CN112611656A - Accurate measurement method for low-temperature elongation of aluminum alloy for aerospace - Google Patents
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- 229910000838 Al alloy Inorganic materials 0.000 title claims abstract description 51
- 238000000691 measurement method Methods 0.000 title claims abstract description 7
- 238000004088 simulation Methods 0.000 claims abstract description 25
- 239000000463 material Substances 0.000 claims abstract description 15
- 239000004576 sand Substances 0.000 claims abstract description 3
- 238000000034 method Methods 0.000 claims description 17
- 238000012545 processing Methods 0.000 claims description 4
- 229910001148 Al-Li alloy Inorganic materials 0.000 claims description 3
- JFBZPFYRPYOZCQ-UHFFFAOYSA-N [Li].[Al] Chemical compound [Li].[Al] JFBZPFYRPYOZCQ-UHFFFAOYSA-N 0.000 claims description 3
- 239000001989 lithium alloy Substances 0.000 claims description 3
- 238000012951 Remeasurement Methods 0.000 claims description 2
- 238000004519 manufacturing process Methods 0.000 abstract description 4
- 238000013461 design Methods 0.000 abstract description 3
- 238000012360 testing method Methods 0.000 description 13
- 238000003466 welding Methods 0.000 description 11
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 6
- 238000001514 detection method Methods 0.000 description 3
- 239000007788 liquid Substances 0.000 description 3
- 229910052757 nitrogen Inorganic materials 0.000 description 3
- 230000003287 optical effect Effects 0.000 description 3
- 238000002474 experimental method Methods 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 238000003860 storage Methods 0.000 description 2
- 238000010998 test method Methods 0.000 description 2
- 239000010953 base metal Substances 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000004927 fusion Effects 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000004021 metal welding Methods 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000011056 performance test Methods 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000009864 tensile test Methods 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/28—Investigating ductility, e.g. suitability of sheet metal for deep-drawing or spinning
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- G—PHYSICS
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- G06F—ELECTRIC DIGITAL DATA PROCESSING
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- G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
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- G16C—COMPUTATIONAL CHEMISTRY; CHEMOINFORMATICS; COMPUTATIONAL MATERIALS SCIENCE
- G16C60/00—Computational materials science, i.e. ICT specially adapted for investigating the physical or chemical properties of materials or phenomena associated with their design, synthesis, processing, characterisation or utilisation
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0001—Type of application of the stress
- G01N2203/0003—Steady
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0014—Type of force applied
- G01N2203/0016—Tensile or compressive
- G01N2203/0017—Tensile
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/02—Details not specific for a particular testing method
- G01N2203/022—Environment of the test
- G01N2203/0222—Temperature
- G01N2203/0228—Low temperature; Cooling means
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
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Abstract
The invention provides an accurate measurement method of low-temperature elongation of an aluminum alloy for aerospace, which comprises the step of measuring the room-temperature fracture elongation delta of an aluminum alloy samplesAnd according to the formula deltad＝a1Tn+a2δs m+a3And accurately obtain the low-temperature fracture elongation delta of the aluminum alloy sampledWherein a is1、a2、a3N and m are the material parameters of the aluminum alloy. The invention solves the problem that the fracture elongation of the high-strength aluminum alloy at low temperature can not be accurately measured by simple equipment and methodThe problem of (2). The relation between the elongation at break at low temperature and the elongation at break at room temperature is established through finite element simulation, the elongation at break at low temperature of the aluminum alloy can be indirectly obtained through directly measuring the elongation at break at room temperature, and accurate reference is provided for the design, manufacture and application of the low-temperature aluminum alloy structure.
Description
Technical Field
The invention belongs to the technical field of low-temperature testing of mechanical properties of aluminum alloy, and particularly relates to an accurate measurement method of low-temperature elongation of a light high-strength aluminum alloy for aerospace.
Background
The high-strength aluminum alloy has the characteristics of high specific strength, strong corrosion resistance, good welding performance and the like, and is widely applied to the field of aerospace. The structural material of the low-temperature propellant tank of the rocket is mainly 2219 aluminum alloy or 2195 aluminum-lithium alloy at present, and the rocket bears various complex stresses such as axial force, torque, bending moment and the like in the flight process and has extremely high requirements on the performance of the material. Researches show that the mechanical properties of the material at low temperature, including tensile strength, yield strength and elongation, are greatly improved, so that the accurate representation of the property change rule of the material at low temperature is extremely important to the safety and reliability of the storage tank structure. At present, the method for measuring the mechanical properties of the aluminum alloy at low temperature mainly comprises the steps of carrying out a tensile test in a liquid nitrogen low-temperature environment according to a national standard processing sample, automatically recording a stress-strain curve by an equipment computer, and obtaining tensile strength and yield strength, but measuring the gauge length by a vernier caliper at room temperature according to the elongation, thereby obtaining the elongation. However, in the method for measuring the elongation, because the gauge length area is marked on the sample at room temperature before the experiment, and the gauge length after the experiment is broken is measured at room temperature, the elongation is not the fracture elongation at low temperature in the true sense, and a certain error exists in the measurement result. Therefore, there is a need in the art for a method of measuring elongation at break under low temperature conditions.
Patent CN201410596978 relates to an optical test method for low-temperature mechanical properties of a metal welding test piece, which comprises firstly, manufacturing the welding test piece, and dividing the welding test piece into a welding zone, a heat affected zone and a base metal zone; then, placing the welding test piece in a low-temperature environment, and installing a digital camera above the welding test piece, wherein the digital camera is connected to a data acquisition system through a data line; calculating a strain value through the speckle images of the welding test piece obtained in the step before and after the load is applied; and calculating the engineering stress, the testing stress, the strength limit and the elongation of each area and the whole welding test piece to obtain the mechanical property parameters of the fusion welding test piece. The beneficial effects of this patent include: the method is suitable for testing the mechanical properties of the aluminum alloy and other metals and welded structures in different welding modes in a low-temperature environment; the method divides the welding test piece into different areas, and solves the technical problem that the optical test method cannot be used for mechanical performance test in a low-temperature environment. However, liquid nitrogen is needed in the detection process of the patent, and detection in the liquid nitrogen environment is affected by steam, so that the problems of frosting of a test sample and refraction error in detection are easily caused; and it is difficult to clearly photograph using a digital camera. In addition, the optical instruments used in the patent are too complex to implement, both apparatus and method.
Therefore, a simple method for accurately measuring the low-temperature elongation of the light high-strength aluminum alloy for aerospace still needs to be provided in the field.
Disclosure of Invention
The invention firstly discloses a method for indirectly obtaining the fracture elongation at low temperature by measuring the fracture elongation at room temperature by means of finite element simulation, so that the measurement of the low-temperature fracture elongation of the high-strength aluminum alloy is more accurate and accords with the actual condition, and the safety of the low-temperature storage tank structure for aerospace is improved.
The invention firstly provides an accurate measurement method of low-temperature elongation of aluminum alloy for aerospace, which comprises the step of measuring the room-temperature fracture elongation delta of an aluminum alloy samplesAnd according to the formula deltad＝a1Tn+a2δs m+a3And accurately obtain the low-temperature fracture elongation delta of the aluminum alloy sampledWherein a is1、a2、a3N and m are the material parameters of the aluminum alloy.
In one specific embodiment, the formula δd＝a1Tn+a2δs m+a3Each material parameter a in (1)1、a2、a3And n and m are obtained by fitting finite element simulation of the aluminum alloy sample under different low temperature conditions.
In a specific embodiment, the finite element simulation of the aluminum alloy sample comprises the steps of firstly carrying out low-temperature cold shrinkage finite element simulation on the aluminum alloy sample, and then carrying out low-temperature tensile fracture finite element simulation on the aluminum alloy sample; and then carrying out room temperature expansion finite element simulation on the two parts of the aluminum alloy sample after the aluminum alloy sample is pulled apart.
In a specific embodiment, the material parameters a in the formula are obtained1、a2、a3The process of n and m comprises the following steps repeated for different cryogenic conditions:
step A, processing an aluminum alloy tensile sample S according to national standard1Then, the scale distance L of the sample is carved at room temperature1；
Step B, performing low-temperature cold shrinkage finite element simulation on the aluminum alloy tensile sample with the marked gauge length, thereby obtaining the length L of the gauge length after low temperature2In this case, the low-temperature sample is referred to as S2；
Step C, for low-temperature sample S2Performing low-temperature tensile fracture finite element simulation, and inputting a material constant and a stress-strain relation at low temperature into a finite element simulation model;
step D, remeasurement S2Gauge length L after tensile fracture of sample3Thereby obtaining elongation at break delta of the sample at low temperatured＝(L3-L2)/L2；
Step E, aligning the fractured sample S2Then carrying out room temperature expansion finite element simulation on the two parts, and then measuring the gauge length L after fracture4To obtain the elongation at break delta at room temperatures＝(L4-L1)/L1。
In a specific embodiment, the aluminum alloy is 2219 aluminum alloy or 2195 aluminum lithium alloy.
The invention solves the problem that the fracture elongation of the high-strength aluminum alloy at low temperature cannot be accurately measured by simple equipment and a method. The relation between the elongation at break at low temperature and the elongation at break at room temperature is established through finite element simulation, the elongation at break at low temperature of the aluminum alloy can be indirectly obtained through directly measuring the elongation at break at room temperature, and accurate reference is provided for the design, manufacture and application of the low-temperature aluminum alloy structure.
Detailed Description
Example 1
1. Processing tensile sample S according to national standard1Then, the scale distance L of the sample is carved at room temperature1；
2. Carrying out low-temperature cold shrinkage finite element simulation on the sample with the marked gauge length so as to obtain the length L of the gauge length after low temperature2In this case, the low-temperature sample is referred to as S2；
3. For low temperature sample S2Performing low-temperature tensile fracture finite element simulation, wherein a material constant and a stress-strain relation at low temperature need to be input into a model;
4. remeasured S2Gauge length L after sample breakage3Thereby obtaining elongation at break delta of the sample at low temperatured＝(L3-L2)/L2；
5. Sample S after being split2Then carrying out room temperature expansion finite element simulation on the two parts, and then measuring the gauge length L after fracture4In this way, the elongation at break delta at room temperature is obtaineds＝(L4-L1)/L1；
6. And (3) repeating the steps 1-5 according to different low-temperature conditions to obtain a plurality of groups of corresponding fracture elongation rates at low temperature and room temperature, and establishing the following relation: deltad＝a1Tn+a2δs m+a3Wherein a is1、a2、a3N and m are material parameters and T is temperature. Thus, the room-temperature elongation at break δ of the specimen was measuredsThe elongation at break delta at low temperature can be accurately obtainedd。
The invention solves the problem that the fracture elongation of the high-strength aluminum alloy at low temperature cannot be accurately measured by simple equipment and a method. The relation between the elongation at break at low temperature and the elongation at break at room temperature is established through finite element simulation, the elongation at break at low temperature of the aluminum alloy can be indirectly obtained through directly measuring the elongation at break at room temperature, and accurate reference is provided for the design, manufacture and application of the low-temperature aluminum alloy structure.
The above-mentioned embodiments only express several embodiments of the present application, and the description thereof is more specific and detailed, but not construed as limiting the scope of the invention. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the concept of the present application, which falls within the scope of protection of the present application. Therefore, the protection scope of the present patent shall be subject to the appended claims.
Claims (5)
1. An accurate measurement method for the low-temperature elongation of an aluminum alloy for aerospace comprises the step of measuring the room-temperature fracture elongation delta of an aluminum alloy samplesAnd according to the formula deltad＝a1Tn+a2δs m+a3And accurately obtain the low-temperature fracture elongation delta of the aluminum alloy sampledWherein a is1、a2、a3N and m are the material parameters of the aluminum alloy.
2. Measuring method according to claim 1, characterized in that said formula δd＝a1Tn+a2δs m+a3Each material parameter a in (1)1、a2、a3And n and m are obtained by fitting finite element simulation of the aluminum alloy sample under different low temperature conditions.
3. The measurement method according to claim 2, wherein the finite element simulation of the aluminum alloy sample comprises performing a low temperature cold shrinkage finite element simulation of the aluminum alloy sample, and then performing a low temperature tensile fracture finite element simulation of the aluminum alloy sample; and then carrying out room temperature expansion finite element simulation on the two parts of the aluminum alloy sample after the aluminum alloy sample is pulled apart.
4. A method according to any one of claims 1 to 3, wherein each material parameter a in the formula is obtained1、a2、a3The process of n and m comprises the following steps repeated for different cryogenic conditions:
step A, processing an aluminum alloy tensile sample S according to national standard1Then, the scale distance L of the sample is carved at room temperature1；
Step B, performing low-temperature cold shrinkage finite element simulation on the aluminum alloy tensile sample with the marked gauge length, thereby obtaining the length L of the gauge length after low temperature2In this case, the low-temperature sample is referred to as S2；
Step C, for low-temperature sample S2Performing low-temperature tensile fracture finite element simulation, and inputting a material constant and a stress-strain relation at low temperature into a finite element simulation model;
step D, remeasurement S2Gauge length L after tensile fracture of sample3Thereby obtaining elongation at break delta of the sample at low temperatured＝(L3-L2)/L2；
Step E, aligning the fractured sample S2Then carrying out room temperature expansion finite element simulation on the two parts, and then measuring the gauge length L after fracture4To obtain the elongation at break delta at room temperatures＝(L4-L1)/L1。
5. The method according to any one of claims 1 to 4, wherein the aluminum alloy is a 2219 aluminum alloy or a 2195 aluminum lithium alloy.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN116189831A (en) * | 2023-03-01 | 2023-05-30 | 深圳市正泰隆科技有限公司 | Method and system for measuring low-temperature fracture elongation of aluminum alloy |
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| CN116189831B (en) * | 2023-03-01 | 2024-03-26 | 深圳市正泰隆科技有限公司 | Method and system for measuring low-temperature fracture elongation of aluminum alloy |
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