CN106202906B - A kind of Corrosion Fatigue Properties characterization and life estimation method - Google Patents
A kind of Corrosion Fatigue Properties characterization and life estimation method Download PDFInfo
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- CN106202906B CN106202906B CN201610527440.1A CN201610527440A CN106202906B CN 106202906 B CN106202906 B CN 106202906B CN 201610527440 A CN201610527440 A CN 201610527440A CN 106202906 B CN106202906 B CN 106202906B
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Abstract
A kind of Corrosion Fatigue Properties characterization and life estimation method, this method have three big steps：Step 1: considering the Corrosion Fatigue Properties surface representing model and its parameter Estimation that stress ratio influences；Step 2: considering the corrosion fatigue life appraising model of sequence effect of loading；Step 3: the accumulative summation algorithm of corrosion fatigue life estimation.The present invention is simple and practical, required calculating parameter is few, computational accuracy is high, has Important Academic meaning and engineering application value.
Description
Technical field
A kind of Corrosion Fatigue Properties characterization of present invention offer and life estimation method, belong to Structural Metallic Fatigue reliability skill
Art field.
Background technology
In Practical Project, material can often be generated damage by the effect of alternating load, fatigue crack occur；And certain
Pulsating stress effect after fracture failure occurs, to threatening to the safety of structure.Structure during military service by
External environment influence can inevitably corrode, for the aviation being exposed under the corrosive environments such as moist, salt fog and seawater
Device, with the increase of service life, damage caused by corroding frequently results in aircraft structure fatigue crackle and germinates and accelerate in advance to expand
Exhibition, or even change the position of fatigue failure on aircraft, flight safety is seriously affected, therefore, the corrosion fatigue behavior of research material
There is important practical significance.Currently, existing corrosion fatigue life evaluation method cannot consider load sequence shadow in loading spectrum
It rings, leading to corrosion fatigue life estimation result, there are large errors, for this purpose, having invented a kind of simple and practical Corrosion Fatigue Properties
Characterization and life estimation method, this method consider stress ratio and sequence effect of loading, more tally with the actual situation, and can improve estimation essence
Degree, the present invention have Important Academic meaning and engineering application value.
Invention content
1, purpose：It is an object of the present invention to provide a kind of Corrosion Fatigue Properties characterizations and life estimation method, this method to examine
The influence for having considered stress ratio and load sequence has the characteristics that simple and practical, calculating parameter is few, computational accuracy is high, for corrosion
Fatigue behaviour and spectrum, which carry life appraisal, under environment important value.
2, technical solution：A kind of Corrosion Fatigue Properties characterization and life estimation method, this method be as follows,
Step 1: considering the Corrosion Fatigue Properties surface representing model and its parameter Estimation of stress ratio effect
According to《Metal material perseverance width axial fatigue test method》(HB5287-96), it is followed by corrosive medium box and solution
Ring pumps, and fatigue test is carried out under corrosive environment.Under simple stress ratio, using group test method and up and down test method, choose
Different maximum fatigue stress loads, obtains the fatigue failure recurring number of corresponding life span, records the knot of every group of fatigue test
Fruit.
Using fatigue behaviour of the three parameter Power Functions expression formulas characterization simple stress than under, and to stress ratio amendment, obtain
Consider the fatigue behaviour characterization model (S of stress ratio effecta-Sm- N surface models)：
In formula, σtFor tensile strength of material；SaAnd SmRespectively fatigue stress amplitude and stress average；S fittings obtain
Fatigue strength；Q and m is material constant；N is burn-out life recurring number.
Q, m and S in formula (4) are undetermined parameter, are needed in test data [Sa,Sm, N] on the basis of, by linear regression
Theoretical fitting obtains.Logarithm is taken to formula (1) both sides, is obtained：
Y=c0+c1X (2)
Y=lgN in formula, c0=lgQ, c1=-m,
According to linear regression theory, undetermined parameter c0And c1And the determination method of pertinency factor r is as follows：
Wherein
From formula (6) to formula (10) as can be seen that intermediate variable L11、L12And L22It is related with undetermined constant S, that is to say, that
They are the functions of S.Therefore, parameter c0And c1Similarly it is the function of S, to, it is necessary first to determine the value of parameter S.It adopts
With pertinency factor optimization method, required S values must make pertinency factor r obtain maximum, i.e. square also acquirement at S of pertinency factor
Extreme value
Undetermined constant S, which is calculated, need to meet following formula
H (S)=L11L20-L12L10=0 (12)
In formula
It can calculating parameter c according to formula (6) and formula (7) using the S values of formula (12) solved0And c1, finally obtain
Step 2: considering the corrosion fatigue life appraising model of sequence effect of loading
Effect of interaction between loads has a significant impact fatigue behaviour, including the high sluggish effect of load caused by residual compressive stress after high load
Answer and low load after hesitation etc. is offset caused by residual tension, but linear cumulative damage Miner theories have ignored load
The reciprocation between order effect and load in course, it is difficult to which the fatigue life under actual measurement loading spectrum load is accurately commented
Estimate.Based on plastic zone theory, Willenborg-Chang models successfully characterize effect of interaction between loads and to random load spectrums
Under crack propagation life predicted.Miner theories are combined with Willenborg-Chang models, introducing has effect
Power mean value Sm,effTo characterize the load interaction in fatigue damage, obtains fatigue damage increment and spectrum carries lower estimation of fatigue life
Formula：
Wherein
In formula, Δ DiIt is fatigue damage increment caused by i-th of Cyclic Stress in random load spectrum；K is one with airborne
Lotus composes number of stress cycles in the block；T is that spectrum carries fatigue life；Smax,OLIt is the maximum fatigue stress of previous overload cycle；rsIt is super
Carry cutoff；Δ D ' is the fatigue damage increment after overload；ZOLIt is overload stagnant regions dimensional parameters.
Step 3: the accumulative summation algorithm of corrosion fatigue life estimation
By formula (17) to formula (20), it can be evaluated whether that material spectrum carries fatigue life under corrosive environment, circular is：
(i) for first Cyclic Stress in random load spectrum, it can obtain corresponding having effect by formula (19) and (20)
Power mean value (Sm,eff)1, formula (17) is substituted into, fatigue damage increment Delta D caused by first cycle is obtained1With current impairment value D1；
(ii) likewise, in D1On the basis of, calculate the effective stress mean value (S of second Cyclic Stressm,eff)2, obtain
Fatigue damage increment Delta D caused by two cycles2With current impairment value D2；
(iii) accumulation of cycle is connect by so recycling, fatigue caused by each follow-up Cyclic Stress during assumed (specified) load is composed
Damage increment is until loading spectrum terminates, at this point, corresponding accumulated damage is the fatigue damage caused by a random load spectrum block
Wound；
(iv) when accumulated damage meets or exceeds the Critical Damage of formula (18) permission, fatigue damage accumulation, which calculates, to be stopped,
Corresponding ultimate failure recurring number is material spectrum load fatigue life under corrosive environment at this time.
Description of the drawings
Fig. 1 is the calculation flow chart of the method for the invention.
Symbol description is as follows in figure：
D in Fig. 1 is current fatigue damage；ΔDiIt is fatigue damage caused by i-th of Cyclic Stress in actual measurement loading spectrum
Increment.
Specific implementation mode
Fig. 1 is the flow diagram of the method for the invention, and the present invention divides three steps to realize, specially：
Step 1: considering the Corrosion Fatigue Properties surface representing model and its parameter Estimation of stress ratio effect
According to《Metal material perseverance width axial fatigue test method》(HB5287-96), it is followed by corrosive medium box and solution
Ring pumps, and fatigue test is carried out under corrosive environment.Under simple stress ratio, using group test method and up and down test method, choose
Different maximum fatigue stress loads, obtains the fatigue failure recurring number of corresponding life span, records the knot of every group of fatigue test
Fruit.
Using fatigue behaviour of the three parameter Power Functions expression formulas characterization simple stress than under, and to stress ratio amendment, obtain
Consider the fatigue behaviour characterization model (S of stress ratio effecta-Sm- N surface models)：
In formula, σtFor tensile strength of material；SaAnd SmRespectively fatigue stress amplitude and stress average；S fittings obtain
Fatigue strength；Q and m is material constant；N is burn-out life recurring number.
Q, m and S in formula (4) are undetermined parameter, are needed in test data [Sa,Sm, N] on the basis of, by linear regression
Theoretical fitting obtains.Logarithm is taken to formula (1) both sides, is obtained：
Y=c0+c1X (2)
Y=lgN in formula, c0=lgQ, c1=-m,
According to linear regression theory, undetermined parameter c0And c1And the determination method of pertinency factor r is as follows：
Wherein
From formula (6) to formula (10) as can be seen that intermediate variable L11、L12And L22It is related with undetermined constant S, that is to say, that
They are the functions of S.Therefore, parameter c0And c1Similarly it is the function of S, to, it is necessary first to determine the value of parameter S.It adopts
With pertinency factor optimization method, required S values must make pertinency factor r obtain maximum, i.e. square also acquirement at S of pertinency factor
Extreme value
Undetermined constant S, which is calculated, need to meet following formula
H (S)=L11L20-L12L10=0 (12)
In formula
It can calculating parameter c according to formula (6) and formula (7) using the S values of formula (12) solved0And c1, finally obtain
Step 2: considering the corrosion fatigue life appraising model of sequence effect of loading
Effect of interaction between loads has a significant impact fatigue behaviour, including the high sluggish effect of load caused by residual compressive stress after high load
Answer and low load after hesitation etc. is offset caused by residual tension, but linear cumulative damage Miner theories have ignored load
The reciprocation between order effect and load in course, it is difficult to which the fatigue life under actual measurement loading spectrum load is accurately commented
Estimate.Based on plastic zone theory, Willenborg-Chang models successfully characterize effect of interaction between loads and to random load spectrums
Under crack propagation life predicted.Miner theories are combined with Willenborg-Chang models, introducing has effect
Power mean value Sm,effTo characterize the load interaction in fatigue damage, obtains fatigue damage increment and spectrum carries lower estimation of fatigue life
Formula：
Wherein
In formula, Δ DiIt is fatigue damage increment caused by i-th of Cyclic Stress in random load spectrum；K is one with airborne
Lotus composes number of stress cycles in the block；T is that spectrum carries fatigue life；Smax,OLIt is the maximum fatigue stress of previous overload cycle；rsIt is super
Carry cutoff；Δ D ' is the fatigue damage increment after overload；ZOLIt is overload stagnant regions dimensional parameters.
Step 3: the accumulative summation algorithm of corrosion fatigue life estimation
By formula (17) to formula (20), it can be evaluated whether that material spectrum carries fatigue life under corrosive environment, circular is：
(i) for first Cyclic Stress in random load spectrum, it can obtain corresponding having effect by formula (19) and (20)
Power mean value (Sm,eff)1, formula (17) is substituted into, fatigue damage increment Delta D caused by first cycle is obtained1With current impairment value D1；
(ii) likewise, in D1On the basis of, calculate the effective stress mean value (S of second Cyclic Stressm,eff)2, obtain
Fatigue damage increment Delta D caused by two cycles2With current impairment value D2；
(iii) accumulation of cycle is connect by so recycling, fatigue caused by each follow-up Cyclic Stress during assumed (specified) load is composed
Damage increment is until loading spectrum terminates, at this point, corresponding accumulated damage is the fatigue damage caused by a random load spectrum block
Wound；
(iv) when accumulated damage meets or exceeds the Critical Damage of formula (18) permission, fatigue damage accumulation, which calculates, to be stopped,
Corresponding ultimate failure recurring number is material spectrum load fatigue life under corrosive environment at this time.
Claims (1)
1. a kind of method of Corrosion Fatigue Properties characterization and life estimate, this method are as follows：
Step 1: considering the Corrosion Fatigue Properties surface representing model and its parameter Estimation of stress ratio effect
According to《Metal material perseverance width axial fatigue test method》(HB5287-96), by corrosive medium box and solution circulation pump,
Fatigue test is carried out under corrosive environment；Under simple stress ratio, using group test method and up and down test method, choose different
Maximum fatigue stress load, obtains the fatigue failure recurring number of corresponding life span, records the result of every group of fatigue test；
Using fatigue behaviour of the three parameter Power Functions expression formulas characterization simple stress than under, and to stress ratio amendment, considered
The fatigue behaviour characterization model of stress ratio effect, i.e. Sa-Sm- N surface models：
In formula, σtFor tensile strength of material；SaAnd SmRespectively fatigue stress amplitude and stress average；S is the fatigue that fitting obtains
Intensity；Q and m is material constant；N is burn-out life recurring number；
Q, m and S in formula (1) are undetermined parameter, are needed in test data [Sa,Sm, N] on the basis of, by linear regression theory
Fitting obtains；Logarithm is taken to formula (1) both sides, is obtained：
Y=c0+c1X (2)
Y=lgN in formula, c0=lgQ, c1=-m,
According to linear regression theory, undetermined parameter c0And c1And the determination method of pertinency factor r is as follows：
Wherein
From formula (6) to formula (10) as can be seen that intermediate variable L11、L12And L22It is related with undetermined constant S, that is to say, that they
It is the function of S；Therefore, parameter c0And c1Similarly it is the function of S, to, it is necessary first to determine the value of parameter S；Using phase
Close factor optimization method, required S values must make pertinency factor r obtain maximum, i.e. pertinency factor square also obtains extreme value at S
Undetermined constant S, which is calculated, need to meet following formula
H (S)=L11L20-L12L10=0 (12)
In formula
It can calculating parameter c according to formula (6) and formula (7) using the S values of formula (12) solved0And c1, finally obtain
Step 2: considering the corrosion fatigue life appraising model of sequence effect of loading
Effect of interaction between loads has a significant impact fatigue behaviour, including high load hesitation caused by residual compressive stress after high load,
And hesitation is offset after low load caused by residual tension, but linear cumulative damage Miner theories have ignored load history
In order effect and the reciprocation between load, it is difficult to the fatigue life progress accurate evaluation lower to actual measurement loading spectrum load；
Based on plastic zone theory, Willenborg-Chang models successfully characterize effect of interaction between loads and under random load spectrums
Crack propagation life is predicted；Miner theories are combined with Willenborg-Chang models, it is equal to introduce effective stress
Value Sm,effTo characterize the load interaction in fatigue damage, obtains fatigue damage increment and spectrum carries lower estimation of fatigue life public affairs
Formula：
Wherein
In formula, Δ DiIt is fatigue damage increment caused by i-th of Cyclic Stress in random load spectrum；K is a random load spectrum block
In number of stress cycles；T is that spectrum carries fatigue life；Smax,OLIt is the maximum fatigue stress of previous overload cycle；rsIt is overload cut-off
Than；Δ D ' is the fatigue damage increment after overload；ZOLIt is overload stagnant regions dimensional parameters；
Step 3: the accumulative summation algorithm of corrosion fatigue life estimation
By formula (17) to formula (20), it can be evaluated whether that material spectrum carries fatigue life under corrosive environment, circular is：
(i) for first Cyclic Stress in random load spectrum, corresponding effective stress mean value is obtained by formula (19) and (20)
(Sm,eff)1, formula (17) is substituted into, fatigue damage increment Delta D caused by first cycle is obtained1With current impairment value D1；
(ii) likewise, in D1On the basis of, calculate the effective stress mean value (S of second Cyclic Stressm,eff)2, obtain second and follow
Fatigue damage increment Delta D caused by ring2With current impairment value D2；
(iii) accumulation of cycle, fatigue damage caused by each follow-up Cyclic Stress during assumed (specified) load is composed are connect by so recycling
Increment is until loading spectrum terminates, at this point, corresponding accumulated damage is the fatigue damage caused by a random load spectrum block；
(iv) when accumulated damage meets or exceeds the Critical Damage of formula (18) permission, fatigue damage accumulation, which calculates, to be stopped, at this time
Corresponding ultimate failure recurring number is material spectrum load fatigue life under corrosive environment.
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| CN109060497A (en) * | 2018-07-18 | 2018-12-21 | 天津大学 | It is a kind of to consider the Analysis of Fatigue method lower than fatigue limit load |
| CN109885920B (en) * | 2019-02-13 | 2020-09-08 | 西安电子科技大学 | Method for predicting high-low cycle composite fatigue life of turbine blade of aircraft engine |
| CN111581830B (en) * | 2020-05-11 | 2021-03-30 | 湖北特种设备检验检测研究院 | Metal structure fatigue life calculation method |
| CN112357771B (en) * | 2020-11-19 | 2023-05-09 | 中船重工(青岛)海洋装备研究院有限责任公司 | Ship and shore integrated equipment state monitoring system and method |
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| CN105067457A (en) * | 2015-07-06 | 2015-11-18 | 北京航空航天大学 | Corrosion crack expansibility characterization and life estimation method |
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| JPH0672838B2 (en) * | 1987-03-02 | 1994-09-14 | 三菱重工業株式会社 | Corrosion fatigue life prediction method |
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| CN102184326A (en) * | 2011-05-04 | 2011-09-14 | 中国航空工业集团公司西安飞机设计研究所 | Method for estimating calendar life of aircraft structure |
| CN104020254A (en) * | 2014-05-20 | 2014-09-03 | 北京航空航天大学 | Strain control method for measuring residual strength and residual service life of composite material |
| CN105067457A (en) * | 2015-07-06 | 2015-11-18 | 北京航空航天大学 | Corrosion crack expansibility characterization and life estimation method |
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