Composite material fatigue performance simulation method, electronic equipment and medium

Abstract

The present application relates to the field of fatigue analysis of composite materials, and specifically, to a composite material fatigue performance simulation method, electronic device and medium. The composite material fatigue performance simulation method includes: obtaining composite material fatigue parameters, cyclically executing the first target operation until the cycle period is greater than a preset value, and outputting the composite material fatigue life and failure mode; the first target operation includes: inputting composite material fatigue parameters, composite material static load parameters and fatigue load into a real-time composite material simulation model; using static analysis to calculate the number of cycles required for crack initiation and crack propagation, respectively, and record crack coordinate data; determining the composite material cycle period according to the number of cycles and the cycle period determined by the previous execution of the first target operation. The present application accurately simulates the initiation and propagation process of fatigue damage cracks in composite laminates, obtains the fatigue life of composite materials, and clarifies the fatigue failure mechanism of composite laminates.

Description

Technical Field

[0001] The present application relates to the field of fatigue analysis of composite materials, and in particular to a composite material fatigue performance simulation method, electronic equipment and medium. Background Art

[0002] Composite materials have the advantages of high specific strength, fatigue resistance, and corrosion resistance, and are widely used in aerospace, energy, and automotive fields. However, there are two material components with different mechanical properties in composite laminates, namely fiber and matrix, which are typical heterogeneous anisotropic materials. At the same time, there are also differences in mechanical properties between different layers. The above structural characteristics make the damage and failure mechanism of composite laminates very complicated, especially for the fatigue damage and failure process. Existing simulation analysis methods are difficult to accurately predict and analyze fatigue life and damage evolution process.

[0003] In view of this, this application is hereby filed. Summary of the invention

[0004] The purpose of this application is to provide a composite material fatigue performance simulation method, electronic equipment and medium to solve the problem that it is difficult to accurately predict and analyze fatigue life and damage evolution process in the prior art.

[0005] In order to achieve the above objectives, this application adopts the following technical solutions:

[0006] In a first aspect, the present application provides a composite material fatigue performance simulation method, comprising:

[0007] Obtain fatigue parameters of the composite material, cyclically execute the first target operation until the cycle period is greater than a preset value, and output the fatigue life and failure mode of the composite material;

[0008] The first target operation includes:

[0009] Inputting the composite material fatigue parameter, composite material static load parameter and fatigue load into a real-time composite material simulation model;

[0010] Using static analysis, the number of cycles required for crack initiation and crack propagation is calculated, and the crack coordinate data is recorded;

[0011] The composite material cycle period is determined according to the cycle number and the cycle period determined by the previous execution of the first target operation.

[0012] In some technical solutions, the static analysis is used to calculate the number of cycles required for crack initiation and crack propagation, and record the crack coordinate data, including:

[0013] Using static analysis to determine the mechanical state of the connecting key in the composite material simulation model; the mechanical state includes strain, stress and energy release rate;

[0014] According to the mechanical state of the connecting key and the fatigue parameters of the composite material, the number of cycles required for crack initiation and crack propagation are calculated respectively, and the crack coordinate data are recorded.

[0015] In some technical solutions, the number of cycles required for crack initiation and crack propagation are calculated according to the mechanical state of the connecting key and the fatigue parameter of the composite material, including:

[0016] Calculating the number of cycles required for crack initiation based on the strain of the connecting key and the fatigue parameter of the composite material;

[0017] The number of cycles required for crack growth is calculated based on the energy release rate of the connecting bond, the distance between material points and the fatigue parameters of the composite material.

[0018] In some technical solutions, determining the cycle period of the composite material according to the number of cycles and the cycle period determined by the previous execution of the first target operation includes:

[0019] Obtaining a damage index, wherein the damage index is used to characterize the relationship between the number of damaged bonds and the total number of bonds at a given material point;

[0020] Determining the damage type according to the damage index; the damage type includes crack initiation damage and crack extension damage;

[0021] The composite material cycle period is determined according to the damage type, the cycle number and the cycle period determined by the previous execution of the first target operation.

[0022] In some technical solutions, determining the cycle period of the composite material according to the damage type, the number of cycles, and the cycle period determined by the previous execution of the first target operation includes:

[0023] Determining a cycle increment based on the type of injury and the number of cycles;

[0024] A composite material cycle period is determined based on the cycle increment and a cycle period determined during a previous execution of the first target operation.

[0025] In some technical solutions, determining the cycle increment according to the damage type and the cycle number includes:

[0026] In the case where the damage type is crack initiation damage, the cycle increment is determined as the minimum value of the number of cycles required for matrix crack initiation, the number of cycles required for fiber crack initiation, and the number of cycles required for delamination crack initiation;

[0027] When the damage type is crack extension damage, the cycle increment is determined as the minimum value of the number of cycles required for matrix crack initiation, the number of cycles required for matrix crack extension, the number of cycles required for fiber crack initiation, the number of cycles required for fiber crack extension, the number of cycles required for delamination crack initiation, and the number of cycles required for delamination extension.

[0028] In some technical solutions, after determining the cycle period of the composite material according to the number of cycles and the cycle period determined by the previous execution of the first target operation, the method further includes:

[0029] According to the damage type, the mechanical state and the damage state of the connecting key in the composite material simulation model are updated.

[0030] In some technical solutions, the fatigue parameter of the composite material is determined in the following manner:

[0031] Determine the composite matrix fatigue parameters based on the SN curve of the composite 90° laminate unidirectional plate fatigue test;

[0032] According to the SN curve of the fatigue test of the composite material 90° laminated unidirectional plate and the stress S m , determine the matrix fatigue life N m ;

[0033] According to the SN curve of the composite material 0° laminated unidirectional plate fatigue test and the matrix fatigue life N m , determine the revised S-(NN m )curve;

[0034] According to the revised S-(NN m ) curve to determine the fatigue parameters of composite fiber.

[0035] In a second aspect, the present application provides an electronic device, including:

[0036] at least one processor, and a memory communicatively coupled to at least one of the processors;

[0037] The memory stores instructions that can be executed by at least one of the processors, and the instructions are executed by at least one of the processors so that at least one of the processors can perform the above method.

[0038] In a third aspect, the present application provides a computer-readable storage medium, on which computer instructions are stored, and the computer instructions are used to enable a computer to execute the above method.

[0039] Compared with the prior art, the beneficial effects of this application are:

[0040] The composite material fatigue performance simulation method provided in the present application executes the first target operation cyclically after obtaining the composite material fatigue parameters until the cycle period is greater than the preset value, and outputs the composite material fatigue life and failure mode, wherein the first target operation includes: inputting the composite material fatigue parameters, composite material static load parameters and fatigue load into the real-time composite material simulation model; using static analysis to calculate the number of cycles required for crack initiation and crack propagation, and record the crack coordinate data; according to the number of cycles and the cycle period determined by the previous execution of the first target operation, determine the composite material cycle period. This method comprehensively considers the initiation and propagation of fatigue cracks in composite materials, accurately simulates the initiation and propagation process of fatigue damage cracks in composite laminates, obtains the fatigue life of composite materials, clarifies the fatigue failure mechanism of composite laminates, and solves the problem of difficulty in accurately predicting and analyzing fatigue life and damage evolution process. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] In order to more clearly illustrate the specific implementation methods of the present application or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0042] Figure 1 It is a schematic diagram of the process of the composite material fatigue performance simulation method provided in this application;

[0043] Figure 2 It is a flow chart of the first target operation in the composite material fatigue performance simulation method provided in the present application;

[0044] Figure 3 It is a schematic diagram of fatigue test of unidirectional panels with 0° and 90° plies;

[0045] Figure 4 is a schematic diagram of connecting bond type I and type II;

[0046] Figure 5 It is a structural schematic diagram of a composite material fatigue performance simulation device provided in the present application;

[0047] Figure 6 It is a structural schematic diagram of the electronic device provided by this application. DETAILED DESCRIPTION

[0048] The following is a description of exemplary embodiments of the present application in conjunction with the accompanying drawings, including various details of the embodiments of the present application to facilitate understanding, which should be considered as merely exemplary. Therefore, it should be recognized by those of ordinary skill in the art that various changes and modifications can be made to the embodiments described herein without departing from the scope and spirit of the present application. Similarly, for the sake of clarity and conciseness, the description of well-known functions and structures is omitted in the following description.

[0049] As mentioned in the background technology, the existing technology has the problem of difficulty in accurately predicting and analyzing fatigue life and damage evolution process. In this regard, the present application is based on composite material fatigue parameters, composite material static load parameters, fatigue load, static analysis, etc., and finally outputs composite material fatigue life and failure mode by cyclically executing the first target operation. The present application is further described in detail below in conjunction with the embodiments.

[0050] The fatigue damage of composite materials defined in this application mainly includes two stages: crack initiation and crack propagation. Since composite materials have two different components, fiber and resin, there are three different types of bonds in the peri-field dynamics model: matrix bonds, fiber bonds and interlayer bonds. In this application, it is considered that the interlayer material of resin-based fiber-reinforced composite materials (such as CFRP, Carbon Fiber Reinforced Polymer, carbon fiber reinforced polymer-based composite materials) is an isotropic matrix material, so the judgment criteria for interlayer bonds are the same as those for matrix bonds. Therefore, the fatigue performance simulation method established in this application mainly considers the initiation and propagation of fatigue cracks of fiber bonds and matrix bonds under fatigue loads.

[0051] Example 1

[0052] Figure 1 It is a flow chart of a composite material fatigue performance simulation method provided in this embodiment. The method can be executed by a composite material fatigue performance simulation device. The device can be composed of software and / or hardware and is generally integrated in an electronic device. The electronic device can be an electronic computer. For ease of understanding, each step in the control method of this embodiment is executed by an electronic computer.

[0053] like Figure 1 As shown, this embodiment provides a composite material fatigue performance simulation method, comprising the following steps:

[0054] S110. Obtain fatigue parameters of the composite material.

[0055] Composite material fatigue parameters refer to parameters related to composite material fatigue damage.

[0056] In an optional embodiment, the fatigue parameter of the composite material is determined in the following manner:

[0057] Determine the composite matrix fatigue parameters based on the SN curve of the composite 90° laminate unidirectional plate fatigue test;

[0058] According to the SN curve of the fatigue test of the composite material 90° laminated unidirectional plate and the stress S m , determine the matrix fatigue life N m ;

[0059] According to the SN curve of the composite material 0° laminated unidirectional plate fatigue test and the matrix fatigue life N m , determine the revised S-(NN m )curve;

[0060] According to the revised S-(NN m ) curve to determine the fatigue parameters of composite fiber.

[0061] Among them, the SN curve is the stress-cycle number curve.

[0062] For example, in a fatigue test, the relationship between the stress on the connecting key and the number of cycles is as follows:

[0063] (1)

[0064] Among them, S ij (N) max is the maximum stress of the bond between material points i and j at the Nth cycle, R is the stress ratio of fatigue loading, Q ij (N) is the stiffness of the bond between material points i and j at the Nth cycle, A and m are fatigue parameters of the composite material, both A and m are greater than zero, and N is the number of cycles. Material points refer to the idealized mass points into which the material is divided according to the peridynamic theory.

[0065] (2), where S ij (N) min is the minimum stress of the bond between material points i and j at the Nth cycle.

[0066] Since the parameters A and m are constants, formula (1) is essentially a function of the maximum stress and the number of cycles. Therefore, for isotropic materials, the parameters A and m can be obtained by fitting the SN curve of the material. Since the composite laminate contains two types of bonds, fiber and matrix. Parameter A f (Fiber fatigue parameter 1) and m f (Fiber fatigue parameter 2) and A m (matrix fatigue parameter) and m m(Matrix fatigue parameters) need to be obtained using the SN curves of the 90° and 0° laminate fatigue tests, respectively, as follows:

[0067] By observation Figure 3 It can be seen that in the fatigue test of the 90° laminated unidirectional plate, both the fiber and the matrix are subjected to the same stress S as the external force S, and the fatigue failure that generally occurs in the 90° unidirectional plate is matrix failure, so it can be roughly considered that the SN curve of the 90° unidirectional plate is the SN curve of the matrix material. m and m m It can be obtained by fitting the SN curve of the 90° laminated unidirectional plate fatigue test.

[0068] By observation Figure 3 In the fatigue test of 0° laminated unidirectional panels, the stresses on the fibers and matrix are:

[0069] , (3)

[0070] Where S f is the fiber stress, S m is the matrix stress, E f is the fiber elastic modulus, E m is the matrix elastic modulus, V f is the fiber volume fraction, V m is the volume fraction of the matrix, and S is the external stress on the composite material in the fatigue test of the 0° laminated unidirectional plate.

[0071] SN curve of 90° one-way plate and stress S on the matrix m , the matrix fatigue life N can be calculated m After the matrix fails, the fiber bears all the external stress S. Therefore, in the unidirectional plate with 0° ply, the fiber experiences two different stress stages during the whole fatigue failure process: Stage 1: , N f1 =N m , Stage 2: S f2 =S,N f2 =NN m Because the stress and cycle number of the fibers in the first stage are low, this stage contributes less to the fatigue failure of the fibers in the 0° laminate, so A f and m f The S-(NN) can be obtained by modifying the SN curve of the 0° one-way plate. m ) curve fitting.

[0072] S120, cyclically executing the first target operation until the cycle period is greater than a preset value, and outputting the fatigue life and failure mode of the composite material.

[0073] Among them, "cycle period" refers to the cycle period of the composite material obtained after executing the first target operation, rather than the number of times the first target operation is executed. "Preset value" is the cycle period used to characterize the failure of the composite material, such as 100,000 times. When the cycle period obtained by simulation is greater than the preset value, it means that the material has been damaged and its fatigue life is the cycle period obtained by the previous first target operation.

[0074] like Figure 2 As shown, the first target operation includes:

[0075] S1211, inputting the composite material fatigue parameter, composite material static load parameter and fatigue load into a real-time composite material simulation model.

[0076] The composite material simulation model in this application is real-time, and "real-time" means that each time the first target operation is performed, the composite material simulation model will be adjusted according to the previous execution result so that all first target operations are continuous. It is understandable that the composite material simulation model when the first target operation is performed for the first time is an initial model, which is related to the initial state of the composite material.

[0077] The static load parameters of composite materials refer to the parameters required for quasi-static performance simulation of composite materials using peri-field dynamics, including elastic modulus, Poisson's ratio, strength, etc.

[0078] S1212. Use static analysis to calculate the number of cycles required for crack initiation and crack propagation, and record the crack coordinate data.

[0079] In an optional implementation, the static analysis is used to calculate the number of cycles required for crack initiation and crack propagation, and record the crack coordinate data, including:

[0080] Using static analysis to determine the mechanical state of the connecting key in the composite material simulation model; the mechanical state includes strain, stress and energy release rate;

[0081] According to the mechanical state of the connecting key and the fatigue parameters of the composite material, the number of cycles required for crack initiation and crack propagation are calculated respectively, and the crack coordinate data are recorded.

[0082] This embodiment simultaneously records crack coordinate data while calculating the number of cycles required for crack initiation and crack propagation, so that the failure mode of the material can be obtained based on the data later. For example, the data can be input into a failure mode analysis model to output a failure model, and the failure mode analysis model can be any one in the art, and this embodiment does not impose any particular limitation on this.

[0083] In an optional implementation, the calculating the number of cycles required for crack initiation and crack propagation respectively according to the mechanical state of the connecting key and the fatigue parameter of the composite material includes:

[0084] Calculating the number of cycles required for crack initiation based on the strain of the connecting key and the fatigue parameter of the composite material;

[0085] The number of cycles required for crack growth is calculated based on the energy release rate of the connecting bond, the distance between material points and the fatigue parameters of the composite material.

[0086] This application mainly focuses on the fatigue problem of composite materials under constant cyclic load. Therefore, in each cycle, when there is no damage to the connecting key, the maximum and minimum strains of the connecting key hardly change. Therefore, the number of cycles for the initiation of fatigue cracks in the connecting key can be calculated by the following formula: (4), where ε ij is the strain of the bond between material points i and j.

[0087] The number of cycles N required for fatigue crack growth to occur in the connection between material point i and material point j propg It can be expressed as: (5); where p i is the coordinate of material point i, p j are the coordinates of material point j, Represents the distance between material point i and material point j (i.e., the distance between material points), also known as the crack length, B ij is the material fatigue parameter 3, d ij is the material fatigue parameter 4, ∆G ij (N) is the change in the energy release rate of the bond between material points i and j in the Nth cycle.

[0088] ∆G ij (N)=G ij (N) max -G ij (N) min (6)

[0089] (7)

[0090] Among them, G ij (N) maxis the maximum energy release rate of the bond between material points i and j in the Nth cycle, G ij (N) min is the minimum energy release rate of the bond between material points i and j in the Nth cycle, G Iij (N) and G Ⅱij (N) refers to the type I and type II bonds between material points i and j in the Nth cycle, respectively (e.g. Figure 4 The energy release rate can be calculated by the following formula:

[0091] (8)

[0092] (9)

[0093] Where Δ is the material point spacing, F 1ij and ε 1ij refers to the stress and strain in the direction of the bond between material points i and j at the Nth cycle, respectively, and F 2ij and ε 2ij They refer to the stress and strain in the direction perpendicular to the connecting bond between material points i and j at the Nth cycle.

[0094] Combined with the calculation formula of R, we can know that: =R(10)

[0095] therefore,

[0096] (12)

[0097] (13)

[0098] in , and , It can be obtained from the double cantilever beam (DCB) and end notch bending (ENF) experimental data. The subscript I represents the first crack and the subscript II represents the second crack. The exponents n, β1 and β2 are determined by curve fitting of the experimental data with different mixed mode ratios. Ⅰij (N) max is the maximum energy release rate of type I and type II connecting bonds between material points i and j in the Nth cycle, G Ⅱij (N) max is the minimum energy release rate of type I and type II connecting bonds between material points i and j in the Nth cycle.

[0099] S1213: Determine a cycle period of the composite material according to the number of cycles and a cycle period determined by the previous execution of the first target operation.

[0100] In an optional embodiment, determining the cycle period of the composite material according to the number of cycles and the cycle period determined by the previous execution of the first target operation includes:

[0101] Obtaining a damage index, wherein the damage index is used to characterize the relationship between the number of damaged bonds and the total number of bonds at a given material point;

[0102] Determining the damage type according to the damage index; the damage type includes crack initiation damage and crack extension damage;

[0103] The composite material cycle period is determined according to the damage type, the cycle number and the cycle period determined by the previous execution of the first target operation.

[0104] This embodiment determines the composite material cycle based on the damage index, damage type, number of cycles and the cycle determined by the previous execution of the first target operation, and has high reliability. It can be understood that if there is no previous first target operation, the cycle determined by the previous execution of the first target operation can be understood as 0, and the composite material cycle is actually determined according to the damage type and the number of cycles.

[0105] Optionally, the injury index The calculation is done using the following formula: ,in, is a parameter used to determine whether the connection bond between material points i and j is invalid. When it is 1, it means the key is not invalid. When it is 0, it means the key is invalid.

[0106] Optionally, when the damage index is greater than or equal to 0.5, the damage type is determined to be crack extension damage; when the damage index is less than 0.5, the damage type is determined to be crack initiation damage.

[0107] In an optional embodiment, determining the cycle period of the composite material according to the damage type, the number of cycles and the cycle period determined by the previous execution of the first target operation includes:

[0108] Determining a cycle increment based on the type of injury and the number of cycles;

[0109] A composite material cycle period is determined based on the cycle increment and a cycle period determined during a previous execution of the first target operation.

[0110] In an optional embodiment, determining the cycle increment according to the damage type and the cycle number includes:

[0111] In the case where the damage type is crack initiation damage, the cycle increment is determined as the minimum value of the number of cycles required for matrix crack initiation, the number of cycles required for fiber crack initiation, and the number of cycles required for delamination crack initiation;

[0112] When the damage type is crack extension damage, the cycle increment is determined as the minimum value of the number of cycles required for matrix crack initiation, the number of cycles required for matrix crack extension, the number of cycles required for fiber crack initiation, the number of cycles required for fiber crack extension, the number of cycles required for delamination crack initiation, and the number of cycles required for delamination extension.

[0113] S1214. Update the mechanical state and damage state of the connecting key in the composite material simulation model according to the damage type.

[0114] This step updates the mechanical state and damage state of the connecting key in the composite material simulation model after the damage type is obtained, so as to use the updated composite material simulation model in subsequent cycles.

[0115] The above method comprehensively considers the initiation and propagation of fatigue cracks in composite materials, accurately simulates the initiation and propagation process of fatigue damage cracks in composite laminates, obtains the fatigue life of composite materials, clarifies the fatigue failure mechanism of composite laminates, and solves the problem of difficulty in accurately predicting and analyzing fatigue life and damage evolution process.

[0116] Example 2

[0117] like Figure 5 As shown, this embodiment provides a composite material fatigue performance simulation device, comprising:

[0118] An acquisition module 201 is used to acquire fatigue parameters of composite materials;

[0119] The composite material fatigue life and failure mode output module 202 is used to cyclically execute the first target operation until the cycle period is greater than a preset value, and output the composite material fatigue life and failure mode; the first target operation includes: inputting the composite material fatigue parameters, composite material static load parameters and fatigue load into a real-time composite material simulation model; using static analysis to calculate the number of cycles required for crack initiation and crack propagation, respectively, and record crack coordinate data; determining the composite material cycle period based on the number of cycles and the cycle period determined by the previous execution of the first target operation.

[0120] The device is used to execute the above method, and thus has at least functional modules and beneficial effects corresponding to the above method.

[0121] Example 3

[0122] like Figure 6 As shown, this embodiment provides an electronic device, including:

[0123] at least one processor; and

[0124] a memory communicatively connected to at least one of the processors; wherein,

[0125] The memory stores instructions executable by at least one of the processors, and the instructions are executed by at least one of the processors to enable at least one of the processors to perform the above method. At least one processor in the electronic device can perform the above method, and thus has at least the same advantages as the above method.

[0126] Optionally, the electronic device also includes interfaces for connecting various components, including high-speed interfaces and low-speed interfaces. The various components are connected to each other using different buses and can be installed on a common mainboard or installed in other ways as needed. The processor can process instructions executed in the electronic device, including instructions stored in or on a memory to display graphical information of a GUI (Graphical User Interface) on an external input / output device (such as a display device coupled to an interface). In other embodiments, if necessary, multiple processors can be used together with multiple memories, and / or multiple buses can be used together with multiple memories. Similarly, multiple electronic devices can be connected (for example, as a server array, a group of blade servers, or a multi-processor system), and each device provides some necessary operations. Figure 6 A processor 301 is taken as an example.

[0127] The memory 302, as a computer-readable storage medium, can be used to store software programs, computer executable programs and modules, such as program instructions / modules corresponding to the composite material fatigue performance simulation method in the embodiment of the present application (for example, the acquisition module in the composite material fatigue performance simulation device, the composite material fatigue life and failure mode output module). The processor 301 executes various functional applications and data processing of the device by running the software programs, instructions and modules stored in the memory 302, that is, realizes the above-mentioned composite material fatigue performance simulation method.

[0128] The memory 302 may mainly include a program storage area and a data storage area, wherein the program storage area may store an operating system and at least one application required for a function; the data storage area may store data created according to the use of the terminal, etc. In addition, the memory 302 may include a high-speed random access memory, and may also include a non-volatile memory, such as at least one disk storage device, a flash memory device, or other non-volatile solid-state storage device. In some instances, the memory 302 may further include a memory remotely arranged relative to the processor 301, and these remote memories may be connected to the device via a network. Examples of the above-mentioned network include, but are not limited to, the Internet, an intranet, a local area network, a mobile communication network, and combinations thereof.

[0129] The electronic device may further include: an input device 303 and an output device 304. The processor 301, the memory 302, the input device 303 and the output device 304 may be connected via a bus or other means. Figure 6 The example of connecting through bus is taken in the following.

[0130] The input device 303 can receive input digital or character information, and the output device 304 can include a display device, an auxiliary lighting device (e.g., LED), and a tactile feedback device (e.g., a vibration motor), etc. The display device can include, but is not limited to, a liquid crystal display (LCD), a light emitting diode (LED) display, and a plasma display. In some embodiments, the display device can be a touch screen.

[0131] Example 4

[0132] This embodiment provides a computer-readable storage medium, on which computer instructions are stored, and the computer instructions are used to enable a computer to execute the above method. The computer instructions on the computer-readable storage medium are used to enable a computer to execute the above method, and thus have at least the same advantages as the above method.

[0133] The medium in this application may adopt any combination of one or more computer-readable media. The medium may be a computer-readable signal medium or a computer-readable storage medium. The medium may be, for example, but not limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, device or device, or any combination thereof. More specific examples of the medium (a non-exhaustive list) include: an electrical connection with one or more wires, a portable computer disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination thereof. In this document, the medium may be any tangible medium containing or storing a program, which may be used by or in combination with an instruction execution system, device, or device.

[0134] Computer-readable signal media may include data signals propagated in baseband or as part of a carrier wave, which carry computer-readable program code. Such propagated data signals may take a variety of forms, including but not limited to electromagnetic signals, optical signals, or any suitable combination of the above. Computer-readable signal media may also be any computer-readable medium other than a computer-readable storage medium, which may send, propagate, or transmit a program for use by or in conjunction with an instruction execution system, apparatus, or device.

[0135] The program code contained on the computer-readable medium can be transmitted using any appropriate medium, including but not limited to wireless, wire, optical cable, RF (Radio Frequency), etc., or any suitable combination of the above.

[0136] Computer program code for performing the operation of the present application can be written in one or more programming languages ​​or a combination thereof, including object-oriented programming languages, such as Java, Smalltalk, C++, and conventional procedural programming languages, such as "C" language or similar programming languages. The program code can be executed entirely on the user's computer, partially on the user's computer, as a separate software package, partially on the user's computer and partially on a remote computer, or entirely on a remote computer or server. In the case of a remote computer, the remote computer can be connected to the user's computer through any type of network, including a local area network (LAN) or a wide area network (WAN), or can be connected to an external computer (e.g., using an Internet service provider to connect through the Internet).

[0137] It should be understood that the various forms of processes shown above can be used to reorder, add or delete steps. For example, the steps recorded in this application can be executed in parallel, sequentially or in different orders, as long as the expected results of the technical solution disclosed in this application can be achieved, and this document is not limited here.

[0138] The above specific implementations do not constitute a limitation on the protection scope of this application. It should be understood by those skilled in the art that various modifications, combinations, sub-combinations and substitutions can be made according to design requirements and other factors. Any modifications, equivalent substitutions and improvements made within the spirit and principles of this application should be included in the protection scope of this application.

Claims

1. A composite material fatigue performance simulation method, characterized in that: include: Obtain fatigue parameters of the composite material, cyclically execute the first target operation until the cycle period is greater than a preset value, and output the fatigue life and failure mode of the composite material; The first target operation includes: Inputting the composite material fatigue parameter, composite material static load parameter and fatigue load into a real-time composite material simulation model; Using static analysis, the number of cycles required for crack initiation and crack propagation is calculated, and the crack coordinate data is recorded; Obtaining a damage index, wherein the damage index is used to characterize the relationship between the number of damaged bonds and the total number of bonds at a given material point; Determining the damage type according to the damage index; the damage type includes crack initiation damage and crack extension damage; Determining a cycle increment based on the type of injury and the number of cycles; determining a composite material cycle period based on the cycle increment and a cycle period determined from a previous execution of the first target operation; Determining the cycle increment according to the damage type and the cycle number includes: In the case where the damage type is crack initiation damage, the cycle increment is determined as the minimum value of the number of cycles required for matrix crack initiation, the number of cycles required for fiber crack initiation, and the number of cycles required for delamination crack initiation; When the damage type is crack extension damage, the cycle increment is determined as the minimum value of the number of cycles required for matrix crack initiation, the number of cycles required for matrix crack extension, the number of cycles required for fiber crack initiation, the number of cycles required for fiber crack extension, the number of cycles required for delamination crack initiation, and the number of cycles required for delamination extension.

2. The composite material fatigue performance simulation method according to claim 1, characterized in that: The static analysis is used to calculate the number of cycles required for crack initiation and crack propagation, and record the crack coordinate data, including: Using static analysis to determine the mechanical state of the connecting key in the composite material simulation model; the mechanical state includes strain, stress and energy release rate; According to the mechanical state of the connecting key and the fatigue parameters of the composite material, the number of cycles required for crack initiation and crack propagation are calculated respectively, and the crack coordinate data are recorded.

3. The composite material fatigue performance simulation method according to claim 2, characterized in that: The method of calculating the number of cycles required for crack initiation and crack propagation respectively according to the mechanical state of the connecting key and the fatigue parameter of the composite material comprises: Calculating the number of cycles required for crack initiation based on the strain of the connecting key and the fatigue parameter of the composite material; The number of cycles required for crack growth is calculated based on the energy release rate of the connecting bond, the distance between material points and the fatigue parameters of the composite material.

4. The composite material fatigue performance simulation method according to claim 1, characterized in that: After determining the cycle period of the composite material according to the number of cycles and the cycle period determined by the previous execution of the first target operation, the method further includes: According to the damage type, the mechanical state and the damage state of the connecting key in the composite material simulation model are updated.

5. The composite material fatigue performance simulation method according to claim 1, characterized in that: The fatigue parameters of the composite material are determined in the following manner: Determine the composite matrix fatigue parameters based on the SN curve of the composite 90° laminate unidirectional plate fatigue test; According to the SN curve of the fatigue test of the composite material 90° laminated unidirectional plate and the stress S m , determine the matrix fatigue life N m ; According to the SN curve of the composite material 0° laminated unidirectional plate fatigue test and the matrix fatigue life N m , determine the revised S-(NN m )curve; According to the revised S-(NN m ) curve to determine the fatigue parameters of composite fiber.

6. An electronic device, characterized in that: include: at least one processor, and a memory communicatively coupled to at least one of the processors; The memory stores instructions executable by at least one of the processors, and the instructions are executed by at least one of the processors so that the at least one processor can execute the method according to any one of claims 1 to 5.

7. A computer-readable storage medium, characterized in that: The medium stores computer instructions, and the computer instructions are used to enable a computer to execute the method according to any one of claims 1 to 5.

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