An ultra-long span all-composite hatch cover and its preparation method

Abstract

The present invention relates to the field of ship composite material structure and forming technology, and provides an ultra-large span all-composite material hatch cover and its preparation method, wherein the hatch cover comprises a lower panel, an intermediate layer, an upper panel and an external connection structure; the lower panel is bonded to the upper panel through the intermediate layer to form a hatch cover body, and both ends of the hatch cover body are respectively connected to the external connection structure, and are quickly and conveniently connected to the external structure by combining the main beam and the lattice structure, playing the role of force transmission support. The preparation method of the hatch cover comprises: step one, forming the lower panel; step two, preparing the intermediate layer; step three, laying the upper panel; step four, connecting the main beam to the external structure; pouring according to the vacuum integrated forming process to obtain the desired hatch cover; the present invention can achieve a span of not less than 5 meters, and the deformation under deadweight conditions is less than 2 mm. The hatch cover has the characteristics of light weight, high strength, high rigidity, designable lattice structure, low manufacturing cost, high forming rate, and low process risk.

Description

Technical Field

[0001] The present invention relates to the technical field of ship composite material structure and molding, and in particular to an ultra-long span all-composite material hatch cover and a preparation method thereof. Background Art

[0002] Currently, composite materials are highly favored in the design of marine equipment due to their excellent high specific stiffness and specific strength. For underwater ships, their hatch covers need to meet various working conditions such as opening and closing, lifting, etc. underwater or on the surface of the water. In the past, hatch covers were mostly metal structures, which were heavy and required a large number of connecting arms, hydraulic devices and other connecting structures in the middle to ensure that the structural strength met the requirements of various working conditions. On the one hand, the structural connections were relatively complex and the cost was high; on the other hand, the overall weight of the structure was heavy, occupying a large amount of the underwater ship weight margin. Today, the shipbuilding industry is developing in the direction of lightweighting and diversification. Ultra-long span all-composite hatch covers can reduce the weight of the hatch covers and lower the center of gravity of the ship. On the other hand, the ultra-long span reduces internal mechanical connections and saves space. The internal sandwich functional core material can provide buoyancy while also being designed with multiple functions.

[0003] To better save ship energy consumption, reduce the number of connecting arms or hydraulic devices connecting the midship to the hatch cover, reduce overall weight, and save equipment space, research on the production of ultra-large span composite hatch covers is particularly important. Lattice-reinforced sandwich composites integrate the respective advantages of traditional foam sandwich composites and composite lattices. They retain the advantages of traditional foam sandwich composites such as lower density, higher strength, and higher modulus, while also leveraging the excellent mechanical properties of composite lattices. Specifically, with a slight increase in overall density, the lightweight, high strength, high stiffness, and mechanical properties of lattice-reinforced foam sandwich composites are significantly improved, including flat compression, lateral pressure, bending, shear, and impact resistance. Therefore, introducing lattice-reinforced sandwich composites into ultra-large span composite hatch covers and effectively connecting and smoothly transitioning lattice-reinforced foam sandwich composites with ultra-span all-composite hatch cover structures is an effective way to solve the above problems.

[0004] In recent years, there have been many achievements in the research of hatch cover design and production. The invention patent "Integrated molding method of composite hatch door and composite hatch" (application number: CN20211193040.9) proposed a method for integral molding of composite hatch door, the invention patent "A self-locking composite pre-deformed hatch structure optimization design method" (application number: CN201610464009.7) proposed a composite hatch of aircraft to prevent deformation in advance by self-locking, the invention patent "A composite integrated cabin door manufacturing method" (application number: CN202311534535.2) proposed a composite integrated infusion molding cabin door manufacturing method, the invention patent Patent application "A Composite Door for Underwater Protective Cover, Underwater Protective Cover, and Preparation Method Thereof" (Application Number: CN202310767455.5) provides a method for preparing a composite door for an underwater protective cover, and invention patent "A Method for Mechanically Forming a Composite Lattice Sandwich Structure Door" (Application Number: CN202311726754.0) proposes a composite lattice sandwich structure door and its forming method. These cases primarily involve forming and manufacturing methods for composite one-piece doors, pre-deformation of self-locking composite doors for aircraft, composite shelter doors, composite doors for underwater protective covers, and composite lattice sandwich structures. None of these cases involve ultra-long-span all-composite hatch cover structures and their preparation methods. Even in patent CN115257123A, a lightweight, high-strength composite sheet and its preparation method are disclosed, which are applied to the field of composite sheet forming technology. The composite sheet has a structure of three layers: upper, middle, and lower. The upper and lower layers are respectively an upper skin and a lower skin. The middle layer has a honeycomb-like structure, which is composed of a plurality of small blocks connected together. The shape of the small blocks is not restricted. Each small block has a foam core in the middle, which is wrapped with a layer of carbon yarn or fiber cloth. The foam core and the carbon yarn or fiber cloth are tightly bonded by hot pressing. The arrangement of the sheet and its preparation method can easily produce large, special-shaped products. The products are lightweight, high-strength, and have a shortened manufacturing cycle. However, due to the relatively complex preparation method, it is easy to cause high costs. The core material prepared by heat foaming molding is prone to low uniformity and tightness between molecules in the sheet, which in turn affects the quality of the sheet. In addition, the arrangement of this sheet structure is not suitable for applications with ultra-large spans.

[0005] As a new type of composite ship hatch cover, the design of ultra-large span hatch covers requires full consideration of their weight and mechanical properties. Furthermore, the connecting arms or hydraulic devices connecting the hatch cover to the midship section of the ship must also be considered. Currently, there are no reports in published domestic and international literature or patents on ultra-large span all-composite hatch cover structures and their preparation methods. Therefore, it is of great significance to study how to achieve the preparation of ultra-large span hatch covers while improving their mechanical properties, reducing the number of connecting arms or hydraulic devices connecting the hatch cover to the midship section, reducing overall weight, and saving equipment space, thereby saving ship energy consumption. Summary of the Invention

[0006] In view of this, the present invention relates to an ultra-large span all-composite hatch cover structure and a preparation method thereof, which mainly solves the problem that there is currently no ultra-large span all-composite cover structure design and a preparation method thereof. The structural design method of the present invention can achieve a span of not less than 5 meters, and a deformation of less than 2mm under deadweight conditions, with the characteristics of light weight, high strength and high rigidity. At the same time, it can effectively reduce the connecting arm or hydraulic device connecting the midship of the ship to the hatch cover, reduce the overall weight, effectively save space and reduce costs. This preparation method can solve the overall stability and quality consistency of the sandwich preform during the molding process of the lattice-reinforced sandwich composite material, and has the characteristics of low manufacturing cost, high molding efficiency, low process risk and stable quality.

[0007] To achieve the above object, the technical solution of the present invention is achieved as follows:

[0008] The present invention relates to an ultra-long span all-composite hatch cover and a preparation method thereof. The ultra-long span all-composite hatch cover has a span of ≥5m and a deformation of the hatch cover under deadweight working conditions of <2mm. The hatch cover comprises a lower panel, an intermediate layer, an upper panel and an external connection structure; the lower panel is bonded to the upper panel via the intermediate layer to form a hatch cover body, and both ends of the hatch cover body are respectively connected to the external connection structure; the intermediate layer comprises a fiber component, a lattice and a core material component; the bottom of the lattice is bonded to the top of the lower panel via the fiber component, the upper outer side wall of the lattice is respectively bonded to the bottom of the upper panel and the outer side wall of the core material component via the fiber component, and the two ends of the core material component are respectively bonded to the lower panel and the upper panel.

[0009] Furthermore, the fiber component is a dry fiber cloth or a prepreg fiber fabric; the material of the upper panel and the lower panel are any one or more fiber fabrics of glass fiber, carbon fiber, carbon / glass hybrid fiber, quartz fiber, Kevler fiber, ultra-high molecular weight polyethylene fiber, and PBO fiber.

[0010] Furthermore, the fiber component includes a fiber component 1 and a fiber component 2; the bottom sides of the fiber component 1 and the core material component are both arranged on the top of the lower panel, and the top side of the fiber component 1 is connected to the lattice; the bottom of the fiber component 2 is arranged at the upper end of the lattice; the top side of the fiber component 2 is respectively fitted with the bottom of the upper panel and the outer side wall of the core material component.

[0011] Furthermore, the lattice structure includes a structural core material and a main beam core material; the structural core material and the main beam core material are staggered; the bottom and top of the structural core material and the main beam core material are respectively bonded to the fiber component one and the fiber component two, and the outer side walls of the structural core material and the main beam core material are bonded to the outer side walls of the core material component through the fiber component two.

[0012] Furthermore, 2N+1 core materials of the structure are provided, and M core materials of the main beam are provided, wherein N and M are both positive integers, and N≥1, M≥1.

[0013] Furthermore, the lattice structure also includes prefabricated blocks, and both ends of the main beam core material are connected to the external connection structure through the prefabricated blocks.

[0014] Furthermore, the core material of the structure and the core material of the main beam are made of any one or more materials selected from PVC, PET, and buoyancy materials.

[0015] Furthermore, the core material component is made of foam material or buoyancy material.

[0016] A method for preparing an ultra-long span all-composite hatch cover, the method being applied to preparing the ultra-long span all-composite hatch cover, the method comprising the following steps:

[0017] Step 1: Lower panel forming: According to the required specifications and dimensions of the lower panel, the type, number of layers and laying method of the reinforcing fiber fabric for preparing the lower panel are selected, and the lower panel is formed by spraying and shaping.

[0018] Step 2: Preparation of the middle layer: Determine the arrangement and location of the fiber assembly, lattice structure, and core material assembly, and assemble the fiber assembly, lattice structure, and core material assembly to obtain the middle layer;

[0019] Step 3: Laying the upper panel: Laying at least one layer of fiber fabric required for the upper panel on the top of the lattice filled with the core material component to obtain the upper panel;

[0020] Step 4: Integral forming: Process according to the VARI forming process to obtain an integrally formed hatch cover.

[0021] Furthermore, step 2 includes:

[0022] Step S21: processing the shapes and sizes of the fiber components, the core materials of the structure, and the core materials of the main beam respectively according to the configuration of the lattice structure and the setting of the main beam structure;

[0023] Step S22: Laying the fiber assembly in the processed fiber assembly on the mold according to the lattice configuration, and bonding the structural core material and the main beam core material with the adhesive coated on the bottom to the fiber assembly;

[0024] Step S23: Laying the second fiber component: According to the lattice configuration, the number of laying layers of the second fiber component is selected, and the second fiber component is alternately laid in the upper end of the lattice in the vertical direction to form a composite material lattice;

[0025] Step S24: Processing the core material component: processing the shape and size of the core material component according to the configuration setting requirements of the lattice;

[0026] Step S25: Filling the core material component: spray an appropriate amount of glue on the top side of the prepared composite material lattice, and place the processed core material component as a whole and stably on the upper side of the second fiber laying component, thereby forming a composite material lattice structure filled with the core material.

[0027] Compared with the prior art, the ultra-long span all-composite hatch cover and its preparation method described in the present invention have the following beneficial effects:

[0028] The hatch cover arrangement and its preparation method primarily include two key processes: the structural arrangement of an ultra-large-span hatch cover and the molding of a lattice-reinforced sandwich composite material. This simplifies the overall structure of the hatch cover, enables the preparation of ultra-large-span hatch covers, optimizes the hatch cover preparation method, reduces hatch cover preparation costs, improves the tightness and uniformity of the internal intermolecular structure of the prepared hatch cover, ensures the quality of the hatch cover, reduces internal mechanical connections, conserves space inside the middle of the ship's hatch cover, reduces the weight of the hatch cover, and achieves lightweight and diversified hatch cover configurations, thereby saving energy during ship operation. Furthermore, it can achieve a span of no less than 5 meters and a deformation of less than 2 mm under deadweight conditions, resulting in a hatch cover with ultra-large spans, light weight, high strength, high rigidity, designable lattice structures, low manufacturing costs, high molding efficiency, and low process risks, making it easy to produce and promote. The ultra-large span all-composite hatch cover structure and its preparation method can be widely used in the fields of shipbuilding, aerospace, etc., and can be quickly and conveniently connected to the external structure by combining the main beam and the lattice structure, and has broad application prospects. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] The accompanying drawings, which constitute part of the present invention, are provided to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the accompanying drawings:

[0030] Figure 1 is a schematic diagram of the lower panel molding structure;

[0031] Figure 2a Schematic diagram of the cross-sectional shape of the core material of the structure;

[0032] Figure 2b A schematic diagram of the cross-sectional shape of the main beam core material;

[0033] Figure 2c is a schematic diagram of the cross-sectional shape of the lattice filling core component;

[0034] Figure 3 This is a schematic diagram of the overall lattice structure assembly;

[0035] Figure 4a Schematic diagram of radial, chordal and cross-laying methods in lattice layup;

[0036] Figure 4b Schematic diagram of the wraparound ply method in lattice ply;

[0037] Figure 5 Schematic diagram of the overall structure of the lattice reinforced sandwich composite preform;

[0038] Figure 6a This is a schematic diagram of the hatch cover's deadweight deformation simulation under deadweight conditions;

[0039] Figure 6b The diagram of the ultimate tension and ultimate compression simulation under the deadweight condition of the hatch cover is shown in Figure 2.

[0040] Figure 6c Schematic diagram of the self-weight plus deformation simulation under the added load case for the hatch cover;

[0041] Figure 6d Schematic diagram of the ultimate tension and ultimate compression simulation with added load cases for the hatch cover.

[0042] Explanation of the accompanying drawings: 1. Lower panel; 2. Middle layer; 20. Fiber assembly; 201. Fiber assembly one; 202. Fiber assembly two; 202a. Fiber one; 202b. Fiber two; 202c. Fiber three; 202d. Fiber four; 202e. Fiber five; 202f. Fiber six; 202g. Fiber seven; 21. Lattice; 211. Core material of the structure; 212. Core material of the main beam; 2121. Prefabricated block; 22. Core material assembly; 3. Upper panel; 4. Mold; 5. External connection structure. DETAILED DESCRIPTION

[0043] The inventive concepts of the present disclosure will be described below using terms commonly used by those skilled in the art to convey the essence of their work to other persons skilled in the art. However, these inventive concepts can be embodied in many different forms and should not be considered limited to the embodiments described herein.

[0044] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features therein may be combined with each other.

[0045] In the description of the present invention, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "top", "bottom", "inside", "outside", etc., indicating directions or positional relationships, are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore should not be understood as limiting the present invention.

[0046] The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with embodiments.

[0047] To address the problems of complex and costly panel preparation methods in the prior art, as well as the low molecular uniformity and tightness of the core material produced by thermal foaming, which in turn affects the panel's quality, this embodiment proposes an ultra-long-span all-composite hatch cover and its preparation method. The ultra-long-span all-composite hatch cover has a span of ≥5m and a deformation under deadweight of <2mm. The hatch cover comprises a lower panel 1, an intermediate layer 2, an upper panel 3, and an external connection structure 5. The lower panel 1 is bonded to the upper panel 3 via the intermediate layer 2 to form the hatch cover body. The ends of the hatch cover body are connected to the external connection structure 5. The intermediate layer 2 comprises a fiber assembly 20, a lattice 21, and a core assembly 22. The bottom of the lattice 21 is bonded to the top of the lower panel 1 via the fiber assembly 20. The upper outer wall of the lattice 21 is bonded to the bottom of the upper panel 3 and the outer wall of the core assembly 22 via the fiber assembly 20. The ends of the core assembly 22 are bonded to the lower panel 1 and the upper panel 3, respectively. The fiber component 20 is a dry fiber cloth or a prepreg fiber fabric. In this embodiment, the outer side wall refers to the side wall composed of the front, back, left and right sides of the component. The material of the upper panel 3 and the lower panel 1 are any one or more fiber fabrics selected from glass fiber, carbon fiber, carbon / glass hybrid fiber, quartz fiber, Kevler fiber, ultra-high molecular weight polyethylene fiber, and PBO fiber. The surface density of the upper panel 3 and the lower panel 1 are both ≥100g / m 2 The thickness, plying method, and fiber fabric type of the upper panel 3 and the lower panel 1 can be the same or different.

[0048] By setting up the hatch cover, the overall structure of the hatch cover can be simplified, the preparation of ultra-large span hatch covers can be realized, the preparation method of the hatch cover can be optimized, the preparation cost of the hatch cover can be reduced, the tightness and uniformity between the internal molecules of the prepared hatch cover can be improved, the quality of the hatch cover can be guaranteed, and the weight of the hatch cover can be reduced; thereby, energy consumption during the operation of the ship can be saved.

[0049] The fiber assembly 20 includes a fiber assembly 201 and a fiber assembly 202. The bottom sides of the fiber assembly 201 and the core material assembly 22 are both arranged on the top of the lower panel 1, and the top side of the fiber assembly 201 is connected to the bottom of the lattice 21. The fiber assembly 201 is strip-shaped, and the width of the fiber assembly 201 is consistent with the bottom width of the lattice 21. At least 2N fiber assemblies 201 are provided, where N is a positive integer. The specific number of strips is set according to needs. The N fiber assemblies 201 are arranged parallel to each other. The N fiber assemblies 201 and the other N fiber assemblies 201 are arranged vertically on the top of the lower panel 1. The bottom of the fiber assembly 202 is arranged at the upper end of the lattice 21. Specifically, the bottom side of the fiber assembly 202 is respectively in contact with the top, left end, right end, front end, and rear end of the lattice 21. The top side of the fiber assembly 202 is respectively in contact with the bottom of the upper panel 3 and the outer wall of the core material assembly 22. The two ends of the fiber component 1 201 abut against the two ends of the fiber component 202, forming a fiber full wrapping of the lattice 21, so as to enhance the structural strength of the hatch cover.

[0050] The fiber fabric used in the fiber assembly 201 is any one or more of glass fiber, carbon fiber, carbon / glass hybrid fiber, quartz fiber, Kevler fiber, ultra-high molecular weight polyethylene fiber, and PBO fiber. The surface density of the fiber assembly 201 is ≥100 g / m 2 The second fiber assembly 202 is a dry fiber cloth or prepreg for the composite lattice 21. The fiber fabric type of the second fiber assembly 202 can be the same as or different from the fiber fabric type of the upper panel 3 or the lower panel 1.

[0051] By setting the fiber component 1 201 and the fiber component 202, the two are respectively set on both sides of the lattice 21. On the one hand, the relative stability between the lattice 21 and the lower panel 1 can be improved, avoiding the problem of positional displacement when filling the core material component 22 into the grid in the lattice 21. On the other hand, the filling density between the filled core material component 22 and the lattice 21 can be improved. By setting the fiber component 202, the friction between the core material component 22 and the lattice 21 can be improved, and the tightness of the fit between the core material component 22 and the lattice 21 can be achieved, thereby improving the strength and rigidity between the components in the hatch cover.

[0052] The second fiber assembly 202 includes long fiber sheets and short fiber sheets. The long fiber sheets and short fiber sheets are alternately laid on the upper end of the lattice 21 to enhance the strength and rigidity of the lattice 21.

[0053] The lattice structure 21 includes a structural core material 211 and a main beam core material 212. The structural core material 211 and the main beam core material 212 are arranged in an alternating manner. The bottom and top of the structural core material 211 and the main beam core material 212 are respectively bonded to the fiber component 1 201 and the fiber component 2 202. The outer side walls of the structural core material 211 and the main beam core material 212 are bonded to the outer side walls of the core material component 22 through the fiber component 202. Among them, there are 2N+1 structural core materials 211 and M main beam core materials 212, where N and M are both positive integers, and N≥1 and M≥1. The 2N+1 structural core materials 211 are arranged perpendicularly or parallel to each other. The structural core material 211 is arranged on the top of the lower panel 1 along the front-to-back direction or the left-to-right direction through the fiber component 1 201. The M main beam core materials 212 are arranged along the left-to-right direction and are connected to the structural core material 211 and the fiber component 1 201 respectively. Specifically, 2N+1 structural core materials 211 and M main beam core materials 212 are staggered to form grids of different sizes distributed along the matrix. The material of the structural core material 211 and the main beam core material 212 are any one or more lightweight materials such as PVC, PET, and buoyancy materials. The characteristics of this lightweight material are high compression hardness and low density. From the perspective of composite material structure design, the cross-sections of the structural core material 211, the main beam core material 212, and the core material assembly 22 are all n-gons, where n is a positive integer and n≥3. Preferably, the cross-sections of the structural core material 211, the main beam core material 212, and the core material assembly 22 can adopt any one or more simple geometric shapes such as rectangle, trapezoid, and triangle.

[0054] In this embodiment, the lattice 21 is composed of 2N+1 structural core materials 211 and 1 main beam core material 212. Specifically, the structural core material 211 has a trapezoidal cross-section, the main beam core material 212 has a hexagonal cross-section, and the core material assembly 22 has a trapezoidal cross-section. The machining tolerances of the structural core material 211 and the main beam core material 212 are respectively ±2 mm. The shapes and sizes of the 2N+1 structural core materials 211 are identical. In addition, the lengths of the structural core material 211 and the main beam core material 212 are both in the range of 1500 mm to 6000 mm. The length of the core material assembly 22 is in the range of 500 mm to 1000 mm. A cross or T-shaped intersection is formed at the intersection of the structural core material 211 and the main beam core material 212. The long fiber sheets and short fiber sheets in the fiber assembly 202 are arranged on the arms of the cross or T-shaped intersection in a staggered manner. It is used to improve the tightness of the connection between the structure core material 211 and the main beam core material 212.

[0055] The distributed arrangement of the structural core material 211 and the main beam core material 212 enables rapid installation of the lattice 21, reducing its production costs. In conjunction with the fiber assembly 20, the structural stability of the lattice 21 is significantly enhanced. Furthermore, the staggered arrangement of the structural core material 211 and the main beam core material 212 enables the construction of hatch covers with spans of up to 5 meters. Combined with the layup structure of the fiber assembly 1 201 and fiber assembly 202, the deformation of the main beam core material 212 under deadweight conditions is reduced to less than 2 mm, enhancing the overall safety and reliability of the hatch cover. Furthermore, the combined structure of the main beam core material 212 and the lattice 21 allows for quick and convenient connection to the external connection structure 5, further enhancing load-transmitting support.

[0056] The lattice structure 21 further includes prefabricated blocks 2121, through which both ends of the main beam core material 212 are connected to the external connection structure 5. The lattice structure 21 further includes bolts, one end of which is disposed on the prefabricated blocks 2121, and the other end of which is connected to the external connection structure 5.

[0057] The provision of the prefabricated blocks 2121 facilitates the fixation between the main beam core material 212 and the external connection structure 5, and also facilitates the pre-embedded provision of bolts, thereby reducing the difficulty of the hatch cover manufacturing process, improving the preparation efficiency of the hatch cover, and realizing the preparation of all-composite hatch covers with ultra-large spans.

[0058] The core component 22 is arranged in the grid inside the lattice 21. Preferably, the material of the core component 22 is a foam material or a buoyant material. The foam material includes any one or more foam materials selected from polyvinyl chloride (PVC), glass beads, polymethacrylimide (PMI), polyethylene terephthalate (PET), and polyurethane (PU). When the core component 22 is a foam material, the density of the core component 22 is ≤300kg / m 3 ±20 kg / m 3 When the core component 22 is a buoyant material, the density of the core component 22 is in the range of 380 kg / m 3 ±20kg / m 3 -500kg / m 3 ±20kg / m 3 When the length of the core component 22 is too long, it can be processed by splicing. The geometric shape of the cross section of the core component 22 is set as required.

[0059] The use of a core component 22 made of foamed or buoyant material can reduce the use of high-cost fibers, increase the processing speed of the core component 22, and enhance the noise and vibration reduction capabilities of the hatch cover. It also prevents fiber layer buckling, maintaining structural stability. It also absorbs energy and disperses impact stress through plastic deformation.

[0060] A method for preparing an ultra-long span all-composite hatch cover, the method being applied to preparing the ultra-long span all-composite hatch cover, the method comprising the following steps:

[0061] Step 1, forming the lower panel 1: according to the required specifications and dimensions of the lower panel 1, the type, number of layers and laying method of the reinforcing fiber fabric for preparing the lower panel 1 are selected, and the formed lower panel 1 is prepared by spraying and shaping.

[0062] Step 2: Preparation of the intermediate layer 2: Determine the arrangement and position of the fiber assembly 20, the lattice 21, and the core assembly 22, and assemble the fiber assembly 20, the lattice 21, and the core assembly 22 to obtain the intermediate layer 2;

[0063] Step 3: Laying the upper panel 3: Laying at least one layer of fiber fabric required for the upper panel 3 on the top of the lattice 21 filled with the core material assembly 22 to obtain the upper panel 3;

[0064] Step 4: Integral Forming: After connecting the main beam core material 212 to the external connection structure 5, vacuum integral molding is performed according to the VARI molding process to obtain the required integrally formed hatch cover. The VARI molding process is a vacuum assisted resin infusion integral molding process.

[0065] The described method addresses the current lack of ultra-long-span all-composite hatch cover structure designs and fabrication methods. It can achieve hatch cover spans of at least 5 meters and deformation of less than 2mm under deadweight conditions. The method primarily involves two key processes: designing the ultra-long-span hatch cover structure and molding the lattice-reinforced sandwich composite material. It also enables hatch covers with ultra-long spans, lightweight, high strength, and high rigidity, flexible lattice 21 configurations, low manufacturing costs, high molding efficiency, low process risks, and consistent quality. It can effectively reduce the number of connecting arms or hydraulic devices connecting the ship's midships to the hatch cover, reducing overall weight, saving space, and ultimately lowering costs. It also addresses the overall stability and quality consistency of the sandwich preform during the molding of the lattice 21-reinforced sandwich composite material. Production and application are readily feasible. This ultra-long-span all-composite hatch cover structure and fabrication method are widely applicable in the marine, aerospace, and other fields. By combining the main beam and lattice 21 structure, it allows for quick and convenient connection to external structures, promising broad application prospects.

[0066] Step one includes:

[0067] Step S11: forming the lower panel 1: determining the preparation specifications and dimensions of the lower panel 1 according to the target thickness of the lower panel 1 and the type of the selected reinforcing fiber fabric; and selecting the type, number of layers, and laying method of the required laying reinforcing fiber fabric for the lower panel 1;

[0068] Step S12: After pre-drying the selected reinforcing fiber fabric, the fabric is laid out according to the fiber laying requirements;

[0069] Step S13: When laying, the entire roll of fiber is laid on a fabric rack for laying, and the glue is evenly sprayed on different layers of fiber fabrics by spraying glue to set the shape, and the fiber fabrics are cut to the required size;

[0070] Step S14: injecting glue into the cut fiber fabric, and then curing and molding it to obtain the molded lower panel 1.

[0071] In step S12, the fiber placement requirement is that the fabric layer be flat, without noticeable wrinkles or bubbles. The fiber fabric dimensions must be greater than the target planar area of ​​the lower panel 1. The planar area refers to the length and width dimensions of the lower panel 1. This is used to improve the efficiency of placing the different layers of fiber fabric. After complete placement, the lower panel 1 is cut to the target dimensions. This facilitates preparation for subsequent glue injection and curing to obtain the lower panel 1, and also facilitates rapid preparation of the lower panel 1.

[0072] By setting up each step in step one, the efficiency and quality of the molding of the lower panel 1 can be improved. By drying the fiber fabric in advance in step S12, it is possible to prevent the mechanical properties from being affected by the subsequent fusion and curing with the resin. In step S13, due to the large laying area, it is necessary to ensure the uniformity of the spraying when spraying the glue for shaping. In addition, placing the entire roll of fiber on the cloth rack for laying is conducive to avoiding fiber distortion, thereby improving the quality of the lower panel 1. It can also prevent the occurrence of the phenomenon of affecting the layout position of the lattice 21 when the vacuum is established during the subsequent molding and perfusion.

[0073] The preparation and arrangement of the lower panel 1 in step 1 can improve the strength, rigidity, and impact resistance of the hatch cover. It can also enhance the hatch cover's ability to resist external impacts and local damage, increase the bending and torsional rigidity of the overall hatch cover structure, and suppress low-frequency vibrations.

[0074] Step 2 includes:

[0075] Step S21: Based on the structural setting of the required hatch cover in the early stage, the shapes and sizes of the fiber assembly 20, the body core material 211 and the main beam core material 212 are processed respectively according to the configuration of the lattice 21 and the setting of the main beam structure.

[0076] Step S22: Laying the fiber assembly 201 in the processed fiber assembly 20 on the mold 4 according to the configuration of the lattice 21, and bonding the structure core material 211 and the main beam core material 212 with the adhesive coated on the bottom to the fiber assembly 201;

[0077] Step S23: Laying the second fiber component 202: According to the number of laying layers of the second fiber component 202 set in the lattice 21, the second fiber component 202 is alternately laid in the upper end of the lattice 21 along the vertical direction to form the composite material lattice 21.

[0078] Step S24: Processing the core component 22: Processing the shape and size of the core component 22 according to the configuration requirements of the lattice 21, especially the size of the grids in the lattice 21;

[0079] Step S25: Filling the core material component 22: Spray an appropriate amount of glue on the top side of the prepared composite material lattice 21, and place the processed core material component 22 stably in the lattice inside the lattice 21 on the upper side of the lower panel 1, so as to fill the processed core material component 22 into the prefabricated composite material lattice 21, thereby forming a composite material lattice 21 structure filled with core material. The composite material lattice 21 structure filled with core material is stably placed as a whole on the laid fiber cloth, i.e., the fiber assembly 201. After the laying is completed, the gaps are filled with fiber filaments to ensure that there are no gaps between the filled lattice 21 and the core material component 22, so as to more accurately control the infusion quality.

[0080] In conjunction with the ultra-long-span hatch cover structure, the key process of forming the sandwich composite material reinforced by the lattice 21 in step 2 improves the stability and reliability of the hatch cover's overall structure. Furthermore, this process ensures the intermolecular tightness of the hatch cover and avoids the problem of excessive stiffness often associated with materials composed of a single fiber fabric. The foam core assembly 22 absorbs energy through plastic deformation and disperses impact stress. Furthermore, due to the low density and light weight of the core assembly 22, the use of the lattice 21 reinforced sandwich composite material helps reduce the cost and weight of the hatch cover, while also improving its impact resistance and energy absorption capacity. Furthermore, the combination of the core assembly 22 and the lattice 21 assembly also helps reduce high-frequency vibration and noise, while suppressing low-frequency vibration.

[0081] Wherein, in step S22, the bottom of the body core material 211 and the main beam core material 212 are all or partially coated with adhesive. It is used to prevent the assembly position of the body core material 211 and the main beam core material 212 from changing with each component, so that the body core material 211 and the main beam core material 212 can be stably bonded to the mold 4. Preferably, in step S22, adjacent different body core materials 211 are arranged in parallel. The main beam core material 212 includes prefabricated blocks 2121, and the prefabricated blocks 2121 are arranged at both ends of the main beam core material 212. The main beam core material 212 is connected to the external connection structure 5 on the mold 4 by bolts. Wherein, the composite material prefabricated block 2121 structure is a protruding part of the main beam core material 212. In step S23 , the cross-intersection position at the connection point of the body core material 211 and the main beam core material 212 in the lattice 21 is subjected to alternating laying from the upper side to the lower side and from the lower side to the upper side to strengthen the lattice 21 .

[0082] The bolts can improve the tightness of the connection between the prefabricated block 2121 and the external connection structure 5, thereby achieving stability in the connection between the main beam core material 212 and the mold 4. Furthermore, the main beam force transmission structure can achieve a structural layout with mechanical characteristics such as high strength and high rigidity.

[0083] Step S23 includes:

[0084] Step S231: cutting the second fiber component 202 into a desired size according to the shape of the intersection of the structure core material 211 and the main beam core material 212 in the lattice structure 21 to obtain long fiber sheets and short fiber sheets;

[0085] Step S232: First, long fiber sheets are laid along the chord direction of the intersection of the structural core material 211 and the main beam core material 212, and short fiber sheets are laid along the radial direction of the intersection of the structural core material 211 and the main beam core material 212. Among them, two or one short fiber sheets are provided depending on whether the intersection of the structural core material 211 and the main beam core material 212 is cross-shaped or T-shaped.

[0086] Step S233: Then, the laying direction is adjusted, and the long fiber sheets are laid radially along the intersection of the structural core material 211 and the main beam core material 212, and the short fiber sheets are laid chordally along the intersection of the structural core material 211 and the main beam core material 212. Depending on whether the intersection of the structural core material 211 and the main beam core material 212 is cross-shaped or T-shaped, two or one short fiber sheets are still provided.

[0087] Step S234: Determine whether the long fiber sheet is laid. If yes, execute step S24; if no, return to step S232. The radial direction is the left-right direction as shown in the figure, and the chord direction is the front-back direction as shown in the figure.

[0088] By selectively laying the fiber secondary assembly 202 according to the shape of the intersection of the body core material 211 and the main beam core material 212, the structural stability of the lattice 21 can be effectively improved, and the strength and rigidity of the intersection of the body core material 211 and the main beam core material 212 in the lattice 21 can be enhanced. This reduces the number of mechanical connections within the hatch cover, saves space inside the middle of the ship's hatch cover, and paves the way for lightweight and diversified hatch cover configurations.

[0089] Step 4 includes: integral molding: connecting the main beam core material 212 with the external connection structure 5; performing vacuum one-piece molding according to the VARI molding process, arranging the demoulding cloth and the guide net in sequence, and setting the glue injection pipeline, glue outlet and glue injection port. After vacuuming with vacuum bag film, the glue injection is completed, and the mold is cured and demoulded to obtain an integrally formed hatch cover.

[0090] Among them, in step 4, the curing temperature is room temperature and the curing time is 48 hours.

[0091] By coordinating step four with steps one, two, and three, on the one hand, the method proposed in this application of combining a hatch cover with a span of not less than 5 meters and a main beam core material 212 with a self-weight deformation of 2 mm with a lattice 21 sandwich composite material can effectively and smoothly transmit the load with the external structure and the self-weight, providing a reliable solution to the strength and weight problems of the ultra-large span composite hatch cover structure. On the other hand, by developing the ultra-large span hatch cover structure, the connecting arm or hydraulic device connecting the midship of the ship to the hatch cover can be effectively reduced, the overall weight can be reduced, space can be effectively saved, and costs can be reduced. In addition, it can also solve the problems of overall stability and quality consistency of the sandwich preform during the molding process of the lattice 21 reinforced sandwich composite material. It has the characteristics of low manufacturing cost, high molding efficiency, low process risk, stable quality, etc., laying the foundation for mass production and application.

[0092] Example 1:

[0093] When a single main beam core material 212 is selected for lattice 21, the lattice 21 reinforced sandwich composite material is used, with the cross-section of the smallest repeating unit of lattice 21 being an isosceles trapezoid. The dimensions of the isosceles trapezoid are an upper base of 41.3 mm, a lower base of 60 mm, and a height of 53 mm. The dimensions of main beam core material 212 are an upper base of 90 mm, a lower base of 164 mm, and a height of 134 mm. The length of upper panel 3 is 5750 mm, and the length of lower panel 1 is 5900 mm. The width and thickness of upper panel 3 and lower panel 1 are the same, 1500 mm and 3.5 mm, respectively. The length and thickness of lattice 21 are 5750 mm and 5 mm, respectively. The cross-section of strip core material components 22 is an isosceles trapezoid. There are 32 strip core material components 22, each 5750 mm long, with cross-sectional dimensions of an upper base of 120 mm, a lower base of 60 mm, and a height of 53 mm. The high-strength connecting structural parts at both ends of the main beam core material 212 are made of titanium alloy TC4, and the connecting bolts are made of TC4 8.8 grade hexagonal cylinders, nuts, and washers. There are two bolt connections on both sides; the upper panel 3 and the lower panel 1 are selected with a surface density of 420g / m 2 The biaxial high-strength carbon fiber cloth has 8 layers; the lattice 21 also has a surface density of 420g / m 2 Biaxial high-strength carbon fiber cloth, 11 layers.

[0094] The method for preparing an ultra-long span all-composite hatch cover in Example 1 specifically comprises the following steps:

[0095] Step 1: Forming the lower panel 1: Based on the target thickness of the lower panel 1 and the type of the selected reinforcing fiber fabric, or fiber assembly 201 within the fiber assembly 20, the number of fiber fabric layers to be laid, as well as any one or more material information in the layup method, are determined. The fiber layers must be flat and free of noticeable wrinkles or bubbles. Glue spraying can be used for final shaping, ensuring uniformity during the spraying process. Due to the large layup area, the entire roll of fiber is placed directly on a fabric rack during the layup process to avoid fiber distortion. The fiber fabric dimensions are 10mm-80mm larger than the desired overspan plane (length x width). The fiber fabric is then cut and glue injected for curing. High-density biaxial carbon fiber cloth is used as the material. This glue injection and curing of the fiber assembly 201 prevents the subsequent vacuum infusion molding process from affecting the layout of the lattice 21 on the lower panel 1. This improves the positioning accuracy of the hatch cover components before and after vacuum infusion molding, and enhances infusion efficiency and quality.

[0096] Step 2: Processing of the structure core material 211, the main beam core material 212, and the corresponding core material bottom surface fiber assembly 201. Through the preliminary structural setting, the core material fiber fabric or prepreg is processed according to the configuration of the lattice 21 and the main beam core material 212, that is, the shape and size of the fiber assembly 201, the structure core material 211, and the main beam core material 212. The material of the fiber assembly 201 is biaxial high-strength carbon fiber cloth, and the surface density of the prepreg is 400Kg / m 3 Buoyancy material.

[0097] The fiber assembly 201, the structural core material 211, and the main beam core material 212 are fixed, bonded, and assembled: Dry fiber cloth or prepreg fiber fabric (fiber assembly 201) is laid onto the mold 4 according to the configuration of the lattice 21. Adhesive is then applied to all or part of the bottom of the structural core material 211 and the main beam core material 212, and bonded to the fiber assembly 201 to prevent position shifting and ensure stable bonding to the mold 4. Adjacent structural core materials 211 are arranged parallel to each other, with the structural core material 211 and the main beam core material 212 perpendicular to each other in the radial and chord directions. The protruding portion of the main beam core material 212 is a 120*100*40 mm (length*width*thickness / mm) composite fiber fabric prefabricated block 2121. The titanium alloy external connecting structure 5 at both ends is pre-embedded and connected to the prefabricated block 2121 using high-strength bolts. It should be noted here that this embodiment only has a single main beam core material 212. In the future, double main beam core materials 212 or more than two main beam core materials 212 can be set as needed, and they need to be reset according to working conditions, weight and equipment space requirements.

[0098] Composite lattice 21 is constructed using dry fiber cloth or prepreg, namely a second fiber assembly 202. As shown in Figures 4a-4b, second fiber assembly 202 includes fiber sheet 1 202a, fiber sheet 202b, fiber sheet 3 202c, fiber sheet 4 202d, fiber sheet 5 202e, fiber sheet 6 202f, and fiber sheet 7 202g. Fiber sheet 1 202a, fiber sheet 202b, fiber sheet 3 202c, fiber sheet 4 202d, fiber sheet 5 202e, fiber sheet 6 202f, and fiber sheet 7 202g are arranged around the upper end of lattice 21. Fiber sheet 1 202a is cut to 100 x 1500 mm, with three layers. Fiber sheet 202b is cut to 100 x 5800 mm, with three layers.

[0099] During the laying process, the first and second fiber sheets 202a and 202b are laid layer by layer, interlaced and separated. After laying, they are cut according to the structure. Next, the third fiber sheet 202c is cut to the following dimensions: 100*1400 mm, 3 layers. The second fiber sheet 202b is cut to the following dimensions: 300*5900 mm, 3 layers. The fourth fiber sheet 202d is cut to the following dimensions: 100*1700 mm, 3 layers.

[0100] Fiber sheet three 202c, fiber sheet seven 202g and fiber sheet four 202d are also laid layer by layer in a cross-sectional and disconnected manner. The operation requires ensuring that each layer of dry fiber cloth or prepreg, namely fiber component two 202, is tightly fitted and compacted with the structure core material 211 and the main beam core material 212.

[0101] Next, lay different layers of six fiber sheets 202f around the structural core 211 and the main beam core 212. Each six fiber sheet 202f is cut to 80*2200 mm, for a total of three layers. Layer by layer, the sheets are intersected and then separated. Five fiber sheets 202e are laid around the cross and T-intersection locations of the lattice 21, wrapping and laying them from top to bottom. Five layers of five fiber sheets 202e are selected, with a fiber sheet size of 200*200 mm. The five fiber sheets 202e must be compacted and tightened during wrapping. Based on the setup requirements, 11 layers are required for the lattice 21. Subsequently, the number of mold frames and component layup is automatically calculated according to the above layup sequence. Finally, after the aforementioned layup is completed, the lattice 21's cross-intersections and T-intersections are wrapped with seven fiber sheets 202g from the bottom to the top. Five layers of fiber sheets 202g are laid, and the fiber cloth dimensions are 200 x 200 mm. The fiber sheets 202g must be compacted during layup to ensure a consistent thickness across the lattice 21. A thickness of 5 mm equals 11 layers. The second fiber component 202 is made of high-density biaxial high-strength carbon fiber cloth.

[0102] Processing of the core component 22. The shape and size of the core component 22 are set according to the configuration of the lattice 21. The material of the core component 22 is selected with a density of 400Kg / m 3 Buoyancy material, on the core material component 22, a φ3mm through hole is opened at a spacing of 30mm*30㎜ (length*width) to prevent the phenomenon of glue being stuck during injection, which will lead to poor injection effect in some parts and affect performance.

[0103] Filling the core material component 22. Spray an appropriate amount of spray glue on the surface of the prepared composite material lattice 21 at a speed of 30 cm / s. Fill the processed core material component 22 into the prefabricated composite material lattice 21, thereby forming a core-filled composite material lattice 21 structure. The entire structure is then placed stably on the laid fiber cloth. After placement, fiber filaments can be added to any gaps to ensure complete filling without gaps, allowing for more precise control of the infusion quality.

[0104] Step 3: Laying the upper panel 3: Lay the upper panel 3 on the composite lattice 21 filled with the core material. The laying requirements are the same as those for the lower panel 1.

[0105] Step 4: Use conventional vacuum infusion molding process for composite materials to encapsulate the entire molded body. Due to the large span, a flow-guiding pipeline is used for relay injection design. A glue injection pipe is set in the middle, and an exhaust pipe is set on both sides (the exhaust pipe is 60±5mm away from the edge of the preform). Two integrated extraction and injection pipes are evenly distributed on the preform. One injection port is set at an interval of 1.5m. When laying the pipeline, the injection pipe is required to be suspended about 30mm above the injection hole; the vacuum tube is kept parallel to the edge of the upper panel 3 as much as possible, and the demoulding cloth wrapped around the vacuum tube overlaps the edge of the shell plate. Each pipeline is equipped with 4 injection ports. Except for the first injection pipe, the other 3 side guide nets are disconnected 30mm at the edge of the board.

[0106] Through the embodiments, the preparation method of the present application can be used to quickly prepare the required hatch cover plates, and the quality and impact resistance of the prepared hatch cover plates are both high, and the cost of the prepared hatch cover plates is lower and the mechanical properties are more stable.

[0107] By performing finite element analysis simulation on the hatch cover prepared by the preparation method of the present application, relevant data of the hatch cover under the deadweight condition and the added load condition are obtained respectively (such as Figures 6a-6d shown).

[0108] The hatch cover's deformation under deadweight conditions ranges from 0.35mm to 0.36mm, with a maximum tensile strength of 9 MPa and a maximum compression of 6.77 MPa. It's easy to see that under no load, the hatch cover's deformation under deadweight conditions is less than 2mm.

[0109] Under the added load condition, the self-weight plus deformation of the hatch cover is between 2.5mm and 2.6mm. The ultimate tensile strength under the design load is 66Mpa, and the ultimate compression is 48Mpa.

[0110] Through the finite element analysis of the hatch cover panels produced by the preparation method of the present application under the above two different working conditions, and by comparing the mechanical properties of the selected materials, it is not difficult to see that the combination of the main beam core material 212 and the lattice 21 of the present application, combined with the different laying methods of the fiber assembly 20, and the cooperation of the vacuum integrated infusion molding process, can greatly improve the structural strength and rigidity of the hatch cover panels. Furthermore, the analysis under the working condition of adding loads further shows that the hatch cover panels produced by the present application can be used for the preparation of all-composite hatch covers with ultra-large spans of not less than 5 meters, and according to the following Figure 6c-6d As shown, it can also be seen that the maximum deformation of the prepared hatch cover is in its center. The overall deformation distribution shows a step-like decreasing trend from the center to the ends of the hatch cover. Therefore, it is easy to see that this application is suitable for the preparation of hatch covers with extremely long spans. The hatch covers also have high strength and high rigidity.

[0111] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. An ultra-long span all-composite hatch cover, characterized in that: The span of the hatch cover is ≥5m, and the deformation of the hatch cover under deadweight working conditions is <2mm. The hatch cover comprises a lower panel (1), an intermediate layer (2), an upper panel (3) and an external connection structure (5); the lower panel (1) is bonded to the upper panel (3) through the intermediate layer (2) to form a hatch cover body, and both ends of the hatch cover body are respectively connected to the external connection structure (5); the intermediate layer (2) comprises a fiber component (20), a lattice (21) and a core material component (22); the bottom of the lattice (21) is connected by the fiber component (20) The top of the lower panel (1) is bonded to the outside wall of the upper end of the lattice (21), and the bottom of the upper panel (3) and the outside wall of the core component (22) are bonded to the bottom of the upper panel (3) and the outside wall of the core component (22) through the fiber component (20), and the two ends of the core component (22) are bonded to the lower panel (1) and the upper panel (3) respectively; the material of the upper panel (3) and the lower panel (1) is any one or more fiber fabrics selected from glass fiber, carbon fiber, carbon / glass hybrid fiber, quartz fiber, Kevler fiber, ultra-high molecular weight polyethylene fiber, and PBO fiber; The fiber assembly (20) includes a fiber assembly (201) and a fiber assembly (202); the bottom sides of the fiber assembly (201) and the core assembly (22) are both arranged on the top of the lower panel (1), and the top side of the fiber assembly (201) is connected to the lattice (21); the bottom of the fiber assembly (202) is arranged at the upper end of the lattice (21); the top side of the fiber assembly (202) is respectively fitted with the bottom of the upper panel (3) and the outer side wall of the core assembly (22); The lattice structure (21) comprises a structure core material (211) and a main beam core material (212); the structure core material (211) and the main beam core material (212) are arranged in an alternating manner; the bottom and top of the structure core material (211) and the main beam core material (212) are respectively bonded to the fiber component 1 (201) and the fiber component 2 (202); the outer side walls of the structure core material (211) and the main beam core material (212) are bonded to the outer side wall of the core material component (22) through the fiber component 2 (202); the material of the structure core material (211) and the main beam core material (212) are any one or more materials selected from PVC, PET, and buoyancy materials; the material of the core material component (22) is a foaming material or a buoyancy material.

2. The ultra-long span all-composite hatch cover according to claim 1, characterized in that: The fiber component (20) is dry fiber cloth or prepreg fiber fabric.

3. The ultra-long span all-composite hatch cover according to claim 1, characterized in that: The structure core materials (211) are provided in 2N+1 pieces, and the main beam core materials (212) are provided in M ​​pieces, wherein N and M are both positive integers, and N≥1, M≥1.

4. The ultra-long span all-composite hatch cover according to claim 1, characterized in that: The lattice structure (21) further comprises a prefabricated block (2121), and both ends of the main beam core material (212) are respectively connected to the external connection structure (5) via the prefabricated blocks (2121).

5. A method for preparing an ultra-long span all-composite hatch cover, characterized in that: The method is applied to prepare an ultra-long span all-composite hatch cover according to any one of claims 1 to 4, and the method comprises the following steps: Step 1: forming the lower panel (1): selecting the type, number of layers and laying method of the reinforcing fiber fabric for preparing the lower panel (1) according to the required specifications and dimensions of the lower panel (1), and preparing the formed lower panel (1) by spraying and shaping; Step 2, preparation of the intermediate layer (2): determining the arrangement mode and arrangement position of the fiber assembly (20), the lattice (21) and the core material assembly (22), and assembling the fiber assembly (20), the lattice (21) and the core material assembly (22) to obtain the intermediate layer (2); Step 3, laying the upper panel (3): laying at least one layer of the required fiber fabric of the upper panel (3) on the top of the lattice (21) filled with the core material component (22) to obtain the upper panel (3); Step 4: Integral forming: Process according to the VARI forming process to obtain an integrally formed hatch cover.

6. The method for preparing an ultra-long span all-composite hatch cover according to claim 5, characterized in that: The second step includes: Step S21: processing the shapes and sizes of the fiber assembly (20), the body core material (211), and the main beam core material (212) respectively according to the configuration of the lattice (21) and the setting of the main beam structure; Step S22: laying the fiber assembly (201) in the processed fiber assembly (20) on the mold (4) according to the configuration of the lattice (21), and bonding the structure core material (211) and the main beam core material (212) with the adhesive applied to the bottom to the fiber assembly (201); Step S23: Laying the second fiber component (202): According to the setting of the lattice (21), the number of laying layers of the second fiber component (202) is selected, and the second fiber component (202) is alternately laid in the upper end of the lattice (21) in the vertical direction to form the composite material lattice (21); Step S24: Processing the core material component (22): processing the shape and size of the core material component (22) according to the configuration setting requirements of the lattice (21); Step S25: Filling the core material component (22): spray an appropriate amount of glue on the top side of the prepared composite material lattice (21), and place the processed core material component (22) as a whole and stably on the upper side of the fiber laying component (202), thereby forming a composite material lattice (21) structure filled with the core material.

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