CN106872299A - A kind of method for predicting magnesium alloy component fatigue limit - Google Patents
A kind of method for predicting magnesium alloy component fatigue limit Download PDFInfo
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- CN106872299A CN106872299A CN201710065251.1A CN201710065251A CN106872299A CN 106872299 A CN106872299 A CN 106872299A CN 201710065251 A CN201710065251 A CN 201710065251A CN 106872299 A CN106872299 A CN 106872299A
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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
- G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
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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
- G01N2203/0005—Repeated or cyclic
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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
-
- 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
- G01N2203/0058—Kind of property studied
- G01N2203/0069—Fatigue, creep, strain-stress relations or elastic constants
- G01N2203/0073—Fatigue
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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
- G01N2203/06—Indicating or recording means; Sensing means
- G01N2203/067—Parameter measured for estimating the property
- G01N2203/0676—Force, weight, load, energy, speed or acceleration
Abstract
A kind of method for predicting magnesium alloy component fatigue limit, belong to the technical field of magnesium alloy materials mechanical property, it is characterized in that, for deformation process of the magnesium alloy under Cyclic Load, because magnesium alloy sample can occur irreversible transformation under compared with high circulation stress, simultaneously with the regular change of strain, obtain averaging loop strain curve, by analyzing the linear relationship between averaging loop strain curve stationary value and cyclic loading, obtain two straight-line intersections, and then try to achieve the fatigue limit of magnesium alloy, the method is observed test specimen always without experimenter, with convenient, fast, accurate the advantages of.
Description
Technical field
A kind of method for predicting magnesium alloy component fatigue limit of the present invention, belongs to the measurement of magnesium alloy materials fatigue dangerous spot
And the application field of fatigue limit prediction.
Background technology
Magnesium alloy is most light structural metallic materials, with density it is low, specific strength and specific stiffness are high, damping shock absorption is good,
Machinability is excellent, accessory size is stable, the features such as easily reclaim, in the delivery equipment industry tool such as " land, sea, air, day " traffic
There is potential application value.Meanwhile, these structures all be unable to do without the support of solder technology, all bear the effect of fatigue load, hold
It is also easy to produce fatigue failure.
Fatigue fracture is a kind of principal mode of metal material and its welding structure failure, and it occurs bearing alternation or arteries and veins
In the structure of dynamic strain, in general, maximum stress during corresponding to fatigue rupture will be less than the tensile strength of material, or even low
In the yield point of material.Statistics shows, in the fracture failure of dynamic load structure, the accident for having 70 % ~ 90 % be due to
What the fatigue fracture of welding point was caused, once there is fatigue failure accident, the bringing on a disaster property of lives and properties for often giving people
Loss and pain.
The determination of the fatigue behaviour of current Structure of magnesium alloy is mainly to be carried out by the means tested, and usual metal material is tired
Labor performance measurement method needs to carry out the cyclic test of cycles up to a million by multiple test specimens, and wherein lifting and lowering method one kind is accomplished by 13
Test specimen more than individual.And non-ferrous metal such as magnesium alloy does not have obvious fatigue limit due to its special institutional framework, experiment is followed
Ring number of times is more up to up to ten million times.Not only expend substantial amounts of human and material resources, and waste the substantial amounts of time, it is necessary to several days even
The time of some months just can be estimated and predict to a kind of fatigue life of material.
Recently, a kind of system and method (application number that magnesium alloy component fatigue limit is predicted based on infrared thermal imaging：
, and a kind of fatigue analysis method based on magnesium alloy surface of test piece temperature profile 201210549354.2)（The patent No.：
ZL201410263559.3）It is suggested, both approaches monitor magnesium alloy in fatigue test process pilot scale using thermal infrared imager
The temperature change on part surface, contrasts the temperature rise value in surface of test piece and different cross section under different stress levels, and then determine that magnesium is closed
The fatigue limit of gold.Compared with current fatigue test method, the method by test specimen without being loaded onto generation fatigue failure or complete
Into all 107Cycle CYCLIC LOADING, saves test period to a certain extent.However, both approaches need to use it is infrared
Thermal imaging system, cost of equipment and use condition are more harsh, and process of the test is not easy enough, are unfavorable for promoting the use of.
The content of the invention
A kind of method for predicting magnesium alloy component fatigue limit of the present invention, it is therefore intended that：For the situation of background technology, make
Low cycle fatigue test machine is used, based on the irreversible defect theory of material and its component during bearing compared with high circulation load,
When load is more than fatigue limit fatigue strength, the irreversible transformation and processing hardening caused by the non-elastic effect of material are existing
As occurring without substantially processing hardening phenomenon during less than fatigue limit, corresponding dynamic strain stabilization when changing according to dynamic load
The Changing Pattern of value, the method for setting up the magnesium alloy component fatigue limit prediction of averaging loop strain curve development law.
A kind of method for predicting magnesium alloy component fatigue limit of the present invention, it is characterised in that comprise the following steps：
First, according to GB GB/T 228-2008 processing magnesium alloy fatigue testing specimens；
Second, according to the test method that standard specifies, fatigue testing specimen is clamped on fatigue tester, tensile testing instrument is used
SDS-100 sound fatigue tester test systems, while installing dynamic extensometer on sample to be tested, record every in loading procedure
Dynamic stress, dynamic strain numerical value under one loaded cycle number of times；
3rd, by the fatigue data obtained by experiment, the mean strain under correspondence cycle-index is obtained, formula is as follows：
（1）
Whereinε rIt isrSecondary strain mean,ε rmaxWithε rminRespectivelyrMaximum and most is strained during secondary circulation
Small value；
4th, using formula（1）Subtract initial mean strain and draw mean strain scope；
（2）
Whereinε 1It is initial mean strain；
5th, by under each stressε rWith cycle-indexNDrawing of Curve takes each stress lower curve in the same coordinate systemε rStationary valueε s；
6th, by fatigue data under each stress obtained by experiment (ε sWithσ max) it is plotted in log-log coordinate (lgε s- lgσ max) in；
7th, the point diagram of drafting is carried out into linear fit, seek two straight-line intersections correspondence cyclic loading and enter with normal experiment result
Row data compare and error analysis.
The advantage of method that the present invention is a kind of to predict magnesium alloy component fatigue limit is：The method is directed to metal material
When bearing fatigue load and acting on, the irreversible transformation of generation measures the dynamic stress of material-should by dynamic extensometer
Varied curve, using mean strain stationary valueε sWith corresponding cyclic loadingσ maxPiecewise fitting is carried out, material or structure is determined
Dangerous Load, the fatigue limit drawn using linear intersection point has obvious advanced, the method technique compared with background technology
Advanced reasonable, continuous and compact can be used to estimate the fatigue limit of in-service Structure of magnesium alloy.
Brief description of the drawings
Fig. 1 Fatigue of Magnesium Alloys pilot system figures
Figure acceptance of the bid invoice is as follows：
1 fatigue test system, 2 tired fixtures, 3 Fatigue of Magnesium Alloys test specimens, 4 fatigue test control devices, 5 dynamics are extended
Meter, 6 overall analysis systems.
Fig. 2 magnesium alloy plate fatigue sample structural representations
Fig. 3 is that the averaging loop strain curve under magnesium alloy plate different loads of the invention initially raises section figure
Figure acceptance of the bid invoice is as follows：
(L2 correspondence 140MPa, L3 correspondence 130 MPa, L4 correspondence 120 MPa, L5 correspondence 110MPa, L6 correspondences 100MPa, L7
30 MPa of correspondence 90MPa, L8 correspondence 70 MPa, L9 correspondence 50MPa, L10 correspondences)
Fig. 4 is averaging loop strain stable value piecewise fitting straight line and tired pole under magnesium alloy plate different loads of the invention
Limit determines point diagram
Figure acceptance of the bid invoice is as follows：
P1 is that averaging loop strain stable is worth larger measuring point, P2 for averaging loop strain stable is worth less measuring point, L11
It to the less measuring point fitting a straight line of averaging loop strain stable value, L12 is the survey larger to averaging loop strain stable value to be
Fixed point fitting a straight line, A points are two straight-line intersections, the correspondence Fatigue of Magnesium Alloys limit.
Fig. 5 obtains fatigue S-N diagram, S-N curve for Chang Fangfa
Figure acceptance of the bid invoice is as follows：
D cycle-indexes corresponding to experiment gained fracture sample pulsating stress, W is the corresponding circulation of unbroken sample pulsating stress
Number of times, L12 is double-log fitting a straight line.
Specific embodiment
One kind prediction magnesium alloy component fatigue limit method, including have the following steps：
The chemical substance material for using is：Magnesium alloy plate, ethanol, propelling pencil, graduated scale and sand paper, it is as follows that it prepares consumption：
With millimeter, milliliter as measurement unit
Magnesium alloy plate：Mm × 300 mm of AZ31B 300 × 3 pieces of 5mm
Ethanol：C2H5OH 500 mL±10 mL
Sand paper：Mm × 0.5 mm × 230 mm 2 of 800 mesh of SiC 276
Sand paper：Mm × 0.5 mm × 230 mm 2 of 1000 mesh of SiC 276
Sand paper：Mm × 0.5 mm × 230 mm 2 of 1500 mesh of SiC 276
First test specimen is processed and prepared
1. 15 AZ31B Fatigue of Magnesium Alloys samples are processed according to GB/T 228-2008 standards, sample is axially plate rolling
Direction；
2. sand papering fatigue sample is used, makes surface of test piece and linear cutter face smooth, it is desirable to test specimen positive and negative and wire cutting
The roughness of machined surface reachesR a=0.32-0.63 μm；
3. fatigue sample is cleaned with ethanol, makes surface of test piece clean；
Second loading specimen and experiment prepare
Fatigue testing specimen is loaded on fatigue tester, dynamic extensometer is clipped in sample marking distance, the zeroing of equipment soft and hardware,
Adjust fatigue test parameter；
3rd damage parameters are set
Each sample one stress parameters of correspondence, circulation maximum stress is respectively adopted 140 MPa, the MPa of 130 MPa 120,110
MPa, 100 MPa, 90 MPa, 70 MPa, 50 MPa, 30 MPa, it is 0.1 to carry cycle specificity coefficient, and resonant frequency is 1 Hz；
4th fatigue data is gathered
Experiment is acquired using dynamic extensometer to stress-strain data simultaneously, and experiment cycle-index stops when being 25000；
5th Data Processing in Experiment and analysis
1. the result of the test that dynamic extensometer is measured is analyzed, based on formula（1）Extract strain of the test specimen under fatigue load effect
Average data；
（1）
Whereinε rIt isrSecondary strain mean,ε rmaxWithε rminRespectivelyrMaximum and most is strained during secondary circulation
Small value.
2. formula is utilized（1）Subtract initial mean strain and draw mean strain scope；
（2）
Whereinε 1It is initial mean strain.
6th, by under each stressε rWith cycle-index N Drawing of Curve in the same coordinate system, each stress lower curve is taken
∆ε rThe stationary value when cycle-index is 25000ε s
7th, using origin softwares by fatigue data under each stress obtained by experiment (ε sWithσ max) it is plotted in double-log seat
Mark (lgε s- lgσ max) in；The fatigue limit 94.05MPa of magnesium alloy plate is determined using curve catastrophe point；
8th tests gained S-N curves using plain fatigue, 107When fatigue limit be 90.43MPa.Step 7 is obtained
Fatigue limit contrasted with plain fatigue result of the test, draw based on mean strain stationary valueε sDetermine Fatigue of Magnesium Alloys
The relative error of the limit is 4.3%.
It should be appreciated that for those of ordinary skills, can according to the above description be improved or converted,
And all these modifications and variations should all belong to the protection domain of appended claims of the present invention.
Claims (1)
1. it is a kind of predict magnesium alloy component fatigue limit method, it is characterised in that for magnesium alloy under Cyclic Load
Deformation process, because magnesium alloy sample can occur irreversible transformation under compared with high circulation stress, at the same with strain rule
Property change, averaging loop strain curve is obtained, by analyzing the line between averaging loop strain curve stationary value and cyclic loading
Sexual intercourse, obtains two straight-line intersections, and then tries to achieve the fatigue limit of magnesium alloy, comprises the following steps that：
The chemical substance material for using is：Magnesium alloy plate, ethanol, propelling pencil, graduated scale and sand paper, it is as follows that it prepares consumption：
With millimeter, milliliter as measurement unit
Magnesium alloy plate：Mm × 300 mm of AZ31B 300 × 3 pieces of 5mm
Ethanol：C2H5OH 500 mL±10 mL
Sand paper：Mm × 0.5 mm × 230 mm 2 of 800 mesh of SiC 276
Sand paper：Mm × 0.5 mm × 230 mm 2 of 1000 mesh of SiC 276
Sand paper：Mm × 0.5 mm × 230 mm 2 of 1500 mesh of SiC 276
First test specimen is processed and prepared
1. 15 AZ31B Fatigue of Magnesium Alloys samples are processed according to GB/T 228-2008 standards, sample is axially plate rolling side
To；
2. sand papering fatigue sample is used, makes surface of test piece and linear cutter face smooth, it is desirable to test specimen positive and negative and wire cutting
The roughness of machined surface reachesR a=0.32-0.63 μm；
3. fatigue sample is cleaned with ethanol, makes surface of test piece clean；
Second loading specimen and experiment prepare
Fatigue testing specimen is loaded on fatigue tester, dynamic extensometer is clipped in sample marking distance, the zeroing of equipment soft and hardware,
Adjust fatigue test parameter；
3rd damage parameters are set
Each sample one stress parameters of correspondence, circulation maximum stress is respectively adopted 140 MPa, the MPa of 130 MPa 120,110
MPa, 100 MPa, 90 MPa, 70 MPa, 50 MPa, 30 MPa, it is 0.1 to carry cycle specificity coefficient, and resonant frequency is 1 Hz；
4th fatigue data is gathered
Experiment is acquired using dynamic extensometer to stress-strain data simultaneously, and experiment cycle-index stops when being 25000；
5th Data Processing in Experiment and analysis
1. the result of the test that dynamic extensometer is measured is analyzed, based on formula（1）Extract strain of the test specimen under fatigue load effect
Average data；
（1）
Whereinε rIt isrSecondary strain mean,ε rmaxWithε rminRespectivelyrMaximum and most is strained during secondary circulation
Small value；
2. formula is utilized（1）Subtract initial mean strain and draw mean strain scope；
（2）
Whereinε 1It is initial mean strain；
6th, by under each stressε rWith cycle-index N Drawing of Curve in the same coordinate system, each stress lower curve is takenε r
The stationary value when cycle-index is 25000ε s；
7th, using origin softwares by fatigue data under each stress obtained by experiment (ε sWithσ max) it is plotted in double-log seat
Mark (lgε s- lgσ max) in；The fatigue limit 94.05MPa of magnesium alloy plate is determined using curve catastrophe point；
8th tests gained S-N curves using plain fatigue, 107When fatigue limit be 90.43MPa, step 7 is obtained
Fatigue limit contrasted with plain fatigue result of the test, draw based on mean strain stationary valueε sDetermine Fatigue of Magnesium Alloys
The relative error of the limit is 4.3%.
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108038311A (en) * | 2017-12-12 | 2018-05-15 | 吉林大学 | The heat resistance magnesium alloy Forecasting Methodology that heavy wear changes at 50-200 DEG C |
| CN109520717A (en) * | 2018-12-20 | 2019-03-26 | 中国航发四川燃气涡轮研究院 | A kind of engine spindle Fatigue Testing Loads determine method |
| CN109855959A (en) * | 2017-11-30 | 2019-06-07 | 中国科学院金属研究所 | A kind of prediction technique of Metal Material Fatigue intensity |
| CN111122357A (en) * | 2019-12-18 | 2020-05-08 | 中国科学院金属研究所 | Method for testing fatigue life of aluminum alloy conductor |
| CN111638148A (en) * | 2020-07-07 | 2020-09-08 | 一汽解放汽车有限公司 | Method for testing S-N curve of similar metal material |
| CN112014218A (en) * | 2020-09-16 | 2020-12-01 | 山东电力设备有限公司 | Compression ratio measuring method |
| CN112284942A (en) * | 2020-10-23 | 2021-01-29 | 哈尔滨工业大学 | Thermal boundary condition control method for fatigue limit evaluation of welding joint |
| CN113252462A (en) * | 2021-06-07 | 2021-08-13 | 潍柴动力股份有限公司 | Method and system for detecting gas cylinder and readable storage medium |
| CN113776964A (en) * | 2021-08-24 | 2021-12-10 | 中国航发北京航空材料研究院 | Method for testing fatigue limit of feature structure simulation piece |
| CN115862789A (en) * | 2023-02-09 | 2023-03-28 | 中国航发四川燃气涡轮研究院 | Low-cycle fatigue life prediction method for fiber reinforced metal matrix composite material component |
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| CN109855959A (en) * | 2017-11-30 | 2019-06-07 | 中国科学院金属研究所 | A kind of prediction technique of Metal Material Fatigue intensity |
| CN109855959B (en) * | 2017-11-30 | 2021-08-10 | 中国科学院金属研究所 | Prediction method for fatigue strength of metal material |
| CN108038311B (en) * | 2017-12-12 | 2021-03-02 | 吉林大学 | Prediction method for severe abrasion transformation of heat-resistant magnesium alloy at 50-200 DEG C |
| CN108038311A (en) * | 2017-12-12 | 2018-05-15 | 吉林大学 | The heat resistance magnesium alloy Forecasting Methodology that heavy wear changes at 50-200 DEG C |
| CN109520717A (en) * | 2018-12-20 | 2019-03-26 | 中国航发四川燃气涡轮研究院 | A kind of engine spindle Fatigue Testing Loads determine method |
| CN109520717B (en) * | 2018-12-20 | 2020-10-20 | 中国航发四川燃气涡轮研究院 | Method for determining fatigue test load of engine spindle |
| CN111122357A (en) * | 2019-12-18 | 2020-05-08 | 中国科学院金属研究所 | Method for testing fatigue life of aluminum alloy conductor |
| CN111638148A (en) * | 2020-07-07 | 2020-09-08 | 一汽解放汽车有限公司 | Method for testing S-N curve of similar metal material |
| CN111638148B (en) * | 2020-07-07 | 2022-08-12 | 一汽解放汽车有限公司 | Method for testing S-N curve of similar metal material |
| CN112014218A (en) * | 2020-09-16 | 2020-12-01 | 山东电力设备有限公司 | Compression ratio measuring method |
| CN112284942A (en) * | 2020-10-23 | 2021-01-29 | 哈尔滨工业大学 | Thermal boundary condition control method for fatigue limit evaluation of welding joint |
| CN112284942B (en) * | 2020-10-23 | 2024-03-26 | 哈尔滨工业大学 | Thermal boundary condition control method for fatigue limit assessment of welded joint |
| CN113252462A (en) * | 2021-06-07 | 2021-08-13 | 潍柴动力股份有限公司 | Method and system for detecting gas cylinder and readable storage medium |
| CN113776964A (en) * | 2021-08-24 | 2021-12-10 | 中国航发北京航空材料研究院 | Method for testing fatigue limit of feature structure simulation piece |
| CN113776964B (en) * | 2021-08-24 | 2023-03-14 | 中国航发北京航空材料研究院 | Method for testing fatigue limit of feature structure simulation piece |
| CN115862789A (en) * | 2023-02-09 | 2023-03-28 | 中国航发四川燃气涡轮研究院 | Low-cycle fatigue life prediction method for fiber reinforced metal matrix composite material component |
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Application publication date: 20170620 |