A method and system for predicting damage of Z-pin reinforced carbon fiber composites

Abstract

The present invention discloses a method and system for predicting damage of Z-pin reinforced carbon fiber composites. The method includes: obtaining the material property parameters of the Z-pin reinforced carbon fiber composites; constructing a three-dimensional macroscopic finite element model of the Z-pin reinforced carbon fiber composites based on the material property parameters; predicting the impact mechanical properties of the three-dimensional macroscopic finite element model to obtain an impact damage prediction result; wherein, the in-plane failure criterion of carbon fiber composites, the interlaminar failure criterion of carbon fiber composites and the Z-pin failure criterion are used for impact damage prediction; comparing the impact damage prediction result with the damage result of the high-speed impact test, and correcting the three-dimensional macroscopic finite element model according to the comparison result to obtain a corrected model; using the corrected model to predict the damage of the Z-pin reinforced carbon fiber composites under impact. The physical mechanism of the present invention is clear, and it can better predict the damage situation of Z-pin reinforced composites and describe its failure process.

Description

Technical Field

[0001] The present invention relates to the technical field of mechanical property analysis of composite materials, and particularly to a method and system for predicting damage of Z-pin reinforced carbon fiber composite materials. Background Art

[0002] The unique combination of excellent mechanical and physical properties such as specific strength and stiffness, fatigue performance, and corrosion resistance, as well as strong design customization, makes composite materials increasingly used as substitutes for metal materials in a wide range of high-performance structural applications, which also puts higher requirements on their performance. However, due to the lack of full-thickness reinforcement, the strength performance of composite laminates in the out-of-plane direction is relatively poor compared to their in-plane performance. Therefore, composite structures have a low resistance to transverse loads and are particularly prone to delamination when subjected to impacts that inevitably occur during manufacturing, service, installation, and maintenance. The Z-pin reinforcement technology is a new technology that can improve the interlaminar performance of composite materials. Z-pins can significantly improve the interlaminar fracture toughness and damage tolerance of composite materials and resist delamination damage. The Z-pin reinforcement technology is to introduce interlayer reinforcement materials between uncured composite material layers, including inserting continuous reinforcement wires or discrete pins in the thickness of the laminate respectively, so as to achieve the purpose of enhancing the interlaminar performance of composite materials. The Z-pin reinforcement technology is convenient for processing, has low cost, and high processing efficiency, and has now been widely used in industries such as aviation, aerospace, and shipbuilding.

[0003] However, in the case of high-speed impact, a large number of matrix cracks, large-area interlaminar delamination, a small amount of fiber fracture, and local matrix extrusion cracks under the impact point will still occur inside the Z-pin reinforced composite material. In order to effectively analyze the structural damage tolerance of the Z-pin reinforced composite laminate, it is necessary to clearly understand the damage failure process during the load-bearing of the laminate. Therefore, using a finite element model to describe the failure process of the Z-pin reinforced composite material and predict the damage of the Z-pin reinforced carbon fiber composite material has important guiding significance for the preparation of the Z-pin reinforced composite material. However, at present, there is only a model describing the tensile behavior of the Z-pin reinforced carbon fiber composite material, and there is no specific finite element model for damage simulation of the Z-pin reinforced carbon fiber composite material. Summary of the Invention

[0004] Aiming at the complex problem of damage prediction and analysis of Z-pin three-dimensional reinforced composite laminates, the present invention provides a method and system for predicting damage of Z-pin reinforced carbon fiber composite materials.

[0005] To achieve the above object, the present invention provides the following solutions:

[0006] A method for predicting damage of Z-pin reinforced carbon fiber composite materials, comprising:

[0007] Obtain the material property parameters of the Z-pin reinforced carbon fiber composite material; the material property parameters include: carbon fiber composite material parameters, Z-pin parameters, and carbon fiber composite material interlayer interface parameters;

[0008] Construct a three-dimensional macroscopic finite element model of the Z-pin reinforced carbon fiber composite material based on the material property parameters;

[0009] Predict the impact mechanical properties of the three-dimensional macroscopic finite element model to obtain an impact damage prediction result; among them, the in-plane failure criterion of the carbon fiber composite material, the interlayer failure criterion of the carbon fiber composite material, and the Z-pin failure criterion are used for impact damage prediction;

[0010] Compare the impact damage prediction result with the damage result of the high-speed impact test, and modify the three-dimensional macroscopic finite element model according to the comparison result to obtain a modified model;

[0011] Use the modified model to predict the damage of the Z-pin reinforced carbon fiber composite material under impact.

[0012] Optionally, the carbon fiber composite material parameters include the density, elastic modulus, Poisson's ratio, shear modulus, and strength of the carbon fiber composite material; the Z-pin parameters include the elastic properties, strength, and fracture toughness of the Z-pin; the carbon fiber composite material interlayer interface parameters include the elastic properties, strength, and fracture toughness of the carbon fiber composite material interlayer interface.

[0013] Optionally, the in-plane failure criterion of the carbon fiber composite material uses the generalized three-dimensional Hashin criterion to predict the in-plane damage of the carbon fiber composite material after impact; the interlayer failure criterion of the carbon fiber composite material uses the cohesive element with bilinear cohesive stress - relative displacement constitutive relationship to predict the interlayer damage of the carbon fiber composite material after impact; the Z-pin failure criterion uses the BK hybrid criterion based on the energy release rate to predict the damage of the Z-pin after impact.

[0014] Optionally, the generalized three-dimensional Hashin criterion is as follows:

[0015] Fiber tensile failure d ft The condition for = 1 is:

[0016]

[0017] Fiber compressive failure d fc The condition for = 1 is:

[0018]

[0019] Matrix tensile failure d mt The condition for = 1 is:

[0020]

[0021] Matrix compressive failure d mc The condition for = 1 is:

[0022]

[0023] Wherein, X T and X C represent the tensile strengths of the carbon fiber composite material in two different directions, Y T and Y C represent the compressive strengths of the carbon fiber composite material in two different directions, S 12 represents the in-plane shear strength of the carbon fiber composite material, and σ 11 , σ2 and σ3 respectively represent the effective stresses in three principal directions.

[0024] Optionally, the expression of the cohesive element of the bilinear cohesive stress - relative displacement constitutive relationship is as follows:

[0025]

[0026] Wherein, d co represents the damage variable, t n represents the normal traction force, t s represents the in-plane shear traction force, t t represents the anti-plane shear traction force, δ n , δ s , δ t respectively represent the separation displacements of t n , t s , t t in the traction force direction.

[0027] Optionally, the BK mixed criterion based on the energy release rate is as follows:

[0028]

[0029] Wherein, G C represents the energy release rate, G I and represent the type I and type II strain energy release rates, G IC and G IIC respectively represent the type I and type II critical strain energy release rates, and η is an empirical parameter.

[0030] The present invention also provides a Z-pin reinforced carbon fiber composite material damage prediction system, including:

[0031] A material property parameter acquisition module for acquiring the material property parameters of Z-pin reinforced carbon fiber composites; the material property parameters include: carbon fiber composite parameters, Z-pin parameters, and carbon fiber composite interlayer interface parameters;

[0032] A three-dimensional macroscopic finite element model construction module for constructing a three-dimensional macroscopic finite element model of the Z-pin reinforced carbon fiber composite based on the material property parameters;

[0033] An impact mechanical property prediction module for predicting the impact mechanical properties of the three-dimensional macroscopic finite element model to obtain an impact damage prediction result; wherein, the carbon fiber composite in-layer failure criterion, the carbon fiber composite interlayer failure criterion, and the Z-pin failure criterion are used for impact damage prediction;

[0034] A correction module for comparing the impact damage prediction result with the high-speed impact test damage result and correcting the three-dimensional macroscopic finite element model according to the comparison result to obtain a corrected model;

[0035] A damage prediction module for predicting the damage of the Z-pin reinforced carbon fiber composite under impact using the corrected model.

[0036] According to the specific embodiments provided by the present invention, the following technical effects are disclosed:

[0037] The present invention provides a method and system for predicting the damage of Z-pin reinforced carbon fiber composites. The method includes: acquiring the material property parameters of the Z-pin reinforced carbon fiber composite; constructing a three-dimensional macroscopic finite element model of the Z-pin reinforced carbon fiber composite based on the material property parameters; predicting the impact mechanical properties of the three-dimensional macroscopic finite element model to obtain an impact damage prediction result; wherein, the carbon fiber composite in-layer failure criterion, the carbon fiber composite interlayer failure criterion, and the Z-pin failure criterion are used for impact damage prediction; comparing the impact damage prediction result with the high-speed impact test damage result and correcting the three-dimensional macroscopic finite element model according to the comparison result to obtain a corrected model; predicting the damage of the Z-pin reinforced carbon fiber composite under impact using the corrected model. The physical mechanism of the present invention is clear, it can better predict the damage situation of Z-pin reinforced composites, describe its failure process, provide strong support for the guidance of its preparation process, and effectively reduce the scientific research cost. Description of the Drawings

[0038] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the accompanying drawings required for use in the embodiments. Obviously, the accompanying drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other accompanying drawings can also be obtained based on these drawings.

[0039] Figure 1 Flow chart of the Z-pin reinforced carbon fiber composite damage prediction method provided by the present invention;

[0040] Figure 2 Schematic diagram of the three-dimensional macroscopic finite element model of the Z-pin reinforced composite laminate of the present invention;

[0041] Figure 3 Schematic diagram of the impact damage prediction result of predicting the impact mechanical properties of the three-dimensional macroscopic finite element model of the Z-pin reinforced composite laminate of the present invention.

[0042] Figure 4 Schematic diagram of the damage result of the high-speed impact experiment on the Z-pin reinforced composite laminate of the present invention. Detailed implementation manners

[0043] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, rather than all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts belong to the scope of protection of the present invention.

[0044] To make the above objects, features, and advantages of the present invention more obvious and understandable, the present invention will be further described in detail below in conjunction with the accompanying drawings and specific implementation manners.

[0045] As Figure 1 shown, a Z-pin reinforced carbon fiber composite damage prediction method provided by the present invention includes the following steps:

[0046] Step 101: Obtain the material property parameters of the Z-pin reinforced carbon fiber composite; the material property parameters include: carbon fiber composite parameters, Z-pin parameters, and carbon fiber composite interlayer interface parameters.

[0047] The carbon fiber composite parameters include the density ρ, elastic modulus E, Poisson's ratio ν, shear modulus G, and strength S of the carbon fiber composite; the Z-pin parameters include the elastic property K of the Z-pin p , strength t p , and fracture toughness G Cp; The interlaminar interface parameters of the carbon fiber composite material include the elastic property K of the interlaminar interface of the carbon fiber composite material f , strength t f , and fracture toughness G Cf .

[0048] Step 102: Construct a three-dimensional macroscopic finite element model of the Z-pin reinforced carbon fiber composite material based on the material property parameters.

[0049] Establish a three-dimensional macroscopic finite element model of the Z-pin reinforced carbon fiber composite material through the ABAQUS platform.

[0050] Step 103: Predict the impact mechanical properties of the three-dimensional macroscopic finite element model to obtain the impact damage prediction results; among them, the in-plane failure criterion of the carbon fiber composite material, the interlaminar failure criterion of the carbon fiber composite material, and the Z-pin failure criterion are used for impact damage prediction.

[0051] The in-plane failure criterion of the carbon fiber composite material uses the generalized three-dimensional Hashin criterion to predict the in-plane damage of the carbon fiber composite material after impact; the interlaminar failure criterion of the carbon fiber composite material uses the cohesive element with a bilinear cohesive stress - relative displacement constitutive relationship to predict the interlaminar damage of the carbon fiber composite material after impact; the Z-pin failure criterion uses the BK mixed criterion based on the energy release rate to predict the damage of the Z-pin after impact.

[0052] Specifically, the in-plane failure criterion of the composite laminate during impact uses the generalized three-dimensional Hashin criterion, and the progressive reduction of material stiffness is carried out according to the damage evolution model proposed by Camanho.

[0053] Generalized three-dimensional Hashin criterion:

[0054] The condition for fiber tensile failure d ft = 1 is:

[0055]

[0056] The condition for fiber compressive failure d fc = 1 is:

[0057]

[0058] The condition for matrix tensile failure d mt = 1 is:

[0059]

[0060] The condition for matrix compressive failure d mc = 1 is:

[0061]

[0062] Among them, X T and X C represent the tensile strengths of the carbon fiber composite material in two different directions, Y T and Y C represent the compressive strengths of the carbon fiber composite material in two different directions, S 12 represents the in-plane shear strength of the carbon fiber composite material, and σ 11 , σ2 and σ3 represent the effective stresses in three principal directions respectively.

[0063] When damage occurs, one or more of the above damage criteria are satisfied, and the stiffness in the corresponding mechanical direction will decay to a certain extent according to the law, and then evolve into failure, rather than quickly causing the failure of the corresponding material components. The asymptotic damage degradation analysis method simulates the damage change by gradually reducing the material parameters. When the Hashin failure criterion is satisfied, the stiffness of the material gradually decays.

[0064] Adopt the Camanho degradation model:

[0065] Camanho believes that the effect of failure on the material stiffness can be represented by an intermediate state variable. On this basis, the principal Poisson's ratio degradation method is introduced. Assume that multiple failures can occur in a single element, that is, cumulative damage, such as both matrix tensile and fiber tensile failures occur. However, if matrix or fiber tensile failure occurs, it is impossible to have matrix or fiber compressive failure again. For elements with multiple failure modes occurring simultaneously, the corresponding degradation parameters are accumulated. The specific method of material degradation is as follows:

[0066] Matrix tensile or shear cracking:

[0067] E′2 = 0.2E2, G′ 12 = 0.22G 12 , ν′ 12 = 0.15ν 12

[0068] Matrix compressive or shear cracking:

[0069] E′2 = 0.4E2, G′ 12 = 0.4G 12 , ν′ 12 = 0.15ν 12

[0070] Fiber tensile fracture:

[0071] E′1 = 0.07E1, E′2 = 0.07E2, G′ 12 = 0.07G 12 , ν′ 12= 0.07ν 12

[0072] Fiber compression fracture:

[0073] E′1 = 0.14E1, E′2 = 0.14E2, G′ 12 = 0.14G 12 , ν′ 12 = 0.14ν 12

[0074] Both matrix tensile or shear cracking and fiber tensile fracture occur:

[0075] E′1 = 0.07E1, E′2 = 0.2E2, G′ 12 = 0.22G 12 , ν′ 12 = 0.15ν 12

[0076] Both matrix compression or shear cracking and fiber compression fracture occur:

[0077] E′1 = 0.14E1, E′2 = 0.4E2, G′ 12 = 0.4G 12 , ν′ 12 = 0.15ν 12

[0078] Where: E i , ν ij , G ij are the current material parameters of the monolayer plate; E′ i , ν′ ij , G′ ij are the degraded material parameters after the monolayer plate fails.

[0079] Specifically, the bilinear cohesive stress - relative displacement constitutive relation is used to describe the strengthening effect of a single Z - pin, the quadratic stress criterion is applied as the initial damage criterion for a single Z - pin in the cohesive element layer during impact, and the BK (Benzeggagh - Kenane) mixed criterion based on the energy release rate is selected as the final failure criterion for a single Z - pin.

[0080] For the Z - pin reinforced area, a cohesive element adopting the bilinear cohesive stress - relative displacement constitutive relation:

[0081]

[0082] Where, d co represents the damage variable, t n represents the normal traction force, t s represents the in - plane shear traction force, tt represents the anti-plane shear traction force, δ n , δ s , δ t respectively represent the separation displacements of t n , t s , t t in the traction force direction.

[0083] Apply the quadratic stress criterion as the initiation criterion for the damage of the cohesive element layer:

[0084]

[0085] In the formula, the interlaminar tensile stress σ is defined as:

[0086]

[0087] Among them, the Macaulay symbol <> indicates that the pure compression process has no damage effect on the cohesive element layer. When the above equation conditions are met, damage occurs to the cohesive element layer. and represent the maximum stresses in three directions.

[0088] Select the BK (Benzeggagh-Kenane) mixed criterion based on the energy release rate as the criterion for the final failure of a single Z-pin:

[0089]

[0090] In the formula, G C represents the energy release rate, G I and G II are the type-I and type-II strain energy release rates, G IC and G IIC are the type-I and type-II critical strain energy release rates respectively. η is an empirical parameter, which is taken as 1.8 in the present invention.

[0091] Step 104: Compare the impact damage prediction results with the damage results of the high-speed impact test, and modify the three-dimensional macroscopic finite element model according to the comparison results to obtain the modified model.

[0092] Step 105: Use the modified model to predict the damage of the Z-pin reinforced carbon fiber composite under impact.

[0093] The specific embodiments are as follows:

[0094] In this embodiment, the high-speed impact test of the quasi-isotropic symmetrically laminated Z-pin reinforced carbon fiber composite laminate is taken as an example to demonstrate its technical effects. Progressive damage analysis is carried out in this example, and the damage morphology of the Z-pin reinforced carbon fiber composite laminate after impact is obtained. The specific process includes the following steps:

[0095] 1. Determine the material property parameters and construct a finite element model. The material parameters of the finite element model are shown in Tables 1 - 3.

[0096] Table 1 Material parameters of T700 / 3234

[0097]

[0098] Table 2 Material parameters of the interlayer interface

[0099]

[0100] Table 3 Z-pin parameters

[0101]

[0102] 2. The three-dimensional macroscopic finite element model of the Z-pin reinforced carbon fiber composite is established based on the ABAQUS platform. During the impact process, the failure criterion within the layer of the Z-pin reinforced carbon fiber composite laminate adopts the generalized three-dimensional Hashin criterion, and the progressive reduction of material stiffness is carried out according to the damage evolution model proposed by Camanho; the interlayer failure of the composite laminate is described by using the cohesive element with a bilinear cohesive stress - relative displacement constitutive relationship. During the impact process, the failure of the Z-pin reinforced area is described by selecting the BK (Benzeggagh-Kenane) mixed criterion based on the energy release rate.

[0103] 3. Input the material property parameters into the ABAQUS finite element model. Through calculation, the damage morphology and failure behavior of the target plate finite element model can be obtained. The comparison of the damage morphology obtained from the experiment is shown in Table 4, which verifies the effectiveness of the proposed solution of the present invention. The damage prediction results of the finite element model in the embodiment of the present invention and the damage results of the high-speed impact experiment of the Z-pin reinforced composite laminate are as Figure 3 、 Figure 4 shown.

[0104] Table 4 Comparison of the high-speed impact experiment results of the Z-pin reinforced carbon fiber composite target plate and the prediction results of the progressive damage model

[0105]

[0106]

[0107] 4. Based on the three-dimensional macroscopic finite element model of the Z-pin reinforced carbon fiber composite material, parametric analysis can be carried out to analyze the influence of relevant parameters such as the Z-pin diameter, the arrangement interval of Z-pins, and the material layup of the carbon fiber composite material on macroscopic damage and failure. The analysis results can provide guidance for the design and preparation of the Z-pin reinforced carbon fiber composite material.

[0108] The present invention also provides a damage prediction system for the Z-pin reinforced carbon fiber composite material, including:

[0109] A material property parameter acquisition module for acquiring the material property parameters of the Z-pin reinforced carbon fiber composite material; the material property parameters include: carbon fiber composite material parameters, Z-pin parameters, and carbon fiber composite material interlayer interface parameters.

[0110] A three-dimensional macroscopic finite element model construction module for constructing a three-dimensional macroscopic finite element model of the Z-pin reinforced carbon fiber composite material based on the material property parameters.

[0111] An impact mechanical property prediction module for predicting the impact mechanical properties of the three-dimensional macroscopic finite element model to obtain an impact damage prediction result; among them, the in-layer failure criterion of the carbon fiber composite material, the interlayer failure criterion of the carbon fiber composite material, and the Z-pin failure criterion are used for impact damage prediction.

[0112] A correction module for comparing the impact damage prediction result with the high-speed impact test damage result and correcting the three-dimensional macroscopic finite element model according to the comparison result to obtain a corrected model;

[0113] A damage prediction module for predicting the damage of the Z-pin reinforced carbon fiber composite material under impact using the corrected model.

[0114] In this specification, each embodiment is described in a progressive manner. The key point of each embodiment is to illustrate the differences from other embodiments. The same or similar parts among the embodiments can be referred to each other. For the system disclosed in the embodiments, since it corresponds to the method disclosed in the embodiments, the description is relatively simple. For the relevant parts, please refer to the description in the method part.

[0115] Specific examples are used in this article to elaborate on the principle and implementation manner of the present invention. The description of the above embodiments is only used to help understand the method and its core idea of the present invention; at the same time, for those of ordinary skill in the art, according to the idea of the present invention, there will be changes in the specific implementation manner and application scope. In summary, the content of this specification should not be construed as a limitation to the present invention.

Claims

1. A damage prediction method for Z-pin reinforced carbon fiber composites, characterized in that, Including: Obtaining the material property parameters of the Z-pin reinforced carbon fiber composite material; The material property parameters include: carbon fiber composite material parameters, Z-pin parameters, and carbon fiber composite material interlayer interface parameters; Constructing a three-dimensional macroscopic finite element model of the Z-pin reinforced carbon fiber composite material based on the material property parameters; Predicting the impact mechanical properties of the three-dimensional macroscopic finite element model to obtain an impact damage prediction result; wherein, the generalized three-dimensional Hashin criterion, the carbon fiber composite material interlayer failure criterion, and the Z-pin failure criterion are used for impact damage prediction; Comparing the impact damage prediction result with the damage result of the high-speed impact test, and correcting the three-dimensional macroscopic finite element model according to the comparison result to obtain a corrected model; Predicting the damage of the Z-pin reinforced carbon fiber composite material under impact using the corrected model.

2. The damage prediction method of the Z-pin reinforced carbon fiber composite material according to claim 1, wherein The carbon fiber composite material parameters include the density, elastic modulus, Poisson's ratio, shear modulus, and strength of the carbon fiber composite material; the Z-pin parameters include the elastic properties, strength, and fracture toughness of the Z-pin; The carbon fiber composite material interlayer interface parameters include the elastic properties, strength, and fracture toughness of the carbon fiber composite material interlayer interface.

3. The damage prediction method for Z-pin reinforced carbon fiber composite materials according to claim 1, wherein, The generalized three-dimensional Hashin criterion is used to predict the in-layer damage of the carbon fiber composite material after impact; the carbon fiber composite material interlayer failure criterion uses a cohesive element with a bilinear cohesive stress - relative displacement constitutive relationship to predict the interlayer damage of the carbon fiber composite material after impact; the Z-pin failure criterion uses the BK mixed criterion based on the energy release rate to predict the damage of the Z-pin after impact.

4. The damage prediction method for Z-pin reinforced carbon fiber composite materials according to claim 3, characterized in that The generalized three-dimensional Hashin criterion is as follows: Fiber tensile failure d ft The condition for = 1 is: Fiber compression failure d fc The condition for = 1 is: Matrix tensile failure d mt The condition for Matrix compression failure d mc The condition for = 1 is: Among them, X T and X C represent the tensile strengths of the carbon fiber composite material in two different directions, Y T and Y C represent the compressive strengths of the carbon fiber composite material in two different directions, S 12 represents the in-plane shear strength of the carbon fiber composite material, and σ 11 , σ2 and σ3 respectively represent the effective stresses in three principal directions.

5. The damage prediction method of the Z-pin reinforced carbon fiber composite material according to claim 3, wherein The expression of the cohesive element with a bilinear cohesive stress - relative displacement constitutive relationship is as follows: Among them, d co represents the damage variable, t n represents the normal traction force, t s represents the in-plane shear traction force, t t represents the anti-plane shear traction force, δ n 、δ s 、δ t respectively represent the separation displacements of t n 、t s 、t t in the traction force direction.

6. The damage prediction method for Z-pin reinforced carbon fiber composite materials according to claim 3, characterized in that, The BK mixed criterion based on the energy release rate is as follows: Among them, G C represents the energy release rate, G I and denote the mode I and mode II strain energy release rates, G IC and G IIC represent the mode I and mode II critical strain energy release rates respectively, and η is an empirical parameter.

7. A damage prediction system for Z-pin reinforced carbon fiber composites, characterized in that, Including: A material property parameter acquisition module for obtaining the material property parameters of the Z-pin reinforced carbon fiber composite material; The material property parameters include: carbon fiber composite material parameters, Z-pin parameters, and carbon fiber composite material interlayer interface parameters; A three-dimensional macroscopic finite element model construction module for constructing a three-dimensional macroscopic finite element model of the Z-pin reinforced carbon fiber composite material based on the material property parameters; An impact mechanical property prediction module for predicting the impact mechanical properties of the three-dimensional macroscopic finite element model to obtain an impact damage prediction result; wherein, the generalized three-dimensional Hashin criterion, the carbon fiber composite material interlayer failure criterion, and the Z-pin failure criterion are used for impact damage prediction; A correction module for comparing the impact damage prediction result with the damage result of the high-speed impact test, and correcting the three-dimensional macroscopic finite element model according to the comparison result to obtain a corrected model; A damage prediction module for predicting the damage of the Z-pin reinforced carbon fiber composite material under impact using the corrected model.

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