CN113408069A - Size design method for ceramic matrix composite and high-temperature alloy mixed connection structure countersunk head bolt based on maximum failure load - Google Patents

Size design method for ceramic matrix composite and high-temperature alloy mixed connection structure countersunk head bolt based on maximum failure load Download PDF

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CN113408069A
CN113408069A CN202110685985.6A CN202110685985A CN113408069A CN 113408069 A CN113408069 A CN 113408069A CN 202110685985 A CN202110685985 A CN 202110685985A CN 113408069 A CN113408069 A CN 113408069A
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ceramic matrix
matrix composite
countersunk head
temperature alloy
failure
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孙茜
赵淑媛
孙新阳
李明瑞
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Harbin Institute of Technology
Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC
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Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC
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Abstract

The invention provides a size design method of a ceramic matrix composite and high-temperature alloy mixed connection structure countersunk head bolt based on maximum failure load. The method is characterized in that a Fortran language is adopted to compile a nonlinear constitutive model, a failure criterion and a material degradation model into a user subprogram UMAT file, the user subprogram UMAT file is embedded into ABAQUS finite element software, the design of the maximum high-temperature failure load of the geometric dimension and the connecting structure of the ceramic matrix composite material and the high-temperature alloy countersunk head bolt based on progressive damage analysis is realized, an interface language Python language of commercial finite element software ABAQUS is used for secondary development, an interface window plug-in is developed, a GUI interface is generated, and a fast and efficient technical support is provided for structural simulation parametric analysis and batch processing. The invention can greatly reduce the test cost, save resources and energy, greatly improve the structural efficiency of the connecting structure and has good practical application potential.

Description

Size design method for ceramic matrix composite and high-temperature alloy mixed connection structure countersunk head bolt based on maximum failure load
Technical Field
The invention relates to a size design method of a ceramic matrix composite and high-temperature alloy mixed connection structure countersunk head bolt based on maximum failure load, and belongs to the technical field of ceramic matrix composite structure design.
Background
The carbon fiber reinforced silicon carbide ceramic matrix composite has a series of excellent performances such as high strength, high hardness, high temperature resistance, ablation resistance, low density and the like, and becomes a new generation high temperature thermal structure with great development prospect in the field of aerospace. Because the C/SiC composite material structure with large size and complex structure is very difficult to manufacture and high in manufacturing cost, the bolt connection structure with the characteristics of repeated disassembly, high load transfer capacity, high reliability, high cost performance and the like is widely applied to aerospace vehicles, especially hypersonic aircraft. Hypersonic aircraft components with aerodynamic profile and stealth performance requirements are more prone to composite countersunk head bolts as the connecting components. Obviously, the structure of countersunk head bolt connection is more complex relative to the structure of raised head bolt connection, the distribution of surrounding stress is more complex, and the strength analysis and design of the bolt connecting piece play a crucial role in improving the bearing efficiency of the structure and maintaining the structural integrity, and become a key technology in the structural design of the aircraft. From the current research situation and the literature retrieval situation at home and abroad, most researches on the influence of the countersunk head bolt fastener on the mechanical property of the connecting structure are concentrated on the fiber reinforced resin matrix composite material mechanical connecting structure, the researches on the design aspect of the geometric dimension of the countersunk head bolt of the ceramic matrix composite material mechanical connecting structure are deficient, and the design of the geometric dimension of the countersunk head bolt of the ceramic matrix composite material mechanical connecting structure through finite element simulation has important engineering practical significance for improving the bearing efficiency of the structure and ensuring the service safety of the connecting structure.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides the method for designing the size of the ceramic matrix composite and high-temperature alloy hybrid connecting structure countersunk bolt based on the maximum failure load, the geometric sizes of the ceramic matrix composite and the high-temperature alloy countersunk bolt and the maximum high-temperature failure load of the connecting structure can be designed, the test cost can be greatly reduced, the resources and the energy are saved, the structural efficiency of the connecting structure is greatly improved, and the method is suitable for guiding the assembly and application process of the composite material in actual production.
A design method for the size of a ceramic matrix composite and high-temperature alloy mixed connection structure countersunk bolt based on the maximum failure load comprises the following steps:
s100, setting geometric parameters of the ceramic matrix composite and high-temperature alloy countersunk head bolt fastener, and setting the notch depth and the design range of the height of the conical section of the countersunk head bolt;
s200, keeping the depth of the opening of the countersunk head screw unchanged, and giving a certain value in the height design range of the conical section of the countersunk head screw;
s300, according to the geometric parameters, the assembly parameters and the environment temperature of the ceramic matrix composite and the high-temperature alloy countersunk head bolt fastener, establishing a three-dimensional finite element analysis model of the ceramic matrix composite and the high-temperature alloy countersunk head bolt fastener under the high-temperature uniaxial tension loading condition by adopting ABAQUS software;
s400, selecting a non-linear constitutive model, a failure criterion and a degradation model of the ceramic matrix composite, establishing a progressive damage analysis model of the C/SiC composite structure, performing stress analysis, and starting to call the stress sigma of the unit integration point in the kth increment stepk；
S500, substituting stress of the integration points of the ceramic matrix composite material unit into a failure criterion for judgment, if the failure criterion is met, failing the material unit point, and at the moment, performing material processing according to a degradation modelMaterial rigidity is degraded; if the failure criterion is not met, the material is not damaged, and the rigidity of the material is not changed at the momentk+1＝CkUpdate the stress σk+1＝σk+Ck+1·ΔεkWherein, wherein;
s600, judging whether damage in the composite material structure causes structural damage or not; if the structure is not damaged, increasing the increment of the mechanical load, and returning to S300; if the structure is damaged, the structure loses the bearing capacity and stops analyzing;
s700, obtaining a high-temperature failure load and a damage failure mode of the C/SiC ceramic matrix composite and the high-temperature alloy countersunk head bolt fastener under given structural geometric parameters under a single working condition;
s800, selecting other values of a certain design variable required by the countersunk head screw, repeating S200 to S700, and obtaining the high-temperature failure load of the C/SiC ceramic matrix composite material and the high-temperature alloy countersunk head screw fastener, which changes along with the design variable;
s900, selecting a design variable value with the largest high-temperature failure load to complete the univariate geometric design of the C/SiC ceramic matrix composite material and the high-temperature alloy countersunk head bolt fastener countersunk head screw;
s1000, giving the depth of the opening of the countersunk head screw with the maximum high-temperature failure load, and selecting a certain value in the height design range of the conical section of the countersunk head screw;
and S1100, repeating S300 to S900, finishing the geometric design of the countersunk head screw of the connecting structural member of the C/SiC ceramic matrix composite and the high-temperature alloy countersunk head bolt, and obtaining the maximum high-temperature failure load of the connecting structure.
Further, in S300, the ABAQUS software is used to establish a three-dimensional finite element analysis model under the high-temperature uniaxial tension loading condition of the ceramic matrix composite and superalloy countersunk head bolt fastener, and the step of establishing the three-dimensional finite element analysis model is as follows:
s310, according to the geometric parameters of the ceramic matrix composite and the high-temperature alloy countersunk head bolt fastener, establishing a three-dimensional geometric model of the ceramic matrix composite and the high-temperature alloy countersunk head bolt fastener by using ABAQUS software;
s320, adopting an eight-node linear reduction integral hexahedron unit C3D8R and setting an enhanced hourglass control to perform structured grid division on the structure;
s330, defining 5 groups of contact pairs in ABAQUS according to the contact relation among the high-temperature alloy plate, the composite material plate and the bolt, wherein the contact pairs are respectively the contact between an upper notch of the screw and an upper notch of the composite material plate, the contact between the middle diameter surface of the screw and the middle diameter surface of the high-temperature alloy plate, the contact between the lower surface of the composite material plate and the upper surface of the alloy plate, the contact between the upper surface of the nut and the lower surface of the alloy plate, and the addition of friction force to each contact surface in the interaction property;
s340, directly applying axial pretightening force on the cross section of the Bolt rod by using a Bolt load command in ABAQUS, applying the gap amount of the nail holes by setting the assembly value of a contact pair between the nail holes, ensuring that the pretightening force is not reduced to be below 0N at high temperature, and applying uniform high-temperature load to the whole connecting structure;
s350, applying solid support restraint to all directions of the end part of the high-temperature alloy plate, applying mechanical load to the X direction of the end part of the ceramic matrix composite plate, and restraining the displacement in the other two directions.
Further, in S400, the implementation process of establishing the nonlinear constitutive model according to the mechanical property test result of the C/SiC composite material is as follows:
s411, obtaining a test stress-strain curve of the C/SiC composite material through uniaxial tension and uniaxial shear loading and unloading tests in the main direction of the C/SiC composite material;
s412, performing polynomial fitting on the data of the uniaxial tension and uniaxial shear stress-relief strain test of the ceramic matrix composite by adopting a high-order polynomial, and then deriving the fitting result:
Figure BDA0003124635250000031
Figure BDA0003124635250000032
Figure BDA0003124635250000033
Figure BDA0003124635250000041
in the formula:
Figure BDA0003124635250000042
the elastic modulus of the ceramic matrix composite material in the process of tensile loading in the main direction;
Figure BDA0003124635250000043
the modulus of elasticity of the material in the process of unloading after the material is stretched in the main direction or before the material is reloaded to an unloading point;
Figure BDA0003124635250000044
the shear modulus in a 1-2 plane in the process of stretching and loading in the main direction of the material;
Figure BDA0003124635250000045
the shear modulus in the plane of the material 1-2 in the unloading process after the material is stretched in the main direction;
Figure BDA0003124635250000046
the maximum tensile strain in the process of tensile loading in the main direction of the material;
Figure BDA0003124635250000047
the strain value from tensile load to fracture in the main direction of the material;
Figure BDA0003124635250000048
the maximum shear strain in a 1-2 plane in the process of stretching, loading and unloading in the main direction of the material;
Figure BDA0003124635250000049
is the in-plane shear fracture strain of the material, Ai，Bi(i 1,2.. 7.) is a shape parameter of a logic functionCounting; p is a radical ofi,xi(i ═ 1,2) are shape parameters of the logistic function;
s413, determining the basic engineering elasticity parameter value of the ceramic matrix composite nonlinear model by the fitting curve, namely:
Figure BDA00031246352500000410
in the formula (I), the compound is shown in the specification,
Figure BDA00031246352500000411
the strain value from the compressive load to the fracture in the main direction of the material;
Figure BDA00031246352500000412
and finally determining the nonlinear constitutive model of the C/SiC ceramic matrix composite material for the stress of the crack closing point in the process of stretching, loading and unloading the material in the main direction of the material.
Further, in S400, the implementation process of predicting the composite failure state by applying the ceramic matrix composite failure criterion is as follows:
s421, reading the unit integral point stress sigma of the ceramic matrix composite and the high-temperature alloy countersunk head bolt connection structure composite platek；
S422, substituting the stress value into a Tsai-Wu strength criterion to judge the failure of the C/SiC composite material unit point, wherein the specific form of the Tsai-Wu strength criterion is as follows:
Figure BDA00031246352500000413
Figure BDA0003124635250000051
Figure BDA0003124635250000052
in the formula:
Figure BDA0003124635250000053
the total number of intensity factors representing the intensity criteria of Tsai-Wu,
Figure BDA0003124635250000054
is the intensity factor component, X, of each stress directiontAnd XcTensile and compressive strengths in the 1-direction of the material, YtAnd YcTensile and compressive strength in the 2-direction, ZtAnd ZcTensile and compressive strengths in the 3 directions, S12、S13、S23Representing the shear strength in three directions, σ1、σ2、σ3And τ12、τ13、τ23Respectively representing the component of the unit stress in different directions, F1、F2、F3、F11、F22、F33、F44、F55、F66、F12、F23、F13All are intermediate variables of a judgment relation;
and S423, updating the unit failure state variable.
Further, in S400, the implementation process of performing material stiffness degradation on the failed material according to the degradation model includes:
s431, when the material unit is judged to be invalid, determining that the rigidity value of the material unit in each direction is reduced to 1% of the original rigidity value, and updating the material attribute;
s432, updating a material rigidity matrix, Ck+1＝CdWherein C represents the post-injury material stiffness;
s433, updating stress sigma of damaged materialk+1＝Ck+1·(εk+Δεk) Wherein, epsilonkStrain, Δ ε, in the kth incremental stepkIs the strain increment;
and S434, executing S500.
The invention has the beneficial effects that: compared with the existing ceramic matrix composite material connection structure experiment characterization means, the prediction method is quick and efficient, can obviously save test time consumption and cost, gets rid of the restriction of expensive test equipment and complex test links, has certain universality, provides important technical guidance for strength analysis and design of the ceramic matrix composite material and high-temperature alloy countersunk bolt connection structure, has good practical application potential, and can be popularized and applied to various technical fields of aerospace, military and national defense, energy and chemical engineering and the like.
Drawings
FIG. 1 is a schematic view of the ceramic matrix composite and superalloy countersunk head bolt connection;
FIG. 2 is a flow chart of progressive damage analysis of a ceramic matrix composite and superalloy countersunk head bolt connection structure;
FIG. 3 is a geometric schematic of a superalloy countersunk head bolt.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention solves the technical problem and provides a method for designing the size of a countersunk bolt of a ceramic matrix composite and high-temperature alloy mixed connection structure based on the maximum failure load, which comprises the following steps:
s100, setting geometric parameters of the ceramic matrix composite and high-temperature alloy countersunk head bolt fastener, and setting the notch depth and the design range of the height of the conical section of the countersunk head bolt;
s200, keeping the depth of the opening of the countersunk head screw unchanged, and giving a certain value in the height design range of the conical section of the countersunk head screw;
s300, according to the geometric parameters, the assembly parameters and the environment temperature of the ceramic matrix composite and the high-temperature alloy countersunk head bolt fastener, establishing a three-dimensional finite element analysis model of the ceramic matrix composite and the high-temperature alloy countersunk head bolt fastener under the high-temperature uniaxial tension loading condition by adopting ABAQUS software;
s400, selecting a non-linear constitutive model, a failure criterion and a degradation model of the ceramic matrix composite, establishing a progressive damage analysis model of the C/SiC composite structure, performing stress analysis, and starting to call the stress sigma of the unit integration point in the kth increment stepk；
S500, substituting stress of the integration points of the ceramic matrix composite material unit into a failure criterion for judgment, if the failure criterion is met, the material unit point fails, and at the moment, performing material rigidity degradation according to a degradation model; if the failure criterion is not met, the material is not damaged, and the rigidity of the material is not changed at the momentk+1＝CkUpdate the stress σk+1＝σk+Ck+1·ΔεkWherein, wherein;
s600, judging whether damage in the composite material structure causes structural damage or not; if the structure is not damaged, increasing the increment of the mechanical load, and returning to S300; if the structure is damaged, the structure loses the bearing capacity and stops analyzing;
s700, obtaining a high-temperature failure load and a damage failure mode of the C/SiC ceramic matrix composite and the high-temperature alloy countersunk head bolt fastener under given structural geometric parameters under a single working condition;
s800, selecting other values of a certain design variable required by the countersunk head screw, repeating S200 to S700, and obtaining the high-temperature failure load of the C/SiC ceramic matrix composite material and the high-temperature alloy countersunk head screw fastener, which changes along with the design variable;
s900, selecting a design variable value with the largest high-temperature failure load to complete the univariate geometric design of the C/SiC ceramic matrix composite material and the high-temperature alloy countersunk head bolt fastener countersunk head screw;
s1000, giving the depth of the opening of the countersunk head screw with the maximum high-temperature failure load, and selecting a certain value in the height design range of the conical section of the countersunk head screw;
and S1100, repeating S300 to S900, finishing the geometric design of the countersunk head screw of the connecting structural member of the C/SiC ceramic matrix composite and the high-temperature alloy countersunk head bolt, and obtaining the maximum high-temperature failure load of the connecting structure.
Further, in S300, the ABAQUS software is used to establish a three-dimensional finite element analysis model under the high-temperature uniaxial tension loading condition of the ceramic matrix composite and superalloy countersunk head bolt fastener, and the step of establishing the three-dimensional finite element analysis model is as follows:
s310, according to the geometric parameters of the ceramic matrix composite and the high-temperature alloy countersunk head bolt fastener, establishing a three-dimensional geometric model of the ceramic matrix composite and the high-temperature alloy countersunk head bolt fastener by using ABAQUS software;
s320, adopting an eight-node linear reduction integral hexahedron unit C3D8R and setting an enhanced hourglass control to perform structured grid division on the structure;
s330, defining 5 groups of contact pairs in ABAQUS according to the contact relation among the high-temperature alloy plate, the composite material plate and the bolt, wherein the contact pairs are respectively the contact between an upper notch of the screw and an upper notch of the composite material plate, the contact between the middle diameter surface of the screw and the middle diameter surface of the high-temperature alloy plate, the contact between the lower surface of the composite material plate and the upper surface of the alloy plate, the contact between the upper surface of the nut and the lower surface of the alloy plate, and the addition of friction force to each contact surface in the interaction property;
s340, directly applying axial pretightening force on the cross section of the Bolt rod by using a Bolt load command in ABAQUS, applying the gap amount of the nail holes by setting the assembly value of a contact pair between the nail holes, ensuring that the pretightening force is not reduced to be below 0N at high temperature, and applying uniform high-temperature load to the whole connecting structure;
s350, applying solid support restraint to all directions of the end part of the high-temperature alloy plate, applying mechanical load to the X direction of the end part of the ceramic matrix composite plate, and restraining the displacement in the other two directions.
Further, in S400, the implementation process of establishing the nonlinear constitutive model according to the mechanical property test result of the C/SiC composite material is as follows:
s411, obtaining a test stress-strain curve of the C/SiC composite material through uniaxial tension and uniaxial shear loading and unloading tests in the main direction of the C/SiC composite material;
s412, performing polynomial fitting on the data of the uniaxial tension and uniaxial shear stress-relief strain test of the ceramic matrix composite by adopting a high-order polynomial, and then deriving the fitting result:
Figure BDA0003124635250000081
Figure BDA0003124635250000082
Figure BDA0003124635250000083
Figure BDA0003124635250000084
in the formula:
Figure BDA0003124635250000085
the elastic modulus of the ceramic matrix composite material in the process of tensile loading in the main direction;
Figure BDA0003124635250000086
the modulus of elasticity of the material in the process of unloading after the material is stretched in the main direction or before the material is reloaded to an unloading point;
Figure BDA0003124635250000087
the shear modulus in a 1-2 plane in the process of stretching and loading in the main direction of the material;
Figure BDA0003124635250000088
the shear modulus in the plane of the material 1-2 in the unloading process after the material is stretched in the main direction;
Figure BDA0003124635250000089
during loading for stretching the material in the main directionMaximum tensile strain;
Figure BDA00031246352500000810
the strain value from tensile load to fracture in the main direction of the material;
Figure BDA00031246352500000811
the maximum shear strain in a 1-2 plane in the process of stretching, loading and unloading in the main direction of the material;
Figure BDA00031246352500000812
is the in-plane shear fracture strain of the material, Ai，Bi(i 1,2.., 7) is a shape parameter of the logic function; p is a radical ofi,xi(i ═ 1,2) are shape parameters of the logistic function;
s413, determining the basic engineering elasticity parameter value of the ceramic matrix composite nonlinear model by the fitting curve, namely:
Figure BDA0003124635250000091
in the formula (I), the compound is shown in the specification,
Figure BDA0003124635250000092
the strain value from the compressive load to the fracture in the main direction of the material;
Figure BDA0003124635250000093
and finally determining the nonlinear constitutive model of the C/SiC ceramic matrix composite material for the stress of the crack closing point in the process of stretching, loading and unloading the material in the main direction of the material.
Further, in S400, the implementation process of predicting the composite failure state by applying the ceramic matrix composite failure criterion is as follows:
s421, reading the unit integral point stress sigma of the ceramic matrix composite and the high-temperature alloy countersunk head bolt connection structure composite platek；
S422, substituting the stress value into a Tsai-Wu strength criterion to judge the failure of the C/SiC composite material unit point, wherein the specific form of the Tsai-Wu strength criterion is as follows:
Figure BDA0003124635250000094
Figure BDA0003124635250000095
Figure BDA0003124635250000101
in the formula:
Figure BDA0003124635250000102
the total number of intensity factors representing the intensity criteria of Tsai-Wu,
Figure BDA0003124635250000103
is the intensity factor component, X, of each stress directiontAnd XcTensile and compressive strengths in the 1-direction of the material, YtAnd YcTensile and compressive strength in the 2-direction, ZtAnd ZcTensile and compressive strengths in the 3 directions, S12、S13、S23Representing the shear strength in three directions, σ1、σ2、σ3And τ12、τ13、τ23Respectively representing unit stress components in different directions;
and S423, updating the unit failure state variable.
Further, in S400, the implementation process of performing material stiffness degradation on the failed material according to the degradation model includes:
s431, when the material unit is judged to be invalid, determining that the rigidity value of the material unit in each direction is reduced to 1% of the original rigidity value, and updating the material attribute;
s432, updating a material rigidity matrix, Ck+1＝CdWherein C represents the post-injury material stiffness;
s433, updating stress sigma of damaged materialk+1＝Ck+1·(εk+Δεk) Wherein, epsilonkStrain, Δ ε, in the kth incremental stepkIs the strain increment;
and S434, executing S500.
The invention adopts Fortran language to compile a nonlinear constitutive model, a failure criterion and a material degradation model into a user subprogram UMAT file, and embeds the UMAT file into ABAQUS finite element software to realize progressive damage analysis of a ceramic matrix composite material and a high-temperature alloy countersunk head bolt fastener under a high-temperature stretching condition, and realizes the geometric dimension of the ceramic matrix composite material and the high-temperature alloy countersunk head bolt and the maximum high-temperature failure load design of a connecting structure.
The above description is only a preferred embodiment of the method for designing the size of the countersunk head screw of the ceramic matrix composite and superalloy hybrid connection structure based on the maximum failure load, and the protection range of the method for designing the size of the countersunk head screw of the ceramic matrix composite and superalloy hybrid connection structure based on the maximum failure load is not limited to the above embodiments, and all technical schemes belonging to the idea belong to the protection range of the invention. It should be noted that several improvements and changes may be made by those skilled in the art without departing from the principle of the present invention, and such changes, modifications, substitutions and alterations should also be considered as the protection scope of the present invention.

Claims (5)

1. A design method for the size of a ceramic matrix composite and high-temperature alloy mixed connection structure countersunk bolt based on the maximum failure load is characterized by comprising the following steps:
s100, setting geometric parameters of the ceramic matrix composite and high-temperature alloy countersunk head bolt fastener, and setting the notch depth and the design range of the height of the conical section of the countersunk head bolt;
s200, keeping the depth of the opening of the countersunk head screw unchanged, and giving a certain value in the height design range of the conical section of the countersunk head screw;
s300, according to the geometric parameters, the assembly parameters and the environment temperature of the ceramic matrix composite and the high-temperature alloy countersunk head bolt fastener, establishing a three-dimensional finite element analysis model of the ceramic matrix composite and the high-temperature alloy countersunk head bolt fastener under the high-temperature uniaxial tension loading condition by adopting ABAQUS software;
s400, selecting a non-linear constitutive model, a failure criterion and a degradation model of the ceramic matrix composite, establishing a progressive damage analysis model of the C/SiC composite structure, performing stress analysis, and starting to call the stress sigma of the unit integration point in the kth increment stepk；
S500, substituting stress of the integration points of the ceramic matrix composite material unit into a failure criterion for judgment, if the failure criterion is met, the material unit point fails, and at the moment, performing material rigidity degradation according to a degradation model; if the failure criterion is not met, the material is not damaged, and the rigidity of the material is not changed at the momentk+1＝CkUpdate the stress σk+1＝σk+Ck+1·ΔεkWherein C represents a stiffness matrix of the material, σ represents stress, Δ ε represents strain increment, and superscript k represents an iteration increment step;
s600, judging whether damage in the composite material structure causes structural damage or not; if the structure is not damaged, increasing the increment of the mechanical load, and returning to S300; if the structure is damaged, the structure loses the bearing capacity and stops analyzing;
s700, obtaining a high-temperature failure load and a damage failure mode of the C/SiC ceramic matrix composite and the high-temperature alloy countersunk head bolt fastener under given structural geometric parameters under a single working condition;
s800, selecting other values of a certain design variable required by the countersunk head screw, repeating S200 to S700, and obtaining the high-temperature failure load of the C/SiC ceramic matrix composite material and the high-temperature alloy countersunk head screw fastener, which changes along with the design variable;
s900, selecting a design variable value with the largest high-temperature failure load to complete the univariate geometric design of the C/SiC ceramic matrix composite material and the high-temperature alloy countersunk head bolt fastener countersunk head screw;
s1000, giving the depth of the opening of the countersunk head screw with the maximum high-temperature failure load, and selecting a certain value in the height design range of the conical section of the countersunk head screw;
and S1100, repeating S300 to S900, finishing the geometric design of the countersunk head screw of the connecting structural member of the C/SiC ceramic matrix composite and the high-temperature alloy countersunk head bolt, and obtaining the maximum high-temperature failure load of the connecting structure.
2. The method for designing the size of the countersunk head bolt of the ceramic matrix composite and superalloy hybrid connection structure based on the maximum failure load according to claim 1, wherein in S300, ABAQUS software is used to build a three-dimensional finite element analysis model of the ceramic matrix composite and superalloy countersunk head bolt fastener under the high temperature uniaxial tensile loading condition, and the step of building the three-dimensional finite element analysis model is as follows:
s310, according to the geometric parameters of the ceramic matrix composite and the high-temperature alloy countersunk head bolt fastener, establishing a three-dimensional geometric model of the ceramic matrix composite and the high-temperature alloy countersunk head bolt fastener by using ABAQUS software;
s320, adopting an eight-node linear reduction integral hexahedron unit C3D8R and setting an enhanced hourglass control to perform structured grid division on the structure;
s330, defining 5 groups of contact pairs in ABAQUS according to the contact relation among the high-temperature alloy plate, the composite material plate and the bolt, wherein the contact pairs are respectively the contact between an upper notch of the screw and an upper notch of the composite material plate, the contact between the middle diameter surface of the screw and the middle diameter surface of the high-temperature alloy plate, the contact between the lower surface of the composite material plate and the upper surface of the alloy plate, the contact between the upper surface of the nut and the lower surface of the alloy plate, and the addition of friction force to each contact surface in the interaction property;
s340, directly applying axial pretightening force on the cross section of the bolt rod by using a Boltload command in ABAQUS, applying the gap amount of the nail holes by setting the assembly value of a contact pair between the nail holes, ensuring that the pretightening force is not reduced to be below 0N at high temperature, and applying uniform high-temperature load to the whole connecting structure;
s350, applying solid support restraint to all directions of the end part of the high-temperature alloy plate, applying mechanical load to the X direction of the end part of the ceramic matrix composite plate, and restraining the displacement in the other two directions.
3. The method for designing the size of the ceramic matrix composite and superalloy hybrid connection structure countersunk bolt based on the maximum failure load according to claim 1, wherein in S400, the implementation process of establishing the nonlinear constitutive model according to the mechanical property test result of the C/SiC composite is as follows:
s411, obtaining a test stress-strain curve of the C/SiC composite material through uniaxial tension and uniaxial shear loading and unloading tests in the main direction of the C/SiC composite material;
s412, performing polynomial fitting on the data of the uniaxial tension and uniaxial shear stress-relief strain test of the ceramic matrix composite by adopting a high-order polynomial, and then deriving the fitting result:
Figure FDA0003124635240000021
Figure FDA0003124635240000031
Figure FDA0003124635240000032
Figure FDA0003124635240000033
in the formula:
Figure FDA0003124635240000034
the elastic modulus of the ceramic matrix composite material in the process of tensile loading in the main direction;
Figure FDA0003124635240000035
the modulus of elasticity of the material in the process of unloading after the material is stretched in the main direction or before the material is reloaded to an unloading point;
Figure FDA0003124635240000036
the shear modulus in a 1-2 plane in the process of stretching and loading in the main direction of the material;
Figure FDA0003124635240000037
the shear modulus in the plane of the material 1-2 in the unloading process after the material is stretched in the main direction;
Figure FDA0003124635240000038
the maximum tensile strain in the process of tensile loading in the main direction of the material is shown, and m represents power;
Figure FDA0003124635240000039
the strain value from tensile load to fracture in the main direction of the material;
Figure FDA00031246352400000310
the maximum shear strain in a 1-2 plane in the process of stretching, loading and unloading in the main direction of the material, wherein m represents power;
Figure FDA00031246352400000311
is the in-plane shear fracture strain of the material, Ai，Bi(i 1,2.., 7) is a shape parameter of the logic function; p is a radical ofi,xi(i ═ 1,2) are shape parameters of the logistic function;
s413, determining the basic engineering elasticity parameter value of the ceramic matrix composite nonlinear model by the fitting curve, namely:
Figure FDA00031246352400000312
in the formula (I), the compound is shown in the specification,
Figure FDA00031246352400000313
the strain value from the compressive load to the fracture in the main direction of the material;
Figure FDA00031246352400000314
finally determining the nonlinear constitutive model G of the C/SiC ceramic matrix composite material for the stress of the crack closing point in the process of stretching, loading and unloading the material in the main direction of the material12The shear modulus of the plane.
4. The method for designing the size of the ceramic matrix composite and superalloy hybrid connection structure countersunk bolt based on the maximum failure load according to claim 1, wherein in S400, the implementation process for predicting the composite failure state by applying the ceramic matrix composite failure criterion is as follows:
s421, reading the unit integral point stress sigma of the ceramic matrix composite and the high-temperature alloy countersunk head bolt connection structure composite platek；
S422, substituting the stress value into a Tsai-Wu strength criterion to judge the failure of the C/SiC composite material unit point, wherein the specific form of the Tsai-Wu strength criterion is as follows:
Figure FDA0003124635240000041
Figure FDA0003124635240000042
Figure FDA0003124635240000043
in the formula:
Figure FDA0003124635240000044
representative of Tsai-Wu StrengthThe total amount of the intensity factor of the criterion,
Figure FDA0003124635240000045
is the intensity factor component, X, of each stress directiontAnd XcTensile and compressive strengths in the 1-direction of the material, YtAnd YcTensile and compressive strength in the 2-direction, ZtAnd ZcTensile and compressive strengths in the 3 directions, S12、S13、S23Representing the shear strength in three directions, σ1、σ2、σ3And τ12、τ13、τ23Respectively representing unit stress components in different directions;
and S423, updating the unit failure state variable.
5. The method for designing the size of the ceramic matrix composite and high-temperature alloy mixed connection structure countersunk head bolt based on the maximum failure load according to claim 1, wherein in S400, the process for performing material rigidity degradation on the failure material according to a degradation model comprises the following steps:
s431, when the material unit is judged to be invalid, determining that the rigidity value of the material unit in each direction is reduced to 1% of the original rigidity value, and updating the material attribute;
s432, updating a material rigidity matrix, Ck+1＝CdWherein C represents the post-injury material stiffness;
s433, updating stress sigma of damaged materialk+1＝Ck+1·(εk+Δεk) Wherein, epsilonkStrain, Δ ε, in the kth incremental stepkIs the strain increment;
and S434, executing S500.
CN202110685985.6A 2021-06-21 2021-06-21 Size design method for ceramic matrix composite and high-temperature alloy mixed connection structure countersunk head bolt based on maximum failure load Pending CN113408069A (en)

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