CN202430445U - Fiber fabric with opening structure - Google Patents

Abstract

The utility model discloses a fiber fabric with an opening structure and a preparation method of a fiber composite material with the opening structure. The fiber trajectory of the fiber fabric is a family of elliptic curves. The magnitudes of a long axis and a short axis are changed in a gradual way from an opening part to the edge of the fiber fabric. Compared with the prior art, the fiber fabric provided by the utility model has the advantages that the fibers are continuous, the fiber direction is parameterized, the curvature radius is controllable, the concentrated stress can be effectively reduced and the mass production can be realized. The fiber composite material with the opening structure which is made of the fiber fabric has the advantages of low cost, high strength, convenience and simplicity in preparation, nearly no fiber material wastage and the like.

Description

Fiber fabric with open cell structure

technical field

The utility model relates to the technical field of fiber composite materials, in particular to a fiber fabric with an open-pore structure and a preparation method for a fiber composite material part with an open-pore structure.

Background technique

Due to its high specific strength, high specific stiffness, excellent shock absorption, fatigue resistance, corrosion resistance and other advantages, fiber composite materials have been widely used in aerospace, sporting goods, automobiles, wind power generation and other fields. Due to the requirements of material connection, weight reduction and viewing windows, holes (openings) are often required on fiber composite parts. However, opening holes (openings) on the fiber composite material will inevitably lead to stress concentration at the edge of the hole (mouth), which greatly reduces the mechanical properties of the fiber composite material.

The existing methods for enhancing the opening are:

(1) Reinforcement method: first open holes in the fiber composite parts, break the fibers, and then use reinforcement sheets to reinforce the opening parts; or place the reinforcement sheets on the opening when preparing fiber composite parts Holes, and then integrally solidified and molded, and then open holes in the formed fiber composite parts, but it is also necessary to break the fibers of the fiber composite body.

(2) Reinforced fabric forming method: The reinforced fabric forming method makes full use of the anisotropy of fiber mechanical properties, avoids interrupting fibers, directly prepares open-pore structure fabrics with fiber ribbons, and then forms open-pore fiber composite parts.

The reinforcement method needs to add an additional layer or several layers of reinforcement sheets to the opening of the fibril composite part, which increases the weight of the part and requires an additional reinforcement process. Compared with the reinforcement method, the reinforced fabric forming method greatly reduces the stress concentration factor of the open-hole fiber composite material at the hole part without requiring additional reinforcement processes, improves the strength, and has a significant weight reduction effect.

In the reinforced fabric forming method, the form of the fiber track when the fiber ribbon is used to prepare the fiber fabric with an open structure mainly includes the following types:

(1) The fiber trajectory is consistent with the principal stress direction

This form of fiber trajectory easily leads to fiber discontinuity and too small curvature radius, resulting in stress concentration.

(2) Pre-embed the screw to extrude the fiber in the hole, so that the fiber track is in a curved shape

This form of fiber trajectory is only suitable for open-cell laminates under tension.

(3) The fiber trajectory at the near hole is a circular curve, and the fiber trajectory at the far hole is a straight line

Due to the large angle change of the fiber direction at the junction of the near hole and the far hole, this form of fiber track is prone to stress concentration, which greatly reduces the strength of the fiber composite product.

Utility model content

The technical purpose of this utility model is to aim at the fiber discontinuity caused by the laying form of the fiber track when the reinforced fabric forming method is used in the above-mentioned prior art to prepare fiber composite parts with an open structure, and the radius of curvature is too small, which is easy to Stress concentration and other deficiencies occur, and a fiber fabric with an open-pore structure is provided. The fiber fabric has the advantages of continuous fiber, parameterized fiber direction, controllable radius of curvature, can effectively reduce stress concentration, and is suitable for mass production. Fiber composite parts with open pores made of fiber fabrics have the advantages of low cost, high strength, convenient and simple production, and almost no waste of fiber materials.

The technical scheme adopted by the utility model to realize the above-mentioned technical purpose is: a fiber fabric with an open structure, the fiber fabric is a single layer or multiple layers laid on a certain trajectory under the action of sutures and/or adhesives. In the fabric formed under, the fiber trajectory is represented by the following elliptic curve family equations:

$\frac{{\mathrm{<span\; class="notranslate">\; x</span>}}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}{{<span\; class="notranslate">\; (</span>\mathrm{<span\; class="notranslate">\; r</span>}<span\; class="notranslate">\; +</span>\mathrm{<span\; class="notranslate">\; vt</span>}<span\; class="notranslate">\; )</span>}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}<span\; class="notranslate">\; +</span>\frac{{\mathrm{<span\; class="notranslate">\; the\; y</span>}}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}{{<span\; class="notranslate">\; (</span>\mathrm{<span\; class="notranslate">\; r</span>}<span\; class="notranslate">\; +</span>\mathrm{<span\; class="notranslate">\; t</span>}<span\; class="notranslate">\; )</span>}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}<span\; class="notranslate">\; =</span>\mathrm{<span\; class="notranslate">\; 1</span>}$

in,

r is the hole radius of the fiber fabric with open-pore structure;

t is the expansion coefficient of the elliptic curve family;

v is an optimized design parameter, which can be any constant or any function of t, and represents the speed of the change of the length of the major axis relative to the minor axis of the elliptic curve family from the edge of the hole to the edge of the fabric.

The fiber is one or a mixture of fiber prepreg tape or dry fiber bundle. Among them, the fiber prepreg refers to fibers impregnated with matrix resin, and at this time, the matrix resin also functions as an adhesive. The matrix resin is selected from one of unsaturated resin, epoxy resin and vinyl ester resin.

The types of fiber bundles include but are not limited to one or more of glass fibers, carbon fibers, and aramid fibers.

The method of using the fiber fabric of the present utility model to prepare a fiber composite material part with an open structure comprises the following steps (the fiber composite material is a composite material formed by a matrix resin material and a fiber material):

Step 1: Lay the fibers according to the trajectory represented by the following elliptic curve family equations, fix the fibers with sutures and/or adhesives to form a single-layer fiber fabric with an open-pore structure, and repeat laying several layers to prepare fiber composite parts With a fiber preform, align the long axes of the layers:

$\frac{{\mathrm{<span\; class="notranslate">\; x</span>}}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}{{<span\; class="notranslate">\; (</span>\mathrm{<span\; class="notranslate">\; r</span>}<span\; class="notranslate">\; +</span>\mathrm{<span\; class="notranslate">\; vt</span>}<span\; class="notranslate">\; )</span>}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}<span\; class="notranslate">\; +</span>\frac{{\mathrm{<span\; class="notranslate">\; the\; y</span>}}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}{{<span\; class="notranslate">\; (</span>\mathrm{<span\; class="notranslate">\; r</span>}<span\; class="notranslate">\; +</span>\mathrm{<span\; class="notranslate">\; t</span>}<span\; class="notranslate">\; )</span>}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}<span\; class="notranslate">\; =</span>\mathrm{<span\; class="notranslate">\; 1</span>}$

Among them, r is the hole radius of fiber composite parts with open-pore structure; t is the expansion coefficient of the elliptic curve family; v is the optimal design parameter, which is an arbitrary constant or any function of t, which means that the elliptic curve family is from the edge of the hole to the fiber At the edge of the fabric, the length of the major axis changes relative to the minor axis;

Step 2: curing and molding the fiber preform obtained in step 1 by using a composite material forming process to obtain a fiber composite material product with an open-pore structure.

The composite material forming process is selected from one of composite material liquid molding process and autoclave forming process. Among them, the composite material liquid molding process includes but not limited to resin transfer molding process, vacuum assisted injection molding process and resin film infiltration molding process. When the fiber is a fiber prepreg tape, the molding process of the composite material adopts an autoclave process.

Compared with the prior art, the fiber fabric provided by the utility model has the following advantages:

(1) The fiber trajectory is a series of ellipses (including circles), and the size of the major axis and minor axis is gradually changed from the hole to the edge of the fiber fabric. Through gradual changes, large angles between the fibers are effectively avoided. Changes to reduce stress concentration; at the same time, the fiber trajectory can ensure the continuity of the fiber, and the radius of curvature is controllable.

(2) The fiber trajectory is parameterized, and the designability is strong, which is conducive to mass production and reduces costs.

(3) The length, width and hole radius of the fiber fabric can be determined according to the needs of fiber composite parts with an open-pore structure. The trajectory of the elliptic curve family equation can be rotated by a certain degree around the central hole to form a corresponding fabric to meet the requirements of different working conditions of the open-hole laminated board.

(4) After optimized design, the fiber composite material parts with opening structure prepared by adopting the fiber fabric of the utility model can greatly reduce the maximum stress, improve the strength and reduce the weight under various working conditions.

In addition, in addition to the above-mentioned advantages, the fiber fabric of the present invention also has the following advantages when preparing a fiber composite product with an open-pore structure:

(1) The preparation process is simple, and no additional reinforcement process is required for the opening part;

(2) There is almost no waste of fiber materials in the preparation process, which greatly reduces the amount of fibers and saves costs. For parts with large-area open-pore structures, the amount of fiber savings is particularly obvious.

Description of drawings

Fig. 1 is a schematic diagram of the shape of the carbon fiber composite laminated plate with open-hole structure and the direction of the tensile load in Examples 1 to 4 of the present invention and Comparative Example 1 and Comparative Example 2;

Fig. 2 is the reinforcing sheet schematic diagram of comparative example 1 and comparative example 2 of the utility model;

Fig. 3 is a schematic diagram of the circular curve family fiber trajectory of the fiber fabric in Example 1 of the utility model;

Fig. 4 is a schematic diagram of the elliptic curve family fiber trajectory of the fiber fabric in Example 2 of the utility model;

Fig. 5 is a schematic diagram of the elliptic curve family fiber trajectory of the fiber fabric in Example 3 of the present utility model;

Fig. 6 is a schematic diagram of the elliptic curve family fiber trajectory of the fiber fabric in Example 4 of the present utility model.

Detailed ways

The utility model will be further described in detail below with reference to the embodiments of the accompanying drawings. It should be noted that the following embodiments are intended to facilitate the understanding of the utility model, but do not limit it in any way.

Comparative Example 1:

In this embodiment, the carbon fiber/epoxy resin composite laminate with an open structure as shown in FIG. 1 is first prepared by using the prior art, and then the opening is reinforced by the reinforcing sheet in the prior art.

Raw materials: Toray 12K T700 carbon fiber is used for carbon fiber, and the epoxy resin is a resin formed by mixing epoxy resin E-20 and epoxy resin E-54 at a mass ratio of 1:1.

Opening structure: carbon fiber/epoxy resin composite laminates are open in the center, with a circular hole with a radius of 0.015m.

The preparation method of the carbon fiber/epoxy resin composite laminate with open cell structure is as follows:

Step 1: Dip Toray 12K T700 carbon fiber into prepreg resin to prepare carbon fiber prepreg tape, wherein the prepreg resin formula is: (1) Resin: epoxy resin E-20 and epoxy resin E-54 mass ratio is 1: 1; (2) curing agent: the mass ratio of dimethyl diphenylmethane, dimethyl diphenyl sulfone and imidazole is 8:20:1;

Step 2: Lay the carbon fiber prepreg tape obtained in step 1 into an isotropic layup (-45°/90°/+45°/0°) _S , and then use the autoclave process to heat up to 90°C for 1.5 hours to cure. Then heat up to 120°C for 2 hours and then cool down naturally to obtain a formed carbon fiber/epoxy resin composite laminate;

Step 3: Drill a hole in the center of the carbon fiber/epoxy resin composite laminate obtained in step 2 with a hole radius of 0.015 m to obtain a carbon fiber/epoxy resin composite laminate with an open-pore structure.

Adopt prior art to carry out reinforcement to the hole position of the above-mentioned carbon fiber/epoxy resin composite laminated plate with hole structure that makes above, concrete method is as follows:

Step 1: Toray 12K T700 carbon fiber cloth prepreg is used to prepare the reinforcing sheet preform as shown in Figure 2;

Step 2: preparing the reinforcing sheet preform obtained in step 1 into a reinforcing sheet through an autoclave molding process;

Step 3: Lay the reinforcing sheet obtained in step 2 on the opening of the prepared carbon fiber/epoxy resin composite laminate with open structure, and connect the reinforcing sheet and the carbon fiber/ring with metal rivets at the edge of the opening Oxygen composite laminates.

Comparative example 2:

In this example, the carbon fiber/unsaturated polyester resin composite laminate with an open structure as shown in Figure 1 is first prepared by using the prior art, and then the opening is repaired using the reinforcing sheet in the prior art. strengthen.

Raw materials: Toray 12K T700 carbon fiber is used as carbon fiber. The unsaturated polyester resin system is made by mixing unsaturated polyester resin, initiator (methyl ethyl ketone peroxide) and accelerator (cobalt octoate) in a ratio of 100:1.5:0.5.

Opening structure: a carbon fiber/unsaturated polyester composite laminate has a central opening, and a circular hole with a radius of 0.015m.

The preparation method of the carbon fiber/unsaturated polyester composite laminate with open-pore structure is as follows:

Step 1: Lay Toray 12K T700 carbon fiber unidirectional fabric according to the size in Figure 1 to form a quasi-isotropic layup (-45°/90°/+45°/0°) _S preform;

Step 2: prepare the unsaturated polyester resin system in proportion, and the formula is mixed with unsaturated polyester resin, initiator (methyl ethyl ketone peroxide) and accelerator (cobalt octanoate) according to the ratio of 100:1.5:0.5;

Step 3: Inject the unsaturated polyester resin system obtained in step 2 into the carbon fiber preform obtained in step 1 through the vacuum-assisted resin injection molding process, then raise the temperature to 90°C for 2 hours and then cure at 40°C for 2 hours, 60 Curing at ℃ for 2 hours, curing at 80℃ for 4 hours and then cooling down naturally to obtain a carbon fiber/unsaturated polyester resin composite laminate;

Step 4: Drill a hole in the center of the carbon fiber/unsaturated polyester resin composite laminate obtained in step 3 with a hole radius of 0.015 m to obtain a carbon fiber/unsaturated polyester resin composite laminate with an open-pore structure.

Adopt prior art to carry out reinforcement to the opening position of the above-mentioned carbon fiber/unsaturated polyester resin composite material laminated plate with opening structure prepared above, concrete method is as follows:

Step 1: Prepare the preform of the reinforcing sheet as shown in Figure 2 with Toray 12K T700 carbon fiber cloth;

Step 2: prepare the unsaturated polyester resin system in proportion, and the formula is mixed with unsaturated polyester resin, initiator (methyl ethyl ketone peroxide) and accelerator (cobalt octanoate) according to the ratio of 100:1.5:0.5;

Step 3: preparing the reinforcement sheet preform obtained in step 1 into a reinforcement sheet by a vacuum-assisted resin injection molding process;

Step 4: Lay the reinforcing sheet obtained in step 3 on the opening of the prepared open-pore structure carbon fiber/unsaturated polyester resin composite laminate, and connect the reinforcing sheet and carbon fiber with metal rivets at the edge of the opening /Unsaturated polyester resin composite laminate.

Example 1:

In this implementation, the raw materials and the hole structure of the carbon fiber/epoxy resin composite laminate with the open structure are exactly the same as those of Comparative Example 1. The difference is that in the carbon fiber/epoxy resin composite laminate with an open structure, the carbon fiber fabric with an open structure formed by the carbon fiber prepreg tape under the action of the adhesive has a certain shape of fiber tracks. The trajectory is represented by the following elliptic curve family equation (1):

$\frac{{\mathrm{<span\; class="notranslate">\; x</span>}}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}{{<span\; class="notranslate">\; (</span>\mathrm{<span\; class="notranslate">\; r</span>}<span\; class="notranslate">\; +</span>\mathrm{<span\; class="notranslate">\; vt</span>}<span\; class="notranslate">\; )</span>}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}<span\; class="notranslate">\; +</span>\frac{{\mathrm{<span\; class="notranslate">\; the\; y</span>}}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}{{<span\; class="notranslate">\; (</span>\mathrm{<span\; class="notranslate">\; r</span>}<span\; class="notranslate">\; +</span>\mathrm{<span\; class="notranslate">\; t</span>}<span\; class="notranslate">\; )</span>}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}<span\; class="notranslate">\; =</span>\mathrm{<span\; class="notranslate">\; 1</span>}<span\; class="notranslate">\; -</span><span\; class="notranslate">\; -</span><span\; class="notranslate">\; -</span><span\; class="notranslate">\; (</span>\mathrm{<span\; class="notranslate">\; 1</span>}<span\; class="notranslate">\; )</span>$

Among them, r is the hole radius 0.015m of the carbon fiber/epoxy resin composite laminate with an open structure, and v is a constant 1, that is, the fiber trajectory is a family of circular curves represented by the following equation (2):

$\frac{{\mathrm{<span\; class="notranslate">\; x</span>}}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}{{<span\; class="notranslate">\; (</span>\mathrm{<span\; class="notranslate">\; 0.015</span>}<span\; class="notranslate">\; +</span>\mathrm{<span\; class="notranslate">\; t</span>}<span\; class="notranslate">\; )</span>}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}<span\; class="notranslate">\; +</span>\frac{{\mathrm{<span\; class="notranslate">\; the\; y</span>}}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}{{<span\; class="notranslate">\; (</span>\mathrm{<span\; class="notranslate">\; 0.015</span>}<span\; class="notranslate">\; +</span>\mathrm{<span\; class="notranslate">\; t</span>}<span\; class="notranslate">\; )</span>}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}<span\; class="notranslate">\; =</span>\mathrm{<span\; class="notranslate">\; 1</span>}<span\; class="notranslate">\; -</span><span\; class="notranslate">\; -</span><span\; class="notranslate">\; -</span><span\; class="notranslate">\; (</span>\mathrm{<span\; class="notranslate">\; 2</span>}<span\; class="notranslate">\; )</span>$

The fiber fabric is 0.2m long and 0.1m wide, and is made of Toray 12K T700 carbon fiber pre-impregnated with an epoxy resin system (the epoxy resin system can be equivalent to an adhesive), wherein the epoxy resin is made of The resin formed by mixing epoxy resin E-20 and epoxy resin E-54 at a mass ratio of 1:1.

Fig. 3 is a schematic diagram of laying the circular curve family fiber track of the carbon fiber fabric shown in equation (2). The dotted lines in the figure are the major axis and the minor axis of the ellipse trajectory, respectively, and the solid lines are some fiber trajectories in the carbon fiber fabric.

The preparation method of the above-mentioned open-pore structure carbon fiber/epoxy resin composite laminate is as follows:

Step 1: Dip Toray 12K T700 carbon fiber into prepreg resin to prepare carbon fiber prepreg tape, wherein the prepreg resin formula is: (1) Resin: epoxy resin E-20 and epoxy resin E-54 mass ratio is 1: 1; (2) curing agent: the mass ratio of dimethyl diphenylmethane, dimethyl diphenyl sulfone and imidazole is 8:20:1;

Step 2: Lay the carbon fiber prepreg tape obtained in step 1 according to the fiber trajectory shown in Figure 3 to form a prepreg fabric, and lay eight layers repeatedly so that the long axes of the eight layers of prepreg fabric are aligned;

Step 3: Use an autoclave process to raise the temperature to 90°C for 1.5 hours, then raise the temperature to 120°C for 2 hours and then cool down naturally to obtain a carbon fiber/epoxy resin composite laminate with an open-pore structure.

Tensile tests were carried out on the carbon fiber/epoxy resin composite laminates with open-cell structure prepared above, and the direction of the tensile load is shown in Figure 1 . The test results show that compared with the unreinforced and reinforced open-cell carbon fiber/epoxy resin composite laminates prepared in Comparative Example 1, the tensile failure loads are increased by 37% and 20% respectively.

At the same time, it can be seen from the above preparation method that, compared with Comparative Example 1, this embodiment simplifies the preparation process on the one hand, and does not require additional reinforcement processes for the opening parts; on the other hand, because there is almost no carbon fiber in the preparation process waste, greatly reducing the amount of carbon fiber and saving costs, especially when the opening area is large.

Example 2:

In this implementation, the raw materials and the hole structure of the carbon fiber/epoxy resin composite laminate with the open structure are exactly the same as those of Comparative Example 1. The difference is that in the carbon fiber/epoxy resin composite laminate with an open structure, the carbon fiber fabric with an open structure formed by fixing the dry carbon fiber with a suture has a fiber track of a certain shape, which is composed of the following The elliptic curve family equation (3) expresses:

$\frac{{\mathrm{<span\; class="notranslate">\; x</span>}}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}{{<span\; class="notranslate">\; (</span>\mathrm{<span\; class="notranslate">\; r</span>}<span\; class="notranslate">\; +</span>\mathrm{<span\; class="notranslate">\; vt</span>}<span\; class="notranslate">\; )</span>}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}<span\; class="notranslate">\; +</span>\frac{{\mathrm{<span\; class="notranslate">\; the\; y</span>}}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}{{<span\; class="notranslate">\; (</span>\mathrm{<span\; class="notranslate">\; r</span>}<span\; class="notranslate">\; +</span>\mathrm{<span\; class="notranslate">\; t</span>}<span\; class="notranslate">\; )</span>}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}<span\; class="notranslate">\; =</span>\mathrm{<span\; class="notranslate">\; 1</span>}<span\; class="notranslate">\; -</span><span\; class="notranslate">\; -</span><span\; class="notranslate">\; -</span><span\; class="notranslate">\; (</span>\mathrm{<span\; class="notranslate">\; 3</span>}<span\; class="notranslate">\; )</span>$

Among them, r is the hole radius 0.015m of the carbon fiber/epoxy resin composite laminate with an open structure, and v is a constant 2, that is, the fiber trajectory is an elliptic curve family represented by the following equation (4):

$\frac{{\mathrm{<span\; class="notranslate">\; x</span>}}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}{{<span\; class="notranslate">\; (</span>\mathrm{<span\; class="notranslate">\; 0.015</span>}<span\; class="notranslate">\; +</span>\mathrm{<span\; class="notranslate">\; t</span>}<span\; class="notranslate">\; )</span>}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}<span\; class="notranslate">\; +</span>\frac{{\mathrm{<span\; class="notranslate">\; the\; y</span>}}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}{{<span\; class="notranslate">\; (</span>\mathrm{<span\; class="notranslate">\; 0.015</span>}<span\; class="notranslate">\; +</span>\mathrm{<span\; class="notranslate">\; t</span>}<span\; class="notranslate">\; )</span>}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}<span\; class="notranslate">\; =</span>\mathrm{<span\; class="notranslate">\; 1</span>}<span\; class="notranslate">\; -</span><span\; class="notranslate">\; -</span><span\; class="notranslate">\; -</span><span\; class="notranslate">\; (</span>\mathrm{<span\; class="notranslate">\; 4</span>}<span\; class="notranslate">\; )</span>$

Fig. 4 is a schematic diagram of laying the elliptical curve family fiber track of the carbon fiber fabric shown in equation (4). The dotted lines in the figure are the major axis and the minor axis of the ellipse trajectory, respectively, and the solid lines are some fiber trajectories in the carbon fiber fabric.

The preparation method of the above-mentioned open-pore structure carbon fiber/epoxy resin composite laminate is as follows:

Step 1: Lay the Toray 12K T700 dry carbon fiber according to the fiber trajectory shown in Figure 4, and fix it with sutures, and then pre-impregnate the resin to form a pre-preg fabric. The pre-impregnation resin formula is: (1) Resin: Ring The mass ratio of epoxy resin E-20 and epoxy resin E-54 is 1: 1; (2) curing agent: the mass ratio of dimethyl diphenylmethane, dimethyl diphenyl sulfone and imidazole is 8: 20: 1;

Step 2: Lay eight layers of the carbon fiber prepreg fabric obtained in step 1 repeatedly, so that the long axes of the eight layers of prepreg fabric are aligned;

Step 3: Use an autoclave process to raise the temperature to 90°C for 1.5 hours, then raise the temperature to 120°C for 2 hours and then cool down naturally to obtain a carbon fiber/epoxy resin composite laminate with an open-pore structure.

Tensile tests were carried out on the carbon fiber/epoxy resin composite laminates with open-cell structure prepared above, and the direction of the tensile load is shown in Figure 1 . The test results show that compared to the unreinforced and reinforced open-cell carbon fiber/epoxy resin composite laminates prepared in Comparative Example 1, the tensile failure load has been increased by 52% and 32% respectively .

At the same time, it can be seen from the above preparation method that, compared with Comparative Example 1, this embodiment simplifies the preparation process on the one hand, and does not require additional reinforcement processes for the opening parts; on the other hand, because there is almost no carbon fiber in the preparation process waste, greatly reducing the amount of carbon fiber and saving costs, especially when the opening area is large.

Example 3:

In this implementation, the raw material and opening structure of the carbon fiber/unsaturated polyester resin composite laminate with an open structure are exactly the same as those in Comparative Example 2. The difference is that in the carbon fiber/unsaturated polyester resin composite laminate with an open structure, the carbon fiber fabric with an open structure formed by fixing the dry carbon fiber with a suture has a fiber track of a certain shape. The elliptic curve after the overall rotation of 15° by the above elliptic curve family equation (4).

Fig. 5 is a schematic diagram of laying of elliptical curve family fiber tracks of the carbon fiber fabric. The dotted lines in the figure are the major axis and the minor axis of the ellipse trajectory, respectively, and the solid lines are some fiber trajectories in the carbon fiber fabric.

The preparation method of the above-mentioned open-pore structure carbon fiber/unsaturated polyester resin composite laminate is as follows:

Step 1: Lay Toray 12K T700 dry carbon fiber according to the fiber trajectory shown in Figure 5, and fix it with sutures to form a carbon fiber fabric;

Step 2: Lay eight layers of the carbon fiber fabric obtained in step 1 repeatedly, so that the long axes of the eight layers of carbon fiber fabric are aligned;

Step 3: prepare unsaturated polyester resin in proportion, and the formula is mixed with unsaturated polyester resin, initiator (methyl ethyl ketone peroxide) and accelerator (cobalt octanoate) according to the mass ratio of 100:1.5:0.5; step 4: Inject the unsaturated polyester resin system obtained in step 3 into the carbon fiber fabric obtained in step 2 through the vacuum-assisted resin injection molding process, then raise the temperature to 90°C for 2 hours, then cure for 2 hours at 40°C, and cure for 2 hours at 60°C , cured at 80°C for 4 hours and then cooled naturally to obtain a carbon fiber/unsaturated polyester resin composite laminate with an open-pore structure.

A tensile test was performed on the carbon fiber/unsaturated polyester resin composite laminate with an open-cell structure prepared above, and the direction of the tensile load is shown in FIG. 1 . The test results show that compared to the non-reinforced and reinforced open-cell carbon fiber/unsaturated polyester resin composite laminate made in comparative example 2, its tensile failure load has been increased by 43% and 43% respectively. twenty four%.

At the same time, it can be seen from the above preparation method that, compared with Comparative Example 2, this embodiment simplifies the preparation process on the one hand, and does not require additional reinforcement processes for the opening parts; on the other hand, because there is almost no carbon fiber in the preparation process waste, greatly reducing the amount of carbon fiber and saving costs, especially when the opening area is large.

Example 4:

In this implementation, the raw material and opening structure of the carbon fiber/unsaturated polyester resin composite laminate with an open structure are exactly the same as those in Comparative Example 2. The difference is that in the carbon fiber/unsaturated polyester resin composite laminate with an open structure, the carbon fiber fabric with an open structure formed by fixing the dry carbon fiber with a suture has a fiber track of a certain shape. It is represented by the following elliptic curve family equation (5):

$\frac{{\mathrm{<span\; class="notranslate">\; x</span>}}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}{{<span\; class="notranslate">\; (</span>\mathrm{<span\; class="notranslate">\; r</span>}<span\; class="notranslate">\; +</span>\mathrm{<span\; class="notranslate">\; vt</span>}<span\; class="notranslate">\; )</span>}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}<span\; class="notranslate">\; +</span>\frac{{\mathrm{<span\; class="notranslate">\; the\; y</span>}}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}{{<span\; class="notranslate">\; (</span>\mathrm{<span\; class="notranslate">\; r</span>}<span\; class="notranslate">\; +</span>\mathrm{<span\; class="notranslate">\; t</span>}<span\; class="notranslate">\; )</span>}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}<span\; class="notranslate">\; =</span>\mathrm{<span\; class="notranslate">\; 1</span>}<span\; class="notranslate">\; -</span><span\; class="notranslate">\; -</span><span\; class="notranslate">\; -</span><span\; class="notranslate">\; (</span>\mathrm{<span\; class="notranslate">\; 5</span>}<span\; class="notranslate">\; )</span>$

Among them, r is the hole radius of the carbon fiber/unsaturated polyester resin composite laminate with open structure 0.015m, v is a function of t, and its function equation is as follows:

v＝f(t)＝2sin(8πt) (6)

That is, the fiber trajectory is an elliptic curve family represented by the following equation (7):

$\frac{{\mathrm{<span\; class="notranslate">\; x</span>}}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}{{<span\; class="notranslate">\; (</span>\mathrm{<span\; class="notranslate">\; 0.015</span>}<span\; class="notranslate">\; +</span>\mathrm{<span\; class="notranslate">\; 2</span>}\mathrm{<span\; class="notranslate">\; sin</span>}<span\; class="notranslate">\; (</span>\mathrm{<span\; class="notranslate">\; 8</span>}\mathrm{<span\; class="notranslate">\; \&pi;t</span>}<span\; class="notranslate">\; )</span>\mathrm{<span\; class="notranslate">\; t</span>}<span\; class="notranslate">\; )</span>}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}<span\; class="notranslate">\; +</span>\frac{{\mathrm{<span\; class="notranslate">\; the\; y</span>}}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}{{<span\; class="notranslate">\; (</span>\mathrm{<span\; class="notranslate">\; 0.015</span>}<span\; class="notranslate">\; +</span>\mathrm{<span\; class="notranslate">\; t</span>}<span\; class="notranslate">\; )</span>}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}<span\; class="notranslate">\; =</span>\mathrm{<span\; class="notranslate">\; 1</span>}<span\; class="notranslate">\; -</span><span\; class="notranslate">\; -</span><span\; class="notranslate">\; -</span><span\; class="notranslate">\; (</span>\mathrm{<span\; class="notranslate">\; 7</span>}<span\; class="notranslate">\; )</span>$

Fig. 6 is a schematic diagram of laying the elliptical curve family fiber track of the carbon fiber fabric shown in equation (7). The dotted lines in the figure are the major axis and the minor axis of the ellipse trajectory, respectively, and the solid lines are some fiber trajectories in the carbon fiber fabric. The preparation method of the above-mentioned open-pore structure carbon fiber/unsaturated polyester resin composite laminate is as follows:

Step 1: Lay Toray 12K T700 dry carbon fiber according to the fiber trajectory shown in Figure 6, and fix it with sutures to obtain a carbon fiber fabric;

Step 2: Lay eight layers of the carbon fiber fabric obtained in step 1 repeatedly, so that the long axes of the eight layers of carbon fiber fabric are aligned;

Step 3: prepare unsaturated polyester resin in proportion, and the formula is mixed with unsaturated polyester resin, initiator (methyl ethyl ketone peroxide) and accelerator (cobalt octanoate) according to the mass ratio of 100:1.5:0.5;

Step 4: Inject the unsaturated polyester resin system obtained in step 3 into the carbon fiber fabric obtained in step 2 through the vacuum-assisted resin injection molding process, then raise the temperature to 90°C for 2 hours and then cure at 40°C for 2 hours, and then cure at 60°C for 2 hours. Curing for 2 hours, curing at 80° C. for 4 hours and then cooling down naturally to obtain a carbon fiber/unsaturated polyester resin composite laminate with an open-pore structure.

A tensile test was performed on the carbon fiber/unsaturated polyester resin composite laminate with an open-cell structure prepared above, and the direction of the tensile load is shown in FIG. 1 . The test results show that compared to the non-reinforced and reinforced open-cell carbon fiber/unsaturated polyester resin composite laminates made in comparative example 2, the tensile failure load has increased by 47% and 27%. %.

At the same time, it can be seen from the above preparation method that, compared with Comparative Example 2, this embodiment simplifies the preparation process on the one hand, and does not require additional reinforcement processes for the opening parts; on the other hand, because there is almost no carbon fiber in the preparation process waste, greatly reducing the amount of carbon fiber and saving costs, especially when the opening area is large.

The embodiments described above have described the technical solutions and beneficial effects of the utility model in detail. It should be understood that the above descriptions are only specific embodiments of the utility model, and are not intended to limit the utility model. Any modification, supplement or equivalent replacement made within the scope of the principle shall be included in the protection scope of the present utility model.

Claims (3)

1. A kind of fiber fabric with open-pore structure, described fiber fabric is the fabric that single-layer or multi-layer is laid with the fiber of certain trajectory and forms under the effect of sewing thread and/or adhesive agent, it is characterized in that: all The fiber trajectory described above is represented by the following elliptic curve family equations: $\frac{{\mathrm{<span\; class="notranslate">\; x</span>}}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}{{<span\; class="notranslate">\; (</span>\mathrm{<span\; class="notranslate">\; r</span>}<span\; class="notranslate">\; +</span>\mathrm{<span\; class="notranslate">\; vt</span>}<span\; class="notranslate">\; )</span>}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}<span\; class="notranslate">\; +</span>\frac{{\mathrm{<span\; class="notranslate">\; the\; y</span>}}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}{{<span\; class="notranslate">\; (</span>\mathrm{<span\; class="notranslate">\; r</span>}<span\; class="notranslate">\; +</span>\mathrm{<span\; class="notranslate">\; t</span>}<span\; class="notranslate">\; )</span>}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}<span\; class="notranslate">\; =</span>\mathrm{<span\; class="notranslate">\; 1</span>}$ in, r is the hole radius of the fiber fabric with open-pore structure; t is the expansion coefficient of the elliptic curve family; v is an optimal design parameter, which is an arbitrary constant or an arbitrary function of t, and represents the speed of change of the length of the major axis relative to the minor axis of the elliptic curve family from the edge of the hole to the edge of the fabric. 2. The fiber fabric with open pores according to claim 1, characterized in that: said fibers are one or a mixture of fiber prepreg and dry fiber bundles. 3. The fiber fabric with an open cell structure according to claim 1 or 2, characterized in that: said fibers include a mixture of one or more of glass fibers, carbon fibers, and aramid fibers.

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