprises the steps of: in step S21, the mass ratio of the carbon nanotubes to acetone is at least 1: 1.
6. the method of claim 5, wherein the method comprises the steps of: in step S22, the mass ratio of acetone to epoxy resin is 4: 1.
7. the method of claim 6, wherein the method comprises the steps of: in step S21, the modulus of the carbon nanotube is 1TPa, and the tensile strength is 50-200 GPa.
8. The method of claim 1, wherein the method comprises the steps of: in steps S11 and S21, aramid pulp and acetone and carbon nanotubes and acetone are stirred by a mechanical stirrer.
9. An interlayer toughened composite material prepared by the method of preparing an interlayer toughened composite material according to any one of claims 1 to 8, wherein: the adhesive comprises a resin-carbon nano tube precoat formed by coating a carbon nano tube-acetone-resin mixture on an interlayer toughening surface and a resin-aramid pulp meal-curing agent adhesive layer formed by coating an aramid pulp meal-resin-curing agent mixture on the resin-carbon nano tube precoat.
10. An interlaminar toughened composite as claimed in claim 9 wherein: the interlayer toughened surface is polished prior to coating the carbon nanotube-acetone-resin mixture to form holes or indentations that increase the contact area of the surface with the resin.
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| US20150166743A1 (en) * | 2013-12-13 | 2015-06-18 | Cytec Industries Inc. | Composite materials with electrically conductive and delamination resistant properties |
| CN109722194A (en) * | 2018-12-27 | 2019-05-07 | 浙江理工大学 | The preparation of multi-walled carbon nanotube modified epoxy and FRP- concrete binding monitoring method |
| CN110117409A (en) * | 2019-05-06 | 2019-08-13 | 西北工业大学 | A method of using multi-walled carbon nanotube toughening composition interlayer |
| CN111320841A (en) * | 2020-01-08 | 2020-06-23 | 浙江精功碳纤维有限公司 | Aramid fiber/carbon nanotube composite reinforced carbon fiber resin prepreg |
| CN111391421A (en) * | 2020-02-25 | 2020-07-10 | 长安大学 | Carbon fiber and metal composite structure and preparation method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US20150166743A1 (en) * | 2013-12-13 | 2015-06-18 | Cytec Industries Inc. | Composite materials with electrically conductive and delamination resistant properties |
| CN109722194A (en) * | 2018-12-27 | 2019-05-07 | 浙江理工大学 | The preparation of multi-walled carbon nanotube modified epoxy and FRP- concrete binding monitoring method |
| CN110117409A (en) * | 2019-05-06 | 2019-08-13 | 西北工业大学 | A method of using multi-walled carbon nanotube toughening composition interlayer |
| CN111320841A (en) * | 2020-01-08 | 2020-06-23 | 浙江精功碳纤维有限公司 | Aramid fiber/carbon nanotube composite reinforced carbon fiber resin prepreg |
| CN111391421A (en) * | 2020-02-25 | 2020-07-10 | 长安大学 | Carbon fiber and metal composite structure and preparation method thereof |
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