Laminate modeling method for composite material layup, impact resistant sandwich structure and apparatus

Abstract

This invention discloses a method for modeling composite material layups, an impact-resistant sandwich structure, and equipment. The method includes: performing feature analysis on the structural characteristics of the composite material layup; dividing the composite material layup into multiple layup partitions based on the feature analysis results; formulating a layup strategy corresponding to each layup partition based on its structural characteristics; setting the layup stacking order of the layup partitions according to the structural stability and process constraints of the composite material layup to form a global layup sequence; mapping the global layup sequence onto the three-dimensional geometric surface of the composite material layup to form the spatial distribution and boundaries of each layup partition; and establishing a target model of the composite material layup based on the layup strategy corresponding to each layup partition, the global layup sequence, and the spatial distribution and boundaries of each layup partition. This systematic modeling based on specific structural characteristics ensures that the layup modeling method is applicable to various structural types, and the modeling results are highly consistent with the structural performance.

Description

Technical Field

[0001] This invention relates to the field of composite material finite element modeling technology, specifically to a composite material layup modeling method, an impact-resistant sandwich structure, and equipment. Background Technology

[0002] Composite laminates comprise two or more layers of different ply structures, and their superior performance has led to a wide range of applications. For example, when ships are navigating, operating, or facing complex sea conditions, their structural components are often subjected to various dynamic loads such as wave impacts, underwater explosions, and collisions. Composite laminates possess excellent strength and stiffness, enabling them to withstand significant loads. Compared to traditional wood and metal materials, composite laminates are lightweight, easy to carry and install, and have good corrosion resistance, making them less susceptible to moisture, decay, and insect infestation.

[0003] In related technologies, composite material layup modeling often relies on experience or trial and error, lacking a systematic modeling method based on specific structural characteristics. In particular, for composite material structures with special geometric partitions or performance requirements, current modeling methods cannot guarantee the consistency between layup schemes and structural performance. Summary of the Invention

[0004] To address the problems mentioned in the background art, the purpose of this application is to provide a method for modeling composite material layups, an impact-resistant sandwich structure and equipment, to ensure that the layup scheme can accurately reflect the geometric partitions, load paths and performance requirements of the structural design.

[0005] To achieve the above objectives, the present invention provides the following technical solution: a method for modeling composite material layups includes: performing feature analysis on the structural features of the composite material layup; dividing the composite material layup into multiple layup partitions based on the feature analysis results; formulating a layup strategy corresponding to each layup partition based on the structural features of each layup partition; setting the layup stacking order of the layup partitions according to the structural stability and process constraints of the composite material layup to form a global layup sequence; mapping the global layup sequence onto the three-dimensional geometric surface of the composite material layup to form the spatial distribution and boundary of each layup partition; and establishing a target model of the composite material layup based on the layup strategy corresponding to each layup partition, the global layup sequence, and the spatial distribution and boundary of each layup partition.

[0006] In some embodiments, the step of performing feature analysis on the structural features of the composite material layup and dividing the composite material layup into multiple layup partitions based on the feature analysis results includes: performing feature analysis on the structural features of the composite material layup and dividing the composite material layup into multiple layup partitions based on the structural stress path and geometry.

[0007] In some embodiments, the step of performing feature analysis on the structural characteristics of the composite material layup and dividing the composite material layup into multiple layup partitions based on the structural stress path and geometry includes: obtaining the composite structural geometry and design parameters of the composite material layup; performing feature identification on the composite structural geometry and design parameters of the composite material layup to determine the geometric configuration, functional area division, and load transfer path of the composite material layup; and analyzing the feature differences of each region of the composite material layup based on the geometric configuration, functional area division, and load transfer path of the composite material layup to divide the composite material layup into multiple layup partitions.

[0008] In some embodiments, the step of identifying features of the composite structure geometry and design parameters of the composite material ply to determine the geometric configuration, functional area division, and load transfer path of the composite material ply includes: identifying features of the composite structure geometry and design parameters of the composite material ply to determine the geometric change positions of the curved surfaces, corners, and thickness variations of the composite material ply; dividing the composite material ply into a panel area, a core area, and a reinforcement area based on the geometric change positions of the composite material ply and the divided ply partitions, and determining the load transfer path between the panel area, the core area, and the reinforcement area.

[0009] In some implementations, the step of formulating a ply strategy for each ply partition based on its structural characteristics includes: determining the ply angle of the ply partition based on its structural characteristics, setting the number of ply layers and the thickness of each ply in the ply partition; and designing a ply configuration based on the ply of the ply partition, wherein the ply configuration design includes considering whether symmetrical ply design, gradient ply design, or local reinforcement design is required.

[0010] In some implementations, determining the ply angle of the ply partition based on its structural characteristics, and setting the number of ply layers and the thickness of each ply in the ply partition, includes: obtaining a parameterized table containing ply angles, thicknesses, and the number of layers; determining the ply angle of the ply partition by querying the parameterized table based on its structural characteristics, and setting the number of ply layers and the thickness of each ply in the ply partition.

[0011] In some embodiments, when the composite material layup includes a honeycomb sandwich panel structure, the structural features of the composite material layup are analyzed, and the composite material layup is divided into multiple layup partitions based on the analysis results, including: dividing the honeycomb sandwich panel structure into a face panel layup partition and a core material layup partition. The step of formulating a layup strategy for each layup partition based on its structural characteristics includes: determining the fiber orientation and the number of layers of the panel layup based on the panel layup partition; and determining the modeling connection relationship for each panel layup partition based on the core material layup partition.

[0012] In some embodiments, when the composite material layup includes a variable-angle layup, the step of setting the layup stacking order of the layup partitions to form a global layup sequence based on the structural stability and process constraints of the composite material layup includes: setting a load direction variation function for the variable-angle layup based on the structural stability and process constraints of the variable-angle layup; determining the layup stacking order of the layup partitions by means of angle gradient based on the load direction variation function; and generating a global layup sequence according to the layup stacking order.

[0013] In some embodiments, an impact-resistant sandwich structure is provided for the layup modeling method of composite material layup described above. The impact-resistant sandwich structure includes an upper skin, a lower skin, and an intermediate core layer. The upper skin and the lower skin are both composite laminates composed of alternating layers of carbon fiber reinforced composite material and glass fiber reinforced composite material. The intermediate core layer has a honeycomb structure and is disposed between the upper skin and the lower skin. The upper skin and the intermediate core layer, as well as the lower skin and the intermediate core layer, are bonded together by a flexible toughened adhesive film layer.

[0014] In some embodiments, a computer device is provided, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the steps of a layup modeling method for composite material layups.

[0015] Compared with the prior art, the beneficial effects of the present invention are: 1. By performing feature analysis on the structural characteristics of the composite material layup, the composite material layup is divided into multiple layup partitions based on the feature analysis results; based on the structural characteristics of each layup partition, a layup strategy corresponding to each layup partition is formulated, and the geometric and mechanical characteristics of the composite structure are directly transformed into a rule system for layup modeling.

[0016] 2. Based on the layup strategy corresponding to each layup partition, the global layup sequence, and the spatial distribution and boundary of each layup partition, a target model of the composite material layup is established, and a systematic process from structural partitioning, layup strategy, sequence generation to boundary mapping is established.

[0017] 3. Systematic modeling based on specific structural features ensures that the layer-by-layer modeling method is applicable to various structural types, and that the modeling results are highly consistent with the structural performance. Attached Figure Description

[0018] Figure 1 This is a flowchart illustrating the layup modeling method for composite material layups provided in an embodiment of the present invention.

[0019] Figure 2 This is an exploded view of the overall structure of the impact-resistant sandwich structure applied by the layup modeling method provided in the embodiments of the present invention.

[0020] Figure 3 This is a cross-sectional view of the upper skin of the first impact-resistant sandwich structure provided by the embodiments of the present invention.

[0021] Figure 4 This is a cross-sectional view of the upper skin of the second impact-resistant sandwich structure provided in the embodiments of the present invention.

[0022] Figure 5 This is a cross-sectional view of the upper skin of the third impact-resistant sandwich structure provided in the embodiments of the present invention.

[0023] Figure 6 This is an internal structural diagram of a computer device provided in an embodiment of the present invention.

[0024] In the attached figures, the following labels are used: 1. Upper skin; 11. Carbon fiber reinforced composite material layer; 12. Glass fiber reinforced composite material layer; 2. Lower skin; 3. Intermediate core layer; 4. Flexible toughened adhesive film layer. Detailed Implementation

[0025] Figure 1 This is a schematic flowchart illustrating the layup modeling method for composite material layups provided in an embodiment of the present invention. Figure 1 As shown, the layup modeling method for composite material layups provided in this embodiment of the invention includes: Step S1: Perform feature analysis on the structural characteristics of the composite material layup, and divide the composite material layup into multiple layup partitions based on the feature analysis results; Step S2: Based on the structural characteristics of each ply partition, formulate the ply strategy corresponding to the ply partition; Step S3: Based on the structural stability and process constraints of the composite material layup, set the layup stacking order of the layup partitions to form a global layup sequence; Step S4: Map the global layup sequence onto the three-dimensional geometric surface of the composite material layup to form the spatial distribution and boundaries of each layup partition; Step S5: Based on the layup strategy corresponding to each layup partition, the global layup sequence, and the spatial distribution and boundaries of each layup partition, establish the target model of composite material layup.

[0026] Specifically, in step S1, feature analysis is performed based on the structural characteristics of the composite material layup, and the layup is divided into multiple partitions to ensure the design of each layup partition is targeted. The structural characteristics are transformed into a rule system for modeling, which can avoid the randomness caused by traditional experience dependence.

[0027] In step S2, based on the design basis of each ply partition divided in step S1, a differentiated ply strategy is formulated according to the specific characteristics of each partition.

[0028] In step S3, the layering sequence is optimized by combining structural stability requirements and process constraints to ensure that the layup scheme is strictly matched with mechanical properties and process requirements.

[0029] In step S4, the global layup sequence is mapped onto the three-dimensional geometric surface to clarify the spatial distribution and boundary relationships of each partition, thereby realizing the transformation from abstract strategy to solid model.

[0030] In step S5, the partitioning strategy, global sequence, and spatial mapping results are integrated to construct a complete layup model, ensuring the consistency between design parameters and structural performance.

[0031] Thus, the layup modeling method provided by the embodiments of the present invention performs feature analysis on the structural features of composite material layups, divides the composite material layups into multiple layup partitions based on the feature analysis results, and formulates layup strategies corresponding to each layup partition based on the structural features of each layup partition, directly transforming the geometric and mechanical features of the composite structure into a rule system for layup modeling.

[0032] The layup modeling method provided in this invention establishes a target model of composite material layups based on the layup strategy corresponding to each layup partition, the global layup sequence, and the spatial distribution and boundaries of each layup partition. It establishes a systematic process from structural partitioning, layup strategy, sequence generation to boundary mapping.

[0033] The layup modeling method provided by the embodiments of the present invention can be systematically modeled according to specific structural features, ensuring that the layup modeling method is applicable to a variety of structural types and that the modeling results are highly consistent with the structural performance.

[0034] In some embodiments, step S1 includes: Step S11: Perform feature analysis on the structural characteristics of the composite material layup, and divide the composite material layup into multiple layup zones according to the structural stress path and geometry.

[0035] Specifically, based on the geometry and stress path of the structure, the mechanical requirements and geometric constraints of each region are clarified, the composite material layup is divided into multiple layup partitions, ensuring the design basis of each layup partition, and the structural features are transformed into a rule system for modeling, which can avoid the randomness caused by traditional experience dependence.

[0036] In some embodiments, step S11 includes: Step S111: Obtain the geometric and design parameters of the composite structure with composite material layups; Step S112: Perform feature identification on the composite structure geometry and design parameters of the composite ply to determine the geometric configuration, functional area division, and load transfer path of the composite ply; Step S113: Analyze the differences in characteristics of each region of the composite material layup based on the geometric configuration, functional area division, and load transfer path of the composite material layup, and divide the composite material layup into multiple layup zones.

[0037] Specifically, when classifying the structural characteristics of composite material layups, the basic data is first obtained by inputting the geometric and design parameters of the composite structure. Then, the geometric configuration, functional area division, and load transfer path are analyzed through feature recognition. Finally, based on the differences in geometric shape and mechanical requirements, the layup is divided into multiple zones, and the boundary of each zone is determined by the significant changes in its geometric characteristics and load transfer behavior.

[0038] In some embodiments, step S112 includes: Feature identification is performed on the composite structure geometry and design parameters of composite plies to determine the geometric changes in the surface, corners, and thickness of the composite plies. Based on the geometric changes and divisions of the composite material layup, the composite material layup is divided into a panel area, a core area, and a reinforcement area, and a load transfer path is determined between the panel area, the core area, and the reinforcement area.

[0039] Specifically, curved areas need to have their curvature radius variation range marked, corner locations need to have their angle abrupt changes and fillet radii identified, and thickness variation areas need to have their gradient range and transition morphology marked. Unlike traditional methods that rely solely on the overall geometric contour, this process precisely defines geometrically sensitive areas through feature quantification (such as curvature thresholds and thickness abrupt change rates), such as thickness jumps at the interface between the face and core materials of a honeycomb sandwich panel, and curved fiber turning areas with varying angles.

[0040] Specifically, functional zones are divided based on geometric features and mechanical requirements. Among them, the panel area can correspond to high-rigidity load-bearing areas (such as the surface of a honeycomb structure), the core material area can correspond to lightweight support areas (such as honeycomb sandwich), and the reinforcement area can correspond to local high-stress areas (such as joints or corners).

[0041] In some implementations, step S2 includes: Step S21: Based on the structural characteristics of the ply partition, determine the ply angle of the ply partition, and set the number of ply layers and the thickness of each ply in the ply partition; Step S22: Design the ply configuration according to the ply partition. The ply configuration design includes considering whether symmetrical ply design, gradient ply design or local reinforcement design is required.

[0042] Specifically, a differentiated design strategy is used to achieve a precise match between ply parameters and structural characteristics. First, the ply angle is determined based on the functional requirements of each zone, such as 0° or 90° ply in the main load direction and ±45° ply combinations for shear resistance. At the same time, the number of layers and the thickness of a single layer are adjusted in combination with stress distribution. For example, multiple thin ply layers are used in high-stress areas to refine the load transfer gradient.

[0043] In ply configuration design, symmetrical ply is used to balance thermal stress and process deformation, gradient ply is suitable for geometric transition zones with continuously changing thickness or angle, and local reinforcement design is based on stress concentration areas.

[0044] In some embodiments, step S21 includes: Step S211: Obtain a parameterized table containing ply angle, thickness, and number of layers; Step S212: Based on the structural characteristics of the ply partition, determine the ply angle of the ply partition by querying the parameterized table, and set the number of ply layers and the thickness of each ply in the ply partition.

[0045] The parameterized table enables rapid matching and standardized definition of ply parameters. First, a parameterized table of ply angle, number of layers, and thickness is pre-established based on structural characteristics (such as functional area load requirements and geometric complexity). By querying the table, the partition characteristics are mapped to parameter rules to determine specific values. Through the strong correlation between characteristic parameters and ply rules, the systematic nature of parameter selection is ensured, and the reusability of multiple structural schemes is improved.

[0046] In some embodiments, when the composite material layup includes a honeycomb sandwich panel structure, step S1 above includes: Step S12: Divide the honeycomb sandwich panel structure into panel layup zones and core material layup zones.

[0047] Step S2 above includes: Step S23: Determine the fiber orientation and the number of layers of the panel ply based on the panel ply zoning; Step S24: Based on the core material layup partitions, establish the modeling connection relationship with the panel layup partitions.

[0048] Specifically, a functional zoning adaptation layering strategy is used to achieve adaptive modeling of the honeycomb sandwich panel structure. Based on the panel layering zoning and its functional positioning as the main load-bearing surface, a layering strategy for fiber direction and panel layer number is formulated to balance in-plane stiffness and buckling resistance.

[0049] The core material layup partitioning is based on its shear support and lightweight requirements. It adopts honeycomb core contour modeling, does not directly set fiber layup, but needs to define the connection parameters with the panel. The continuity of stress transfer at the core-panel interface is ensured through symmetrical layup constraints.

[0050] In some embodiments, when the composite material layup includes a variable angle layup, step S3 above includes: Step S31: Based on the structural stability and process constraints of the variable angle ply, set the load direction variation function for the variable angle ply; Step S32: Based on the load direction change function, determine the ply stacking order of the ply partition by means of angle gradual change, and generate a global ply sequence according to the ply stacking order.

[0051] Specifically, based on the geometric characteristics and stress properties of variable-angle layups, a load direction variation function or nonlinear function is defined. This function maps spatial positions to fiber angles, ensuring precise matching between the layup direction and the local load path. Subsequently, based on the discrete angle sequence generated by the function, the layup stacking order is adjusted in conjunction with process constraints to form a global gradient sequence, maintaining structural stability while meeting layup process requirements.

[0052] The layup modeling method provided by this invention can be used for the shock-resistant sandwich structure of ships.

[0053] Figure 2 This is an exploded view of the overall structure of the impact-resistant sandwich structure applied by the layup modeling method of this invention. (See diagram below.) Figure 2 As shown, the impact-resistant sandwich structure includes an upper skin 1, a lower skin 2, and an intermediate core layer 3. The intermediate core layer 3 is disposed between the upper skin 1 and the lower skin 2. The upper skin 1 and the intermediate core layer 3, as well as the lower skin 2 and the intermediate core layer 3, are bonded together by a flexible toughening adhesive film layer 4, so that the sandwich structure consists of, from top to bottom, the upper skin 1, the flexible toughening adhesive film layer 4, the intermediate core layer 3, the flexible toughening adhesive film layer 4, and the lower skin 2. Figure 3 , Figure 4 , Figure 5This is a cross-sectional schematic diagram of the upper skin 1 used in the layup modeling method of this invention. In step S1 above, based on the feature analysis results, the composite material layup can be divided into five layup zones corresponding to the upper skin 1, the flexible toughened adhesive film layer 4, the intermediate core layer 3, the flexible toughened adhesive film layer 4, and the lower skin 2.

[0054] In step S2 above, a layup strategy corresponding to the layup partition is formulated based on the structural characteristics of the upper skin 1, the flexible toughened adhesive film layer 4, the intermediate core layer 3, the flexible toughened adhesive film layer 4 and the lower skin 2.

[0055] In step S3 above, based on the structural stability and process constraints of the composite material layup, the layup sequence is set from top to bottom as follows: upper skin 1, flexible toughened adhesive film layer 4, intermediate core layer 3, flexible toughened adhesive film layer 4 and lower skin 2, forming a global layup sequence.

[0056] In step S4 above, the global layup sequence is mapped onto a three-dimensional geometric surface to form the spatial distribution and boundaries of each layup partition.

[0057] In step S5 above, the modeling output yields a ply distribution map / ply table / 3D ply.

[0058] Both the upper skin 1 and the lower skin 2 are composite panels consisting of alternating layers of carbon fiber reinforced composite material 11 and glass fiber reinforced composite material 12. The middle core layer 3 is an aramid paper honeycomb core material, which is lightweight, has high specific strength and good energy absorption characteristics. The thickness and cell size of the honeycomb core material can be designed and selected according to specific load-bearing and impact resistance requirements.

[0059] The flexible toughened adhesive film layer 4 is an adhesive film with epoxy resin as the matrix and containing toughening particles (such as rubber particles and thermoplastic microparticles). It has excellent toughness, high peel strength and elongation at break. As an adhesive layer, the adhesive film firmly bonds the upper skin 1, the lower skin 2 and the middle core layer 3. When subjected to impact, it can dissipate energy through its own deformation, significantly reducing the stress peak at the interface between the rigid panel and the honeycomb core material and preventing debonding.

[0060] In the composite laminate, the carbon fiber reinforced composite material layer 11 and the glass fiber reinforced composite material layer 12 are laid alternately in an asymmetrical manner. The glass fiber reinforced composite material layer 12 is located on the outer surface of the composite laminate. This arrangement enables the glass fiber reinforced composite material layer 12 to provide good impact resistance, corrosion resistance and functional interface (such as wave transmission) for the outer layer, while the glass fiber reinforced composite material layer 12 of the inner or intermediate layer provides core stiffness and strength.

[0061] In step S2 above, the intermediate core layer 3 is an aramid paper honeycomb core material. Based on the structural characteristics of the corresponding layup zones of the intermediate core layer 3, a layup strategy is formulated, requiring the honeycomb sandwich panel structure to be divided into a face panel layup zone and a core material layup zone. Specifically, based on the face panel layup zone and its functional positioning as the main load-bearing surface, a fiber orientation and the number of face panel layers are determined to balance in-plane stiffness and buckling resistance. The core material layup zone, based on its shear support and lightweight requirements, uses a honeycomb core contour model. While fiber layups are not directly set, connection parameters with the face panel must be defined, and symmetrical layup constraints ensure the continuity of stress transfer at the core-panel interface.

[0062] In step S3 above, both the upper skin 1 and the lower skin 2 are composite panels composed of alternating layers of carbon fiber reinforced composite material 11 and glass fiber reinforced composite material 12. It is necessary to set the load direction variation function of the variable angle ply based on the structural stability and process constraints of the variable angle ply. Based on the load direction variation function, the ply stacking order of the ply partition is determined by the angle gradient method, and a global ply sequence is generated according to the ply stacking order.

[0063] In one embodiment, a computer device is provided, which may be a server, and its internal structure diagram may be as follows: Figure 6 As shown, the computer device includes a processor, memory, network interface, and database connected via a system bus. The processor provides computational and control capabilities. The memory includes non-volatile storage media and internal memory. The non-volatile storage media stores the operating system, computer programs, and database. The internal memory provides an environment for the operation of the operating system and computer programs in the non-volatile storage media. The database stores plywood modeling data for composite material plywoods. The network interface allows communication with external terminals via a network connection. When executed by the processor, the computer program implements a plywood modeling method for composite material plywoods.

[0064] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from its spirit or essential characteristics. Therefore, the embodiments should be considered in all respects as exemplary and non-limiting, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within the present invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0065] Those skilled in the art will recognize that the units and algorithm steps of the various examples described in conjunction with the embodiments disclosed herein can be implemented in electronic hardware, or a combination of computer software and electronic hardware. Whether these functions are implemented in hardware or software depends on the specific application and design constraints of the technical solution. Those skilled in the art can use different methods to implement the described functions for each specific application, but such implementation should not be considered beyond the scope of this application.

[0066] In the description of this invention, unless otherwise stated, "a plurality of" means two or more; the terms "upper," "lower," "left," "right," "inner," "outer," "front end," "rear end," "head," "tail," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. Furthermore, the terms "first," "second," "third," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0067] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "connected" and "linked" should be interpreted broadly. For example, they can refer to fixed connections or detachable connections; mechanical connections or electrical connections; direct connections or indirect connections through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

Claims

1. A method for modeling the layup of composite material layers, characterized in that, The method includes: The structural features of the composite material layup are analyzed, and based on the analysis results, the composite material layup is divided into multiple layup zones. Based on the structural characteristics of each ply partition, formulate the ply strategy corresponding to each ply partition; Based on the structural stability and process constraints of the composite material layup, the layup stacking order of the layup partitions is set to form a global layup sequence; The global layup sequence is mapped onto the three-dimensional geometric surface of the composite material layup to form the spatial distribution and boundary of each layup partition; Based on the layup strategy corresponding to each layup partition, the global layup sequence, and the spatial distribution and boundaries of each layup partition, a target model for the composite material layup is established.

2. The layup modeling method for composite material layups according to claim 1, characterized in that, The structural features of the composite material layup are analyzed, and based on the analysis results, the composite material layup is divided into multiple layup partitions, including: The structural features of the composite material layup are analyzed, and the composite material layup is divided into multiple layup partitions according to the structural stress path and geometry.

3. The layup modeling method for composite material layers according to claim 2, characterized in that, The structural characteristics of the composite material layup are analyzed, and the composite material layup is divided into multiple layup partitions according to the structural stress path and geometry, including: Obtain the composite structure geometry and design parameters of the composite material layup; The composite structure geometry and design parameters of the composite material layup are characterized to determine the geometric configuration, functional area division and load transfer path of the composite material layup. Based on the geometric configuration, functional zone division, and load transfer path of the composite material layup, the differences in the characteristics of each region of the composite material layup are analyzed, and the composite material layup is divided into multiple layup zones.

4. The layup modeling method for composite material layups according to claim 3, characterized in that, The process of identifying the features of the composite structure geometry and design parameters of the composite material layup to determine the geometric configuration, functional area division, and load transfer path of the composite material layup includes: Feature identification is performed on the composite structure geometry and design parameters of the composite material layup to determine the geometric changes in the surface, corners, and thickness of the composite material layup; Based on the geometric changes and divisions of the composite material layup, the composite material layup is divided into a panel area, a core area, and a reinforcement area, and a load transfer path is determined between the panel area, the core area, and the reinforcement area.

5. The layup modeling method for composite material layers according to claim 1, characterized in that, The step of formulating a ply strategy for each ply partition based on its structural characteristics includes: Based on the structural characteristics of the ply partition, the ply angle of the ply partition is determined, and the number of ply layers and the thickness of each ply are set for the ply partition. The ply configuration is designed based on the ply of the ply partition, and the ply configuration design includes considering whether symmetrical ply design, gradient ply design or local reinforcement design is required.

6. The layup modeling method for composite material layups according to claim 5, characterized in that, The step of determining the ply angle of the ply partition based on its structural characteristics, and setting the number of ply layers and the thickness of each ply layer in the ply partition, includes: Obtain a parameterized table containing ply angle, thickness, and number of layers; Based on the structural characteristics of the ply partition, the ply angle of the ply partition is determined by querying the parameterized table, and the number of ply layers and the thickness of each ply are set for the ply partition.

7. The layup modeling method for composite material layers according to claim 1, characterized in that, When the composite material layup includes a honeycomb sandwich panel structure, the structural features of the composite material layup are analyzed, and based on the analysis results, the composite material layup is divided into multiple layup partitions, including: The honeycomb sandwich panel structure is divided into a panel layup zone and a core material layup zone; The step of formulating a ply strategy for each ply partition based on its structural characteristics includes: Based on the panel layup partitioning, determine the fiber orientation and the number of panel layup layers; Based on the core material layup partitions, the modeling connection relationships of each panel layup partition are defined.

8. The layup modeling method for composite material layups according to claim 1, characterized in that, When the composite material layup includes variable-angle layups, the step of setting the layup stacking order of the layup partitions to form a global layup sequence based on the structural stability and process constraints of the composite material layup includes: Based on the structural stability and process constraints of the variable angle ply, the load direction variation function of the variable angle ply is set; Based on the load direction change function, the ply stacking order of the ply partition is determined by the angle gradual change method, and a global ply sequence is generated according to the ply stacking order.

9. An impact-resistant sandwich structure, characterized in that, The layup modeling method for composite material layup according to any one of claims 1 to 8, wherein the impact-resistant sandwich structure includes an upper skin (1), a lower skin (2) and an intermediate core layer (3), wherein the upper skin (1) and the lower skin (2) are both composite plates formed by alternating layup of carbon fiber reinforced composite material layer (11) and glass fiber reinforced composite material layer (12), the intermediate core layer (3) is a honeycomb structure, the intermediate core layer (3) is disposed between the upper skin (1) and the lower skin (2), and the upper skin (1) and the intermediate core layer (3) and the lower skin (2) and the intermediate core layer (3) are bonded together by a flexible toughening adhesive film layer (4).

10. A computer device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that, When the processor executes the computer program, it implements the steps of the method according to any one of claims 1 to 8.

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