CN115901453A - Tensile cracking failure test method and system for layered composite material - Google Patents
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- 230000008569 process Effects 0.000 claims abstract description 62
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Abstract
The invention discloses a tensile cracking failure test method and a system for a layered composite material, which comprise the following steps: preparing a composite board tensile sample; stretching the composite board tensile sample, and collecting test data in the stretching process; selecting test data at different stages in the stretching process, and comparing the selected test data by using a digital image technology to obtain a comparison result; and observing and analyzing the composite board tensile sample after the stretching is finished to obtain an analysis result. The method can effectively describe the complex strain evolution process and the fracture behavior and reveal the new rule of the tensile fracture damage evolution and the crack propagation of the laminated composite board. The forming performance of the laminated composite plate can be further optimized and the potential of the laminated composite plate can be exerted with greater efficiency.
Description
Technical Field
The invention belongs to the technical field of failure detection of laminated composite materials, and particularly relates to a tensile cracking failure test method and system of a laminated composite material.
Background
The magnesium-aluminum explosive composite board is formed by successfully connecting magnesium and aluminum plates together through an explosive welding method. Compared with other welding modes, the explosive welding method has the advantages that the element diffusion at the intermetallic joint surface is less, the metal compound diffusion layer is thinner, the defects of holes, looseness and the like cannot be generated, and the bonding strength is higher. The composite material has the advantages of magnesium and aluminum alloy, can reduce weight and cost, is better than single-layer metal in performance, and has higher practicability.
Most of the previous research has focused on the effect of the explosion process and annealing temperature on the tensile properties of the composite panels. In order to maximize the advantages and the maximum performance of the layered composite material, there are few reports on the research on the local strain evolution, the interface delamination and the fracture failure behavior of the layered composite material during the stretching process.
Disclosure of Invention
In order to solve the problems in the prior art, the invention mainly aims to provide a tensile cracking failure test method and a tensile cracking failure test system for a layered composite material, which are convenient for further optimizing the process in the aspect of forming performance of the layered composite material.
In order to achieve the purpose, the invention provides the following scheme:
a method for tensile crack failure testing of a layered composite comprising:
preparing a composite board tensile sample;
stretching the composite board tensile sample, and collecting test data in the stretching process;
selecting test data at different stages in the stretching process, and comparing the selected test data by using a digital image technology to obtain a comparison result;
and observing and analyzing the composite board tensile sample after the stretching is finished to obtain an analysis result.
Preferably, the preparation method of the composite board tensile sample comprises the following steps:
preparing a composite board, and carrying out heat treatment process treatment on the composite board by adopting different processes;
and spraying paint on the surface of the composite board in the thickness direction to obtain speckle test points.
Preferably, the painting method includes: spraying a matte white paint, and spraying a matte black paint after the matte white paint is dried.
Preferably, the heat treatment process comprises: 150 ℃/2h, 200 ℃/2h, 250 ℃/2h and 300 ℃/2h.
Preferably, the composite board tensile sample is stretched by a 100kN universal testing machine, and the stretching speed is 1mm/min.
Preferably, the process of collecting said test data during stretching comprises:
adjusting the distance between a camera and the sample to ensure that a lens is horizontal to the surface of the sample, and the position of the irradiation light source does not cause the surface of the sample to be exposed, so that the obvious sawtooth-shaped patterns at the edge of a strain field can be seen;
and acquiring an image in the stretching process by adopting a three-dimensional motion and deformation measurement system to obtain the test data.
Preferably, the method of obtaining the comparison result comprises:
establishing a strain field on the surface of the sample by utilizing the gray scale change of the digital image of the sample surface before and after stretching deformation;
selecting strain field pictures at different stages based on different composition layers of the test sample;
and comparing the strain and the fracture behaviors of different stages in the stretching process based on different heat treatment processes to obtain a comparison result.
Preferably, the observing and analyzing the tensile sample of the composite board after the stretching is finished comprises: macro-physiognomy and micro-physiognomy.
The invention also provides a tensile cracking failure test system for the layered composite material, which comprises: the system comprises a sampling system, a testing system, a comparison system and an analysis system;
the sampling system is used for preparing a composite board tensile sample;
the test system is used for stretching the composite board tensile sample and collecting test data in the stretching process;
the comparison system is used for selecting test data at different stages in the stretching process, and comparing the selected test data by using a digital image technology to obtain a comparison result;
and the analysis system is used for observing and analyzing the composite board tensile sample after the stretching is finished to obtain an analysis result.
The invention has the beneficial effects that:
the invention provides a method and a system for testing the tensile cracking failure of a layered composite material, which are used for acquiring and storing images of a tensile process of a sample with different annealing temperatures and performing digital image correlation analysis on the images of the tensile process, and directly measuring the displacement and the strain field of the surface of a test piece by using the gray scale change of 2 digital images before and after the surface of the tensile sample is deformed. Because the magnesium-aluminum composite board is composed of different composition layers, obvious phenomena such as uneven local strain concentration, interface delamination, necking deformation and the like can be observed based on a digital image correlation analysis method. By comparing deformation and fracture behaviors expressed in the stretching process of different samples, stress-strain curves at different annealing temperatures and a stretching strain distribution diagram measured by a digital image correlation analysis method (DIC) are drawn. The local strain concentration positions are distributed differently along with the difference of the temperature, so that the cracking failure behaviors of the plate are different. Therefore, the method can effectively describe the complex strain evolution process and the fracture behavior and reveal the new rule of the tensile fracture damage evolution and the crack propagation of the laminated composite board. The forming performance of the laminated composite board is further optimized and the potential of the laminated composite board is exerted with higher efficiency.
Drawings
In order to more clearly illustrate the technical solution of the present invention, the drawings needed to be used in the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to these drawings without inventive labor.
FIG. 1 is a schematic flow chart of a tensile cracking failure test method of a layered composite material according to an embodiment of the present invention;
FIG. 2 is a schematic representation of a tensile specimen according to an embodiment of the present invention;
FIG. 3 is a stress-strain plot of uniaxial tension of a composite panel according to an embodiment of the present invention;
FIG. 4 is a graph of tensile strain distribution measured by DIC at various conditions according to an embodiment of the present invention;
FIG. 5 is a macro topography of tensile specimen fracture for an embodiment of the present invention;
FIG. 6 is a microstructure of a tensile specimen at break according to an embodiment of the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the 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 obtained by a person skilled in the art without making any creative effort based on the embodiments in the present invention, belong to the protection scope of the present invention.
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
Example one
As shown in fig. 1, a schematic flow chart of a tensile cracking failure test method of the layered composite material of the present invention is shown, and comprises the following steps:
s1, preparing a composite board tensile sample;
the method for preparing the sample specifically comprises the following steps:
in this embodiment, a magnesium-aluminum explosive composite plate is taken as an example; the total thickness of the adopted magnesium-aluminum explosive composite board is 10mm, the magnesium layer is 6mm, and the aluminum layer is 4mm. Obtaining a longitudinal tensile sample on the magnesium-aluminum explosive composite board by wire cutting according to the national standard GB/T228-2010; the length of the parallel section of the tensile sample is 80mm, the width of the parallel section is 12.5mm, the total length is 147.43mm, and the total width is 20mm. The dimensional model of the tensile specimen is shown in fig. 2.
And spraying the surface of the selected tensile sample in the thickness direction to obtain a speckle test point. The spraying method comprises the following steps: and spraying a matte white paint on the surface of the selected tensile sample in the thickness direction, and spraying a matte black paint after the matte white paint is dried. The speckle test points with good contrast, uniform size and convenient tracking of instruments can be obtained by adopting the matte black paint.
The magnesium-aluminum explosive composite board is subjected to annealing process treatment by adopting different processes, which respectively comprise the following steps: in an unannealed state, 150 ℃/2h, 200 ℃/2h, 250 ℃/2h, 300 ℃/2h.
S2, stretching the composite board tensile sample, and collecting test data in the stretching process;
in the embodiment, a 100kN universal tester is adopted to stretch the composite board tensile sample, and the stretching speed is 1mm/min.
Adjusting the distance between a camera and a tensile sample to ensure that a lens is horizontal to the surface of the sample, irradiating the position of a light source to avoid the exposure phenomenon on the surface of the sample, focusing the camera, adjusting the resolution to enable the picture to be clear to image, and observing the obvious saw-toothed pattern on the edge of a strain field;
and acquiring images in the stretching process by adopting a three-dimensional motion and deformation measurement system, wherein the image acquisition frequency is 1HZ, and obtaining test data. In this embodiment, the test data is a three-dimensional deformation image.
S3, selecting test data at different stages in the stretching process, and comparing the selected test data by using a digital image technology to obtain a comparison result;
selecting strain field pictures at different stages in the stretching process in the main strain field, wherein the strain field pictures respectively comprise: the first appearance of local strain concentration, interface delamination, plate sequential fracture, complete failure and the like. In order to quantitatively study the strain process, stress-strain curves at different annealing temperatures were plotted, as well as tensile strain profiles measured by digital image correlation analysis (DIC). And analyzing the damage evolution and crack propagation behaviors of the sample by combining the stress-strain trend and the strain evolution distribution conditions of different stages in the stretching process. The test results are shown in table 1.
In this embodiment, the adopted DIC method analysis software is moire soft ware, and the acquired image information is subjected to DIC method analysis. The DIC analysis method adopts a sequence similarity image registration method, selects 3 non-collinear speckle subsets in each image, respectively performs correlation analysis on the 3 speckle subsets to obtain the displacement of the 3 speckle subsets, and then substitutes the displacement into a finite element method to solve strain through unit node displacement, and finally obtains 2 strain components, namely strain fields obtained by strain in the stretching direction and strain in the vertical stretching direction. As shown in particular in figure 3.
The method specifically comprises the following steps:
and establishing a strain field on the surface of the sample by utilizing the gray scale change of 2 digital images before and after the surface of the tensile sample is deformed.
Selecting strain field pictures at different stages based on different composition layers of the sample;
and comparing the strain and the fracture behaviors of different stages in the stretching process based on different annealing processes to obtain a comparison result.
TABLE 1
| Annealing temperature (. Degree.C.) | Tensile strength (MPa) | Elongation to failure (%) |
| Original | 309.69 | 14.23 |
| 150 | 268.83 | 20.63 |
| 200 | 253.05 | 25.16 |
| 250 | 191.04 | 23.11 |
| 300 | 162.61 | 18.50 |
As can be seen from fig. 3, the stress-strain curve shows a tendency of rising first and then falling. Two inflection points with suddenly reduced stress values appear on the curve in the whole stretching process, and the first inflection point appears when the single-layer plate is broken and is called as a failure point. The second inflection point occurs when both sheets break, referred to as the break point. In conjunction with table 1, it can be seen that: the tensile strength of the explosion-welded magnesium-aluminum composite plate reaches the maximum value of 309.690Mpa before annealing, and the failure elongation is 14.230%. After annealing at different temperatures, when the annealing condition is 200 ℃/2h, the comprehensive performance of the magnesium-aluminum composite board is optimal, the tensile strength value is 253.51MPa, and the failure elongation is 25.16%. A large difference in fracture behaviour under different annealing processes can be seen by means of fig. 5. When the annealing temperature is 150 ℃, the interface bonding condition after fracture is the best, and when the temperature is 300 ℃, the cracking condition of the composite interface of the magnesium-aluminum plate after fracture is the most serious. Meanwhile, it can be seen that magnesium alloy is broken at first at the original temperature of 150 ℃ and 200 ℃; at 250 ℃ and 300 ℃, the aluminum alloy breaks first.
The effective strain profile obtained by Digital Image Correlation (DIC) is shown in fig. 4, revealing the strain evolution and the fracture mechanism of the layers of different compositions during stretching. DIC-based analysis shows that significant non-uniform local strain concentration occurs during the stretching process, particularly at 250 ℃ and 300 ℃, the strain concentration occurs at the interface, which coincides with the phenomenon of interface-first delamination under the annealing process. Meanwhile, the appearance sequence and the expansion route of the cracks can be observed more obviously, and more accurate prediction is provided for the application of the plate.
Combining the above, the comparison results are: during the stretching process, obvious uneven local strain concentration, interface delamination, plate sequential fracture and complete failure occur, particularly, the strain concentration occurs at the interface at 250 ℃ and 300 ℃, and the interface cracks first. Meanwhile, the position where the local strain concentration occurs coincides with the position where the crack occurs.
And S4, observing and analyzing the composite board tensile sample after the tensile process is finished to obtain an analysis result.
The observation and analysis of the composite board tensile sample after the stretching comprises the following steps: macro-physiognomy and micro-physiognomy.
As shown in FIG. 5, the magnesium-side macroscopic tensile fracture of the stretched sample cracks at 45 degrees with the stretching direction, and the section of the sample is flat and regular, such as a blade.
After the microscopic morphology analysis of the fracture, the following results can be obtained: obvious fracture surface characteristics can be observed in the original state, which indicates that the explosive composite plate is brittle fracture. From fig. 6, it can be seen that a distinct dissociation surface characteristic can be observed in the original state, which indicates that the fracture morphology of the magnesium alloy in this state is mainly based on a gradient dissociation surface. The fracture by dissociation is usually a manifestation of macroscopic brittle fracture, i.e. fracture surface is separated along a certain crystal plane, and the crack is developed rapidly so as to form a platform with a step-shaped fracture surface, thus indicating that the explosive clad plate is brittle fracture. The fracture surface after annealing exhibited dimple characteristics compared to before annealing. Dimple is the primary microscopic feature of metal plastic fracture, which is consistent with the tendency of greater increase in elongation to failure after annealing. In particular at 300 ℃, the dimples have a larger average diameter and a larger depth compared to other temperatures, whereas generally a larger dimple size indicates better plasticity of the material. This conclusion is also demonstrated in FIG. 3, where the elongation at break reaches a maximum of 35.042% under annealing conditions of 300 ℃/2h.
Example two
The invention also provides a tensile cracking failure test system for the layered composite material, which comprises: the system comprises a sampling system, a testing system, a comparison system and an analysis system;
the sampling system is used for preparing a composite board tensile sample;
the sampling system comprises the following specific working processes:
in this embodiment, a magnesium-aluminum explosive composite plate is taken as an example; the total thickness of the adopted magnesium-aluminum explosive composite board is 10mm, the magnesium layer is 6mm, and the aluminum layer is 4mm. Obtaining a longitudinal tensile sample on the magnesium-aluminum explosive composite plate by wire cutting according to the national standard GB/T228-2010; the length of the parallel section of the tensile sample is 80mm, the width of the parallel section is 12.5mm, the total length is 147.43mm, and the total width is 20mm.
And spraying the surface of the selected tensile sample in the thickness direction to obtain a speckle test point. The spraying method comprises the following steps: and spraying a matte white paint on the surface of the selected tensile sample in the thickness direction, and spraying a matte black paint after the matte white paint is dried. The speckle test points with good contrast, uniform size and convenient tracking of instruments can be obtained by adopting the matte black paint.
Annealing the magnesium-aluminum explosive composite board by adopting different processes, which respectively comprises the following steps: in an unannealed state, 150 ℃/2h, 200 ℃/2h, 250 ℃/2h, 300 ℃/2h.
The test system is used for stretching the composite board tensile sample and collecting test data in the stretching process;
in this embodiment, the test system adopts a 100kN universal tester to stretch the composite board tensile sample, and the stretching rate is 1mm/min.
Adjusting the distance between a camera and a tensile sample to ensure that a lens is horizontal to the surface of the sample, irradiating the position of a light source to avoid the exposure phenomenon on the surface of the sample, focusing the camera, adjusting the resolution to enable the picture to be clear to image, and observing the obvious saw-toothed pattern on the edge of a strain field;
and acquiring images in the stretching process by adopting a three-dimensional motion and deformation measurement system, wherein the image acquisition frequency is 1HZ, and obtaining test data. In this embodiment, the test data is a three-dimensional deformation image.
The comparison system is used for selecting test data at different stages in the stretching process, and comparing the selected test data by using a digital image technology to obtain a comparison result;
the working process of the comparison system specifically comprises the following steps:
selecting strain field pictures at different stages in the stretching process in the main strain field, wherein the strain field pictures respectively comprise: the first appearance of local strain concentration, interface layering, plate sequential fracture, complete failure and the like. In order to quantitatively study the strain process, stress-strain curves at different annealing temperatures were plotted, as well as tensile strain profiles measured by digital image correlation analysis (DIC). And analyzing the damage evolution and crack propagation behaviors of the sample by combining the stress-strain trend and the strain evolution distribution conditions of different stages in the stretching process.
In this embodiment, the adopted DIC method analysis software is moire soft ware, and the acquired image information is subjected to DIC method analysis. The DIC analysis method adopts a sequence similarity image registration method, 3 non-collinear speckle subsets are selected in each image, correlation analysis is carried out on the 3 speckle subsets respectively to obtain the displacement of the 3 speckle subsets, then the displacement is substituted into a finite element method, strain is solved through unit node displacement, and finally 2 strain components, namely strain fields obtained through strain in the stretching direction and strain in the vertical stretching direction are obtained. As shown in particular in figure 3.
And finally, comparing the strain and the fracture behavior at different stages in the stretching process based on different annealing processes to obtain a comparison result.
Based on the test results of the first embodiment, and the comparison results obtained by combining fig. 3, fig. 4 and fig. 5 are as follows: during the stretching process, obvious uneven local strain concentration, interface delamination, plate sequential fracture and complete failure occur, particularly, the strain concentration occurs at the interface at 250 ℃ and 300 ℃, and the interface cracks first. Meanwhile, the position where the local strain concentration occurs coincides with the position where the crack occurs.
And the analysis system is used for observing and analyzing the composite board tensile sample after the tensile process is finished to obtain an analysis result.
The observation and analysis of the composite board tensile sample after the stretching comprises the following steps: macro-physiognomy and micro-physiognomy. The method specifically comprises the following steps:
as shown in FIG. 5, the magnesium-side macroscopic tensile fracture of the stretched sample cracks at 45 degrees with the stretching direction, and the section of the sample is flat and regular, such as a blade.
After the microscopic morphology analysis of the fracture, the following results can be obtained: obvious fracture surface characteristics can be observed in the original state, which indicates that the explosive composite plate is brittle fracture. From fig. 6, it can be seen that a distinct dissociation surface characteristic can be observed in the original state, which indicates that the fracture morphology of the magnesium alloy in this state is mainly based on a gradient dissociation surface. The fracture by dissociation is usually a manifestation of macroscopic brittle fracture, i.e. fracture surface is separated along a certain crystal plane, and the crack is developed rapidly so as to form a platform with a step-shaped fracture surface, thus indicating that the explosive clad plate is brittle fracture. The fracture surface after annealing exhibited dimple characteristics compared to before annealing. The dimple is the primary microscopic feature of metal plastic fracture, which is consistent with the tendency for a large increase in elongation to failure after annealing. In particular at 300 c the average diameter and depth of the dimple is larger compared to other temperatures, while generally the larger the dimple size indicates the better plasticity of the material. This conclusion is also demonstrated in FIG. 3, where the elongation at break reaches a maximum of 35.042% under annealing conditions of 300 ℃/2h.
The above-described embodiments are only intended to describe the preferred embodiments of the present invention, and not to limit the scope of the present invention, and various modifications and improvements made to the technical solution of the present invention by those skilled in the art without departing from the spirit of the present invention should fall within the protection scope defined by the claims of the present invention.
Claims (9)
1. A tensile cracking failure test method and a system for a layered composite material are characterized by comprising the following steps:
preparing a composite board tensile sample;
stretching the composite board tensile sample, and collecting test data in the stretching process;
selecting test data at different stages in the stretching process, and comparing the selected test data by using a digital image technology to obtain a comparison result;
and observing and analyzing the composite board tensile sample after the stretching is finished to obtain an analysis result.
2. The method for testing the tensile cracking failure of the layered composite material according to claim 1, wherein the method for preparing the tensile test sample of the composite board comprises the following steps:
preparing a composite board, and carrying out heat treatment process treatment on the composite board by adopting different processes;
and spraying paint on the surface of the composite board in the thickness direction to obtain speckle test points.
3. The method for testing the tensile crack failure of the layered composite of claim 2, wherein the painting process comprises: spraying a matte white paint, and spraying a matte black paint after the matte white paint is dried.
4. The method for testing the tensile cracking failure of the layered composite material as set forth in claim 2, wherein the heat treatment process comprises: 150 ℃/2h, 200 ℃/2h, 250 ℃/2h and 300 ℃/2h.
5. The method for testing the tensile cracking failure of the layered composite material according to claim 1, wherein a 100kN universal tester is used for stretching the tensile sample of the composite board, and the stretching speed is 1mm/min.
6. The method for testing the tensile cracking failure of the layered composite material according to claim 1, wherein the process of collecting the test data in the stretching process comprises:
adjusting the distance between a camera and the sample to ensure that a lens is horizontal to the surface of the sample, and the position of the irradiation light source does not cause the surface of the sample to be exposed, so that the obvious sawtooth-shaped patterns at the edge of a strain field can be seen;
and acquiring an image in the stretching process by adopting a three-dimensional motion and deformation measurement system to obtain the test data.
7. The method for testing the tensile crack failure of a layered composite material according to claim 1, wherein the method for obtaining the comparative results comprises:
establishing a strain field on the surface of the sample by utilizing the gray scale change of the digital image of the sample surface before and after stretching deformation;
selecting strain field pictures at different stages based on different composition layers of the test sample;
and comparing the strain and the fracture behavior at different stages in the stretching process based on different heat treatment processes to obtain a comparison result.
8. The method for testing the tensile cracking failure of the layered composite material according to claim 1, wherein the observation and analysis of the tensile sample of the composite board after the stretching is finished comprises the following steps: macro-physiognomy and micro-physiognomy.
9. A tensile crack failure test system for a layered composite, comprising: the system comprises a sampling system, a testing system, a comparison system and an analysis system;
the sampling system is used for preparing a composite board tensile sample;
the test system is used for stretching the composite board tensile sample and collecting test data in the stretching process;
the comparison system is used for selecting test data at different stages in the stretching process, and comparing the selected test data by using a digital image technology to obtain a comparison result;
and the analysis system is used for observing and analyzing the composite board tensile sample after the stretching is finished to obtain an analysis result.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117110346A (en) * | 2023-10-23 | 2023-11-24 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Analysis method for microstructure of laser selective melting plate |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114414376A (en) * | 2022-01-24 | 2022-04-29 | 齐鲁工业大学 | Method for determining fracture strain of hot stamping part |
| CN115326552A (en) * | 2022-08-02 | 2022-11-11 | 南京航空航天大学 | Clamping device for preventing composite board from being unstable in continuous tension and compression experiment |
-
2022
- 2022-12-13 CN CN202211602869.4A patent/CN115901453A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114414376A (en) * | 2022-01-24 | 2022-04-29 | 齐鲁工业大学 | Method for determining fracture strain of hot stamping part |
| CN115326552A (en) * | 2022-08-02 | 2022-11-11 | 南京航空航天大学 | Clamping device for preventing composite board from being unstable in continuous tension and compression experiment |
Non-Patent Citations (4)
| Title |
|---|
| 孙涛;梁晋;蔡勇;王伊卿;: "用数字散斑法测量铜/铝复层板拉伸变形", 光学精密工程, no. 12 * |
| 李志等: ""基于DIC 方法R60702/TA2 爆炸焊接复合板力学性能研究"", 《稀有金属》, vol. 44, no. 8, pages 1 - 1 * |
| 魏亮鱼;李磊;崔晓;刘道启;: "基于DIC方法的不同退火温度下Cu-Ni19合金损伤演变研究", 工程力学, no. 04 * |
| 龚永平;张德闯;高晓;林建国;: "退火温度对Ti-7.5Nb-4Mo-2Sn合金组织与超弹性的影响", 材料热处理学报, no. 09 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117110346A (en) * | 2023-10-23 | 2023-11-24 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Analysis method for microstructure of laser selective melting plate |
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