Equivalent modeling method for foam core composite material structure and related device

Abstract

The invention belongs to an equivalent modeling method, and provides a foam core material composite material structure equivalent modeling method and a related device aiming at the technical problems that according to an existing foam sandwich composite material structure design method, time and labor are consumed in the calculation iteration process, and especially for a geometrically irregular special-shaped structure, related research is lacked. The method comprises the following steps: according to an enveloping appearance curved surface, endowing a fiber composite material with layer attributes and thickness, firstly, carrying out preliminary proofing design according to the enveloping appearance curved surface, selecting an appearance curved surface of a foam core material in a modeling process, endowing the foam core material with the attributes with equivalent thickness, and carrying out modeling; then, the optimized fiber composite material laying layer and foam core material attribute design result is determined through iterative optimization, under the condition that the design requirement is met through optimization, the fiber composite material is endowed with a face body attribute, the foam core material is endowed with an entity attribute, and the attributes of the fiber composite material and the foam core material are confirmed through strength checking; and an equivalent modeling result is ensured to meet a final requirement.

Description

Technical Field

[0001] The present application relates to an equivalent modeling method, and specifically to an equivalent modeling method for a foam core composite material structure and a related device. Background Art

[0002] Foam sandwich composite structures are widely used in the field of UAV equipment due to their advantages such as high specific strength, high specific stiffness and low manufacturing cost, especially in UAV wings, tail wings and control surface structures.

[0003] For the design of foam sandwich composite material structure, finite element modeling is performed using face + solid unit under the premise of preliminary definition of load conditions and structural dimensions, and the safety margin of the structure can be obtained through strength verification. However, when the overall structural dimensions of the aircraft have not been defined and the load conditions are not clear, the finite element modeling of the entire aircraft is performed on the UAV, and the overall structural dimensions are defined through iterative calculation of inertial load balance. Then, the finite element modeling of foam sandwich wing / tail / rudder and other structures is performed using the face + solid unit method. The calculation iteration process is very time-consuming and laborious, especially when there are hundreds or even thousands of operating conditions for the entire UAV, it is almost difficult to quickly perform a preliminary definition of the structural cross-sectional dimensions. In addition, for geometrically regular foam sandwich structures, some engineers use sandwich equivalent theory for modeling and calculation, but for geometrically irregular structures, especially special-shaped structures such as wings, tails and rudders, few people have conducted similar research. Summary of the invention

[0004] This application aims at the existing foam sandwich composite material structure design method, the calculation iteration process is time-consuming and labor-intensive, especially for irregular geometric shaped structures, and the lack of relevant research technical problems, and provides a foam core composite material structure equivalent modeling method and related devices.

[0005] In order to achieve the above objectives, this application adopts the following technical solutions: In a first aspect, the present application proposes an equivalent modeling method for a foam core composite material structure, wherein the foam core composite material structure comprises at least two layers of fiber composite materials and a foam core material located between the fiber composite materials; the equivalent modeling method comprises: Extract the envelope shape surface of the foam core composite structure; According to the envelope shape surface, assigning fiber composite material ply properties and thickness; Select the outer surface of the foam core material and assign properties to the foam core material with equivalent thickness; Divide the finite element mesh according to the envelope shape surface to obtain multiple shell elements, assign shell element properties, apply load conditions, and perform corresponding calculations; Compare the calculation results with the design requirements. If the difference meets the preset requirements, complete the fiber composite material ply and foam core material property design. Otherwise, reassign the fiber composite material ply properties and thickness and perform iterative optimization until the difference meets the preset requirements. According to the design results of fiber composite material plies and foam core material properties, the fiber composite material is assigned surface properties, and the foam core material is assigned solid properties. Strength verification is used to confirm whether the properties of the fiber composite material and the foam core material meet the preset requirements.

[0006] Further, the method of imparting properties to the foam core material with equivalent thickness comprises: The properties of the foam core are assigned to the shell element constitutive model.

[0007] Furthermore, the equivalent thickness includes: Half of the maximum thickness of the outer surface of the foam core material or the weighted average thickness or any value within the selected range.

[0008] Furthermore, the step of imparting entity properties to the foam core material comprises: The foam core material entity properties are assigned to the entity model.

[0009] Furthermore, the strength check includes: Check static strength and dynamic strength; the static strength includes stress, strain, deformation and buckling, and the dynamic strength includes mode and frequency.

[0010] Furthermore, the reassigning of the fiber composite material ply properties and thickness and performing iterative optimization includes: Adjust fiber composite ply properties and thickness in order of priority of ply thickness, ply angle, and ply density.

[0011] In a second aspect, the present application proposes an equivalent modeling system for a foam core composite material structure, wherein the foam core composite material structure comprises at least two layers of fiber composite materials and a foam core material located between the fiber composite materials; the equivalent modeling system comprises: Extraction module, used to extract the envelope shape surface of the foam core composite material structure; A first definition module is used to assign fiber composite material ply properties and thickness according to the envelope shape surface; The second definition module is used to select the outer surface of the foam core material and assign properties to the foam core material with equivalent thickness; The initial verification module is used to divide the finite element mesh according to the envelope shape surface, obtain multiple shell elements, assign shell element properties, apply load conditions, and perform corresponding calculations; The optimization module is used to compare the calculation results with the design requirements. If the difference meets the preset requirements, the fiber composite material ply and foam core material property design is completed. Otherwise, the fiber composite material ply properties and thickness are reassigned and iterative optimization is performed until the difference meets the preset requirements. The final verification module is used to assign surface properties to the fiber composite material and entity properties to the foam core material according to the design results of the fiber composite material ply and foam core material properties, and to confirm whether the properties of the fiber composite material and foam core material meet the preset requirements through strength verification.

[0012] Further, the imparting of properties to the foam core material by equivalent thickness includes: imparting properties to the foam core material as a shell element constitutive model; The equivalent thickness includes: half of the maximum thickness of the outer curved surface of the foam core material or the weighted average thickness or any value within the selected range; The step of assigning entity attributes to the foam core material includes: assigning entity attributes to the foam core material as an entity model; The strength check includes: checking static strength and dynamic strength; the static strength includes stress, strain, deformation and buckling, and the dynamic strength includes mode and frequency; The reassigning of the fiber composite material ply properties and thickness and performing iterative optimization includes: adjusting the fiber composite material ply properties and thickness according to the priority order of ply thickness, ply angle, and ply density.

[0013] In a third aspect, the present application provides an electronic device, comprising: Memory for storing computer programs; A processor is used to implement the steps of the above-mentioned foam core composite material structure equivalent modeling method when executing the computer program.

[0014] In a fourth aspect, the present application proposes a computer-readable storage medium, in which a computer program is stored. When the computer program is executed by a processor, the steps of the above-mentioned method for equivalent modeling of foam core composite material structure are implemented.

[0015] Compared with the prior art, this application has the following beneficial effects: The present application proposes an equivalent modeling method for a foam core composite material structure, which assigns properties and thickness to the fiber composite material ply according to the envelope shape surface. First, a preliminary proofing design is performed according to the envelope shape surface. During the modeling process, the shape surface of the foam core is selected, and the foam core material properties are assigned with equivalent thickness. Especially for special-shaped solid foam core materials, the equivalent thickness of the two-dimensional surface is used as the thickness-related value of the special-shaped structure, which can quickly perform optimization analysis. Then, the optimized fiber composite material ply and foam core material property design results are determined through iterative optimization. When the optimization meets the design requirements, the fiber composite material is assigned with surface properties, and the foam core is assigned with entity properties. The properties of the fiber composite material and the foam core are confirmed through strength verification to ensure that the equivalent modeling results meet the final requirements. The equivalent modeling method of the present application can effectively enhance the engineering analysis means of special-shaped components and greatly improve the efficiency of defining the structural section size.

[0016] The present application also proposes a foam core composite material structure equivalent modeling system, an electronic device and a computer storage medium, which have all the advantages of the above-mentioned foam core composite material structure equivalent modeling method. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. It should be understood that the following drawings only show certain embodiments of the present application and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related drawings can be obtained based on these drawings without creative work.

[0018] Figure 1 This is a first schematic flow chart of a method for equivalent modeling of a foam core composite material structure of the present application; Figure 2 This is a second schematic flow chart of a method for equivalent modeling of a foam core composite material structure of the present application; Figure 3 A schematic diagram of an equivalent modeling system for a foam core composite material structure of the present application. DETAILED DESCRIPTION

[0019] In order to make the purpose, technical solution and advantages of the embodiments of the present application clearer, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, rather than all the embodiments. The components of the embodiments of the present application described and shown in the drawings here can be arranged and designed in various different configurations.

[0020] Therefore, the following detailed description of the embodiments of the present application provided in the accompanying drawings is not intended to limit the scope of the present application for which protection is sought, but merely represents selected embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without creative work are within the scope of protection of the present application.

[0021] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, further definition and explanation thereof is not required in subsequent drawings.

[0022] In the description of the embodiments of the present application, it should be noted that if the terms "upper", "lower", "horizontal", "inner", etc. appear, the orientation or position relationship indicated is based on the orientation or position relationship shown in the drawings, or the orientation or position relationship in which the invented product is usually placed when used. It is only for the convenience of describing the present application and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present application. In addition, the terms "first", "second", etc. are only used to distinguish the description, and cannot be understood as indicating or implying relative importance.

[0023] In addition, if the term "horizontal" appears, it does not mean that the component must be absolutely horizontal, but can be slightly tilted. For example, "horizontal" only means that its direction is more horizontal than "vertical", which does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0024] In the description of the embodiments of the present application, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "set", "install", "connect", and "connect" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal connection of two components. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0025] The foam sandwich composite structure is a layered composite material composed of a panel (skin) and a lightweight foam core. This structure has been widely used in many fields such as aerospace, construction, automobiles, and ships due to its advantages of light weight, high strength, and versatility. In the foam sandwich composite structure, the panel is usually made of fiber-reinforced resin-based composite materials, such as glass fiber or carbon fiber panels. The panel mainly bears bending and in-plane loads and is the main load-bearing component of the structure. As the central component of the "sandwich structure", the foam core has the characteristics of low density, light weight, good thermal insulation, and good sound absorption. Commonly used foam core materials include PVC foam, polyurethane foam, PET foam, etc. In addition, the panel and foam core can usually be obtained by laying. Lamination usually involves thickness and angle. Lamination thickness refers to the thickness of the panel material. It is a key parameter in the design of foam sandwich composite structures. The selection of lamination thickness usually takes into account multiple factors, including the load-bearing capacity, weight requirements, and cost budget of the structure. Generally speaking, the greater the thickness of the layer, the stronger the load-bearing capacity of the structure, because thicker panels can more effectively disperse and resist external loads, thereby improving the overall strength and stiffness of the structure. In practical applications, the selection of ply thickness often requires comprehensive consideration and weighing based on specific design requirements and working conditions. For example, in the field of aerospace, due to the extremely high requirements for weight and strength, the ply thickness of foam sandwich composite materials is usually determined through precise calculation and optimization. The ply angle refers to the laying direction of the fibers in the panel material. Different ply angles can adapt to different stress conditions and improve the bearing capacity and damage resistance of the structure. For example, the fiber direction of the 0° ply is consistent with the main force direction of the structure, and it mainly bears axial loads. In structures that need to bear large axial loads, the proportion of 0° plies can be appropriately increased to improve the bearing capacity of the structure. For another example, the fiber direction of the 90° ply is perpendicular to the main force direction of the structure, and is mainly used to balance the in-plane stress and prevent the structure from warping. In structures that need to maintain the plane stability of the structure, the proportion of 90° plies can be appropriately increased.

[0026] For geometrically regular foam sandwich structures, engineers can use the sandwich equivalent theory for modeling and calculation. However, for some special-shaped structures, the sandwich equivalent theory will have some problems: In geometrically irregular structures, the applicability of sandwich core equivalent theory may be limited due to factors such as complex shapes and uneven stress distribution. Special-shaped structures such as wings, tail planes and rudders have complex geometric shapes and stress distributions, and more geometric parameters and stress states need to be considered to ensure the accuracy and reliability of the model. Therefore, more advanced calculation methods may be required, which are more complex and difficult to calculate.

[0027] Based on the above situation, the present application proposes a foam core composite material structure equivalent modeling method and related devices, and the present application is described in detail below in conjunction with embodiments and drawings.

[0028] For the convenience of the following description, the foam core composite material structure includes at least two layers of fiber composite materials and a foam core material located between the fiber composite materials.

[0029] like Figure 1 As shown, it is a first flow chart of a method for equivalent modeling of a foam core composite material structure of the present application, which may include: S101, extracting the envelope shape surface of the foam core composite material structure.

[0030] It should be noted that in the foam core composite material structure, the envelope shape surface represents the external shape of the entire structure and is the basis for subsequent design steps. In practical applications, 3D modeling software can be used to obtain the envelope shape surface, select the external boundary of the structure and generate a smooth surface to represent its shape.

[0031] S102, assigning fiber composite material ply properties and thickness according to the envelope shape surface.

[0032] It should be noted that the ply properties and thickness of the fiber composite material can be defined on the extracted envelope shape surface, including the selection of appropriate fiber type, ply direction, number of layers, thickness of each layer, etc., which can be defined accordingly according to design requirements.

[0033] S103, selecting an outer curved surface of the foam core material, and assigning properties to the foam core material with an equivalent thickness.

[0034] It should be noted that the properties of the foam core material may include density, elastic modulus, shear modulus, etc.

[0035] S104, dividing the finite element mesh according to the envelope shape surface to obtain a plurality of shell elements, assigning attributes to the shell elements, applying load conditions, and performing corresponding calculations.

[0036] It should be noted that finite element analysis software can be used here to divide the mesh on the envelope surface, generate multiple shell elements, and assign appropriate properties to each shell element, such as material type, thickness, etc. Then apply load conditions, such as pressure, temperature, etc., and perform calculations to analyze the response of the structure.

[0037] S105, comparing the calculation results with the design requirements, if the difference meets the preset requirements, the fiber composite material ply and foam core material property design is completed, otherwise, the fiber composite material ply properties and thickness are reassigned, and iterative optimization is performed until the difference meets the preset requirements.

[0038] S106, according to the design results of the fiber composite material ply and the foam core material properties, the fiber composite material is assigned surface properties, and the foam core material is assigned entity properties, and strength verification is performed to confirm whether the properties of the fiber composite material and the foam core material meet the preset requirements.

[0039] In practical applications, according to the final design results, the fiber composite material can be given surface properties, and the foam core material can be given solid properties, and then the strength check can be carried out to ensure that the selected material properties and thickness can meet the strength and stability requirements of the structure. If the requirements are not met, corresponding adjustments can be made according to the strength check results.

[0040] like Figure 2 As shown, it is a second flow chart of a method for equivalent modeling of a foam core composite material structure of the present application, which may include: S201, extracting the envelope outer surface of the foam sandwich composite material structure, that is, extracting the outer surface of the foam sandwich composite material structure.

[0041] S202, assigning material properties and thicknesses to different fiber composite material plies based on the envelope shape surface.

[0042] S203, for the foam sandwich layer, select the outer surface, assign the foam core material properties with equivalent thickness, the assigned foam core material properties are shell unit constitutive model, and the assigned equivalent thickness of the foam core material is half of the maximum thickness or the equal weighted average thickness or a value within the selected range.

[0043] It should be noted that the constitutive model of the shell element is a mathematical model that describes the relationship between stress and strain of the shell element under load. The shell element is usually used to simulate the situation where the scale (thickness) in one direction of the structure is much smaller than the scale in other directions, and the stress along the thickness direction is ignored. Shell elements can be used to analyze two-dimensional mesh types of thin-walled structures, such as plates and shells. The reference surface is discretized by defining the plane size, surface normal and initial curvature of the unit, and the deformation in the thickness direction is usually ignored, thereby simplifying the model establishment and solution process.

[0044] S204, dividing the finite element mesh for the envelope shape surface, assigning shell unit attributes, applying load conditions, and performing calculation processing.

[0045] S205, iteratively optimize the properties of the fiber composite ply and the foam core material according to the calculation results and the design requirements.

[0046] S206, based on the optimization results, perform surface + solid modeling analysis on the foam sandwich composite material structure, assign surface properties to the fiber composite material, assign solid properties to the foam core material, and finally confirm the properties of the fiber composite material and the foam core material through strength verification. Among them, the properties assigned to the foam core material are solid models.

[0047] It should be noted that the solid model can be an isotropic model, which is a representation of the actual object and is used to analyze and predict the behavior of the object. In the modeling process, the geometry, size and layout of the foam core can be accurately represented. The interaction between the foam core and the surrounding structure can also be considered. In practical applications, in the solid model, the physical and mechanical properties of the foam core, such as density, elastic modulus, Poisson's ratio, thermal conductivity, etc., can be accurately assigned to the model. After the attributes are assigned, the model can more accurately reflect the behavior and performance of the actual foam core.

[0048] This application targets special-shaped entities, and the foam core material can use two-dimensional surface shell elements for equivalent modeling analysis, which greatly improves the iterative optimization efficiency. The effect is outstanding for special-shaped structures. For example, it can be applied to the fields of special-shaped wings, horizontal tails, vertical tails and other components of drones, and can also be used in the analysis of other special-shaped foam sandwich composite mechanical structures. Through the equivalent modeling method of this application, the engineering analysis methods of such special-shaped components can be effectively enhanced, and the efficiency of defining the structural section size can be greatly improved.

[0049] The following is an example of an equivalent modeling method for a foam core composite structure using this application: (1) Extract the envelope shape surface of the UAV horizontal tail (length 1800mm × width 240mm) foam sandwich composite material structure; (2) Based on the curved surface, give 10 layers of carbon fiber composite fabric (0.21 mm / layer) ±45°; (3) For the foam core layer, select the outer surface with an equivalent thickness of half the maximum thickness of the foam core, 26 mm; (4) Divide the finite element mesh (8000 quadrilateral shell elements) for the envelope surface, assign shell element properties, apply load conditions, and perform calculations; (5) Based on the calculation results and design requirements, optimize the selection of foam core material PMI 50 specifications; (6) According to the optimization results, for the foam sandwich composite structure, the fiber composite material is given face properties (8000 quadrilateral shell elements), and the foam core material is given solid properties (2000000 tetrahedral elements). The properties of the fiber composite material and the foam core material are finally confirmed through strength verification.

[0050] When the overall structural dimensions of the aircraft are not yet defined and the load conditions are not clear, the finite element modeling of the entire aircraft is carried out, and the finite element modeling of the foam sandwich wing / tail / rudder and other structures is carried out using the surface + solid unit method. The calculation iteration process is very time-consuming and laborious. The equivalent modeling method of this application can solve this problem, greatly shorten the finite element calculation and analysis time of the entire aircraft, and quickly perform the preliminary definition of the structural section dimensions.

[0051] Based on the above-mentioned equivalent modeling method of foam core composite material structure, such as Figure 3 As shown, the present application also proposes a foam core composite material structure equivalent modeling system, which may include: Extraction module, used to extract the envelope shape surface of the foam core composite material structure; A first definition module is used to assign fiber composite material ply properties and thickness according to the envelope shape surface; The second definition module is used to select the outer surface of the foam core material and assign properties to the foam core material with equivalent thickness; The initial verification module is used to divide the finite element mesh according to the envelope shape surface, obtain multiple shell elements, assign shell element properties, apply load conditions, and perform corresponding calculations; The optimization module is used to compare the calculation results with the design requirements. If the difference meets the preset requirements, the fiber composite material ply and foam core material property design is completed. Otherwise, the fiber composite material ply properties and thickness are reassigned and iterative optimization is performed until the difference meets the preset requirements. The final verification module is used to assign surface properties to the fiber composite material and entity properties to the foam core material according to the design results of the fiber composite material ply and foam core material properties, and to confirm whether the properties of the fiber composite material and foam core material meet the preset requirements through strength verification.

[0052] It should be noted that in the several embodiments provided in the present application, it should be understood that the disclosed devices and methods can be implemented in other ways. For example, the device embodiments described above are only schematic. For example, the division of each module is only a logical function division. There may be other division methods in actual implementation. For example, multiple modules can be combined or integrated into another device, or some features can be ignored or not executed. The module described as a separate component may or may not be physically separated. The component displayed as a module may be a physical unit or multiple physical units, that is, it may be located in one place, or it may be distributed in multiple different places. Some or all of the modules may be selected according to actual needs to achieve the purpose of the scheme of this embodiment.

[0053] In addition, each module in each embodiment of the present invention may be integrated into a processing unit, each module may exist physically separately, or two or more modules may be integrated into one unit. The above-mentioned integrated unit may be implemented in the form of hardware or in the form of a software functional unit.

[0054] An electronic device provided in an embodiment of the present application includes a memory and a processor. The memory stores a computer program. When the processor executes the computer program, the steps of the method for equivalent modeling of a foam core composite material structure described in any of the above embodiments are implemented.

[0055] Another electronic device provided in the embodiment of the present application may also include: an input port connected to the processor, used to transmit multimodal data collected by an external acquisition device to the processor; and a display unit connected to the processor, used to display the processing results of the processor to the outside world; a communication module connected to the processor, used to realize the communication between the electronic device and the outside world. The display unit can be a display panel, a laser scanning display, etc.; the communication mode adopted by the communication module includes but is not limited to mobile high-definition link technology (HML), universal serial bus (USB), high-definition multimedia interface (HDMI), wireless connection (including wireless fidelity technology (WiFi), Bluetooth communication technology, low-power Bluetooth communication technology, and communication technology based on IEEE802.11s).

[0056] An embodiment of the present application provides a computer-readable storage medium, in which a computer program is stored. When the computer program is executed by a processor, the steps of the method for equivalent modeling of a foam core composite material structure described in any of the above embodiments are implemented.

[0057] The computer-readable storage medium involved in the present application includes random access memory (RAM), internal memory, read-only memory (ROM), electrically programmable ROM, electrically erasable programmable ROM, registers, hard disks, removable disks, CD-ROMs, or any other form of storage medium known in the technical field.

[0058] For the description of the relevant parts of the foam core composite material structure equivalent modeling system, electronic device and computer readable storage medium provided in the embodiment of the present application, please refer to the detailed description of the corresponding parts in the foam core composite material structure equivalent modeling method provided in the embodiment of the present application, which will not be repeated here. In addition, the parts of the above technical solutions provided in the embodiment of the present application that are consistent with the corresponding technical solutions in the prior art are not described in detail to avoid excessive elaboration.

[0059] The above are only preferred embodiments of the present application and are not intended to limit the present application. For those skilled in the art, the present application may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A method for equivalent modeling of a foam core composite material structure, wherein the foam core composite material structure comprises at least two layers of fiber composite materials and a foam core material located between the fiber composite materials; It is characterized in that Equivalent modeling approaches include: Extract the envelope shape surface of the foam core composite structure; According to the envelope shape surface, assigning fiber composite material ply properties and thickness; Select the outer surface of the foam core material and assign properties to the foam core material with equivalent thickness; Divide the finite element mesh according to the envelope shape surface to obtain multiple shell elements, assign shell element properties, apply load conditions, and perform corresponding calculations; Compare the calculation results with the design requirements. If the difference meets the preset requirements, complete the fiber composite material ply and foam core material property design. Otherwise, reassign the fiber composite material ply properties and thickness and perform iterative optimization until the difference meets the preset requirements. According to the design results of fiber composite material ply and foam core material properties, the fiber composite material is assigned surface properties, and the foam core material is assigned solid properties. Strength verification is performed to confirm whether the fiber properties meet the preset requirements.

2. According to the method for equivalent modeling of a foam core composite material structure as claimed in claim 1, It is characterized in that The foam core material is given properties with equivalent thickness, including: The properties of the foam core are assigned to the shell element constitutive model.

3. According to the method for equivalent modeling of a foam core composite material structure as claimed in claim 2, It is characterized in that The equivalent thickness includes: Half of the maximum thickness of the outer surface of the foam core material or the weighted average thickness or any value within the selected range.

4. According to claim 3, a foam core composite material structure equivalent modeling method, It is characterized in that The step of imparting entity properties to the foam core material comprises: The foam core material entity properties are assigned to the entity model.

5. A method for equivalent modeling of a foam core composite material structure according to claim 4, It is characterized in that The strength check includes: Check static strength and dynamic strength; the static strength includes stress, strain, deformation and buckling, and the dynamic strength includes mode and frequency.

6. A method for equivalent modeling of a foam core composite material structure according to claim 5, It is characterized in that The method of re-assigning the fiber composite material ply properties and thickness and performing iterative optimization includes: Adjust fiber composite ply properties and thickness in order of priority of ply thickness, ply angle, and ply density.

7. An equivalent modeling system for a foam core composite material structure, the foam core composite material structure comprising at least two layers of fiber composite material and a foam core material located between the fiber composite materials; It is characterized in that Equivalent modeling systems include: Extraction module, used to extract the envelope shape surface of the foam core composite material structure; A first definition module is used to assign fiber composite material ply properties and thickness according to the envelope shape surface; The second definition module is used to select the outer surface of the foam core material and assign properties to the foam core material with equivalent thickness; The initial verification module is used to divide the finite element mesh according to the envelope shape surface, obtain multiple shell elements, assign shell element properties, apply load conditions, and perform corresponding calculations; The optimization module is used to compare the calculation results with the design requirements. If the difference meets the preset requirements, the fiber composite material ply and foam core material property design is completed. Otherwise, the fiber composite material ply properties and thickness are reassigned and iterative optimization is performed until the difference meets the preset requirements. The final verification module is used to assign surface properties to the fiber composite material and entity properties to the foam core material according to the design results of the fiber composite material ply and foam core material properties, and to confirm whether the properties of the fiber composite material and foam core material meet the preset requirements through strength verification.

8. A foam core composite material structure equivalent modeling system according to claim 7, It is characterized in that The step of assigning properties to the foam core material by using equivalent thickness includes: assigning the properties to the foam core material as a shell element constitutive model; The equivalent thickness includes: half of the maximum thickness of the outer curved surface of the foam core material or the weighted average thickness or any value within the selected range; The step of assigning entity attributes to the foam core material includes: assigning entity attributes to the foam core material as an entity model; The strength check includes: checking static strength and dynamic strength; the static strength includes stress, strain, deformation and buckling, and the dynamic strength includes mode and frequency; The reassigning of the fiber composite material ply properties and thickness and performing iterative optimization includes: adjusting the fiber composite material ply properties and thickness according to the priority order of ply thickness, ply angle, and ply density.

9. An electronic device, It is characterized in that include: Memory for storing computer programs; A processor is used to implement the steps of the method for equivalent modeling of a foam core composite material structure as claimed in any one of claims 1 to 6 when executing the computer program.

10. A computer-readable storage medium, It is characterized in that The computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, the steps of the method for equivalent modeling of a foam core composite material structure according to any one of claims 1 to 6 are implemented.

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