Crack opening displacement prediction method and system for fiber reinforced ceramic matrix composites

Abstract

The present application discloses a method and system for predicting crack opening displacement of fiber-reinforced ceramic matrix composite materials, which relates to the technical field of composite material crack opening displacement prediction. The method includes obtaining basic data of fiber-reinforced ceramic matrix composite materials, establishing an interface phase oxidation model; then establishing a unit cell model to determine the microscopic stress field between fiber and matrix; calculating the temperature, stress and time-dependent matrix crack length according to the microscopic stress field between fiber and matrix and the matrix random cracking model; then calculating the temperature, stress and time-dependent fiber axial displacement and matrix axial displacement at the matrix crack plane; then using the fracture mechanics interface debonding criterion to calculate the temperature, stress and time-dependent interface debonding length, thereby calculating the matrix crack opening displacement. The present application can comprehensively consider the coupling effects of temperature, stress and oxidation factors, and accurately predict and calculate the matrix crack opening displacement of fiber-reinforced ceramic matrix composite materials.

Description

Technical Field

[0001] The present application relates to the technical field of composite material crack opening displacement prediction, and in particular to a method and system for predicting crack opening displacement of a fiber-reinforced ceramic matrix composite material. Background Art

[0002] Fiber-reinforced ceramic matrix composites are widely used in aviation, aerospace, energy and other fields. Their service environment is extremely harsh, including complex stress states, high temperatures, chemical corrosion, etc. With the increase of ambient temperature, the increase of use loads, and the effect of oxidative environment, the modulus and strength gradually decline over time, and the ability to resist deformation becomes poor. The coupling effect of heat, force and oxygen refers to the combined effect of temperature, stress and oxidation. Under the coupling effect of heat, force and oxygen, the matrix cracks open, allowing oxidizing gases to enter the interior of the fiber-reinforced ceramic matrix composites, and oxidize the interface phase and fibers, etc., thereby causing the internal damage of the fiber-reinforced ceramic matrix composites to increase. In order to ensure the reliability and safety of fiber-reinforced ceramic matrix composites during use, it is necessary to establish a fiber-reinforced ceramic matrix composite matrix crack opening displacement model under the action of heat, force and oxygen coupling, so as to predict the evolution relationship of crack opening displacement over time.

[0003] However, there are few studies on the matrix crack opening displacement of fiber-reinforced ceramic matrix composites under the action of thermal-mechanical-oxygen coupling, and none of them can accurately predict the matrix crack opening displacement of fiber-reinforced ceramic matrix composites under the action of thermal-mechanical-oxygen coupling. Therefore, how to consider the coupling effects of multiple factors such as temperature, load and oxidation, and accurately predict the matrix crack opening displacement of fiber-reinforced ceramic matrix composites under the action of thermal-mechanical-oxygen coupling, is a technical problem that needs to be solved urgently to ensure the practical engineering application of fiber-reinforced ceramic matrix composites. Summary of the invention

[0004] The purpose of this application is to provide a method and system for predicting crack opening displacement of fiber-reinforced ceramic matrix composite materials, which can comprehensively consider the coupling effects of multiple factors such as temperature, load and oxidation, and accurately predict the matrix crack opening displacement of fiber-reinforced ceramic matrix composite materials under the action of heat-mechanics-oxygen coupling.

[0005] To achieve the above objectives, this application provides the following solutions.

[0006] In a first aspect, the present application provides a method for predicting crack opening displacement of a fiber reinforced ceramic matrix composite material, and the method for predicting crack opening displacement of a fiber reinforced ceramic matrix composite material comprises the following steps.

[0007] Obtain basic data of the fiber-reinforced ceramic matrix composite material; the basic data include test temperature, fiber radius, fiber elastic modulus, matrix elastic modulus and volume percentage of fiber to matrix.

[0008] According to the basic data, an interfacial phase oxidation model of the fiber-reinforced ceramic matrix composite material is established; the interfacial phase oxidation model refers to a model of temperature- and time-dependent interfacial phase oxidation of the fiber-reinforced ceramic matrix composite material based on a thermal-mechanical-oxygen coupling mechanism.

[0009] According to the interface phase oxidation model, a unit cell model of the fiber reinforced ceramic matrix composite material is established, and the temperature and time-dependent microscopic stress field of the fiber and the matrix is ​​determined according to the unit cell model.

[0010] The temperature, stress and time-dependent matrix crack length is calculated based on the fiber and matrix microscopic stress field and the matrix random cracking model; the matrix random cracking model refers to a model in which internal defects of the matrix cause randomness in the cracking position of the fiber-reinforced ceramic matrix composite material under load.

[0011] The temperature, stress and time-dependent fiber axial displacement and matrix axial displacement at the matrix crack plane are calculated based on the temperature, stress and time-dependent matrix crack length and the fiber and matrix microscopic stress field.

[0012] According to the temperature, stress and time-dependent fiber axial displacement and matrix axial displacement at the matrix crack plane, the temperature, stress and time-dependent interface debonding length is calculated by adopting the fracture mechanics interface debonding criterion.

[0013] The matrix crack opening displacement is calculated based on the temperature, stress and time-dependent interface debonding length.

[0014] In a second aspect, the present application provides a fiber reinforced ceramic matrix composite crack opening displacement prediction system, comprising: a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the fiber reinforced ceramic matrix composite crack opening displacement prediction method described in the first aspect.

[0015] According to the specific embodiments provided in this application, this application discloses the following technical effects:

[0016] The present application provides a method and system for predicting crack opening displacement of fiber-reinforced ceramic matrix composite materials. By comprehensively considering the coupling effects of multiple factors such as temperature, load and oxidation, based on the thermal-mechanical-oxygen coupling mechanism, firstly, according to the basic data of fiber-reinforced ceramic matrix composite materials, an interface phase oxidation model is established; then, according to the interface phase oxidation model, a single cell model of the fiber-reinforced ceramic matrix composite material is established to obtain the microscopic stress field of the fiber and the matrix; then, according to the microscopic stress field of the fiber and the matrix and the random cracking model of the matrix, the temperature, stress and time-dependent matrix crack length is calculated; then, according to the temperature, stress and time-dependent matrix crack length and the microscopic stress field of the fiber and the matrix, the matrix crack length is calculated. The temperature, stress and time-dependent fiber axial displacement and matrix axial displacement are calculated by using the field, so as to further calculate the temperature, stress and time-dependent fiber axial displacement and matrix axial displacement at the matrix crack plane; then, according to the temperature, stress and time-dependent fiber axial displacement and matrix axial displacement at the matrix crack plane, the temperature, stress and time-dependent interface debonding length is calculated by using the fracture mechanics interface debonding criterion; finally, according to the temperature, stress and time-dependent interface debonding length, the matrix crack opening displacement is calculated, so as to accurately predict and calculate the matrix crack opening displacement of fiber-reinforced ceramic matrix composites under the action of heat-mechanics-oxygen coupling. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0018] Figure 1 A flowchart of a method for predicting crack opening displacement of a fiber-reinforced ceramic matrix composite material provided in one embodiment of the present application.

[0019] Figure 2 A graph showing the change in matrix crack opening displacement with stress for a SiC / SiC composite material provided in one embodiment of the present application under the action of heat-mechanics-oxygen coupling. DETAILED DESCRIPTION

[0020] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0021] In order to make the above-mentioned objects, features and advantages of the present application more obvious and easy to understand, the present application is further described in detail below in conjunction with the accompanying drawings and specific implementation methods.

[0022] like Figure 1 As shown, this embodiment provides a method for predicting crack opening displacement of fiber reinforced ceramic matrix composite materials. The method is mainly used to accurately predict and calculate the matrix crack opening displacement of fiber reinforced ceramic matrix composite materials under the coupling of heat, force and oxygen, so as to determine the matrix crack opening displacement result, and specifically includes the following steps.

[0023] Step S1, obtaining basic data of fiber reinforced ceramic matrix composite materials.

[0024] In this embodiment, the basic data includes various data such as test temperature, fiber radius, fiber elastic modulus, matrix elastic modulus and volume percentage of fiber to matrix for crack opening displacement related tests on fiber-reinforced ceramic matrix composite materials, which are mainly used in the subsequent model establishment and data calculation process.

[0025] Step S2: establishing an interface phase oxidation model of a fiber-reinforced ceramic matrix composite material based on basic data.

[0026] In this embodiment, the interface phase oxidation model refers to a model of temperature and time-dependent interface phase oxidation of fiber-reinforced ceramic matrix composites based on the thermal-mechanical-oxygen coupling mechanism. The thermal-mechanical-oxygen coupling mechanism refers to the mechanism by which the interface phase of fiber-reinforced ceramic matrix composites undergoes oxidation under the coupling of temperature, stress and oxidation, resulting in damage that affects the mechanical behavior. Temperature and time dependence refers to the dependence between temperature and time, that is, the correlation between temperature changes over time.

[0027] Step S3: According to the interface phase oxidation model, a unit cell model of the fiber-reinforced ceramic matrix composite material is established to obtain the microscopic stress field of the fiber and the matrix.

[0028] In this embodiment, the unit cell model refers to a microscopic mechanical model composed of fibers and a matrix of a fiber-reinforced ceramic matrix composite material. The fiber and matrix microscopic stress field refers to a microscopic stress field based on the fiber and the matrix, which is used to characterize the temperature and time-dependent fiber axial stress and matrix axial stress.

[0029] Step S4: Calculate the temperature, stress and time-dependent matrix crack length based on the fiber and matrix microscopic stress field and the matrix random cracking model.

[0030] In this embodiment, the matrix random cracking model refers to a model in which internal defects of the matrix cause random cracking positions of the fiber reinforced ceramic matrix composite material under load. Temperature, stress and time dependence refers to the dependence relationship between temperature, stress and time.

[0031] Step S5, calculating the temperature, stress and time-dependent fiber axial displacement and matrix axial displacement at the matrix crack plane based on the temperature, stress and time-dependent matrix crack length and the fiber and matrix microscopic stress field.

[0032] In this embodiment, step S5 calculates the temperature, stress and time-dependent fiber axial displacement and matrix axial displacement at the matrix crack plane based on the temperature, stress and time-dependent matrix crack length and the fiber and matrix microscopic stress field, and specifically includes the following steps.

[0033] Step S51, calculating the temperature, stress and time-dependent fiber axial displacement and matrix axial displacement according to the temperature, stress and time-dependent matrix crack length and the fiber and matrix microscopic stress field.

[0034] Step S52, calculating the temperature, stress and time-dependent fiber axial displacement and matrix axial displacement at the matrix crack plane based on the temperature, stress and time-dependent fiber axial displacement and matrix axial displacement and the fiber and matrix microscopic stress field.

[0035] Step S6, according to the temperature, stress and time-dependent fiber axial displacement and matrix axial displacement at the matrix crack plane, the temperature, stress and time-dependent interface debonding length is calculated using the fracture mechanics interface debonding criterion.

[0036] Step S7: Calculate the matrix crack opening displacement according to the temperature, stress and time-dependent interface debonding length.

[0037] In order to make the technical solution of this embodiment clearer, the specific implementation process of the technical solution of this embodiment is described in detail below in the form of examples. The specific implementation steps are as follows.

[0038] (1) Obtain basic data and establish an interfacial phase oxidation model for fiber-reinforced ceramic matrix composites based on the thermal-mechanical-oxygen coupling mechanism.

[0039] In this embodiment, under the action of heat-mechanics-oxygen coupling, the carbon interface phase on the fiber surface reacts with oxygen, causing the interface phase to oxidize, and the interface oxidation length l o It is a function of temperature and time, and the expression is as follows.

[0040] (1).

[0041] in, is the interface oxidation length, is the interface phase oxidation model constant, is the oxidation time, is the Kelvin temperature,α and β is the temperature-dependent oxidation parameter and is calculated using the following formula.

[0042] (2).

[0043] (3).

[0044] (2) According to the damage state reflected by the interfacial phase oxidation model of fiber-reinforced ceramic matrix composites, a unit cell model of fiber-reinforced ceramic matrix composites is established to obtain the temperature and time-dependent fiber and matrix microscopic stress field of fiber-reinforced ceramic matrix composites.

[0045] In this embodiment, in the microscopic stress field between the fiber and the matrix, the expressions of the temperature- and time-dependent fiber axial stress and matrix axial stress are as follows, respectively.

[0046] (4).

[0047] (5).

[0048] in, is the temperature and time dependent fiber axial stress, is the temperature and time dependent matrix axial stress, is the volume content ratio of fiber to matrix, The fibers on the matrix crack plane bear the stress. is stress, is the length along the fiber axis, is the fiber radius, is the temperature and time dependent interfacial oxidation length, is the shear stress in the interface oxidation zone, is the interface oxidation length, is the oxidation time, is the Kelvin temperature, is the temperature and time dependent matrix crack length, is the temperature and time dependent interfacial debonding length, is the shear stress in the interface debonding zone, are model parameters, is the stress in the fiber bonding area, is the stress in the bonding area of ​​the substrate, is the shear lag model parameter.

[0049] (3) Based on the fiber-matrix microscopic stress field and the matrix random cracking model, the temperature, stress and time-dependent matrix crack length is calculated.

[0050] In this embodiment, the temperature, stress and time dependent matrix crack length is calculated using the following formula.

[0051] (6).

[0052] in, is the temperature, stress and time dependent matrix crack length, is the temperature and time dependent matrix crack length, is the saturated nominal crack spacing, is the ratio of the interfacial shear stress between the oxidation zone and the debonding zone, is the fiber radius, is the ratio of the Young's modulus of the matrix to the Young's modulus of the composite material, is the shear stress in the interface debonding zone, is the temperature and time dependent interfacial oxidation length, is the interface oxidation length, is stress, is the oxidation time, is the Kelvin temperature, is the volume content ratio of fiber to matrix, is the matrix cracking characteristic stress, is the initial matrix cracking stress, is the thermal residual stress, is the matrix Weibull modulus.

[0053] (4) Based on the temperature, stress and time-dependent matrix crack length and the fiber and matrix microscopic stress fields, the temperature, stress and time-dependent fiber axial displacement and matrix axial displacement are calculated.

[0054] In this embodiment, the temperature, stress and time-dependent fiber axial displacement are calculated using the following formula.

[0055] (7).

[0056] In this embodiment, the temperature, stress and time-dependent axial displacement of the substrate is calculated using the following formula.

[0057] (8).

[0058] in, is the temperature, stress and time dependent fiber axial displacement, is the temperature, stress and time dependent matrix axial displacement, is stress, is the length along the fiber axis, is the oxidation time, is the Kelvin temperature, The fibers on the matrix crack plane bear the stress. is the fiber radius, is the matrix crack length, is the fiber elastic modulus, is the matrix elastic modulus, is the temperature, stress and time dependent interfacial debonding length, is the temperature and time dependent interfacial oxidation length, is the temperature, stress and time dependent matrix crack length, is the fiber axial stress in the interface bonding zone, is the friction shear stress in the interface oxidation zone, is the friction shear stress in the interface debonding zone, are model parameters, is the volume content ratio of fiber to matrix, is the axial stress of the matrix in the interface bonding area.

[0059] (5) Based on the temperature, stress and time-dependent fiber axial displacement and matrix axial displacement as well as the microscopic stress field of the fiber and matrix, the temperature, stress and time-dependent fiber axial displacement and matrix axial displacement at the matrix crack plane are calculated.

[0060] In this embodiment, at the matrix crack plane ( ), the expressions for the temperature, stress and time dependent fiber and matrix axial displacements are as follows.

[0061] (9).

[0062] (10).

[0063] in, is the temperature, stress and time-dependent fiber axial displacement at the matrix crack plane, is the temperature, stress and time-dependent matrix axial displacement at the matrix crack plane, is stress, is the length along the fiber axis, represents the matrix crack plane, is the oxidation time, is the Kelvin temperature, The fibers on the matrix crack plane bear the stress. is the fiber elastic modulus, is the matrix elastic modulus, is the fiber radius, is the temperature, stress and time dependent interfacial debonding length, is the temperature and time dependent interfacial oxidation length, is the temperature, stress and time dependent matrix crack length, is the fiber axial stress in the interface bonding zone, is the friction shear stress in the interface oxidation zone, is the friction shear stress in the interface debonding zone, is the interface shear stress, are model parameters, is the volume content ratio of fiber to matrix, is the axial stress of the matrix in the interface bonding area.

[0064] (6) Based on the temperature, stress and time-dependent fiber axial displacement and matrix axial displacement at the matrix crack plane, the temperature, stress and time-dependent interface debonding length is calculated using the fracture mechanics interface debonding criterion.

[0065] In this embodiment, the expression of the fracture mechanics interface debonding criterion is as follows.

[0066] (11).

[0067] in, is the interfacial debonding energy, The fibers on the matrix crack plane bear the stress. is the temperature, stress and time dependent fiber axial displacement in the matrix crack plane, is the temperature, stress and time dependent fiber relative displacement to the matrix, is stress, is the length along the fiber axis, represents the matrix crack plane, is the oxidation time, is the Kelvin temperature, is the fiber radius, is the interface debonding length, Denotes partial derivative operation. The temperature, stress and time-dependent interface debonding length is obtained from the axial displacement of the fiber and matrix, and the expression is as follows.

[0068] (12).

[0069] in, is the temperature, stress and time dependent interfacial debonding length, is the ratio of the interfacial shear stress between the oxidation zone and the debonding zone, is the temperature and time dependent interfacial oxidation length, is the volume content ratio of fiber to matrix, is the ratio of the Young's modulus of the matrix to the Young's modulus of the composite material, is the friction shear stress in the interface debonding zone, are model parameters, is the fiber elastic modulus, is the matrix volume fraction.

[0070] (7) The matrix crack opening displacement is calculated based on the temperature, stress, and time-dependent interface debonding length.

[0071] In this embodiment, the following formula is used to calculate the matrix crack opening displacement.

[0072] (13).

[0073] in, is the matrix crack opening displacement, The fibers on the matrix crack plane bear the stress. is the fiber elastic modulus, are model parameters, is the ratio of the Young's modulus of the matrix to the Young's modulus of the composite material, is the temperature, stress and time dependent interfacial debonding length, is the temperature and time dependent interfacial oxidation length, is the interface oxidation length, is stress, is the oxidation time, is the Kelvin temperature, is the temperature, stress and time dependent matrix crack length, is the fiber radius, is the fiber axial stress in the interface bonding zone, is the friction shear stress in the interface oxidation zone, is the friction shear stress in the interface debonding zone, is the volume content ratio of fiber to matrix, is the axial stress of the matrix in the interface bonding area, is the ratio of the Young's modulus of the matrix to the Young's modulus of the composite material, is the matrix volume fraction, is the damage factor corresponding to the interface debonding length that depends on temperature, stress and time, is the damage factor corresponding to the matrix crack length that is dependent on temperature, stress and time.

[0074] The fiber-reinforced ceramic matrix composite material of this embodiment is tested by taking SiC / SiC composite material as an example, and the crack opening displacement comparison test is carried out at the test temperature of 800°C for 1 hour, 2 hours and 3 hours respectively. Figure 2 The predicted results of the matrix crack opening displacement versus stress curve of SiC / SiC composite materials under the action of heat-mechanics-oxygen coupling are shown. Figure 2 It can be seen intuitively that with the increase of oxidation time, the crack opening displacement increases under the same stress, and with the increase of stress, the crack opening displacement also increases at the same temperature.

[0075] In an exemplary embodiment, a fiber-reinforced ceramic matrix composite material crack opening displacement prediction system is also provided, including a memory and a processor, wherein a computer program is stored in the memory, and when the processor executes the computer program, the above-mentioned fiber-reinforced ceramic matrix composite material crack opening displacement prediction method is implemented.

[0076] In this embodiment, based on the thermal-mechanical-oxygen coupling mechanism and the basic data of the fiber-reinforced ceramic matrix composite material, an interface phase oxidation model is first established; then, based on the interface phase oxidation model, a unit cell model of the fiber-reinforced ceramic matrix composite material is established to obtain the microscopic stress field between the fiber and the matrix; then, based on the microscopic stress field between the fiber and the matrix and the random cracking model of the matrix, the temperature, stress and time-dependent matrix crack length is calculated; then, based on the temperature, stress and time-dependent matrix crack length and the fiber and matrix microscopic stress field, the temperature, stress and time-dependent fiber axial displacement and matrix axial displacement are calculated, so as to further calculate the temperature, stress and time-dependent fiber axial displacement and matrix axial displacement at the matrix crack plane; then, based on the temperature, stress and time-dependent fiber axial displacement and matrix axial displacement at the matrix crack plane, the temperature, stress and time-dependent interface debonding length is calculated using the fracture mechanics interface debonding criterion; finally, based on the temperature, stress and time-dependent interface debonding length, the matrix crack opening displacement is calculated.

[0077] The technical features of the above embodiments may be combined arbitrarily. To make the description concise, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0078] This article uses specific examples to illustrate the principles and implementation methods of this application. The description of the above embodiments is only used to help understand the method and core ideas of this application. At the same time, for those skilled in the art, according to the ideas of this application, there will be changes in the specific implementation methods and application scope. In summary, the content of this specification should not be understood as limiting this application.

Claims

1. A method for predicting crack opening displacement of fiber reinforced ceramic matrix composite materials, characterized in that: The fiber reinforced ceramic matrix composite crack opening displacement prediction method comprises: Obtaining basic data of the fiber-reinforced ceramic matrix composite material; the basic data includes test temperature, fiber radius, fiber elastic modulus, matrix elastic modulus and volume percentage of fiber to matrix; According to the basic data, an interfacial phase oxidation model of the fiber-reinforced ceramic matrix composite material is established; the interfacial phase oxidation model refers to a model of temperature- and time-dependent interfacial phase oxidation of the fiber-reinforced ceramic matrix composite material based on a thermal-mechanical-oxygen coupling mechanism; The expression of the interface phase oxidation model is: ； in, is the interface oxidation length, is the interface phase oxidation model constant, is the oxidation time, is the Kelvin temperature, α and β is the temperature-dependent oxidation parameter; According to the interface phase oxidation model, a unit cell model of the fiber-reinforced ceramic matrix composite material is established, and the temperature- and time-dependent fiber and matrix microscopic stress field is determined according to the unit cell model; The expression of the microscopic stress field between the fiber and the matrix is: ； ； in, is the temperature and time dependent fiber axial stress, is the temperature and time dependent matrix axial stress, is the volume content ratio of fiber to matrix, The fibers on the matrix crack plane bear the stress. is stress, is the length along the fiber axis, is the fiber radius, is the temperature and time dependent interfacial oxidation length, is the shear stress in the interface oxidation zone, is the interface oxidation length, is the oxidation time, is the Kelvin temperature, is the temperature and time dependent matrix crack length, is the temperature and time dependent interfacial debonding length, is the shear stress in the interface debonding zone, are model parameters, is the stress in the fiber bonding area, is the stress in the bonding area of ​​the substrate, is the shear lag model parameter; Calculating the temperature, stress and time-dependent matrix crack length according to the fiber and matrix microscopic stress field and matrix random cracking model; the matrix random cracking model refers to a model in which internal defects of the matrix cause randomness in the crack position of the fiber-reinforced ceramic matrix composite material under load; The temperature, stress and time dependent matrix crack length was calculated using the following formula: ； in, is the temperature, stress and time dependent matrix crack length, is the temperature and time dependent matrix crack length, is the saturated nominal crack spacing, is the ratio of the interfacial shear stress between the oxidation zone and the debonding zone, is the fiber radius, is the ratio of the Young's modulus of the matrix to the Young's modulus of the composite material, is the shear stress in the interface debonding zone, is the temperature and time dependent interfacial oxidation length, is the interface oxidation length, is stress, is the oxidation time, is the Kelvin temperature, is the volume content ratio of fiber to matrix, is the matrix cracking characteristic stress, is the initial matrix cracking stress, is the thermal residual stress, is the matrix Weibull modulus; Calculating the temperature, stress and time-dependent fiber axial displacement and matrix axial displacement at the matrix crack plane according to the temperature, stress and time-dependent matrix crack length and the fiber and matrix microscopic stress field; According to the temperature, stress and time-dependent fiber axial displacement and matrix axial displacement at the matrix crack plane, the temperature, stress and time-dependent interface debonding length is calculated using the fracture mechanics interface debonding criterion; Calculating the matrix crack opening displacement based on the temperature, stress and time-dependent interface debonding length; The matrix crack opening displacement is calculated using the following formula: ； in, is the matrix crack opening displacement, The fibers on the matrix crack plane bear the stress. is the fiber elastic modulus, are model parameters, is the ratio of the Young's modulus of the matrix to the Young's modulus of the composite material, is the temperature, stress and time dependent interfacial debonding length, is the temperature and time dependent interfacial oxidation length, is the interface oxidation length, is stress, is the oxidation time, is the Kelvin temperature, is the temperature, stress and time dependent matrix crack length, is the fiber radius, is the fiber axial stress in the interface bonding zone, is the friction shear stress in the interface oxidation zone, is the friction shear stress in the interface debonding zone, is the volume content ratio of fiber to matrix, is the axial stress of the matrix in the interface bonding area, is the ratio of the Young's modulus of the matrix to the Young's modulus of the composite material, is the matrix volume fraction, is the damage factor corresponding to the interface debonding length that depends on temperature, stress and time, is the damage factor corresponding to the matrix crack length that is dependent on temperature, stress and time.

2. The method for predicting crack opening displacement of fiber reinforced ceramic matrix composite materials according to claim 1, characterized in that: According to the temperature, stress and time-dependent matrix crack length and the fiber and matrix microscopic stress field, the temperature, stress and time-dependent fiber axial displacement and matrix axial displacement at the matrix crack plane are calculated, specifically including: Calculating the temperature, stress and time-dependent fiber axial displacement and matrix axial displacement according to the temperature, stress and time-dependent matrix crack length and the fiber and matrix microscopic stress field; The temperature, stress and time-dependent fiber axial displacement and matrix axial displacement at the matrix crack plane are calculated based on the temperature, stress and time-dependent fiber axial displacement and matrix axial displacement and the fiber and matrix microscopic stress field.

3. The method for predicting crack opening displacement of fiber reinforced ceramic matrix composite materials according to claim 2, characterized in that: The temperature, stress and time dependent fiber axial displacement and matrix axial displacement are calculated using the following formula: ； ； in, is the temperature, stress and time dependent fiber axial displacement, is the temperature, stress and time dependent matrix axial displacement, is stress, is the length along the fiber axis, is the oxidation time, is the Kelvin temperature, The fibers on the matrix crack plane bear the stress. is the fiber radius, is the matrix crack length, is the fiber elastic modulus, is the matrix elastic modulus, is the temperature, stress and time dependent interfacial debonding length, is the temperature and time dependent interfacial oxidation length, is the temperature, stress and time dependent matrix crack length, is the fiber axial stress in the interface bonding zone, is the friction shear stress in the interface oxidation zone, is the friction shear stress in the interface debonding zone, are model parameters, is the volume content ratio of fiber to matrix, is the axial stress of the matrix in the interface bonding area.

4. The method for predicting crack opening displacement of fiber reinforced ceramic matrix composite materials according to claim 2, characterized in that: The temperature, stress and time-dependent fiber axial displacement and matrix axial displacement at the matrix crack plane are calculated using the following formula: ； ； in, is the temperature, stress and time-dependent fiber axial displacement at the matrix crack plane, is the temperature, stress and time-dependent matrix axial displacement at the matrix crack plane, is stress, is the length along the fiber axis, represents the matrix crack plane, is the oxidation time, is the Kelvin temperature, The fibers on the matrix crack plane bear the stress. is the fiber elastic modulus, is the matrix elastic modulus, is the fiber radius, is the temperature, stress and time dependent interfacial debonding length, is the temperature and time dependent interfacial oxidation length, is the temperature, stress and time dependent matrix crack length, is the fiber axial stress in the interface bonding zone, is the friction shear stress in the interface oxidation zone, is the friction shear stress in the interface debonding zone, is the interface shear stress, are model parameters, is the volume content ratio of fiber to matrix, is the axial stress of the matrix in the interface bonding area.

5. The method for predicting crack opening displacement of fiber reinforced ceramic matrix composite materials according to claim 1, characterized in that: The temperature, stress and time dependent interfacial debonding length was calculated using the following formula: ； ； in, is the interfacial debonding energy, The fibers on the matrix crack plane bear the stress. is the temperature, stress and time dependent fiber axial displacement in the matrix crack plane, is the temperature, stress and time dependent fiber relative displacement to the matrix, is stress, is the length along the fiber axis, represents the matrix crack plane, is the oxidation time, is the Kelvin temperature, is the interface debonding length, is the temperature, stress and time dependent interfacial debonding length, is the ratio of the interfacial shear stress between the oxidation zone and the debonding zone, is the temperature and time dependent interfacial oxidation length, is the fiber radius, is the volume content ratio of fiber to matrix, is the ratio of the Young's modulus of the matrix to the Young's modulus of the composite material, is the friction shear stress in the interface debonding zone, are model parameters, is the fiber elastic modulus, represents the partial derivative operation, is the matrix volume fraction.

6. A fiber-reinforced ceramic matrix composite crack opening displacement prediction system, comprising: A memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the method for predicting crack opening displacement of a fiber-reinforced ceramic matrix composite material according to any one of claims 1 to 5.

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