CN108920792A - A kind of agitating friction weldering Fatigue Life Prediction method based on crackle extension - Google Patents
A kind of agitating friction weldering Fatigue Life Prediction method based on crackle extension Download PDFInfo
- Publication number
- CN108920792A CN108920792A CN201810646505.3A CN201810646505A CN108920792A CN 108920792 A CN108920792 A CN 108920792A CN 201810646505 A CN201810646505 A CN 201810646505A CN 108920792 A CN108920792 A CN 108920792A
- Authority
- CN
- China
- Prior art keywords
- crackle
- crack
- formula
- stress
- fatigue life
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
-
- 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
- G06F2119/04—Ageing analysis or optimisation against ageing
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- Computer Hardware Design (AREA)
- Evolutionary Computation (AREA)
- Geometry (AREA)
- General Engineering & Computer Science (AREA)
- General Physics & Mathematics (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
Abstract
A kind of agitating friction weldering Fatigue Life Prediction method based on crackle extension, belongs to mechanical structure fatigue diagnostic analysis technical field.Bone-shaped plane plate specimen is prepared, the small fatigue crack growth replica test under different stress loadings and different stress ratios is carried out in connector different zones, calculates crackle spreading rate with secant method；Connector crackle stress intensity factor range is calculated using New-Raju model；The semicircular arc-shaped depth direction c value and width direction a/2 value in crack Propagation area in connector different zones fracture apperance is measured, calculates that crackle is profound to compare 2c/a；Draw the curve that crack growth rate changes with stress intensity factor range；Calculate effective stress intensity factor；Determine crackle spreading rate formula；Determine initial crack size a0With critical crack size ac；Crackle spreading rate formula is integrated, the fatigue life of welded unit is obtained.The program being capable of simpler, accurately prediction agitating friction weldering component fatigue life.
Description
Technical field
The present invention relates to a kind of Prediction method for fatigue life, in particular to a kind of agitating friction weldering based on crackle extension
Fatigue Life Prediction method belongs to mechanical structure fatigue diagnostic analysis technical field.
Background technique
For agitating friction weldering component, welding point is part most weak in total, the master of welded unit
Wanting failure mode is fatigue fracture.Fatigue testing specimen undergoes the process of crack initiation, crackle extension and long crack extension.Wherein,
The germinating of crackle and extension phase account about the 70%~80% of fatigue life.In most cases, due to material itself
It is intrinsic be mingled with, the initial microdefect such as hardened granules and Micro-v oid or due to being collided in process, indentation and corrosion
Deng and cause sample exist damage.For friction stir welding, the initiating life of crackle is shared in Fatigue Life
Ratio it is smaller, therefore, omit this part initiating life, and predicted based on Theory of Fracture Mechanics and the propagation law of crackle
Fatigue life can make prediction result relatively reliable.
When establishing crack propagation model for agitating friction weldering component, need to consider that the microstructure of connector different zones becomes
The factors such as change.Since the material parameters such as each region microstructure of agitating friction weldering welding point and performance are all different, for sprouting
The raw crackle in connector different zones, is influenced by microstructure and performance, and crackle propagation law is simultaneously different, is difficult with system
One formula carries out life prediction.When carrying out fatigue life prediction to agitating friction weldering component, in fatigue fracture Location-Unknown
In the case where, how the crackle propagation law based on different zones predicts that agitating friction welds the fatigue life of welding point.This
Crackle propagation law of the invention based on agitating friction weldering welding point different zones accurately predicts agitating friction weldering component
Fatigue life, being on active service to the safety of welded unit has theory significance and engineering application value.
Summary of the invention
It is an object of the invention to be based on crackle propagation law, more simply, accurately prediction agitating friction welds component
Fatigue life.
In order to solve the above technical problems, a kind of agitating friction weldering based on crackle extension of the technical solution adopted by the present invention
Fatigue Life Prediction method, specific step is as follows for this method：
Step 1)：The bone-shaped plate that the cracked region of expected welding point is smallest cross-sectional is made to welding fatigue testing specimen
Sample carries out the small fatigue crack growth replica examination under the different stress loadings of welding point different zones and different stress ratios
It tests, crackle spreading rate is calculated using secant method, formula is as follows：
Wherein Δ N is intercycle, and Δ a is crack length variation, aiTo be N in recurring numberiWhen crack length；
Step 2)：Using New-Raju model, welding point crackle stress intensity factor range is calculated：
Wherein Δ S is the range of stress, and a is face crack length, and Q is form factor, and F is the edge correction factor, and c is crackle
Depth, t are sample thickness, and b is specimen width,For angle function；0 < c/a≤1/2,0 < c/t≤1, a/b < 1,
According to elliptic integral of the second kind, formula is as follows for the calculating of form factor Q：
F is the dimensionless edge correction factor, and formula is as follows：
Wherein M1、M2、M3、fφ、g、fωIt is calculated with following formula：
Step 3)：Measure the semicircular arc-shaped depth side of crack Propagation area in welding point different zones fracture apperance
It to c value and width direction a/2 value, calculates that crackle is profound than 2c/a, takes the mean value of different zones 2c/a agitating friction as a whole
The profound ratio of plumb joint crackle,60 ° are taken, as shown in Figure 2.
Step 4)：Using Paris formula, both sides take logarithm：
Lg (da/dN)=lgC+mlg (Δ K) (11)
Wherein C, m are constant, and da/dN is crack growth rate, and Δ K is stress intensity factor range；
Draw crackle under welding point different zones difference stress loading and different stress ratio crack growth rate with
The curve of stress intensity factor range variation；
Step 5)：Effective stress intensity factor is calculated, considers the active strength factor Δ K of crack closureeffDefinition such as
Under：
ΔKeff=U Δ K (12)
Wherein U is crack closure coefficient；
When stress ratio is R, crack closure coefficient is U (R), and closure coefficient, which is added, can introduce stress ratio influence, makes connector
Different zones crack growth rate and effective stress intensity factor more level off to linear relationship；The crackle for selecting Schijve to propose
It is closed coefficient formula：
U (R)=0.55+0.33R+0.12R2 (13)
Step 6)：Based on Paris formula, determine that the expression formula of crackle spreading rate is：
It is fitted to obtain C according to the corresponding data of crackle spreading rate and effective stress intensity factor*、m*。
Step 7)：Initial crack size a0With critical crack size acDetermination；Most of crackles result from the micro- of material
Defect is seen, takes the sizes of different zones in 3-5 connector upper greater than Ordinary hardening, Particulate Inclusion or one times of surface unevenness
The size average of microdefect is stated as initial crack size a0；With sample thickness and the corresponding crackle ruler of joint breaking toughness
Smaller value in very little is as critical crack size ac；The fracture toughness K of material is wherein obtained by testC, calculation formula is as follows：
Wherein Y is crack shape coefficient, σcFor fracture strength；
Step 8)：Formula (14) is integrated, the fatigue life of welded unit is obtained, formula is as follows：
Beneficial effect
The beneficial effects of the present invention are：A kind of agitating friction based on crackle extension of the present invention welds Predict Fatigue Life of Components
Prediction technique is not required to consider connector different zones microstructure and performance shadow for germinating the crackle in connector different zones
It rings, the crack propagation data of connector different zones is handled using Uniform Formula.The fatigue fracture Location-Unknown the case where
Under, Friction Stir Welding under different stress loadings and different stress ratios can be predicted based on the crackle propagation law of different zones
The fatigue life of head, calculation are simpler, accurate.
Detailed description of the invention
Fig. 1 is that a kind of agitating friction based on crackle propagation law of the present invention welds Fatigue Life Prediction method flow
Figure.
Fig. 2 is the geometry schematic diagram of face crack of the present invention.
Fig. 3 is test specimen lead crack spreading rate under stress ratios different in the embodiment of the present invention 1 with stress intensity factor range
Change diagram.
Fig. 4 is crack growth rate in the embodiment of the present invention 1 with the effective stress intensity range change curve.
Fig. 5 is 7075 Aluminum Alloy Friction Stir Welding head life prediction figures in the embodiment of the present invention 1.
Specific embodiment
Below with reference to embodiment, the present invention will be further described, but the present invention is not limited to following embodiments.
As shown in Figure 1, a kind of specific reality of the agitating friction weldering Fatigue Life Prediction method based on crackle extension
It is as follows to apply mode：
Step 1)：The bone-shaped plane plate specimen that expected cracked region is smallest cross-sectional is made to welding fatigue testing specimen, is opened
The small fatigue crack growth replica test under the different stress loadings of connector different zones and different stress ratios is opened up, using secant
Method calculates crackle spreading rate, and formula is as follows：
Wherein Δ N is intercycle, and Δ a is crack length variation, aiTo be N in recurring numberiWhen crack length；
Step 2)：Using New-Raju model, welding point crackle stress intensity factor range is calculated：
Wherein Δ S is the range of stress, and a is face crack length, and Q is form factor, and F is the edge correction factor, and c is crackle
Depth, t are sample thickness, and b is specimen width,For angle function；0 < c/a≤1/2,0 < c/t≤1, a/b < 1,
According to elliptic integral of the second kind, formula is as follows for the calculating of form factor Q：
F is the dimensionless edge correction factor, and formula is as follows：
Wherein M1、M2、M3、fφ、g、fωIt is calculated with following formula：
Step 3)：Measure the semicircular arc-shaped depth side of crack Propagation area in welding point different zones fracture apperance
It to c value and width direction a/2 value, calculates that crackle is profound than 2c/a, takes the mean value of different zones 2c/a agitating friction as a whole
The profound ratio of plumb joint crackle,60 ° are taken, as shown in Figure 2.
Step 4)：Using Paris formula, both sides take logarithm：
Lg (da/dN)=lgC+mlg (Δ K) (11)
Wherein C, m are constant, and da/dN is crack growth rate, and Δ K is stress intensity factor range；
Draw crackle under connector different zones difference stress loading and different stress ratio crack growth rate with stress
The curve of intensity factor range variation.
Step 5)：Effective stress intensity factor is calculated, considers the active strength factor Δ K of crack closureeffDefinition such as
Under：
ΔKeff=U Δ K (12)
Wherein U is crack closure coefficient；
When stress ratio is R, closure coefficient is U (R), and closure coefficient, which is added, can introduce stress ratio influence, keeps connector different
Zone crack spreading rate and effective stress intensity factor more level off to linear relationship.The crack closure for selecting Schijve to propose
Coefficient formula：
U (R)=0.55+0.33R+0.12R2 (13)
Step 6)：Based on Paris formula, determine that the expression formula of crackle spreading rate is：
It is fitted to obtain C according to the corresponding data of crackle spreading rate and effective stress intensity factor*、m*。
Step 7)：Initial crack size a0With critical crack size acDetermination.Most of crackles result from the micro- of material
Defect is seen, takes the sizes of different zones in 3-5 connector upper greater than Ordinary hardening, Particulate Inclusion or one times of surface unevenness
The size average of microdefect is stated as initial crack size a0.With sample thickness and the corresponding crackle ruler of joint breaking toughness
Smaller value in very little is as critical crack size ac.The fracture toughness K of material is obtained by testC, calculation formula is as follows：
Wherein Y is crack shape coefficient, σcFor fracture strength；
Step 8)：Formula (14) is integrated, the fatigue life of welded unit is obtained, formula is as follows：
This method is further illustrated below by way of specific embodiment：
Example 1：The 7075 Aluminum Alloy Friction Stir Welding head fatigue life predictions based on crackle extension
(1) 7075 aluminum alloy stirring friction welding fatigue testing specimens are prepared, the different stress loadings in connector different zones are carried out
And the small fatigue crack growth replica that stress ratio is 0.1 and -0.3 is tested, and calculates crackle spreading rate using secant method；(2)
Using New-Raju model, welding point crackle stress intensity factor range is calculated；(3) measurement welding point different zones are disconnected
Crack Propagation area in degree of lip-rounding looks semicircular arc-shaped depth direction c value and width direction a/2 value, calculate the profound ratio of crackle
The average value of 2c/a is about 0.9；(4) draw different stress when under different stress levels crack growth rate with stress intensity because
The curve of subrange variation, as shown in Figure 3；(5) the crack closure coefficient formula for selecting Schijve to propose calculates effective stress
Intensity factor, crack growth rate are as shown in Figure 4 with the effective stress intensity range change curve；(6) it is with Paris formula
Basis determines crackle spreading rate formula；(7) size of different zones in 5 connectors is taken to be greater than Ordinary hardening, Particulate Inclusion
Or the size average of one times of surface unevenness of above-mentioned microdefect is as initial crack size, this experiment resulting 7075
Aluminum Alloy Friction Stir Welding head initial crack size is taken as 10 μm.With sample thickness and the corresponding crackle ruler of joint breaking toughness
Smaller value in very little is as critical crack size, and it is corresponding to be less than the fracture toughness that test measures for fatigue testing specimen thickness in this experiment
Crack size, thickness of materialsing is as critical crack size；(8) crackle spreading rate formula is integrated, 7075 aluminium close
Golden friction stir welding life prediction figure is as shown in Figure 5.The bimetry of most of test specimen error compared with test life exists
Within twice of factor, life prediction works well.
Claims (2)
1. a kind of agitating friction based on crackle extension welds Fatigue Life Prediction method, step is：
Step 1)：The bone-shaped plate that the cracked region of expected welding point is smallest cross-sectional is made to welding fatigue testing specimen to try
Sample carries out the small fatigue crack growth replica examination under the different stress loadings of welding point different zones and different stress ratios
It tests, crackle spreading rate is calculated using secant method, formula is as follows：
Wherein Δ N is intercycle, and Δ a is crack length variation, aiTo be N in recurring numberiWhen crack length；
Step 2)：Using New-Raju model, welding point crackle stress intensity factor range is calculated：
Wherein Δ S is the range of stress, and a is face crack length, and Q is form factor, and F is the edge correction factor, and c is that crackle is deep
Degree, t is sample thickness, and b is specimen width,For angle function；0 < c/a≤1/2,0 < c/t≤1, a/b < 1,
According to elliptic integral of the second kind, formula is as follows for the calculating of form factor Q：
F is the dimensionless edge correction factor, and formula is as follows：
Wherein M1、M2、M3、fφ、g、fωIt is calculated with following formula：
Step 3)：Measure the semicircular arc-shaped depth direction c in crack Propagation area in welding point different zones fracture apperance
Value and width direction a/2 value, calculating crackle is profound than 2c/a, takes the mean value Friction Stir Welding as a whole of different zones 2c/a
The profound ratio of cephalic slit line；
Step 4)：Using Paris formula, both sides take logarithm：
Lg (da/dN)=lg C+m lg (Δ K) (11)
Wherein C, m are constant, and da/dN is crack growth rate, and Δ K is stress intensity factor range；
Draw crackle under welding point different zones difference stress loading and different stress ratio crack growth rate with stress
The curve of intensity factor range variation；
Step 5)：Effective stress intensity factor is calculated, considers the active strength factor Δ K of crack closureeffIt is defined as follows：
ΔKeff=U Δ K (12)
Wherein U is crack closure coefficient；
When stress ratio is R, crack closure coefficient is U (R), and closure coefficient, which is added, can introduce stress ratio influence, keeps connector different
Zone crack spreading rate and effective stress intensity factor more level off to linear relationship；The crack closure for selecting Schijve to propose
Coefficient formula：
U (R)=0.55+0.33R+0.12R2 (13)
Step 6)：Based on Paris formula, determine that the expression formula of crackle spreading rate is：
It is fitted to obtain C according to the corresponding data of crackle spreading rate and effective stress intensity factor*、m*；
Step 7)：Initial crack size a0With critical crack size acDetermination；Most of crackles result from the microcosmic of material and lack
It falls into, takes the sizes of different zones in 3-5 connector above-mentioned micro- greater than Ordinary hardening, Particulate Inclusion or one times of surface unevenness
The size average of defect is seen as initial crack size a0；In sample thickness and the corresponding crack size of joint breaking toughness
Smaller value as critical crack size ac；The fracture toughness K of material is wherein obtained by testC, calculation formula is as follows：
Wherein Y is crack shape coefficient, σcFor fracture strength；
Step 8)：Formula (14) is integrated, the fatigue life of welded unit is obtained, formula is as follows：
2. a kind of agitating friction based on crackle extension according to claim 1 welds Fatigue Life Prediction method,
It is characterized in that：The depth of the mean value of different zones 2c/a friction stir welding crackle as a whole is taken described in the step 3)
Long ratio,Take 60 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810646505.3A CN108920792B (en) | 2018-06-21 | 2018-06-21 | Friction stir welding component fatigue life prediction method based on small crack propagation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810646505.3A CN108920792B (en) | 2018-06-21 | 2018-06-21 | Friction stir welding component fatigue life prediction method based on small crack propagation |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108920792A true CN108920792A (en) | 2018-11-30 |
| CN108920792B CN108920792B (en) | 2022-04-19 |
Family
ID=64421734
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810646505.3A Active CN108920792B (en) | 2018-06-21 | 2018-06-21 | Friction stir welding component fatigue life prediction method based on small crack propagation |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108920792B (en) |
Cited By (23)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110008554A (en) * | 2019-03-27 | 2019-07-12 | 哈尔滨工业大学 | It is a kind of that prediction optimization method is shaped based on the stirring friction welding seam of numerical simulation and deep learning |
| CN110362926A (en) * | 2019-07-17 | 2019-10-22 | 佛山科学技术学院 | A kind of copper alloy butt plates welding fire check prediction technique based on ansys |
| CN110749500A (en) * | 2019-10-12 | 2020-02-04 | 广州特种承压设备检测研究院 | Prediction method for service life of in-service buried pipe |
| CN110967267A (en) * | 2019-11-25 | 2020-04-07 | 中国民用航空飞行学院 | Test method for judging fatigue crack initiation life |
| CN111024487A (en) * | 2019-12-29 | 2020-04-17 | 北京工业大学 | Method for predicting fatigue life of friction stir welding joint based on grain size and microhardness |
| CN111539142A (en) * | 2020-04-20 | 2020-08-14 | 中车青岛四方机车车辆股份有限公司 | Method and system for calculating crack propagation driving force of pipeline |
| CN111678990A (en) * | 2020-06-19 | 2020-09-18 | 四川大学 | Ultrasonic fatigue crack propagation rate measuring method based on natural frequency |
| CN111735695A (en) * | 2020-06-09 | 2020-10-02 | 西北工业大学 | Fatigue life prediction method based on CT test piece |
| CN111751199A (en) * | 2020-06-09 | 2020-10-09 | 西北工业大学 | Fatigue life prediction method based on EIFS distribution |
| CN112129660A (en) * | 2020-08-10 | 2020-12-25 | 北京工业大学 | Method for predicting fatigue life of friction stir welding joint after shot blasting |
| CN112182927A (en) * | 2020-09-15 | 2021-01-05 | 西北工业大学 | Method for simulating mutual influence of cracks of high-temperature alloy linear friction welding joint |
| CN112285140A (en) * | 2020-10-20 | 2021-01-29 | 北京航空航天大学 | Quantitative characterization method for early-stage propagation rate of internal crack of single crystal ultrahigh cycle fatigue |
| CN112329195A (en) * | 2020-09-14 | 2021-02-05 | 北京航空航天大学 | Method for calculating relatively small crack propagation rate in durability analysis |
| CN112834368A (en) * | 2020-10-27 | 2021-05-25 | 西南交通大学 | Prediction method for fatigue crack propagation life of pantograph |
| CN113340749A (en) * | 2021-04-30 | 2021-09-03 | 成都飞机工业（集团）有限责任公司 | Stress monitoring-based fatigue crack propagation life prediction method for high-lock bolt connecting piece |
| CN113378420A (en) * | 2020-11-27 | 2021-09-10 | 东南大学 | Method for predicting service life of crack pipeline |
| CN114047089A (en) * | 2021-09-30 | 2022-02-15 | 南京航空航天大学 | Method for calculating service life of material under action of thermal shock load |
| CN114117670A (en) * | 2021-11-24 | 2022-03-01 | 江苏科技大学 | Method for estimating fatigue striation spacing of grinding camshaft |
| CN114136827A (en) * | 2021-08-31 | 2022-03-04 | 江阴兴澄特种钢铁有限公司 | Test method for evaluating hydrogen-induced delayed crack tendency of high-strength steel welding |
| CN114216803A (en) * | 2021-09-30 | 2022-03-22 | 中国航发北京航空材料研究院 | High cycle fatigue full-life prediction method for metal material |
| CN114218661A (en) * | 2022-02-21 | 2022-03-22 | 中国海洋大学 | Fatigue crack propagation-based fatigue life prediction method |
| CN115019913A (en) * | 2022-05-12 | 2022-09-06 | 中国航发四川燃气涡轮研究院 | Method for calculating fatigue crack propagation life of dual-performance powder disc |
| CN117494421A (en) * | 2023-11-01 | 2024-02-02 | 北京航空航天大学 | Fatigue life prediction method for laser deposition forming titanium alloy |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105740551A (en) * | 2016-02-02 | 2016-07-06 | 湖南大学 | Weld joint fatigue life prediction method |
| CN105825030A (en) * | 2016-04-01 | 2016-08-03 | 长沙理工大学 | Method for evaluating fatigue life of aged reinforced concrete bridge |
| CN106153824A (en) * | 2016-06-22 | 2016-11-23 | 北京工业大学 | A kind of Prediction method for fatigue life based on crack closure effect |
-
2018
- 2018-06-21 CN CN201810646505.3A patent/CN108920792B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105740551A (en) * | 2016-02-02 | 2016-07-06 | 湖南大学 | Weld joint fatigue life prediction method |
| CN105825030A (en) * | 2016-04-01 | 2016-08-03 | 长沙理工大学 | Method for evaluating fatigue life of aged reinforced concrete bridge |
| CN106153824A (en) * | 2016-06-22 | 2016-11-23 | 北京工业大学 | A kind of Prediction method for fatigue life based on crack closure effect |
Non-Patent Citations (5)
| Title |
|---|
| DONGKAI SHANGGUAN等: "Analysis of crack growth in solder joints", 《SOLDERING & SURFACE MOUNT TECHNOLOGY》 * |
| GUOQIN SUN等: "Fatigue modeling and life prediction for friction stir welded joint based on microstructure and mechanical characterization", 《ACCEPTED MANUSCRIPT》 * |
| 张丽等: "基于小裂纹理论的GH4169高温合金的疲劳全寿命预测", 《航空材料学报》 * |
| 戴启雷等: "AA6082铝合金搅拌摩擦焊接头疲劳扩展速率", 《焊接》 * |
| 牛亚辉等: "基于等效裂纹初始尺寸的断裂力学疲劳评定", 《焊接技术》 * |
Cited By (35)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110008554B (en) * | 2019-03-27 | 2022-10-18 | 哈尔滨工业大学 | Method for optimizing technological parameters and welding tool structure of friction stir welding seam forming prediction based on numerical simulation and deep learning |
| CN110008554A (en) * | 2019-03-27 | 2019-07-12 | 哈尔滨工业大学 | It is a kind of that prediction optimization method is shaped based on the stirring friction welding seam of numerical simulation and deep learning |
| CN110362926B (en) * | 2019-07-17 | 2023-02-07 | 佛山科学技术学院 | Copper alloy flat plate butt welding thermal crack prediction method based on ansys |
| CN110362926A (en) * | 2019-07-17 | 2019-10-22 | 佛山科学技术学院 | A kind of copper alloy butt plates welding fire check prediction technique based on ansys |
| CN110749500A (en) * | 2019-10-12 | 2020-02-04 | 广州特种承压设备检测研究院 | Prediction method for service life of in-service buried pipe |
| CN110967267A (en) * | 2019-11-25 | 2020-04-07 | 中国民用航空飞行学院 | Test method for judging fatigue crack initiation life |
| CN111024487A (en) * | 2019-12-29 | 2020-04-17 | 北京工业大学 | Method for predicting fatigue life of friction stir welding joint based on grain size and microhardness |
| CN111539142A (en) * | 2020-04-20 | 2020-08-14 | 中车青岛四方机车车辆股份有限公司 | Method and system for calculating crack propagation driving force of pipeline |
| CN111539142B (en) * | 2020-04-20 | 2023-12-22 | 中车青岛四方机车车辆股份有限公司 | Pipeline crack propagation driving force calculation method and system |
| CN111735695A (en) * | 2020-06-09 | 2020-10-02 | 西北工业大学 | Fatigue life prediction method based on CT test piece |
| CN111751199A (en) * | 2020-06-09 | 2020-10-09 | 西北工业大学 | Fatigue life prediction method based on EIFS distribution |
| CN111751199B (en) * | 2020-06-09 | 2021-07-09 | 西北工业大学 | Fatigue life prediction method based on EIFS distribution |
| CN111735695B (en) * | 2020-06-09 | 2021-09-28 | 西北工业大学 | Fatigue life prediction method based on CT test piece |
| CN111678990A (en) * | 2020-06-19 | 2020-09-18 | 四川大学 | Ultrasonic fatigue crack propagation rate measuring method based on natural frequency |
| CN111678990B (en) * | 2020-06-19 | 2021-04-20 | 四川大学 | Ultrasonic fatigue crack propagation rate measuring method based on natural frequency |
| CN112129660B (en) * | 2020-08-10 | 2024-02-23 | 北京工业大学 | Fatigue life prediction method for friction stir welding joint after shot blasting |
| CN112129660A (en) * | 2020-08-10 | 2020-12-25 | 北京工业大学 | Method for predicting fatigue life of friction stir welding joint after shot blasting |
| CN112329195A (en) * | 2020-09-14 | 2021-02-05 | 北京航空航天大学 | Method for calculating relatively small crack propagation rate in durability analysis |
| CN112329195B (en) * | 2020-09-14 | 2023-05-02 | 北京航空航天大学 | Method for calculating relatively small crack growth rate in durability analysis |
| CN112182927A (en) * | 2020-09-15 | 2021-01-05 | 西北工业大学 | Method for simulating mutual influence of cracks of high-temperature alloy linear friction welding joint |
| CN112285140A (en) * | 2020-10-20 | 2021-01-29 | 北京航空航天大学 | Quantitative characterization method for early-stage propagation rate of internal crack of single crystal ultrahigh cycle fatigue |
| CN112834368A (en) * | 2020-10-27 | 2021-05-25 | 西南交通大学 | Prediction method for fatigue crack propagation life of pantograph |
| CN112834368B (en) * | 2020-10-27 | 2022-03-08 | 西南交通大学 | Prediction method for fatigue crack propagation life of pantograph |
| CN113378420A (en) * | 2020-11-27 | 2021-09-10 | 东南大学 | Method for predicting service life of crack pipeline |
| CN113340749A (en) * | 2021-04-30 | 2021-09-03 | 成都飞机工业（集团）有限责任公司 | Stress monitoring-based fatigue crack propagation life prediction method for high-lock bolt connecting piece |
| CN113340749B (en) * | 2021-04-30 | 2022-04-08 | 成都飞机工业（集团）有限责任公司 | Stress monitoring-based fatigue crack propagation life prediction method for high-lock bolt connecting piece |
| CN114136827A (en) * | 2021-08-31 | 2022-03-04 | 江阴兴澄特种钢铁有限公司 | Test method for evaluating hydrogen-induced delayed crack tendency of high-strength steel welding |
| CN114047089B (en) * | 2021-09-30 | 2022-08-05 | 南京航空航天大学 | Method for calculating service life of material under action of thermal shock load |
| CN114216803A (en) * | 2021-09-30 | 2022-03-22 | 中国航发北京航空材料研究院 | High cycle fatigue full-life prediction method for metal material |
| CN114047089A (en) * | 2021-09-30 | 2022-02-15 | 南京航空航天大学 | Method for calculating service life of material under action of thermal shock load |
| CN114117670A (en) * | 2021-11-24 | 2022-03-01 | 江苏科技大学 | Method for estimating fatigue striation spacing of grinding camshaft |
| CN114117670B (en) * | 2021-11-24 | 2024-05-31 | 江苏科技大学 | Method for estimating fatigue striation spacing of grinding cam shaft |
| CN114218661A (en) * | 2022-02-21 | 2022-03-22 | 中国海洋大学 | Fatigue crack propagation-based fatigue life prediction method |
| CN115019913A (en) * | 2022-05-12 | 2022-09-06 | 中国航发四川燃气涡轮研究院 | Method for calculating fatigue crack propagation life of dual-performance powder disc |
| CN117494421A (en) * | 2023-11-01 | 2024-02-02 | 北京航空航天大学 | Fatigue life prediction method for laser deposition forming titanium alloy |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108920792B (en) | 2022-04-19 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108920792A (en) | A kind of agitating friction weldering Fatigue Life Prediction method based on crackle extension | |
| Niu et al. | Defect tolerant fatigue assessment of AM materials: Size effect and probabilistic prospects | |
| Burns et al. | Effect of corrosion severity on fatigue evolution in Al–Zn–Mg–Cu | |
| Yatomi et al. | Theoretical and numerical modelling of creep crack growth in a carbon–manganese steel | |
| WO2016045024A1 (en) | Method for measuring and determining fracture toughness of structural material in high-temperature environment | |
| CN102426137B (en) | Testing and measuring method capable of axially loading low cycle fatigue crack initiation | |
| Ranganathan et al. | Fatigue crack initiation at a notch | |
| CN107843510B (en) | Method for estimating residual endurance life of supercritical unit T/P91 heat-resistant steel based on room-temperature Brinell hardness prediction | |
| Bandara et al. | Fatigue failure predictions for steels in the very high cycle region–a review and recommendations | |
| CN105181492A (en) | Measuring method for surface strengthening member fatigue crack expansion rate | |
| CN111024487A (en) | Method for predicting fatigue life of friction stir welding joint based on grain size and microhardness | |
| Fujii et al. | Strain-based approach to investigate intergranular stress corrosion crack initiation on a smooth surface of austenitic stainless steel | |
| Tyson et al. | Low-constraint toughness testing: results of a round robin on a draft SE (T) test procedure | |
| WO2023108810A1 (en) | Method for predicting evolution behaviors of creep damage and deformation over time | |
| Xiannian et al. | Fatigue crack propagation analysis in an aero-engine turbine disc using computational methods and spin test | |
| Main et al. | Microstructure and surface finish influences on AA7085-T7452 small fatigue crack growth rates | |
| RU2730102C1 (en) | Method of assessing resistance of pipeline steels to "groove" corrosion | |
| Louks et al. | Static assessment of brittle/ductile notched materials: an engineering approach based on the Theory of Critical Distances | |
| CN104898724B (en) | Automatic pH value control device for sulfide stress cracking resistance test, and control method thereof | |
| Dreyer et al. | An approach for a complete evaluation of resistance to thermal shock | |
| Zhu et al. | Evaluation of size effect in low cycle fatigue for Q&T rotor steel | |
| Kroon et al. | A probabilistic model for cleavage fracture with a length scale–Parameter estimation and predictions of growing crack experiments | |
| Liu et al. | Fatigue life prediction of semi-elliptical surface crack in 14MnNbq bridge steel | |
| Patil et al. | Acoustic emission-based mathematical procedure for quantification of rebar corrosion in reinforced concrete | |
| US20220221387A1 (en) | Corrosion Evaluation Support Apparatus and Corrosion Evaluation Support Method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |