Method for manufacturing rib using three-dimensional woven composite material, and rib

Abstract

The invention discloses a method for manufacturing a wing rib by using a three-dimensional woven composite material and the wing rib, and relates to the technical field of wings, the method comprises the following steps: S1, determining the form of an integrally woven three-dimensional woven preform according to the geometrical shape of the wing rib to be manufactured; s2, determining a tissue form and basic weaving parameters of a three-dimensional woven fabric of the preform according to the geometric dimension of the wing rib; s3, weaving a prefabricated body; s4, preparing a forming mold; and molding in a molding cavity through a vacuum-assisted resin transfer molding process to obtain the wing rib. According to the wing rib woven through the method, due to the strengthening effect generated by interweaving of the yarn in the three-dimensional woven fabric, the layering resistance of the wing rib is improved when the wing rib bears complex loads, and the bearing capacity of a web flange connecting area is also improved.

Description

Technical Field

[0001] The present invention relates to the technical field of wings, and in particular to a method for manufacturing a wing rib using a three-dimensional woven composite material and the wing rib. Background Art

[0002] In the aviation industry, multi-rib wings are a widely used structural form, and their design and manufacturing technology has always been the focus of research. This type of wing mainly includes spars, ribs, skins and stringers. The ribs not only support and define the shape of the wing, but are also responsible for effectively transferring and distributing the dispersed aerodynamic loads to the entire wing structure. Depending on their function and position, ribs can be divided into ordinary ribs and reinforced ribs. Ordinary ribs mainly provide the necessary in-plane stiffness and torsional stiffness, while reinforced ribs, on this basis, also need to bear and transfer specific concentrated loads.

[0003] With the increasing requirements for energy conservation and emission reduction of aircraft, carbon fiber reinforced composite materials with significant weight advantages are increasingly used in aircraft manufacturing, including the manufacture of wing rib structures. Traditional wing rib structures are designed in a variety of ways, with the most common ones being C-shaped, H-shaped, L-shaped, flat web and truss types. These structural forms have their own advantages and disadvantages, but they generally face the problems of high manufacturing costs and complex molding processes. Especially when using laminated composite material technology for manufacturing, the complex laying process and autoclave curing molding increase the manufacturing cost, and the defects of laminated composite materials themselves, such as poor impact resistance and easy delamination, also limit the mechanical properties of the wing ribs, affect the advantages of carbon fiber composite materials, and hinder the overall energy consumption reduction and efficiency improvement of the aircraft.

[0004] Especially for the key area where the rib flange is connected to the skin, it needs to bear out-of-plane loads while bearing in-plane loads, and out-of-plane loads can easily cause delamination failure of laminated composite materials. Therefore, in order to meet the load-bearing requirements, the wing ribs made of laminated composite materials need to increase the structural dimensions. This part of the increased structural dimensions not only leads to an increase in weight and thus affects the structural efficiency of the wing, but also makes the laying process more complicated during the manufacturing process, increasing the manufacturing cost. At present, how to improve the manufacturing efficiency of composite wing ribs while ensuring or even improving their structural mechanical properties has become a technical problem that needs to be solved urgently. This is not only related to the overall safety and economy of the wing, but also the key to promoting the progress of the aviation manufacturing industry. Summary of the invention

[0005] The object of the present invention is to provide a method for manufacturing a wing rib using a three-dimensional woven composite material and a wing rib, so as to solve the problems existing in the above-mentioned prior art, improve the mechanical properties of the wing rib, and reduce its manufacturing cost.

[0006] To achieve the above object, the present invention provides the following solutions: The present invention provides a method for manufacturing a rib using a three-dimensional woven composite material, comprising the following steps: S1. Determine the shape of the preform according to the geometric shape of the rib to be manufactured; If the rib is C-shaped, L-shaped or flat web-shaped, the preform is in the form of a flat plate; If the wing rib is H-shaped, the preform is in the shape of a flat plate, and two forked bodies are provided at both ends of the preform, and the two forked bodies located at the same end of the preform are not connected to each other and are integrally formed with the preform; S2. The material of the preform is a three-dimensional woven fabric. The organization form and basic weaving parameters of the preform are determined according to the geometric dimensions and mechanical performance requirements of the rib; the organization form is a three-dimensional orthogonal weaving or a three-dimensional angle interlocking weaving, and the basic weaving parameters include the number of warp yarn layers, the number of weft yarn layers, the warp yarn density, the weft yarn density and the total number of yarns; S3, using a three-dimensional loom to weave the preform according to the basic weaving parameters; S4, preparing a molding die, wherein the shape and size of the molding cavity of the molding die are exactly the same as the shape and size of the rib; Placing the preform in the molding cavity and fixing the shape of the preform by the molding die so that the shape of the preform is the same as the shape of the rib; The preform is formed in the molding cavity by a vacuum-assisted resin transfer molding process, wherein the matrix is ​​formed by curing the resin that completely impregnates the preform in the molding cavity; Then demoulding is performed to obtain the rib.

[0007] Preferably, when the wing rib is C-shaped, the wing rib includes a web and two flanges respectively connected to the web; the thickness of the preform, the thickness of the web and the thickness of each flange are equal, the length of the preform, the length of the web and the length of each flange are equal, and the width of the preform is the sum of the height of the web and the width of the two flanges.

[0008] Preferably, when the wing rib is L-shaped, the wing rib includes a web and a flange connected to the web; the thickness of the preform, the thickness of the web and the thickness of the flange are equal, the length of the preform, the length of the web and the length of the flange are equal, and the width of the preform is the sum of the height of the web and the width of the flange.

[0009] Preferably, when the wing rib is of a flat web type, the wing rib only includes the web, the thickness of the preform is equal to the thickness of the web, the length of the preform is equal to the length of the web, and the width of the preform is equal to the height of the web.

[0010] Preferably, when the wing rib is H-shaped, the wing rib includes a web, two upper flanges respectively located on both sides of the top end of the web, and two lower flanges respectively located on both sides of the bottom end of the web; the thickness of the preform is equal to the thickness of the web, the thickness of each upper flange and the thickness of each lower flange are half of the thickness of the web, the length of the preform, the length of the web, the length of each upper flange and the length of each lower flange are equal, and the width of the preform is the sum of the height of the web, the width of one upper flange and the width of one lower flange.

[0011] Preferably, when the wing rib is H-shaped, the part of the preform except the bifurcated body is the main body, and the bifurcated body and the main body share the weft yarn; The two side surfaces of the preform along the thickness direction are respectively a first side surface and a second side surface, and the direction from the first side surface to the second side surface is a first direction; The arrangement order of the layers of the weft yarns in the two forked bodies at the same end of the preform along the first direction is a first arrangement order, and the arrangement order of the layers of the weft yarns in the main body along the first direction is a second arrangement order, and the first arrangement order is the same as or different from the second arrangement order.

[0012] Preferably, the first arrangement order is different from the second arrangement order, the second arrangement order is 1, 2, ..., m, m+1, ..., m+n, and the first arrangement order is m+1, m+2, ..., m+n, 1, 2, ..., m, and the number of layers of weft yarns in the two forked bodies at the same end of the preform are m and n respectively.

[0013] Preferably, the first arrangement order is different from the second arrangement order, the second arrangement order is 1, 2, ..., m, m+1, ..., m+n, and the first arrangement order is m+n, m+n-1, ..., m+1, m, m-1, ..., 1, and the number of layers of weft yarns in the two forked bodies at the same end of the preform are m and n respectively.

[0014] The present invention also provides a wing rib, which is manufactured by the method for manufacturing wing ribs using a three-dimensional woven composite material according to the above technical solution.

[0015] Compared with the prior art, the present invention has achieved the following technical effects: The method of manufacturing wing ribs using three-dimensional woven composite materials of the present invention adopts three-dimensional woven fabric as a preform, impregnates the preform with resin, and forms a matrix to shape the wing ribs after the resin is cured. Since the Z-direction yarn (i.e., binding yarn) in the three-dimensional woven fabric strengthens the fabric structure in the thickness direction and effectively locks each layer of weft yarn, various parts of the preform are organically combined into a whole. The reinforcing effect produced by the interweaving of yarns (including binding yarns, weft yarns and warp yarns) in the three-dimensional woven fabric fundamentally solves the interface stratification problem commonly seen in traditional laminated composite materials.

[0016] Furthermore, when the wing rib is H-shaped, the arrangement order of the layers of weft yarns in the forked body and the main body in the preform is different. The unique arrangement order design brings excellent strength performance to the connection structure between the forked body and the main body, and significantly improves the overall mechanical bearing capacity.

[0017] Furthermore, the present invention abandons high-investment molding methods such as traditional autoclaves and adopts vacuum-assisted resin transfer molding technology, which significantly reduces equipment investment and operating costs, greatly reducing the economic burden of the entire production process.

[0018] Furthermore, thanks to the integrity and continuity of the three-dimensional woven fabric, the present invention avoids the cumbersome multiple cutting and layer-by-layer covering processes in the traditional solution during the preforming stage, greatly improving the production efficiency and reducing the time cost caused by manual operation. The production process has low dispersion and high production efficiency.

[0019] Furthermore, due to the integrity and consistency of the three-dimensional woven fabric, the material dispersion problem that is prone to occur during multiple laying processes of traditional laminated materials is effectively avoided, ensuring the stability and consistency of product quality. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0021] Figure 1 It is a schematic diagram of the structure of the C-shaped wing rib; Figure 2 It is a schematic diagram of the structure of the L-shaped wing rib; Figure 3 It is a schematic diagram of the structure of a flat web type wing rib; Figure 4 It is a schematic diagram of the structure of the H-shaped wing rib; Figure 5 It is a schematic structural diagram of a prefabricated body of an H-shaped rib in the present invention; Figure 6 This is a schematic diagram of the H-shaped rib preform in the present invention unfolding into an H-shape; Figure 7 A schematic diagram of a weft yarn arrangement scheme for a preform of an H-shaped rib; Figure 8 A schematic diagram of another weft yarn arrangement scheme for a preform of an H-shaped rib; Fig. 9 A schematic diagram of another weft yarn arrangement scheme for a preform of an H-shaped rib; Fig.10 A schematic diagram of placing a preform of an H-shaped rib in a forming cavity of a forming mold; Fig.11 A schematic diagram of placing a preform of an L-shaped rib in a molding cavity of a molding mold; Fig.12 A schematic diagram of placing a preform of a C-shaped rib in a forming cavity of a forming mold; Fig.13 A schematic diagram of a portion of the yarn structure of an H-shaped rib in a three-dimensional orthogonal weaving structure; Fig.14 A schematic diagram of a portion of the yarn structure of an H-shaped rib in a three-dimensional angle interlocking weave; In the figure: 10, preform of H-shaped rib; 11, main body; 12, bifurcated body; 13, interface; 14, connection area between bifurcated body and main body; 21. Upper mold; 22. Lower mold; 23. Right mold; 24. Left mold; 25. Female mold; 26. Male mold; 30, weft yarn; 40, warp yarn; 50, binding yarn; 60, dividing line; 70. Preform of L-shaped rib; 80. Preform of C-shaped wing rib. DETAILED DESCRIPTION

[0022] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0023] The object of the present invention is to provide a method for manufacturing a wing rib using a three-dimensional woven composite material and a wing rib, so as to solve the problems existing in the above-mentioned prior art, improve the mechanical properties of the wing rib, and reduce its manufacturing cost.

[0024] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0025] like Figures 1 to 14 As shown, the present invention provides a method for manufacturing a rib using a three-dimensional woven composite material, comprising the following steps: S1. Determine the shape of the preform according to the geometric shape of the rib to be manufactured; If the rib is C-shaped, L-shaped or flat web type, the preform is in the form of a flat plate; If the rib is H-shaped, the preform is in the shape of a flat plate, and two forked bodies 12 are provided at both ends of the preform, the two forked bodies 12 at the same end of the preform are not connected to each other and are integrally formed with the preform, and there is a dividing interface 13 between the two forked bodies 12 at the same end of the preform; S2. The material of the preform is a three-dimensional woven fabric. The organization form and basic weaving parameters of the preform are determined according to the geometric dimensions and mechanical performance requirements of the rib to be manufactured; the organization form is a three-dimensional orthogonal weaving or a three-dimensional angle interlocking weaving, and the basic weaving parameters include the number of warp yarn layers, the number of weft yarn layers, the warp yarn density, the weft yarn density and the total number of yarns; S3, weaving the preform according to basic weaving parameters using a three-dimensional loom; S4. Prepare a molding die, wherein the shape and size of the molding cavity of the molding die are exactly the same as the shape and size of the rib; The preform is placed in the molding cavity, and the shape of the preform is fixed by the molding die so that the shape of the preform is the same as the shape of the rib; Fig.10 , Fig.11 and Fig.12 As shown, Fig.10 The preform 10 of the middle H-shaped wing rib is fixed and compacted by the upper mold 21, the lower mold 22, the left mold 24, and the right mold 23. Fig.11 The preform 70 of the middle L-shaped rib is fixed and compacted by the female mold 25 and the male mold 26. Fig.12 The preform 80 of the middle C-shaped rib is fixed and compacted by the female mold 25 and the male mold 26 .

[0026] The preform is formed in a molding cavity by a vacuum-assisted resin transfer molding process, and the matrix is ​​formed by curing the resin that completely impregnates the preform in the molding cavity; Then demould to obtain the wing rib.

[0027] Specifically, in step S2, according to the fiber volume content of the rib and the thickness of the ribs The number of warp layers can be determined and number of weft yarn layers , and warp density and weft density . Further according to the web height and flange width (In the H-shaped rib, The total number of yarns can be determined by , .

[0028] It is worth mentioning that three-dimensional orthogonal weaving and three-dimensional angle interlocking weaving are two existing organizational forms of three-dimensional woven fabrics. Determining the organizational form means selecting the organizational form of the three-dimensional woven fabric of the preform to be three-dimensional orthogonal weaving or three-dimensional angle interlocking weaving according to the geometric dimensions and mechanical properties of the wing ribs to be manufactured. It is sufficient to select a more appropriate one of these two organizational forms.

[0029] In this embodiment, when the rib is C-shaped, the rib includes a web and two flanges respectively connected to the web; the thickness of the preform, the thickness of the web and the thickness of each flange are equal, the length of the preform, the length of the web and the length of each flange are equal, and the width of the preform is the sum of the height of the web and the width of the two flanges.

[0030] In this embodiment, when the rib is L-shaped, the rib includes a web and a flange connected to the web; the thickness of the preform, the thickness of the web and the thickness of the flange are equal, the length of the preform, the length of the web and the length of the flange are equal, and the width of the preform is the sum of the height of the web and the width of the flange.

[0031] In this embodiment, when the wing rib is a flat web type, the wing rib only includes the web, the thickness of the preform is equal to the thickness of the web, the length of the preform is equal to the length of the web, and the width of the preform is equal to the height of the web.

[0032] In this embodiment, when the wing rib is H-shaped, the wing rib includes a web, two upper flanges respectively located on both sides of the top end of the web, and two lower flanges respectively located on both sides of the bottom end of the web; the thickness of the preform is equal to the thickness of the web, the thickness of each upper flange and the thickness of each lower flange are half of the thickness of the web, the length of the preform, the length of the web, the length of each upper flange and the length of each lower flange are equal, and the width of the preform is the sum of the height of the web, the width of an upper flange and the width of a lower flange.

[0033] It is worth noting that, referring to Fig.13 and Fig.14When the rib is in H shape, the manufacturing of the forked bodies 12 at both ends of the preform can be understood as follows: the two forked bodies 12 at the same end of the preform do not share the binding yarn 50 (i.e., the Z-direction yarn), and in the bifurcated area, part of the binding yarn 50 only passes through one forked body 12, and the other half of the binding yarn 50 only passes through the other forked body 12, so that the two forked bodies 12 are independent of each other, and the preform can be unfolded, so that the preform can be formed into an H shape. In addition, for the convenience of understanding, in Fig.13 and Fig.14 A dividing line 60 is drawn in the figure, one side of the dividing line 60 is a forked body 12 of the preform in the H-shaped rib, and the other side of the dividing line 60 is another forked body 12 located at the same end as the forked body 12.

[0034] In the optional scheme of this embodiment, it is more preferred that when the rib is H-shaped, the part of the preform except the bifurcated body 12 is the main body 11, and the bifurcated body 12 and the main body 11 share the weft yarn; Two side surfaces of the preform along the thickness direction are respectively a first side surface and a second side surface, and a direction from the first side surface to the second side surface is a first direction; The arrangement order of all the weft yarn layers in the two forked bodies 12 at the same end of the preform along the first direction is the first arrangement order, and the arrangement order of the weft yarn layers in the main body 11 along the first direction is the second arrangement order. The first arrangement order is the same as the second arrangement order (refer to Figure 7 ) or different (refer to Figure 8 and Fig. 9 ).

[0035] This embodiment specifically provides two solutions to make the first arrangement order different from the second arrangement order: The first type: Figure 8 As shown, the second arrangement order is 1, 2, ..., m, m+1, ..., m+n, and the first arrangement order is m+1, m+2, ..., m+n, 1, 2, ..., m. The number of weft yarn layers in the two forked bodies 12 at the same end of the preform is m and n respectively. In this embodiment, m=n. In actual applications, m>n or m can be made according to actual needs. <n。

[0036] The second type: Fig. 9 As shown, the first arrangement order is different from the second arrangement order. The second arrangement order is 1, 2, ..., m, m+1, ..., m+n, and the first arrangement order is m+n, m+n-1, ..., m+1, m, m-1, ..., 1. The number of weft yarn layers in the two forked bodies 12 at the same end of the preform is m and n respectively. In this embodiment, m=n. In actual applications, m>n or m can be made according to actual needs. <n。

[0037] It should be noted that in the above two arrangement schemes that make the first arrangement order different from the second arrangement order, different layers of weft yarns 30 are interwoven in the connection area 14 of the fork body and the main body, thereby improving the stability of the connection between the fork body 12 and the main body 11.

[0038] It is worth mentioning that in actual production, if the total number of yarn layers in the main body 11 is an odd number, the weft yarns 30 of the middle weft yarn layer can all be double-plied, and the middle weft yarn 30 can be regarded as two yarns, so the total number of weft yarns 30 can still be equally divided into two parts.

[0039] The present embodiment also provides a rib, which is manufactured by the above method for manufacturing a rib using a three-dimensional woven composite material.

[0040] The following is a specific example to illustrate the implementation of the method for manufacturing a rib using a three-dimensional woven composite material of the present invention.

[0041] Embodiment 1

[0042] Manufacture of H-shaped three-dimensional woven composite rib with web height of 120 mm, upper and lower flange widths of 60 mm, web thickness of 4 mm, upper and lower flange thicknesses of 2 mm, and length of 1000 mm: (1) The weaving process is a three-dimensional orthogonal weaving process. According to the structural size and fiber volume content, the number of warp yarn layers in the web area is selected to be 6, the number of weft yarn layers is selected to be 7 (the fourth layer of weft yarn 30 is two-ply), the warp yarn density is 3.33 yarns / cm, and the weft yarn density is 2.22 yarns / cm. The entire preform has 360 warp yarns 40 and 1554 weft yarns 30; the bifurcated body 12 has 3 layers of warp yarns 40 and 4 layers of weft yarns 30. The other parameters are the same as those of the main body 11 area. There are three optional schemes for the distribution of the weft yarns 30 of the preform 10 of the H-shaped rib, such as Figures 7 to 9 In this embodiment, different weft yarn 30 paths can realize the feature that the preform is unfolded along a specified plane.

[0043] (2) In this example, a three-dimensional loom is used to weave the preform.

[0044] (3) In the liquid molding process, a rigid mold made of metal material is used to mold the preform individually. Fig.10 As shown, the upper mold 21 and the lower mold 22 in the molding mold are used to compact the main body 11 area of ​​the preform, and the preform is unfolded along a specified plane to the flange reserved groove in the molding cavity, and the left mold 24 and the right mold 23 in the molding mold are used to compact the forked body 12 on the left and right sides, and finally the entire mold is tightened.

[0045] (4) VARTM molding is used, and the resin system is epoxy resin. After the mold is tightened and sealed in step (3), the resin system is poured into the mold cavity under a vacuum degree of -0.08Mpa using vacuum-assisted technology to infiltrate the preform; after the pouring is completed, the entire mold is moved into an oven and kept at 100°C for 2 hours to complete the curing.

[0046] (5) Demolding to obtain a three-dimensional woven composite wing rib.

[0047] The present invention uses specific examples to illustrate the principles and implementation methods of the present invention. The above examples are only used to help understand the method and core ideas of the present invention. At the same time, for those skilled in the art, according to the ideas of the present invention, there will be changes in the specific implementation methods and application scope. In summary, the content of this specification should not be understood as limiting the present invention.

Claims

1. A method for manufacturing a rib using a three-dimensional woven composite material, characterized in that: The following steps are involved: S1. Determine the shape of the preform according to the geometric shape of the rib to be manufactured; If the rib is C-shaped, L-shaped or flat web-shaped, the preform is in the form of a flat plate; If the wing rib is H-shaped, the preform is in the shape of a flat plate, and two forked bodies are provided at both ends of the preform, and the two forked bodies located at the same end of the preform are not connected to each other and are integrally formed with the preform; S2. The material of the preform is a three-dimensional woven fabric. The organization form and basic weaving parameters of the preform are determined according to the geometric dimensions and mechanical performance requirements of the rib; the organization form is a three-dimensional orthogonal weaving or a three-dimensional angle interlocking weaving, and the basic weaving parameters include the number of warp yarn layers, the number of weft yarn layers, the warp yarn density, the weft yarn density and the total number of yarns; S3, using a three-dimensional loom to weave the preform according to the basic weaving parameters; S4, preparing a molding die, wherein the shape and size of the molding cavity of the molding die are exactly the same as the shape and size of the rib; Placing the preform in the molding cavity and fixing the shape of the preform by the molding die so that the shape of the preform is the same as the shape of the rib; The preform is formed in the molding cavity by a vacuum-assisted resin transfer molding process, wherein the matrix is ​​formed by curing the resin that completely impregnates the preform in the molding cavity; Then demoulding is performed to obtain the rib.

2. The method for manufacturing a rib using a three-dimensional woven composite material according to claim 1, characterized in that: When the wing rib is C-shaped, the wing rib includes a web and two flanges respectively connected to the web; the thickness of the preform, the thickness of the web and the thickness of each flange are equal, the length of the preform, the length of the web and the length of each flange are equal, and the width of the preform is the sum of the height of the web and the width of the two flanges.

3. The method for manufacturing a rib using a three-dimensional woven composite material according to claim 1, characterized in that: When the wing rib is L-shaped, the wing rib includes a web and a flange connected to the web; the thickness of the preform, the thickness of the web and the thickness of the flange are equal, the length of the preform, the length of the web and the length of the flange are equal, and the width of the preform is the sum of the height of the web and the width of the flange.

4. The method for manufacturing a rib using a three-dimensional woven composite material according to claim 1, characterized in that: When the wing rib is of a flat web type, the wing rib only includes the web, the thickness of the preform is equal to the thickness of the web, the length of the preform is equal to the length of the web, and the width of the preform is equal to the height of the web.

5. The method for manufacturing a rib using a three-dimensional woven composite material according to claim 1, characterized in that: When the wing rib is H-shaped, the wing rib includes a web, two upper flanges respectively located on both sides of the top end of the web, and two lower flanges respectively located on both sides of the bottom end of the web; the thickness of the preform is equal to the thickness of the web, the thickness of each upper flange and the thickness of each lower flange are half of the thickness of the web, the length of the preform, the length of the web, the length of each upper flange and the length of each lower flange are equal, and the width of the preform is the sum of the height of the web, the width of one upper flange and the width of one lower flange.

6. The method for manufacturing a rib using a three-dimensional woven composite material according to claim 1, characterized in that: When the wing rib is H-shaped, the part of the preform except the bifurcated body is the main body, and the bifurcated body and the main body share the weft yarn; The two side surfaces of the preform along the thickness direction are respectively a first side surface and a second side surface, and the direction from the first side surface to the second side surface is a first direction; The arrangement order of the layers of the weft yarns in the two forked bodies at the same end of the preform along the first direction is a first arrangement order, and the arrangement order of the layers of the weft yarns in the main body along the first direction is a second arrangement order, and the first arrangement order is the same as or different from the second arrangement order.

7. The method for manufacturing a rib using a three-dimensional woven composite material according to claim 6, characterized in that: The first arrangement order is different from the second arrangement order, the second arrangement order is 1, 2, ..., m, m+1, ..., m+n, and the first arrangement order is m+1, m+2, ..., m+n, 1, 2, ..., m, and the number of layers of weft yarns in the two forked bodies at the same end of the preform are m and n respectively.

8. The method for manufacturing a rib using a three-dimensional woven composite material according to claim 6, characterized in that: The first arrangement order is different from the second arrangement order, the second arrangement order is 1, 2, ..., m, m+1, ..., m+n, and the first arrangement order is m+n, m+n-1, ..., m+1, m, m-1, ..., 1, and the number of layers of weft yarns in the two forked bodies at the same end of the preform are m and n respectively.

9. Wing rib, characterized in that: The rib is manufactured by the method for manufacturing a rib using a three-dimensional woven composite material as claimed in any one of claims 1 to 8.

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