CN115424685A - Design and performance prediction method of metal matrix composite material - Google Patents

Design and performance prediction method of metal matrix composite material Download PDF

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CN115424685A
CN115424685A CN202211046777.2A CN202211046777A CN115424685A CN 115424685 A CN115424685 A CN 115424685A CN 202211046777 A CN202211046777 A CN 202211046777A CN 115424685 A CN115424685 A CN 115424685A
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怯喜周
钟武
彭艳杰
陈刚
赵玉涛
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Abstract

The invention relates to a metal matrix composite material, in particular to a method for designing and predicting performance of a metal matrix composite material. The invention adopts a finite element method based on physical properties and structural parameters of the model composite material, fully considers the influence of an interface matrix strengthening micro-area on the performance of the composite material in the process of establishing the model, effectively reflects the influence of real interface performance and debonding behavior on the service failure of the composite material, truly reduces the internal condition of the composite material, realizes the performance-oriented design and performance prediction of the metal matrix composite material, and has the characteristics of truly reducing the characteristics of the composite material and accurate performance prediction.

Description

Design and performance prediction method of metal matrix composite
Technical Field
The invention relates to a metal matrix composite material, in particular to a method for designing and predicting performance of a metal matrix composite material.
Technical background:
the metal-based composite material has the characteristics of high specific strength, high specific modulus, high heat conductivity, low expansion, high damping, electric conductivity and the like, and has wide application in the fields of aerospace, rail transit, energy and power, advanced weapons and the like. However, the introduction of the reinforcement inevitably generates a large number of complex interfaces while reinforcing the matrix (high strength, high modulus, low expansion, high damping, etc.), and divides the matrix into a near interface reinforced region and a far interface unreinforced region, significantly reduces the ductility, electrical conductivity, thermal conductivity, etc. of the composite material, making the design and performance prediction of the metal matrix composite material difficult. The invention provides a finite element method based on physical properties and structural parameters of a model composite material, which realizes the performance oriented design and performance prediction of a metal matrix composite material and has important significance for the design and preparation of a high-performance metal matrix composite material.
Through technical literature retrieval, the invention patent with the application number of '201910054500.6' discloses a method for designing and predicting mechanical properties of a discontinuous reinforced metal-based composite material, wherein the mechanical properties of the composite material are predicted through a finite element simulation technology, but the influence of an interface matrix reinforced micro-area on the performance of the composite material is not considered, and the influence of real interface properties and debonding behavior on service failure of the composite material cannot be effectively reflected. So far, no literature or patent reports on methods for designing and predicting the performance of the metal matrix composite based on the matrix micro-area and the interface performance exist. Therefore, the invention provides a finite element method based on physical properties and structural parameters of a model composite material, which realizes the performance oriented design and performance prediction of the metal matrix composite material, improves the design and preparation efficiency of the metal matrix composite material and reduces the trial and error cost.
Disclosure of Invention
The invention aims to provide a method for designing a metal matrix composite and predicting the performance of the metal matrix composite aiming at the defects of the prior art. The design and performance prediction method comprises four steps of model material design preparation, physical property and interface parameter measurement, finite element modeling and characteristic parameter determination and composite material organization performance design and prediction, and realizes the design and performance prediction of the metal matrix composite material. The specific technical scheme is as follows:
(1) Designing and preparing a model material: according to the performance requirement of the composite material, the required metal matrix and the reinforcement are reasonably selected, and the preparation of the model composite material is realized by adopting a corresponding technical process.
(2) Physical property and interface parameter measurement: firstly, determining the strength, elongation at break, elastic modulus, poisson's ratio, density, thermal expansion coefficient and thermal conductivity of a matrix and a reinforcement of the model composite material, and the physical parameters of the appearance, distribution and size of the reinforcement; secondly, measuring a stress-strain curve of the model composite material, measuring the size and the performance of the reinforced micro-area of the reinforcement body, and counting the distribution state of the reinforcement body.
(3) Finite element modeling and characteristic parameter determination: and (3) establishing a three-dimensional finite element model according to the physical property parameters, the composite material performance and the reinforcement distribution obtained in the step (2), and simulating and correcting the model parameters to make the simulation result consistent with the measurement result of the model composite material including the stress-strain curve, the fracture behavior and the size of the near-interface strengthening region.
(4) Designing and predicting the composite material structure performance: designing the content, size, morphology, distribution and interface structure of the composite material reinforcement with required performance based on the finite element model obtained in the step (3); and further predicting the physical property, mechanical property and failure behavior of the composite material.
The design and performance prediction method of the metal matrix composite material is provided. The method is characterized in that: in the step (1), the performance requirements include at least one of mechanical property, heat conductivity, electrical conductivity, thermal expansion performance and damping performance.
The design and performance prediction method of the metal matrix composite material is provided. The method is characterized in that: in the step (1), the metal matrix is at least one of aluminum, magnesium, titanium, iron, copper, nickel, zirconium, niobium, tantalum metal and alloy thereof. The reinforcement is Si, C (graphite particles, carbon nano tube, graphene, fullerene, etc.), siC, B 4 C、Al 2 O 3 、B 2 O 3 、TiB 2 、ZrB 2 、Si 3 N 4 Quasi-crystal (e.g., al) 65 Cu 23 Fe 12 ) High entropy alloys (e.g.: co-Cr-Fe-Ni-Ti), etc., the size of the reinforcer is 0.02-200 μm, the content of the reinforcer is 0.5-50 vol.%, and the shape of the reinforcer is spherical, polyhedral, short rod-shaped, lamellar, needle-shaped or onion-shaped.
The design and performance prediction method of the metal matrix composite material is provided. The method is characterized in that: in the step (1), the technical process comprises liquid casting, semi-solid casting, an extrusion casting method, powder metallurgy, spray forming, pressureless infiltration, pressure infiltration and 3D printing. The model composite material is a composite material preliminarily prepared according to performance requirements based on the characteristics of the metal matrix and the reinforcement and the technical process.
The design and performance prediction method of the metal matrix composite material is provided. The method is characterized in that: in the step (2), the physical properties and the interface parameters are measured, wherein the elongation at break, the elastic modulus, the Poisson ratio, the density, the thermal expansion coefficient and the thermal conductivity, the shape, the distribution and the size of the reinforcement body and the stress-strain curve of the model composite material adopt an industry standard measuring method; the size and performance of the reinforcement micro-area are strengthened by adopting a nano indentation method, wherein the number of the indentations is 20 on both sides of the interface (the interval is 500-800 nm, the indentation depth is 50-100nm, and the indentation rate is 0.01-0.05 nm s -1 )。
The method for designing and predicting the performance of the metal matrix composite is characterized by comprising the following steps: in step (2), the modified modulus E is used r The influence of the incomplete rigid pressure head in the nano indentation method on the indentation experiment is corrected. E r With the material modulus of elasticity E, the indenter modulus of elasticity E i The relationship of (a) to (b) is as follows:
Figure BDA0003822664330000031
wherein upsilon and upsilon i The poisson ratios of the measured material and the indenter are respectively. The stiffness of a material can be calculated by the formula:
Figure BDA0003822664330000032
s (stiffness) is the highest point slope of the unloading curve in the experiment, h is the indentation depth, E r Is the defined correction modulus, and A is the projected area of the elastically deformed contact surface. P is the maximum load, the hardness of the material is calculated as:
Figure BDA0003822664330000033
h is Vickers hardness, P MAX For maximum load, A is the indentation area.
The design and performance prediction method of the metal matrix composite material is provided. The method is characterized in that: in the step (3), the shape, size and distribution of the reinforcements are obtained through scanning of an SEM (scanning electron microscope), and the distribution of the reinforcements in the finite element model is constructed by means of Image-Pro on the basis of an SEM (scanning electron microscope) Image of the model composite material. The three-dimensional finite element model adopts commercial finite element software, such as: abaqus, ANSYS, COMSOL, MARC, hyperworks, establishes a coupling model containing force, heat, electricity and damping, wherein the matrix constitutive relation is set by adopting a Ductile fracture criterion (Ductile damage), an enhancer is set by adopting a Brittle fracture criterion (Brittle cracking), and an interface is set by adopting a linear pulling-separating criterion.
The design and performance prediction method of the metal matrix composite material is provided. The method is characterized in that: in the step (3), the simulation and correction of the model parameters refers to the adjustment of the fracture criterion type and parameters, the interface traction separation criterion type and parameters, the grid type and the stress type, so that the simulation result is consistent with the experiment result, and the model parameters are determined.
The design and performance prediction method of the metal matrix composite material is provided. The method is characterized in that: in the step (4), the distribution of the composite material reinforcement is measured, the dispersion degree of the reinforcement is determined by a formula theta = (A-B)/A, wherein A is the average distance between adjacent sparsely dispersed particles, B is the average distance between adjacent densely dispersed particles, and theta ∈ [0,1], and when theta tends to 0, the particles are uniformly dispersed; when θ approaches 1, the particles are not uniformly dispersed and are biased.
The design and performance prediction method of the metal matrix composite material is provided. The method is characterized in that: and (4) predicting the performance of the composite material, namely predicting the mechanical property, the heat conduction property, the electric conduction property, the thermal expansion property, the damping and the failure mode of fracture of the designed composite material by changing the size, the shape, the volume fraction, the distribution and the matrix strength adaptation of the reinforcement based on a finite element model of the physical property and the structural parameters of the model composite material. Analysis methods such as a response surface method combined with multiple groups of variables provide guidance suggestions for the design and preparation of the metal matrix composite.
Compared with the prior art, the method adopts a finite element method based on physical properties and structural parameters of the model composite material, fully considers the influence of an interface matrix strengthening micro-area on the performance of the composite material in the process of establishing the model, effectively reflects the influence of real interface performance and debonding behavior on service failure of the composite material, truly reduces the internal condition of the composite material, realizes performance-oriented design and performance prediction of the metal matrix composite material, and has the characteristics of truly reducing the characteristics of the composite material and being accurate in performance prediction.
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FIG. 1 is a flow chart of a method for designing and predicting the performance of a ceramic particle reinforced metal matrix composite
FIG. 2a.10vol% 4 C (20 μm)/AA6016. SEM picture; b. enhancing the three-dimensional model of the body particles; c.10vol% B 4 C (20 μm)/AA 6016 three-dimensional model map
10vol% obtained by simulation in FIG. 3 4 The C (20 mu m)/AA 6016 matrix dislocation strain strengthening zone is compared with an actual material, and the interface strengthening zone simulated by the model is consistent with the corresponding experiment.
10vol% obtained by simulation in FIG. 4 4 The section of the C (20 mu m)/AA 6016 composite material is compared with the actual material, the material failure behavior can be seen to correspond to the experiment, and the particle fracture behavior corresponds to the experiment.
10vol% obtained in simulation of FIG. 5B 4 The C (20 μm)/AA 6016 stress-strain curves are compared with the experimental data.
FIG. 6 10vol% B 4 C/Al simulated stress distribution diagram (A. The substrate is pure aluminum B. The substrate is AA 6016), B 4 C particle diameter D 50 =21 μm. As can be seen from the figure, when pulling the displacementThe ratio is 0.03, the maximum stress to which the material is subjected and the maximum stress to which the particles and the interfaces thereof are subjected become smaller gradually with the increase of the strength of the matrix, and as can be seen from the color of the stress distribution in the figure, when the matrix is AA6016, the range of the stress distribution of the matrix is wider, and the common deformability is better.
FIG. 7 10vol% B 4 C/AA6016 the resulting stress-strain curve (B) is simulated 4 C:1 to 50 μm) from the curve, 1 to 10vol% of B 4 C. The matrix is selected from AA6016 composite material, and if the tensile strength of the prepared material is not less than 400Mpa and the elongation is not less than 10%, B in the preparation process 4 The particle size of the C reinforcement should not exceed D 50 ＝12μm。
Detailed Description
The present invention is carried out in accordance with the following examples, but not limited thereto, the terms used in the present invention generally have meanings commonly understood by those of ordinary skill in the art, unless otherwise specified, and it should be understood that these examples are for illustrative purposes only and do not limit the scope of the present invention in any way; in the following examples, various procedures and methods not described in detail are conventional methods well known in the art.
Example 1
The target is as follows: commercial AA6016 aluminum ingots and B are adopted 4 C powder, designing and preparing B with tensile strength not less than 400Mpa and elongation not less than 10% 4 C/AA6016 composite material.
Commercial 6016 aluminum ingot B is adopted 4 C powder (D) 50 =22.4 μm), B is first brought together 4 C is dried for 2h at 200 ℃ to remove adsorbed water vapor on the surface, and 5vol.% B is prepared by a melt stirring method 4 The elongation of the C/AA6016 model composite material is 0.1087, the elastic modulus is 83GPa, the Poisson ratio is 0.3, and the density is 2.89g/cm 3 280MPa of yield strength, 340MPa of ultimate tensile strength and 2.1e of thermal expansion coefficient -5 /° C, thermal conductivity 180W/K · m; b is 4 Elongation of C is 0.01, elastic modulus is 430GPa, poisson's ratio is 0.17, ultimate tensile strength is 1100MPa, density is 2.52g/cm 3 Coefficient of thermal expansion 3.4e -6 /° C, thermal conductivity 67W/K · m, by nanoindentationThe interfacial modulus of elasticity of the model composite material was measured to be 230GPa, and the interfacial adhesion strength was set to be 1000MPa. The stress-strain curve (yield strength 280MPa, ultimate tensile strength 360MPa, elongation at break 10.8%) of the model composite material was determined by uniaxial tensile test, the particle distribution (theta = 0.23) of the model composite material was obtained by scanning electron microscopy, and the model composite material B was obtained by nano-indentation 4 The range of a C reinforced particle near-interface matrix dislocation strengthening region (2.1-3 mu m) is determined by the physical parameters of AA6016 and B 4 And introducing physical parameters and interface parameters of the C into a representative volume element model which is established by Abaqus/CAE according to the particle distribution condition of the model composite material, setting a matrix constitutive relation and adopting a Ductile fracture criterion (Ductile dam), setting a reinforcement and adopting a Brittle fracture criterion (Brittle fracture), setting an interface and adopting a linear drawing-separating criterion, and adopting C3D4 (four-node tetrahedron) and 3D Stress type of grid Stress. The loading mode is set as follows: (1) cooling from 470 ℃ to 25 ℃; (2) performing uniaxial stretching (displacement/representative volume element size = 0.3), (3) adjusting (type and parameter of fracture criteria, type and parameter of interface pulling separation criteria, type of grid, type of stress), so that the simulation result is consistent with the experimental result; (4) designing the content, size, morphology, distribution, interface structure and the like of the composite material reinforcement. The composite material can meet the requirements of tensile strength of more than or equal to 400Mpa and elongation of more than or equal to 10 percent. Final design meets Performance B 4 The size of a reinforcement of the C/AA6016 composite material is less than or equal to 12 microns, the content of the reinforcement is 6.5-12.5 vol%, and the uniformity of the reinforcement is (theta = 0.2), and the preparation method can be realized by adopting an electromagnetic ultrasonic assisted melt stirring method (wherein the electromagnetic stirring frequency is 12Hz, and the ultrasonic power is 5 kW).
Example 2
The target is as follows: commercial 2024Al aluminum ingot and Al are adopted 2 O 3 Powder, and Al with tensile strength not lower than 350MPa and elongation not lower than 8% 2 O 3 The/2024 Al composite material.
First, a commercial 2024Al ingot, al was used 2 O 3 Powder (D) 50 =49 μm), preparation of 10vol.% Al by semi-solid stirring method 2 O 3 Model/2024 Al composite material, elongation of 2024Al is determined by experiment to be 0.1836. Elastic modulus 72GPa, poisson's ratio 0.31, density 2.81g/cm 3 Yield strength 289MPa, ultimate tensile strength 432MPa, coefficient of thermal expansion 2.1e -5 /° C, thermal conductivity 175W/K · m, al 2 O 3 An elongation of 0.02, an elastic modulus of 373GPa, a Poisson's ratio of 0.17, an ultimate tensile strength of 1100MPa, a density of 3.98g/cm 3 Thermal expansion coefficient 8.1e -6 The interface elastic modulus of the model composite material is measured to be 171GPa by a nano indentation method, the interface bonding strength is set to be 1200MPa, the stress-strain curve (yield strength 270MPa, ultimate tensile strength 330MPa and elongation at break 6.8%) of the model composite material is measured by a uniaxial tensile experiment, the particle distribution condition (theta = 0.17) of the model composite material is obtained by a scanning electron microscope, and the Al of the model composite material is obtained by the nano indentation method 2 O 3 Reinforcing particle near-interface matrix dislocation strengthening region range (1.7-2.5 μm), and mixing Al 2 O 3 The physical property parameters, the physical property parameters and the interface parameters of 2024Al are introduced into a representative volume element model which is established by ANSYS according to the particle distribution condition of a model composite material, and the matrix constitutive relation is set by adopting a Ductile fracture criterion (Ductle damage), the reinforcement body adopts a Brittle fracture criterion (Brittle fracture), the interface adopts a linear drawing-separating criterion, the grid type adopts C3D4 (four-node tetrahedron) and the grid Stress type adopts 3D Stress. (1) Cooling from 440 ℃ to 25 ℃; (2) performing uniaxial stretching (displacement/representative volume element size = 0.2), (3) adjusting (type and parameter of fracture criteria, type and parameter of interfacial pull separation criteria, type of grid, type of stress) to make the simulation result consistent with the experimental result; (4) designing the composite reinforcement content, size, distribution, etc. Obtaining simulated stress-strain curve data, and processing the data by a response surface method to obtain Al with the tensile strength of more than or equal to 350Mpa and the elongation of more than or equal to 8 percent 2 O 3 2024Al composite material, when prepared, al 2 O 3 The size of the particles should be less than or equal to 35 μm, the volume fraction should not exceed 25vol.%, the uniformity of the reinforcement (theta = 0.15), and the preparation method can be realized by a semi-solid mechanical stirring method (the stirring speed is 200 r/min).
Example 3
The target is as follows: the SiC/Al composite material with the size of an interface strengthening micro-area larger than or equal to 2 mu m and the tensile strength larger than or equal to 120MPa is designed and prepared by adopting commercial pure aluminum powder and SiC powder.
Using commercially pure aluminum powder, siC powder (D) 50 =23.7 μm), 10vol.% SiC/Al model composite material was prepared by powder metallurgy method, elongation of pure aluminum 0.3187, elastic modulus 63GPa, poisson's ratio 0.33, density 2.71g/cm was experimentally determined 3 55MPa of yield strength, 68MPa of ultimate tensile strength and 2.3e of coefficient of thermal expansion -5 /° C, thermal conductivity 180W/K · m; the elongation of SiC was 0.01, the elastic modulus was 380GPa, the Poisson's ratio was 0.17, the ultimate tensile strength was 1200MPa, and the density was 3.2g/cm 3 Coefficient of thermal expansion of 3.4e -6 The method comprises the steps of measuring the interface elastic modulus of a model composite material to be 89GPa by a nano indentation method, setting the interface bonding strength to be 400MPa, measuring the Stress-strain curve (yield strength to be 70MPa, ultimate tensile strength to be 85MPa and breaking elongation to be 16.2%) of the model composite material by a uniaxial tensile test, obtaining the distribution condition (theta = 0.13) of sample particles by a scanning electron microscope, obtaining the dislocation strengthening region size (1.3-2.1 mu m) of the near-interface matrix of the SiC reinforced particles of the model composite material by the nano indentation method, introducing the physical parameters of pure aluminum, the physical parameters of SiC and the interface parameters into a representative volume element model which is established according to the distribution condition of the particles of the model composite material by using Abaqus/CAE, setting the matrix constitutive relation to adopt a Ductile fracture criterion (Ductly dam), setting the reinforcement to adopt a Brittle fracture criterion (Brittle fracturing), adopting a linear-separation criterion for the interface, adopting C3D4 (four-node) and adopting a tetrahedral Stress type 3D Stress. (1) Cooling from 450 ℃ to 25 ℃; (2) performing uniaxial stretching (displacement/representative volume element size = 0.4); (3) adjusting (fracture criterion type and parameters, interface traction separation criterion type and parameters, grid type and stress type) to make the simulation result consistent with the experiment result; (4) continuously changing the size (1-200 μm) and volume fraction of the SiC powder of the reinforcement body for simulation, and displaying by simulation analysis results that the width of the interface strengthening micro-area is larger and the tensile strength of the material is higher when the particle size of the reinforcement body is smaller, and the width of the near interface strengthening micro-area tends to be constant when the particle size is less than or equal to 3 μmThe value is about 2.8 mu m, the uniformity theta of the reinforcement is =0.08, and the SiC/Al composite material with the size of the interface strengthening micro-area being more than or equal to 2 mu m and the tensile strength being more than or equal to 120MPa is prepared, then the SiC should be D 50 The preparation method adopts powder metallurgy, the matrix and SiC powder are mixed and ball-milled for 48h, the cold pressing is carried out at 350MPa for 5min, the reaction sintering temperature is 525 ℃, the hot pressing axial pressure is 100MPa, and the heat preservation is carried out for 1h.
Example 4
The target is as follows: using commercial pure copper, tiB 2 The powder is prepared by designing TiB with the electric conductivity of more than or equal to 85 percent IACS and the tensile strength of more than or equal to 250MPa 2 A Cu composite material.
Using commercially pure copper, tiB 2 Particles (D) 50 =10 μm), 10vol.% TiB was prepared by melt stirring 2 The elongation of pure copper is 0.3923, the elastic modulus is 101GPa, the Poisson ratio is 0.33, and the density is 8.7g/cm 3 Yield strength of 62MPa, ultimate tensile strength of 213MPa, coefficient of thermal expansion of 1.6e -5 /° C, thermal conductivity 395W/K · m and specific resistance 1.8e -8 Ω·m；TiB 2 An elongation of 0.01, an elastic modulus of 483GPa, a Poisson's ratio of 0.19, an ultimate tensile strength of 1000MPa, and a density of 4.52g/cm 3 Coefficient of thermal expansion of 4.8e -6 /° C, thermal conductivity 82W/K · m, electrical resistivity 1.4e -7 Omega · m, the interfacial elastic modulus of the model composite material is measured to be 123GPa by a nano indentation method, the interfacial adhesion strength is set to be 1200MPa, the stress-strain curve (yield strength 65MPa, ultimate tensile strength 236MPa and elongation at break 18.7%) of the model composite material is measured by a uniaxial tensile experiment, the distribution condition of sample particles (theta = 0.16) is obtained by a scanning electron microscope, and the TiB of the model composite material is obtained by the nano indentation method 2 The size (1.4-2.3 μm) of the dislocation strengthening region of the near-interface matrix of the reinforced particles is obtained by mixing the physical parameters of pure copper and TiB 2 Introducing physical parameters and interface parameters into a representative volume element model established by Abaqus/CAE according to the particle distribution condition of the model composite material, setting a Ductile fracture criterion (Ductive dam) for a matrix constitutive relation, a Brittle fracture criterion (Brittle cracking) for an reinforcer, a linear drawing-separating criterion for an interface, and a C3D (carbon-to-metal) for a grid type4 (four-node tetrahedron) and a grid Stress type 3D Stress. (1) Cooling from 450 ℃ to 25 ℃; (2) performing uncoupled thermoelectric analysis (applied current density of 2A/μm) 2 ) And uniaxial stretching (displacement/representative volume element size = 0.4); (3) adjusting (fracture criterion type and parameters, interface traction separation criterion type and parameters, grid type and stress type) to make the simulation result consistent with the experiment result; (4) constantly changing the reinforcement TiB 2 The powder size (1-200 μm) and volume fraction are subjected to load-displacement simulation and non-coupling thermoelectric analysis, and TiB with the electric conductivity of more than or equal to 85% IACS and the tensile strength of more than or equal to 250MPa is finally designed and prepared 2 Composite material of/Cu, tiB 2 The particle size should be less than or equal to 2 μm, the volume fraction is 5-8vol.%, the uniformity of the reinforcement (theta = 0.1), and the preparation method can be realized by adopting an electromagnetic ultrasonic assisted melt stirring method (wherein the electromagnetic stirring frequency is 10Hz, and the ultrasonic power is 3 kW).

Claims (10)

1. A design and performance prediction method of a metal matrix composite is characterized by comprising four steps of model material design preparation, physical property and interface parameter measurement, finite element modeling and characteristic parameter determination and composite material organization performance design and prediction, and realizes the design and performance prediction of the metal matrix composite, and the specific steps are as follows:
(1) Designing and preparing a model material: according to the performance requirements of the composite material, reasonably selecting the required metal matrix and reinforcement, and adopting a corresponding technical process to realize the preparation of the model composite material;
(2) And (3) measuring physical properties and interface parameters: firstly, determining the strength, elongation at break, elastic modulus, poisson's ratio, density, thermal expansion coefficient and thermal conductivity of a matrix and an enhanced body of the model composite material, and the physical property parameters of the morphology, distribution and size of the enhanced body; secondly, measuring a stress-strain curve of the model composite material, measuring the size and the performance of the reinforcement micro-area of the reinforcement, and counting the distribution state of the reinforcement;
(3) Finite element modeling and characteristic parameter determination: establishing a three-dimensional finite element model according to the physical property parameters, the composite material performance and the reinforcement distribution obtained in the step (2), and simulating and correcting the model parameters to ensure that the simulation result is consistent with the measurement result of the model composite material comprising a stress-strain curve, a fracture behavior and a near interface strengthening region;
(4) Designing and predicting the composite material structure performance: designing the content, size, morphology, distribution and interface structure of the composite material reinforcement with required performance based on the finite element model obtained in the step (3); and further predicting the physical property, mechanical property and failure behavior of the composite material.
2. The method of claim 1, wherein the method comprises: in the step (1), the performance requirements include at least one of mechanical property, heat conductivity, electrical conductivity, thermal expansion performance and damping performance.
3. The method of claim 1, wherein the method comprises: in the step (1), the metal matrix is at least one of aluminum, magnesium, titanium, iron, copper, nickel, zirconium, niobium, tantalum and alloy thereof; the reinforcement is Si, C, siC, B 4 C、Al 2 O 3 、B 2 O 3 、TiB 2 、ZrB 2 、Si 3 N 4 At least one of quasi-crystal and high-entropy alloy, the size of the reinforcement is 0.02-200 mu m, the content of the reinforcement is 0.5-50 vol.%, and the shape of the reinforcement is spherical, polyhedral, short rod-shaped, lamellar, needle-shaped or onion-shaped.
4. The method of claim 1, wherein the method comprises the steps of: in the step (1), the technical process comprises liquid casting, semi-solid casting, extrusion casting, powder metallurgy, spray forming, pressureless infiltration, pressure infiltration and 3D printing; the model composite material is a composite material preliminarily prepared according to performance requirements based on the characteristics of the metal matrix and the reinforcement and the technical process.
5. The method of claim 1, wherein the method comprises: in the step (2), the physical properties and the interface parameters are measured, wherein the elongation at break, the elastic modulus, the Poisson ratio, the density, the thermal expansion coefficient and the thermal conductivity, the shape, the distribution and the size of the reinforcement body and the stress-strain curve of the model composite material adopt an industry standard measuring method; the size and performance of the micro-area are strengthened by the reinforcement, and then a nano indentation method is adopted, wherein the number of indentations is 20 on each side of the interface; spacing: 500-800 nm, depth of indentation: 50-100nm, pressing rate: 0.01 to 0.05nm · s -1 。
6. The method of claim 1, wherein the method comprises the steps of: in step (2), the modified modulus E is used r To correct the influence of incomplete rigid indenter on indentation experiment in nano indentation method, E r With the material modulus of elasticity E, the indenter modulus of elasticity E i The relationship of (a) to (b) is as follows:
Figure FDA0003822664320000021
wherein upsilon and upsilon i Respectively the Poisson's ratio of the measured material and the pressure head; the stiffness of a material can be calculated by the formula:
Figure FDA0003822664320000022
stiffness S is the highest slope of the unloading curve in the experiment, h is indentation depth, E r Is a defined correction modulus, A is the projected area of the elastic deformation contact surface, P is the maximum load, and the hardness of the material is calculated by the following formula:
Figure FDA0003822664320000023
h is Vickers hardness, P MAX For maximum load, A is the indentation area.
7. The method of claim 1, wherein the method comprises: in the step (3), the shape, the size and the distribution of the reinforcement are obtained through scanning of an SEM (scanning electron microscope), and the distribution of the reinforcement in the finite element model is constructed by means of Image-Pro based on an SEM (scanning electron microscope) Image of the model composite material; the three-dimensional finite element model adopts commercial finite element software, such as: abaqus, ANSYS, COMSOL, MARC, hyperworks, wherein the matrix constitutive relation is set by Ductile fracture criterion (Ductile damage), the reinforcement is set by Brittle fracture criterion (Brittle cracking), and the interface is set by linear pull-separation criterion.
8. The method of claim 1, wherein the method comprises: in the step (3), the simulation and correction of the model parameters refers to the adjustment of the fracture criterion type and parameters, the interface traction separation criterion type and parameters, the grid type and the stress type, so that the simulation result is consistent with the experiment result, and the model parameters are determined.
9. The method of claim 1, wherein the method comprises: in the step (4), the distribution of the composite material reinforcement is determined, and the dispersion degree of the reinforcement is determined by a formula theta = (A-B)/A, wherein A is the average spacing between adjacent sparsely dispersed particles, B is the average spacing between adjacent densely dispersed particles, and theta ∈ [0,1], and when theta tends to 0, the particles are uniformly dispersed; when θ approaches 1, the particles are not uniformly dispersed and are biased.
10. The method of claim 1, wherein the method comprises: step (4), predicting the performance of the composite material, namely predicting the mechanical property, the heat conduction property, the electric conductivity, the thermal expansion property, the damping and the failure mode of fracture of the designed composite material by changing the size, the shape, the volume fraction, the distribution and the matrix strength adaptation of the reinforcement based on a finite element model of the physical property and the structural parameters of the model composite material; analysis methods such as a response surface method combined with multiple groups of variables provide guidance and suggestions for the design and preparation of the metal matrix composite.
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CN117219212A (en) * 2023-11-07 2023-12-12 宝鸡拓普达钛业有限公司 Method and device for reinforcing internal structure and mechanical property of titanium alloy based on boron content
CN117634052A (en) * 2024-01-25 2024-03-01 中国航发四川燃气涡轮研究院 Accurate positioning design method for metal matrix composite leaf ring reinforced core

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117219212A (en) * 2023-11-07 2023-12-12 宝鸡拓普达钛业有限公司 Method and device for reinforcing internal structure and mechanical property of titanium alloy based on boron content
CN117219212B (en) * 2023-11-07 2024-02-06 宝鸡拓普达钛业有限公司 Method and device for reinforcing internal structure and mechanical property of titanium alloy based on boron content
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