Manufacturing process of fiber reinforced composite materials and fiber reinforced composite materials

Abstract

The present invention relates to the technical field of fiber-reinforced composite materials, and in particular to a manufacturing process for fiber-reinforced composite materials and a fiber-reinforced composite material prepared by the manufacturing process. The manufacturing process mainly involves regularly interlocking a number of fiber bundles to form a three-dimensional preform. The three-dimensional preform is a three-dimensional fabric, which has an internal structure and an outer contour interwoven into one, and is a non-layered integral structure; the three-dimensional preform is sequentially dried, pretreated, resin-impregnated, and pultruded to form a fiber-reinforced composite material, and the fiber-reinforced composite material is post-cured; the fiber bundles, the three-dimensional preform, and the fiber-reinforced composite material are pulled forward by the same traction force, so that the above process is carried out continuously under the action of the traction force. Combining the three-dimensional preform with the pultrusion process gives full play to the continuity and low cost characteristics of the composite material pultrusion process and the excellent comprehensive performance of the three-dimensional preform and the characteristics of the integrated net size molding.

Description

Technical Field

[0001] The present invention relates to the technical field of fiber reinforced composite materials, and in particular to a manufacturing process of a fiber reinforced composite material and a fiber reinforced composite material prepared by using the manufacturing process of the fiber reinforced composite material. Background Art

[0002] Composite materials generally refer to new materials formed by combining two or more materials of different genera. High-performance fibers, with their excellent mechanical properties, can be combined with resins to create composite materials that can be used as load-bearing structures. These composite materials are known as fiber-reinforced composites. The fibers, as the primary load-bearing structure, are called reinforcements, while the resin, responsible for protecting and integrating the fibers, ensuring their uniform dispersion, improving the uniformity of force applied to each filament within the fiber, and fully utilizing the fiber's mechanical properties, is known as the matrix.

[0003] In the existing technology, the manufacturing processes of fiber-reinforced composite materials mainly include the following: spraying short fiber process, unidirectional tape laying process, prepreg fabric laying process, filament winding process, preform vacuum assisted induction molding process (hereinafter referred to as VARTM), preform resin transfer molding process (hereinafter referred to as RTM), pultrusion process, etc.

[0004] Among them, the spraying short fiber process is mostly used in the preparation of fiberglass plastics, such as old trash cans, car trim panels, etc. Its reinforcement is short fibers that are randomly and disorderly overlapped. Its performance is improved compared to pure engineering plastics, but the overall performance is insufficient, and it is mostly mass-produced as single parts. The unidirectional tape prepreg layering process is a relatively basic composite material preparation process on the market. It mainly prepares prepregs by expanding the fiber bundle width, and then layers them in a unidirectional fiber tape prepreg width overlap manner to obtain a preform, which is then heated and cured in an autoclave to obtain a composite material. Prepreg refers to a transitional form material in which fibers or their products are first impregnated with a portion of resin and then stored in a wet and viscous state, which can be further impregnated and combined with resin and used for complete curing to prepare composite materials. This process is prepared by stacking one-dimensional raw materials, and the composite material's resistance to interlayer delamination, bending, torsion, impact and other properties is insufficient. The prepreg fabric layup process is an upgrade of the material dimension of the unidirectional tape prepreg layup process, upgrading the one-dimensional raw material unidirectional tape prepreg to a two-dimensional fabric, but the principle of lamination remains unchanged. The composite material's resistance to interlayer delamination, torsion resistance, bending resistance, and impact resistance are improved, but interlayer delamination, rapid crack diffusion, and poor impact resistance are still the main problems of this process. The filament winding process is mostly a circumferential reinforcement process for gas cylinders or a certain section of circular tubes. It is a circumferential winding lamination principle within a certain interval. It is a circumferential improvement method for the unidirectional tape prepreg layup process. The circumferential compressive effect of the composite material is significantly improved, but it still belongs to the lamination principle and cannot avoid the disadvantage of rapid diffusion of impact damage. In general, these processes cannot use three-dimensional preforms to prepare composite materials. They can be generally understood as directly combining raw material fibers in different forms (such as dry fibers, short fibers, wet fibers, i.e., fiber prepregs, dry fiber fabrics, and wet fiber fabrics, i.e., fabric prepregs) with resins to prepare composite materials.

[0005] Based on the original layered preforms and resin curing, VARTM and RTM are now mostly used for three-dimensional preforms as reinforcements. After vacuuming, the resin matrix is injected to complete heating and curing to prepare composite materials. The main difference between the two is that RTM is formed by a double-sided hard mold, and the resulting composite material has two smooth decorative surfaces, while VARTM is formed by a single-sided hard mold and has only one smooth decorative surface. In addition, RTM can withstand greater vacuum pressure, has better sealing than VARTM, has lower internal pores in the composite material, and has better composite molding quality. However, the existing three-dimensional preform RTM process can only be prepared in batches and cannot achieve continuous preparation. It is highly dependent on comprehensive indicators such as the resin injection system, resin binding ability, metal mold sealing, injection hole position, and mold inner surface accuracy, and the initial investment cost is relatively high.

[0006] Pultrusion processes can be categorized into fiber-based and fabric-based pultrusion, depending on the form of the raw materials. Fiber-based pultrusion uses dry fibers or fiber prepregs as raw materials, directly utilizing the fiber form. After adding resin and shaping through a mold, composite materials, such as composite cores, are produced. The fibers within these pultruded composites are essentially parallel, formed solely through the interfacial bonding between the resin and the fiber filaments. While these composites exhibit excellent tensile strength in the fiber extension direction, mechanical properties in other directions, such as diametrical compression and bending resistance, axial torsion resistance, and impact resistance, are relatively poor. Subsequently, improved processes, such as combined pultrusion and braiding, have emerged. These processes use the fiber pultrusion process as the core, and then add fiber winding or tubular braiding around the core in a circumferential direction. This results in fiber-reinforced composites with surface helical structures or braided sheaths. However, these processes are only suitable for circumferential reinforcement of circular rods or tubes. The resulting reinforcement is limited, requiring the coordinated integration of multiple processes and machinery, resulting in a complex process. Furthermore, the quality of the finished product is significantly affected by the coordination between the two processes. Any mismatch can result in product failure or even failure. In particular, the combination of the winding / weaving process and the unidirectional fiber pultrusion process both form a "skin-core structure", in which the winding layer and the braided layer are both the skin layer, and the fiber pultrusion part is the shaft core. In the production of such components, when the winding or weaving rate is abnormally matched with the pultrusion rate, stratification is easily formed, seriously affecting product performance. In addition, the skin layer cannot effectively control the propagation of cracks inside the shaft core. Once the shaft core is damaged, the composite material still has a tendency to fail rapidly. Therefore, the fatigue resistance and impact resistance of composite materials with a "skin-core structure" are poor. The poor performance of the overall mechanical properties limits the application of composite materials, making it difficult to meet more stringent usage requirements.

[0007] Fabric pultrusion is a composite material produced by stacking a variety of raw materials such as two-dimensional fabrics, fiber felts, and fibers, adding resin, and then molding through a mold. This type of process is mostly used to prepare I / L / H / , rectangular, cylindrical, and special-shaped composite materials. Since the various fiber raw materials are still stacked internally, problems such as interlayer cracking, rapid and large-scale crack propagation, insufficient impact resistance, and insufficient fatigue resistance are the main forms of failure. The existing technology covers the outer surface of each fabric stack with a continuous fabric as a protective layer to alleviate the tendency of the internal fabric layer to delaminate. However, the closing layer of the surface covered with the fabric layer becomes a stress concentration area when the composite material is subjected to stress, and is the preferred point of damage. This method only treats the symptoms and not the root cause. It cannot restrain the delamination of the internal fabric layers and cannot effectively inhibit the rapid propagation of cracks between the internal layers. Its structure can be macroscopically classified as a skin-core structure. Summary of the Invention

[0008] In view of the above-mentioned defects of the prior art, the technical problem to be solved by the present invention is to provide a manufacturing process of a fiber reinforced composite material, which can obtain a fiber reinforced composite material with excellent comprehensive mechanical properties.

[0009] In order to solve the above technical problems, the present invention adopts the following technical solutions:

[0010] The present invention provides a manufacturing process for a fiber-reinforced composite material, which comprises the following steps in sequence: step 1, regularly and alternately interlocking a plurality of fiber bundles to form a three-dimensional preform, wherein the three-dimensional preform is a three-dimensional fabric, and the three-dimensional preform has an internal structure and an outer contour interwoven into one, and the three-dimensional preform is a non-layered integral structure; step 2, drying the three-dimensional preform; step 3, pretreating the dried three-dimensional preform; step 4, resin-impregnating and pultruding the pretreated three-dimensional preform to form a fiber-reinforced composite material; step 5, post-curing the fiber-reinforced composite material; the fiber bundles, the three-dimensional preform and the fiber-reinforced composite material are pulled forward by the same traction force, and steps 1 to 5 are performed continuously under the action of the traction force.

[0011] Preferably, in step one, continuous fiber bundles distributed along the circumferential direction are arranged on the outer contour of the three-dimensional preform.

[0012] Preferably, in step one, a three-dimensional weaving process is used to prepare the three-dimensional preform.

[0013] Preferably, in step three, the pretreatment includes primary shaping and secondary shaping, wherein the primary shaping is to perform a primary compression on the dried three-dimensional preform, and the secondary shaping is to perform a secondary compression on the three-dimensional preform after the primary shaping.

[0014] Preferably, in step three, a compression direction of the three-dimensional preform by the primary molding and a compression direction of the three-dimensional preform by the secondary molding are perpendicular to each other.

[0015] Preferably, in step 4, the resin infiltration is performed by pressure-injecting the resin into the three-dimensional preform.

[0016] Preferably, in step five, the post-cured fiber reinforced composite material is cooled.

[0017] Preferably, the method further comprises step six, performing online testing on the fiber reinforced composite material obtained in step five.

[0018] The present invention also provides a fiber-reinforced composite material, which is prepared using the above-mentioned manufacturing process for the fiber-reinforced composite material.

[0019] Compared with the prior art, the present invention has significant improvements:

[0020] The manufacturing process of the fiber-reinforced composite material of the present invention combines the three-dimensional preform molding with the composite material pultrusion process, giving full play to the continuity, low cost, high efficiency, and high-quality control characteristics of the composite material pultrusion process, and the three-dimensional preform can effectively improve the comprehensive performance of interlayer shear resistance, impact resistance, fatigue resistance, etc., as well as the characteristics of integrated net size molding. The three-dimensional preform is a complete, non-layered, and non-skin-core structure composed of fiber bundles. It can be integrated with net size molding and has the distribution characteristics of multi-axial fiber reinforcement. This makes the fiber-reinforced composite material have more outstanding comprehensive properties such as tensile strength, compression resistance, bending resistance, and torsion resistance, while also having dynamic fatigue and impact resistance. It has excellent comprehensive mechanical properties and has the advantages of high degree of integrated structural molding, outstanding contour design capabilities, strong multi-axial performance designability, strong strength, toughness, and light weight. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a schematic structural diagram of a fiber-reinforced composite material prepared by the manufacturing process of the fiber-reinforced composite material according to an embodiment of the present invention.

[0022] Figure 2 yes Figure 1 A schematic diagram of the local structure of a three-dimensional preform in a fiber-reinforced composite material is shown.

[0023] Figure 3 yes Figure 1 A schematic diagram of the side structure of a three-dimensional preform in a fiber-reinforced composite material is shown.

[0024] Figure 4 It is a schematic structural diagram of a three-dimensional textile machine used in the manufacturing process of the fiber-reinforced composite material according to an embodiment of the present invention.

[0025] Figure 5 It is a schematic structural diagram of a fiber bundle preforming and bundling device used in the manufacturing process of a fiber reinforced composite material according to an embodiment of the present invention.

[0026] Figure 6 yes Figure 1 A schematic diagram of the cross-sectional structure of a three-dimensional preform in a fiber-reinforced composite material is shown.

[0027] Figure 7 yes Figure 1 Schematic diagram of the cross-sectional structure of the fiber reinforced composite material.

[0028] Figure 8 It is a schematic diagram of the process route of the manufacturing process of the fiber reinforced composite material according to an embodiment of the present invention.

[0029] Figure 9 It is a schematic structural diagram of a preforming device used in the manufacturing process of a fiber reinforced composite material according to an embodiment of the present invention.

[0030] Figure 10 It is a schematic structural diagram of a compression device used in the manufacturing process of a fiber-reinforced composite material according to an embodiment of the present invention.

[0031] Figure 11 It is a structural schematic diagram of a shaping die used in the manufacturing process of the fiber reinforced composite material according to an embodiment of the present invention.

[0032] The description of the accompanying drawings is as follows:

[0033] 100 3D prefabs

[0034] 101 Warp

[0035] 102, 102a Weft yarn

[0036] 200 resin

[0037] 201 resin surface layer

[0038] 202 resin filling layer

[0039] 300 Three-Dimensional Textile Machine

[0040] 301 steel reed

[0041] 302 cloth area

[0042] 400 Fiber bundle preforming and bundling device

[0043] 1 Creel

[0044] 2 Three-dimensional preform forming device

[0045] 3 Preforming device

[0046] 31 Preformed opening and closing part

[0047] 32 Preformed Cavity

[0048] 32a Preformed straight section

[0049] 32b Preformed bell section

[0050] 4 Drying device

[0051] 5 Compression device

[0052] 51 Compression opening and closing part

[0053] 52 Compression chamber

[0054] 52a Compressed straight section

[0055] 52b Compression bell section

[0056] 53 First resin injection port

[0057] 6. Molding mold

[0058] 61 High temperature curing area

[0059] 62 molding cavity

[0060] 63 Second resin injection port

[0061] 64 Resin-infiltrated area

[0062] 7 Post-curing device

[0063] 8 Cooling device

[0064] 9 Collection system

[0065] 10 Tractor

[0066] 11 Online detection device DETAILED DESCRIPTION

[0067] The following is a further detailed description of the specific embodiments of the present invention in conjunction with the accompanying drawings. These embodiments are only used to illustrate the present invention, and are not intended to limit the present invention.

[0068] In the description of the present invention, it should be noted that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "back," "left," "right," "vertical," "horizontal," "top," "bottom," "inside," and "outside" and the like, indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely to facilitate the description of the present invention and simplify the description. They do not indicate or imply that the devices or components referred to must have a specific orientation, be constructed, or operate in a specific orientation. Therefore, they should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0069] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood in a broad sense. For example, they may refer to fixed, detachable, or integral connections; mechanical or electrical connections; direct or indirect connections through an intermediate medium; and internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0070] Furthermore, in the description of the present invention, unless otherwise specified, “plurality” means two or more.

[0071] To compensate for the shortcomings of pultruded composite materials, existing technologies, such as winding and braiding, employ a layer-by-layer stacking process to enhance their circumferential performance. If adding one layer still fails to meet the required performance, multiple layers are considered. However, regardless of the number of layers added or the stacking method, the resulting structure is a skin-core structure. Separation at the skin-core interface during composite failure is unavoidable, and the skin layer cannot effectively inhibit the propagation of crack damage within the core layer, leading to rapid composite failure and poor overall mechanical properties.

[0072] In order to overcome the defects of the skin-core structure, the present invention proposes a fiber-reinforced composite material with an integral structure. The fibers in the fiber-reinforced composite material constitute a complete, non-layered, integral structure without a skin-core structure. The fiber-reinforced composite material with this integral structure has more outstanding comprehensive properties such as tensile strength, compression strength, bending strength and torsional strength, and can have both dynamic fatigue and impact resistance, and therefore has more excellent comprehensive mechanical properties.

[0073] Prior research has used three-dimensional preforms with monolithic structures as composite reinforcements. However, these preforms are currently primarily used in the RTM molding process for high-performance, high-quality composite materials for load-bearing structural components. Products are repeatedly produced in single or multiple sections and batches, meaning a mold is used to produce a certain number of products at a time, followed by repeated production in multiple batches. This results in high manufacturing costs and low production efficiency. The pultrusion process for composite materials is one of the few processes in the composites field that allows for continuous production, delivers outstanding mechanical properties in the pultrusion direction, and offers highly consistent quality, making it ideally suited to the low-cost, high-quality demands of industrialization. However, in existing research, researchers on the pultrusion process of composite materials are too focused on improving the performance of composite materials in a single direction, while researchers on the RTM molding process of composite materials are too focused on optimizing the manufacturing cost and production efficiency of the segmented and batch preparation method of three-dimensional preforms. In addition, due to the relatively simple molding mechanism and simple structure of existing composite materials such as the winding combination and the weaving combination, it is easier to control the equipment, manufacturing quality, and especially the degree of resin impregnation than the three-dimensional preforms. Therefore, the existing technology for the research of pultruded composite materials is still focused on improving the performance of the skin-core structure, without considering the use of three-dimensional preforms in the preparation of pultruded composite materials to replace the skin-core structure to improve the comprehensive mechanical properties of pultruded composite materials. This is a technical bias in the technical field of pultruded composite material preparation.

[0074] The present invention overcomes the above-mentioned technical prejudices and combines the three-dimensional preform molding with the composite material pultrusion process to obtain a fiber-reinforced composite material with an integral structure. The three-dimensional preform has the characteristics of strong designability, outstanding comprehensive performance (especially in terms of anti-delamination, impact resistance, fatigue resistance, etc.), high added value, and high manufacturing cost (mainly due to the large waste during segmented manufacturing). The continuous preparation of the composite material pultrusion process accurately offsets the problem of high manufacturing cost of the three-dimensional preform. In this way, a composite material with better comprehensive mechanical properties can be obtained. Moreover, since the molding of the three-dimensional preform is combined with the composite material pultrusion process to form a continuous preparation process, the manufacturing cost and production efficiency can be effectively and reasonably controlled, giving full play to the continuity, low cost, high efficiency, and high-quality control characteristics of the composite material pultrusion process and the three-dimensional preform can effectively improve the comprehensive performance of interlayer shear resistance, impact resistance, fatigue resistance, etc. and the characteristics of integrated net size molding.

[0075] Furthermore, existing resin infiltration methods in composite pultrusion processes mostly use slotted resin baths. The degree of resin infiltration is significantly affected by resin fluidity and infiltration time. When combining three-dimensional preform molding with composite pultrusion, using a slotted resin bath makes it difficult for the resin to penetrate the preform's interior due to its complex internal structure. Incomplete infiltration of the preform creates numerous pores within the preform, severely impacting the composite's performance. To address this issue of resin infiltration within the preform, the present invention proposes the use of resin injection for infiltration of the preform in composite pultrusion processes. Resin injection infiltration technology originates from the field of plastic extrusion technology. Liquid resin is pressurized and injected into a mold cavity of target size containing fibers using a separate machine. High-quality resin infiltration is achieved through high pressure, a specific cavity structure, injection port location, and good sealing. It has since been widely used in the segmented and batch production of composite materials. However, due to the strict requirements of the injection system for sealing, pressure, and injection volume, it has not been applied in the field of continuous composite pultrusion technology. In order to solve the problem that conventional slotted resin baths are difficult to thoroughly infiltrate three-dimensional preforms, the present invention combines the resin injection infiltration process with the composite material pultrusion process, thereby forming a process system for continuously preparing fiber-reinforced composite materials with an integral structure through the three-dimensional preform molding-resin injection infiltration-pultrusion process.

[0076] Based on this, the present invention provides a manufacturing process of a fiber-reinforced composite material, which is used to prepare a fiber-reinforced composite material with an integral structure.

[0077] like Figures 1 to 11 FIG. 1 is an embodiment of a manufacturing process of a fiber-reinforced composite material provided by the present invention.

[0078] See also Figure 1The manufacturing process of the fiber reinforced composite material of this embodiment includes the following steps in sequence.

[0079] Step 1: Regularly and alternately interlock several fiber bundles to form a three-dimensional preform 100. The three-dimensional preform 100 is a three-dimensional fabric. The three-dimensional preform 100 has an internal structure and an outer contour that are interwoven into one. The three-dimensional preform 100 is a non-layered integral structure.

[0080] Step 2: Drying the three-dimensional preform 100 obtained in step 1 to remove moisture from the fiber bundles in the three-dimensional preform 100 and improve the subsequent resin impregnation degree and molding quality.

[0081] Step 3: pre-treating the three-dimensional preform 100 to shrink the three-dimensional preform 100 into a pre-form.

[0082] Step 4: The pretreated three-dimensional preform 100 is impregnated with resin 200 and pultruded to form a fiber-reinforced composite material.

[0083] Step 5: Post-curing the fiber-reinforced composite material obtained in Step 4 to obtain a fiber-reinforced composite material product. The main purpose of post-curing is to remove the internal stress generated by the high-temperature curing process during pultrusion by heating, thereby reducing the risk of warping and deformation of the fiber-reinforced composite material due to the internal stress.

[0084] The fiber bundle, the three-dimensional preform 100 and the fiber-reinforced composite material are pulled forward by the same pulling force, and steps one to five are performed continuously under the action of the pulling force.

[0085] The manufacturing process of the fiber-reinforced composite material of this embodiment combines the formation of a three-dimensional preform 100 with a composite material pultrusion process, fully leveraging the continuity, low cost, high efficiency, and high-quality control characteristics of the composite material pultrusion process, as well as the three-dimensional preform 100's ability to effectively improve comprehensive interlayer shear resistance, impact resistance, fatigue resistance, and other comprehensive properties, as well as its ability to be integrally formed to a net size. The three-dimensional preform 100 is a complete, non-layered, and non-skin-core structure composed of fiber bundles, capable of integrally forming to a net size. It features a multi-axial fiber reinforcement distribution, which gives the fiber-reinforced composite material more outstanding comprehensive properties such as tensile, compressive, bending, and torsional resistance, while also possessing dynamic fatigue and impact resistance, resulting in excellent comprehensive mechanical properties. Furthermore, it offers the advantages of a high degree of integral structural formability, outstanding contour design capabilities, strong multi-axial performance designability, and strength, toughness, and light weight.

[0086] In this embodiment, preferably, in step 1, continuous fiber bundles are arranged circumferentially on the outer contour of the three-dimensional preform 100. These continuous fiber bundles form a part of the outer contour of the three-dimensional preform 100, constraining the internal structure of the three-dimensional preform 100 and interweaving with the internal structure of the three-dimensional preform 100 to form an integral whole, without forming a skin-core structure.

[0087] In step 1, preferably, a three-dimensional weaving process is used to prepare the three-dimensional preform 100. During preparation, fiber bundles are used as yarns, and through a combination of yarn opening configuration, yarn specification configuration, continuous weft weaving and other technologies, the integrated net size molding of the three-dimensional preform 100 can be achieved, so that the obtained three-dimensional preform 100 has the basic net size profile of the target composite material. It should be noted that the three-dimensional weaving process is an existing mature process, but when preparing the three-dimensional preform 100 in the manufacturing process of the fiber-reinforced composite material of this embodiment, in order to facilitate the resin infiltration and pultrusion process of the three-dimensional preform 100, the three-dimensional weaving process can be optimized and adjusted to obtain a three-dimensional preform 100 that is infinitely close to a round rod shape and has a relatively uniform internal structure.

[0088] Specifically, the structure of the three-dimensional preform 100 obtained by forming the fiber bundle through the three-dimensional weaving process is as follows: Figure 2 and Figure 3 As shown. The fiber bundle is divided into warp yarn 101 and weft yarn 102 as yarns. The warp yarn 101 extends along the direction of the composite material pultrusion process (warp direction), and the weft yarn 102 extends along the direction perpendicular to the warp direction (weft direction) in the horizontal plane. In the three-dimensional weaving process, the warp yarn 101 overlaps the weft yarn 102 of different layers by bending. After regular cycles, the cross-sections of the weft yarn 102 are stacked to achieve an overall structure of interlocking layers, that is, a three-dimensional preform 100 is obtained. In practice, the warp yarn 101 and the weft yarn 102 are bent to each other, but the degree of bending of the warp yarn 101 is smaller than that of the weft yarn 102. This is because the warp yarn 101 is subjected to greater traction. The overall structure of the three-dimensional preform 100 can be freely designed by changing the number of yarn bending points and the span of the yarn bending points. The fewer the yarn bending points and the larger the span of the yarn bending points, the stronger the deformation ability of the three-dimensional preform 100, and the better the mechanical properties along the yarn extension direction. The three-dimensional textile machine 300 is a device that regularly interlocks the warp yarn 101 and the weft yarn 102 in a three-dimensional weaving process. It is an existing device, and its structure is shown in FIG. Figure 4As shown, during operation, the yarn (fiber bundle) passes through the heald holes of the three-dimensional textile machine 300 and the reed 301 and is then formed. The heald holes of the existing three-dimensional textile machine 300 are arranged in a spatial rectangular shape, and the heald holes of the three-dimensional textile machine 300 move up and down. The upward movement can drive the fiber bundle to be lifted, and the lifted fiber bundle and the unlifted fiber bundle form a triangular opening. After the weft yarn 102 is introduced into the opening, the reed 301 pushes the weft yarn 102 into the triangular opening for tightening, and then the lifted fiber bundle descends, and the original unlifted fiber bundle is lifted, and this cycle repeats, forming a cross-interlocking structure between the fiber bundles. In this embodiment, the heald holes of the three-dimensional textile machine 300 are preferably designed to be tilted front and back and left and right to reduce friction between the yarns. In this embodiment, a fiber bundle preforming and bundling device 400 is provided on the rear side of the yarn cloth area 302 at the rear end of the three-dimensional textile machine 300, as shown in FIG. Figure 5As shown, the fiber bundle preforming and bundling device 400 is equipped with several grids, each of which can constrain a line of fiber bundles. Each grid corresponds one-to-one to a heald hole of the three-dimensional textile machine 300. Based on the target composite material's diameter, fiber volume content, and the fiber raw material's linear and bulk densities, the required number of fiber bundles can be calculated. Taking the target composite material's diameter and the three-dimensional textile machine's warp yarn distribution into consideration, a square grid is formed on the fiber bundle preforming and bundling device 400. A circle is drawn within the square grid based on the fiber bundle quantity required. The area within this circle serves as the yarn distribution area, and the required number of fiber bundles is evenly arranged within the circle. Fiber bundles are first arranged within the complete individual grids within the circle. At the edge of the circle, fiber bundles are arranged within the grids whose area within the circle exceeds two-thirds of the individual grid area. Fiber bundles are not arranged in the grids whose area within the circle is less than one-third of the individual grid area. At the stage when the fiber bundle is initially formed into a three-dimensional preform, the fiber bundle preforming and bundling device 400 is placed on the rear side of the yarn cloth area 302 of the three-dimensional textile machine 300. After the fiber bundle passes through the heald wire hole and the reed 301 of the three-dimensional textile machine 300, it passes through the fiber bundle preforming and bundling device 400 and is constrained in the yarn cloth area on the square grid of the fiber bundle preforming and bundling device 400. When the fiber bundle is formed into a three-dimensional preform 100 by the three-dimensional textile machine 300, the fiber bundle preforming and bundling device 400 is pulled at the rear side of the three-dimensional preform 100. The fiber bundles are guided forward synchronously; as the formed length of the three-dimensional preform 100 in front of the fiber bundle preforming and bundling device 400 continues to increase, when the fiber bundles not involved in the forming and the formed three-dimensional preform portion are able to pass through the subsequent path and be pulled and held by the traction force, the fiber bundle preforming and bundling device 400 is disassembled, and the fiber bundle preforming and bundling device 400 is withdrawn from the fiber bundle advance path, so that the formed three-dimensional preform 100 can smoothly enter the next process, and the three-dimensional textile machine 300 continues to form the three-dimensional preform 100 under the traction force. In this way, the fiber bundle preforming and bundling device 400 plays a preforming and bundling function for the initial forming of the fiber bundles, which can ensure the straightness and contour forming quality of the three-dimensional preform 100, improve the degree of fit between the outer contour of the three-dimensional preform 100 and the circular shape of the target composite material, and obtain a three-dimensional preform 100 with a shape close to that of the target composite material.

[0089] Figure 6The figure shows the yarn threading pattern of a cross-sectional structure of a three-dimensional preform 100 formed using a three-dimensional weaving process. Weft yarns 102a are arranged circumferentially along the outer contour of the three-dimensional preform 100. These weft yarns 102a are continuous fiber bundles distributed circumferentially along the outer contour of the three-dimensional preform 100. The continuous weft yarns 102a interlock different warp yarn layers and form a circumferential fiber bundle on the surface layer. The weft yarns 102a extend in different directions, and their paths continue after passing around the warp yarns 101 arranged at the edge of the circle. The continuous weft yarn 102a structure constrains the warp yarns 101 in a quasi-entanglement manner along the circumference of the three-dimensional preform 100, further achieving a unified and non-stratified internal structure and outer contour of the three-dimensional preform 100. The closed weft yarn loops formed at the edges of different warp yarn layers are one of the foundations of the integrated molding of the three-dimensional preform 100. In particular, in actual operation, additional fine tension yarns may be added at the warp yarn arrangement points at the circular edge or the tension of the warp yarns at the circular edge points may be increased to improve the molding quality of the three-dimensional preform 100 .

[0090] Figure 7 The cross-sectional structure of a fiber-reinforced composite material with an integral structure, produced from a three-dimensional preform 100 formed using a three-dimensional weaving process, is shown. When the preform 100 is impregnated with resin 200, the fiber bundles on the outer contour of the preform 100 are covered by the resin 200, forming a resin surface layer 201. The resin 200 then enters the interior of the preform 100, filling the spaces between the fiber bundles and forming a resin filling layer 202. The three-dimensional preform 100, impregnated with resin 200, is then pultruded and cured to produce a fiber-reinforced composite material with an integral structure.

[0091] It should be noted that Figure 6 and Figure 7 To illustrate the layers of warp yarns 101, weft yarns 102, and resin 200, the layers are shown as elliptical cross-sections, solid lines, and dashed lines, respectively. In practice, warp yarns 101 and weft yarns 102 are both irregular, ribbon-like fiber bundles that, after regular alternating interlocking, form a roughly oblate shape. During the pultrusion process, the fiber bundles move relative to each other to fill larger voids within the three-dimensional preform 100's internal structure, with resin 200 further filling all of these voids. To distinguish the layers of warp yarns 101, weft yarns 102, and resin 200, the boundaries and positions of the warp yarns 101, weft yarns 102, and the circumferentially distributed fiber bundles and resin 200 on the outer contour are enlarged for better clarity.

[0092] In this embodiment, the fiber bundle can be any one or more combinations of carbon fiber, glass fiber, ultra-high molecular weight polyethylene fiber, aramid fiber, polyimide fiber, PBO fiber (short for polyparaphenylene benzobisoxazole fiber), mixed fiber (a mixture of multiple different fibers), modified fiber (such as introducing carbon nanotubes, toughening particles and other substances into the surface of a certain existing fiber to improve certain properties, etc.) and plant fiber (such as lignin fiber).

[0093] See also Figure 8 In step 1 of the manufacturing process for the fiber-reinforced composite material of this embodiment, when preparing the three-dimensional preform 100 using a three-dimensional weaving process, specifically, fiber bundles are used as yarns (warp yarns 101 and weft yarns 102), and the fiber bundles are placed on a creel 1 in a wound state on a reel. The creel 1 primarily serves to hold the fiber drum (reel). Under the action of a traction force, the fiber bundles are tangentially unwound from the reel into a single bundle, which is then introduced into the three-dimensional preform forming device 2 through a ceramic eye. To improve the pultrusion quality of the three-dimensional preform 100, the single-drum unwinding tension device can be upgraded on the creel 1 to achieve independent and precise magnetic damping control of each fiber drum, with adjustable tension, ultimately achieving a relatively uniform distribution of the fiber bundle structure within the three-dimensional preform 100. The three-dimensional preform forming device 2 includes a three-dimensional textile machine 300 and a fiber bundle preforming and bundling device 400. After the unwound fiber bundle passes through the heald hole and the reed 301 of the three-dimensional textile machine 300, it is formed into a three-dimensional preform 100 with a shape close to the shape of the target composite material. In the initial stage of forming, the fiber bundle preforming and bundling device 400 is placed on the rear side of the yarn cloth area 302 of the three-dimensional textile machine 300 to preform and bundle the fiber bundle. After a certain length of the three-dimensional preform is formed, the fiber bundle that does not participate in the forming and the formed three-dimensional preform part can pass through the subsequent path and be pulled and held by the traction force, the fiber bundle preforming and bundling device 400 is disassembled and exits the fiber bundle forward path. Thus, the integrated net size forming of the three-dimensional preform 100 is achieved through step one, and the obtained three-dimensional preform 100 has the basic net size outline of the target composite material.

[0094] In this embodiment, in step 2, the three-dimensional preform 100 obtained in step 1 is dried by a drying device 4. The drying device 4 preferably adopts an ultrasonic heating device. The ultrasonic heating device is an existing equipment. Drying the three-dimensional preform 100 by ultrasonic heating can ensure that the interior of the three-dimensional preform 100 is completely heated without any moisture residue.

[0095] In this embodiment, preferably, in step 3, the pretreatment includes primary shaping and secondary shaping, wherein the primary shaping compresses the dried three-dimensional preform 100 once, and the secondary shaping compresses the three-dimensional preform 100 twice after the primary shaping. The three-dimensional preform 100 is shrunk and preformed by the two compression shapings.

[0096] Among them, the primary shaping can be completed by the preforming device 3. Figure 9 In this embodiment, the preforming device 3 preferably includes two preforming opening and closing portions 31 that are arranged opposite each other and can be separated or joined along the compression direction A of the primary compression. A continuous preforming cavity 32 is formed between the two joined preforming opening and closing portions 31. The preforming cavity 32 includes a preforming straight section 32a having a diameter smaller than the outer diameter of the three-dimensional preform 100, and a preforming flared section 32b extending from both ends of the preforming straight section 32a and having a gradually increasing diameter. As the three-dimensional preform 100 passes through the preforming cavity 32 of the preforming device 3, the two preforming opening and closing portions 31 regularly separate and join, shaping the three-dimensional preform 100 to a relatively uniform target diameter through the preforming straight sections 32a of the preforming cavity 32. The opening and closing speed of the preforming device 3 is coordinated with the forward speed of the three-dimensional preform 100, so that the length of each pressing can overlap from beginning to end, avoiding omissions. The length of the preforming cavity 32 of the preforming device 3 is related to the target diameter. The larger the target diameter, the longer the preforming cavity 32 should be and the more points of force for opening and closing should be added to ensure uniform compression force. The preforming bell-mouth sections 32b at both ends of the preforming cavity 32 can facilitate the introduction and export of the three-dimensional preform 100 into the preforming cavity 32. Preferably, the two preforming bell-mouth sections 32b and the preforming straight section 32a are smoothly connected by chamfers to avoid sharp edges or corners that may damage the three-dimensional preform 100 and to avoid large indentations. Preferably, the cavity wall of the preforming cavity 32 is provided with a coating to improve the wear resistance of the preforming cavity 32 and reduce the friction coefficient.

[0097] Secondary shaping can be accomplished by compression device 5. Figure 10In this embodiment, the compression device 5 preferably includes two compression opening and closing portions 51 that are arranged opposite each other and can be separated or joined along the compression direction B of the secondary compression. A through compression chamber 52 is formed between the two joined compression opening and closing portions 51. The compression chamber 52 includes a compression straight section 52a having a diameter no greater than the outer diameter of the three-dimensional preform 100 after the primary compression, and compression bell-shaped sections 52b extending from both ends of the compression straight section 52a and having gradually increasing diameters. When the three-dimensional preform 100, which has undergone the primary shaping, passes through the compression chamber 52 of the compression device 5, the two compression opening and closing portions 51 regularly separate and join, and the three-dimensional preform 100 is subjected to a second-stage shaping to the target diameter by the compression straight sections 52a of the compression chamber 52. The abundant elastic relaxation space within the three-dimensional preform 100 is further compressed to ensure the fiber volume content and molding quality of the final composite material, and to ensure that the shape of the three-dimensional preform 100 approximates the target composite material shape. The opening and closing speed of the compression device 5 is coordinated with the forward speed of the three-dimensional preform 100, so that the length of each pressing can overlap from beginning to end to avoid omissions. The length of the compression chamber 52 of the compression device 5 is related to the target diameter. The larger the target diameter, the longer the compression chamber 52 should be and the more points of force for opening and closing should be added to ensure uniform compression force. The compression bell-mouth sections 52b at both ends of the compression chamber 52 can facilitate the introduction and export of the three-dimensional preform 100 into the compression chamber 52. Preferably, the two compression bell-mouth sections 52b and the compression straight section 52a are smoothly connected by chamfers to avoid sharp edges or corners that may damage the three-dimensional preform 100 and to avoid large indentations. Preferably, the wall of the compression chamber 52 is provided with a wear-resistant and anti-stick coating to improve the wear resistance of the compression chamber 52 and reduce the friction coefficient.

[0098] Furthermore, in step 3, the three-dimensional preform 100 after the primary shaping can be pre-impregnated with resin while the secondary shaping is being performed. The resin pre-impregnation is preferably performed by pressure injection of the resin into the three-dimensional preform 100. The secondary shaping and resin pre-impregnation can be completed by the compression device 5. Figure 10In a preferred embodiment, at least one compression opening and closing portion 51 of the compression device 5 is provided with a first resin injection port 53 in communication with the compression chamber 52. The first resin injection port 53 is used to pressure-inject resin into the compression chamber 52. The first resin injection port 53 is connected to a resin injection system, which is an existing device. A resin recovery device can be provided below the compression device 5 to receive excess resin squeezed out of the compression device 5. During each opening and closing of the compression device 5, resin is injected into the compression chamber 52 through the first resin injection port 53. Under the injection pressure, the resin infiltrates into the three-dimensional preform 100. Furthermore, due to the closed compression force of the compression device 5 and the capillary effect, the resin gradually diffuses within the three-dimensional preform 100, forming a preliminary infiltration. Excess resin is squeezed out of the compression device 5, recovered and filtered by the recovery device below the compression device 5, and then returned to the resin injection system, thereby achieving secondary shaping and resin pre-infiltration of the three-dimensional preform 100. Preferably, a first resin injection port 53 is respectively provided on the two compression opening and closing parts 51. The two first resin injection ports 53 are respectively located at the two ends of the compression straight section 52a and are arranged in a counter-position along the compression direction B of the secondary compression. Through the pressure offset of the two counter-positioned first resin injection ports 53, the three-dimensional preform 100 can be thoroughly infiltrated and the resin overflow from the fracture of the compression device 5 can be slowed down.

[0099] Therefore, in step three, the shape of the three-dimensional preform 100 after secondary shaping and resin pre-impregnation is close to the target shape of the fiber reinforced composite material, and the resin 200 is diffused in the internal structure of the three-dimensional preform 100 after secondary shaping and resin pre-impregnation to form preliminary resin impregnation.

[0100] In this embodiment, preferably, in step 3, the compression direction A of the preforming device 3 performing the primary compression on the three-dimensional preform 100 and the compression direction B of the compression device 5 performing the secondary compression on the three-dimensional preform 100 are perpendicular to each other. Preferably, the compression direction A of the primary compression is horizontal, and the compression direction B of the secondary compression is vertical. The perpendicular compression directions of the two shaping processes can neutralize indentation deformation, making the cross-section of the three-dimensional preform 100 after the secondary shaping process more rounded.

[0101] In this embodiment, preferably, the resin infiltration in step 4 is preferably carried out by resin pressure injection infiltration of the three-dimensional preform 100. The resin pressure injection infiltration uses low viscosity (300cps-1500cps) resin and high injection pressure (4bar-10bar) to inject the resin into the injection mold (the shaping mold 6 described below), which can be thoroughly infiltrated with the three-dimensional preform 100.

[0102] In step 4, the resin impregnation and pultrusion of the pre-treated three-dimensional preform 100 can be completed by the shaping die 6. Figure 8 and Figure 11A molding cavity 62 is formed inside the molding die 6 and passes through in the traction direction of the traction force. A second resin injection port 63 connected to the molding cavity 62 and a high-temperature curing zone 61 for heating the interior of the molding cavity 62 are provided on the molding die 6. The second resin injection port 63 is used to pressure-inject resin into the molding cavity 62. The high-temperature curing zone 61 is located on the side of the second resin injection port 63 away from the compression device 5. The molding cavity 62 of the molding die 6 has a long length, and the end of the molding cavity 62 close to the compression device 5 is set to be a trumpet-shaped that expands outward, so that the pretreated three-dimensional preform 100 can enter the molding cavity 62 of the molding die 6 more easily. After pretreatment, the three-dimensional preform 100 that has been compressed and molded for the second time by the compression device 5 can enter the molding die 6 more easily. The second resin injection port 63 can be connected to the resin injection system through a mixing head, and the resin injection system is an existing equipment. When the pretreated three-dimensional preform 100 passes through the molding cavity 62 of the shaping mold 6, the resin in the resin injection system undergoes initial degassing under ultrasonic conditions. The resin is then injected into the molding cavity 62 through the second resin injection port 63 under high pressure, completing the final injection and infiltration of the three-dimensional preform 100. Preferably, an ultrasonic transmitter is positioned outside the resin infiltration area 64 of the shaping mold 6, where the second resin injection port 63 is located. A set frequency allows the ultrasonic wave to penetrate the three-dimensional preform 100 and the infiltrated resin. This further promotes degassing of the resin injected into the three-dimensional preform 100 and reduces the internal porosity of the composite material. Preferably, the portion of the molding cavity 62 of the shaping mold 6 located in the resin infiltration area 64 is designed as a curved siphon shape, with a relatively open resin collection cavity formed at a certain bending node. This creates a large fluid pressure differential within the molding cavity 62 located in the resin infiltration area 64, thereby enhancing the resin infiltration effect. The finally impregnated three-dimensional preform 100 is heated in the high-temperature curing zone 61 to cure the three-dimensional preform 100 impregnated with resin and finally pulled out of the shaping mold 6 to obtain a fiber-reinforced composite material with an integral structure.

[0103] In this embodiment, the resin 200 impregnated with the three-dimensional preform 100 may be any one of a thermoplastic resin and a thermosetting resin, or a combination of the two (eg, toughening particles of thermoplastic resin added to thermosetting resin).

[0104] In this embodiment, the resin impregnation mold (resin impregnation area 64 of the shaping mold 6) and the pultrusion heating and curing mold (high-temperature curing area 61 of the shaping mold 6) are designed as an integrated structure (the entire shaping mold 6), which is a preferred embodiment. In actual application, the two can also be separated.

[0105] Since the surface texture structure of the three-dimensional preform 100 is relatively complex than the conventional unidirectional fiber structure, the friction between it and the wall of the shaping cavity 62 of the shaping mold 6 is relatively greater. In order to reduce the damage to the surface fabric structure of the three-dimensional preform 100 caused by friction, it is preferred that the wall of the shaping cavity 62 of the shaping mold 6 be finely ground and coated to improve its wear resistance and reduce the friction coefficient. The type of coating is not limited, for example, it can be chrome-plated or coated with Teflon coating or coated with other low-friction and high-wear-resistant coatings. In order to improve the internal thermal radiation uniformity of the three-dimensional preform 100 temperature, it is preferred that a hot oil circulation path surrounding the shaping cavity 62 be opened on the outer peripheral side of the shaping cavity 62 inside the shaping mold 6, and high-temperature hot oil is circulated and heated in the hot oil circulation path to provide relatively uniform thermal radiation, which can improve the curing quality of the composite material and reduce the risk of scrap due to uneven heating.

[0106] In this embodiment, in step 5, the fiber-reinforced composite material obtained in step 4 can be post-cured by a post-curing device 7. The heating temperature of the post-curing device is lower than the heating temperature of the high-temperature curing zone 61 of the shaping mold 6. The post-curing device can use existing heating equipment.

[0107] Furthermore, the post-cured fiber reinforced composite material retains a certain temperature, therefore, see Figure 8 In step five, the post-cured fiber-reinforced composite material is cooled to room temperature to facilitate collection and packaging. The post-cured fiber-reinforced composite material can be cooled by a cooling device 8 , which can use air cooling or water cooling to cool the post-cured fiber-reinforced composite material.

[0108] Preferably, a collection system 9 for collecting the composite material can be installed on the side of the cooling device 8 away from the post-curing device 7. After the fiber-reinforced composite material is drawn from the shaping mold 6 and post-cured in the post-curing device 7 and cooled by the cooling device 8, it is collected by the collection system 9. Depending on the bending properties of the fiber-reinforced composite material, the collection system 9 can collect the composite material in a continuous roll or cut to length. Cutting to length requires a cutter that can match the drawing speed. Existing equipment can be used for the collection system 9.

[0109] See also Figure 8In the manufacturing process of the fiber-reinforced composite material of this embodiment, a traction force can be provided by a traction machine 10 to pull the fiber bundle, the three-dimensional preform 100, and the fiber-reinforced composite material forward from the creel 1, so that steps 1 to 5 are continuously performed under the action of the traction force. Specifically, the traction machine 10 sequentially pulls the fiber bundle on the creel 1 through the three-dimensional preform forming device 2 (the three-dimensional textile machine 300 and the fiber bundle preform bundling device 400) to form the three-dimensional preform 100, pulls the three-dimensional preform 100 through the drying device 4 for drying, passes through the preforming device 3 for a primary compression molding to a relatively uniform target diameter, passes through the compression device 5 for a secondary compression molding to an approximate target composite material shape, passes through the shaping mold 6 for final resin injection infiltration and heat curing to form the fiber-reinforced composite material, pulls the fiber-reinforced composite material out of the shaping mold 6 and passes through the post-curing device 7 for post-curing, passes through the cooling device 8 for cooling, and then enters the collection system 9, thereby forming a continuous production process system of three-dimensional preform molding-resin injection infiltration-pultrusion process, and can produce a fiber-reinforced composite material with an integral structure.

[0110] The tractor 10 is preferably positioned between the cooling device 8 and the collection system 9. The tractor 10 preferably utilizes a crawler-type drafting mechanism. This mechanism comprises two upper and lower crawler belts that clamp the material, providing a large clamping area. The two crawler belts advance in opposite directions, resulting in a more stable drafting force output. This ensures a relatively uniform speed when the fiber-reinforced composite material is pulled out of the shaping die 6, further enhancing the quality of the fiber-reinforced composite material. Preferably, the crawler-type tractor structure can be improved to a servo motor-driven crawler belt drafting mechanism, which allows for more refined and quantitative control of the drafting speed, facilitating process quantification, refinement, and lean manufacturing.

[0111] Preferably, a length counting device is installed on the path where the fiber reinforced composite material passes after the tractor 10, which can be a physical counting method, a photoelectric counting method, etc., for recording the length of the prepared fiber reinforced composite material.

[0112] See also Figure 8Preferably, the manufacturing process of the fiber reinforced composite material of this embodiment further includes step six, online detection of the fiber reinforced composite material obtained in step five, for online measurement of several indicators of the obtained fiber reinforced composite material and making judgments. Online detection can be completed by an online detection device 11, and the online detection device 11 is not limited, and corresponding existing detection equipment can be selected according to the indicators to be detected. For example, the detection of the width index of the composite material can be carried out by laser calibration, image recognition and other means to fully cover the detection width, statistical data, and make judgment instructions according to the requirements of abnormal data; the detection of the surface quality of the composite material can be carried out by image recognition, infrared and other means to fully cover the detection, statistical data, and make judgment instructions according to the requirements of abnormal data; the detection of internal defects of the composite material such as pores, inclusions, fiber balls, fabric wrinkles, etc. can be carried out by infrared, ultrasonic, X-ray and other means for non-destructive detection, statistical data, and make judgment instructions according to the requirements of abnormal data.

[0113] Based on the manufacturing process of the above-mentioned fiber-reinforced composite material, this embodiment also provides a fiber-reinforced composite material. The fiber-reinforced composite material of this embodiment is prepared by the manufacturing process of the above-mentioned fiber-reinforced composite material of this embodiment. Since the three-dimensional preform 100 is a complete, non-layered, and skin-core structural integral structure composed of fiber bundles, it can be formed into an integrated net size and has the distribution characteristics of multi-axial fiber reinforcement. The fiber-reinforced composite material of this embodiment has more outstanding comprehensive properties such as tensile strength, compression strength, bending strength, and torsion strength, while also having dynamic fatigue and impact resistance, excellent comprehensive mechanical properties, and has the advantages of high degree of integrated structural forming, outstanding contour design capability, strong multi-axial performance designability, strong toughness, and light weight.

[0114] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and substitutions can be made without departing from the technical principles of the present invention. These improvements and substitutions should also be regarded as the scope of protection of the present invention.

Claims

1. A process for manufacturing a fiber-reinforced composite material, characterized in that: The following steps are included in sequence: Step 1: Regularly and alternately interlocking a plurality of fiber bundles to form a three-dimensional preform, wherein the three-dimensional preform is a three-dimensional fabric, wherein the three-dimensional preform has an internal structure and an outer contour interwoven into one, and the three-dimensional preform is a non-layered integral structure; Step 2: drying the three-dimensional preform; Step 3: Pre-treating the dried three-dimensional preform, wherein the pre-treating includes primary shaping and secondary shaping, wherein the primary shaping performs a primary compression on the dried three-dimensional preform, and the secondary shaping performs a secondary compression on the three-dimensional preform after the primary shaping, wherein the compression direction of the primary shaping on the three-dimensional preform is perpendicular to the compression direction of the secondary shaping on the three-dimensional preform; Step 4: resin impregnation and pultrusion molding are performed on the pretreated three-dimensional preform to form a fiber-reinforced composite material; Step 5, post-curing the fiber-reinforced composite material; The fiber bundle, the three-dimensional preform, and the fiber-reinforced composite material are pulled forward by the same traction force, and steps one to five are performed continuously under the action of the traction force.

2. The manufacturing process of the fiber reinforced composite material according to claim 1, characterized in that: In the step 1, continuous fiber bundles distributed along the circumferential direction are arranged on the outer contour of the three-dimensional preform.

3. The manufacturing process of the fiber reinforced composite material according to claim 1, characterized in that: In the step 1, the three-dimensional preform is prepared by using a three-dimensional weaving process.

4. The process for manufacturing a fiber-reinforced composite material according to claim 1, wherein: In the step 4, the resin infiltration is carried out by pressure-injecting the resin into the three-dimensional preform.

5. The manufacturing process of the fiber reinforced composite material according to claim 1, characterized in that: In the step five, the post-cured fiber reinforced composite material is cooled.

6. The process for manufacturing a fiber-reinforced composite material according to claim 1, wherein: The method further includes step six, performing online testing on the fiber-reinforced composite material obtained in step five.

7. A fiber-reinforced composite material, characterized in that: The fiber-reinforced composite material is prepared by the manufacturing process of any one of claims 1 to 6.

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