# Experimental and Numerical Study of Fatigue Damage Assessment under Combined High and Low Cycle Loading

Authors: Chaoshuai Han; Xianqiang Qu; Yongliang Ma; Dexin Shi
Journal: Shock and Vibration
 (2018)

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## Abstract

This paper studies fatigue damage under combined high and low cycle loading. The interaction of two types of loading will greatly reduce fatigue life of structures. Existing methods usually neglect the minor high cycle loading, which obviously underestimates the total fatigue damage. To solve this problem, four methods are proposed and extended for the case of combined loading. Numerical simulations based on the superposition of two sine waves are performed. Experiments are carried out using “DH36” smooth round-type specimens. Damage predictions results by four methods are compared to the experimental results. It is concluded that some methods give satisfactory fatigue damage estimations and can be regarded as a safe design tool in engineering application.


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## Body

## 1. Introduction

Many important engineering structures experience low cycle loading and are also subjected to high cycle loading [1]. A typical example may be a wave frequency response due to wave and a high frequency response excited by whipping/springing for some flexible and fast merchant ships and containerships [2–4]. During one voyage, wave frequency response includes low frequency major stress cycles which can be regarded as low cycle loading, while springing and whipping response produces high frequency minor stress cycles which is considered to be high cycle loading. Many studies show that fatigue damage induced by whipping/springing response takes up an important contribution to the total fatigue damage [2–4]. Mao finds that HF response produced by whipping/springing contributes fatigue damage of larger than 30% although HF response induces average energy of less than 3% [2]. Thus, it is necessary to predict fatigue damage under combined high and low cycle loading.For the combination of low cycle loading and high cycle loading, a simple treatment is to ignore the high frequency minor cycle loading [5]. However, the coupling effect of LCL and HCL will greatly reduce fatigue life of structures when these high frequency minor stress cycles are superimposed on part of the low frequency major stress cycles. Therefore, the above approach is not suitable for safe design of structures. Another traditional method is to transform combined cycle loading into single cycle loading. After that, the amplitude of single cycle loading is the sum of low cycle loading and high cycle loading, and the cycle number is equal to the cycle number of low cycle loading. Unfortunately, several studies show that single cycle treatment cannot evaluate the fatigue damage due to high frequency minor stress cycles. The third method is the simple damage summation method; damage from high and low cycle loading is calculated independently and then simply added [6]. This method provides highly nonconservative damage predictions because of the nonlinear relation of fatigue damage and stress. Recently, some researchers reveal the interaction of LCL and HCL in terms of superposition of damage from the separate loading [7–10]. Fu and Cebon assumed the combination of two sine waves in the time domain [7]. By rainflow counting algorithm, the combined damage can be split up into two major parts: one is the large cycles; the other is the small cycles. The total damage can then be the sum of the large cycles and the small cycles. Based on the above idea, Lotsberg derived a formula associated with the individual frequency and fatigue damage, which has been introduced into the DNV rule for estimating the fatigue damage due to high and low cycle loading [8, 9]. In addition, there are other methods which may be used in terms of combination of damage equivalent stress ranges. If nothing is known on the phase relation, an in-phase superposition of damage equivalent stress ranges from LCL and HCL can be combined fatigue loading; this treatment may provide a conservative combined fatigue damage prediction [11]. More recently, Han and Ma derived a simple formula which is expressed as a function of individual damage [12]; this method will be applied to calculate the combined fatigue damage induced by high and low cycle loading. In addition, for combination of low cycle fatigue and high cycle fatigue, Szala and Ligaj present a hybrid method to calculate construction steel fatigue life; this hybrid method points out that low cycle fatigue is performed with strain based approach and high cycle fatigue is computed through stress based approach; the total fatigue damage is summed with low cycle fatigue damage and high cycle fatigue damage [13]. The combined stress process may be a broad process; at this situation, Szala and Ligaj consider using some models of two-parameter fatigue characteristics (modelIM[14], modelII[14], modelIII[14], and modelIV[14]) for determining the equivalent load spectra; based on this, fatigue life can be obtained in the preliminary stage of structural design process [15].The purpose of this paper is to find a method to evaluate fatigue damage due under combined high and low cycle loading. Numerical simulations are first carried out to validate the accuracy of different methods. Then, experimental study is conducted and experimental results are compared with some proposed methods.


## 2. Theory Background

### 2.1. Basic Fatigue Theory

Fatigue life is based onS-N curves, which are obtained from fatigue tests of small specimens in test laboratories. For anS-N curve, it can be expressed as(1)N=K·S-m,where N is predicted number of cycles to failure for stress range and S, K, and m are constants associated with the material properties, the ratio of stress, and the type of loading. In particular, it should be noted that the material parameter m has a significant impact on calculated fatigue damage since the value of m depends on different materials. For instance, m is usually taken as 3,4,5 for welded steel, while it is taken as 8,9,10 for ceramics and glass and even 20 for smooth round bars. It has been proven that the theoretical results of fatigue prediction are different for m=3 and m=4 by Jiao and Moan [16]. In addition, it is convenient to assumeS-N curve with one slope. In Kuhn’s thesis, m=4 is used as a linear approximation of the bilinear curve of m=3 and m=5 [11]. In order to make the process of derivation brief and convenient, the influence of the mean stresses is negligible.Figure1 illustrates three curve types proposed by DNV rules [9]. Type A is a bilinear curve which has a transition in slope from m=3 to m=5, and type B is an only one slope curve after the inverse slope of m=3 is extended, while type C is used when a fatigue limit is considered.Figure 1
Example ofS-N curve according to DNV rule.Note that, in most cases, type A with bilinear inverse slopes is the most appropriate for analyzing the fatigue damage on the certification level. However, in the preliminary design stage and when an analytical evaluation of combined fatigue damage is desired, the assumption of a constant slope is convenient. In this paper, numerical simulations, experimental study, and derivation of combined damage formula are based on a one-slopeS-N curve.Fatigue deterioration or damage,D, is defined as the ratio between the reference number of cycles during the design lifetime and predicted number of cycles to failure. The total damage is calculated under the assumption of linear cumulative damage, i.e., Palmgren-Miner rule [17], which equals the summation of the ratio between the reference number of cycles, ni, and the predicted number of cycles, Ni, for all stress range classes.(2)D=∑i=1niNi.In order to achieve all stress ranges, the rainflow cycle counting originally proposed by Matsuishi and Endo is selected as the only counting procedure [18, 19], and the approach has been widely adopted and considered to be the most efficient counting method.


### 2.2. Damage Equivalent Theory

In general, it is convenient to introduce damage equivalent, constant amplitude stress range, which can be regarded as a concise description of fatigue damage. It should be noted that the principle of equal damage must be followed. For a constant slopeS-N curve, equivalent stress range depends only on the slope parameter m, the material parameter K, the range of cycles, and an arbitrary reference number of cycles. For example, the damage with the number of stress cycles, k, in a stress time history can be equivalent to the damage with only one stress cycle with respect to the reference number of cycles, nr, namely, by(3)∑i=1kniNi=nrNΔσeqThe equivalent stress range can be then obtained by the union of (2) and (3) as(4)Δσeq=1nr·∑i=1kni·Δσim1/m,where NΔσeq denotes the number of cycles to failure for the equivalent stress range, Δσeq, and Δσi is the stress range for class i.


## 2.1. Basic Fatigue Theory

Fatigue life is based onS-N curves, which are obtained from fatigue tests of small specimens in test laboratories. For anS-N curve, it can be expressed as(1)N=K·S-m,where N is predicted number of cycles to failure for stress range and S, K, and m are constants associated with the material properties, the ratio of stress, and the type of loading. In particular, it should be noted that the material parameter m has a significant impact on calculated fatigue damage since the value of m depends on different materials. For instance, m is usually taken as 3,4,5 for welded steel, while it is taken as 8,9,10 for ceramics and glass and even 20 for smooth round bars. It has been proven that the theoretical results of fatigue prediction are different for m=3 and m=4 by Jiao and Moan [16]. In addition, it is convenient to assumeS-N curve with one slope. In Kuhn’s thesis, m=4 is used as a linear approximation of the bilinear curve of m=3 and m=5 [11]. In order to make the process of derivation brief and convenient, the influence of the mean stresses is negligible.Figure1 illustrates three curve types proposed by DNV rules [9]. Type A is a bilinear curve which has a transition in slope from m=3 to m=5, and type B is an only one slope curve after the inverse slope of m=3 is extended, while type C is used when a fatigue limit is considered.Figure 1
Example ofS-N curve according to DNV rule.Note that, in most cases, type A with bilinear inverse slopes is the most appropriate for analyzing the fatigue damage on the certification level. However, in the preliminary design stage and when an analytical evaluation of combined fatigue damage is desired, the assumption of a constant slope is convenient. In this paper, numerical simulations, experimental study, and derivation of combined damage formula are based on a one-slopeS-N curve.Fatigue deterioration or damage,D, is defined as the ratio between the reference number of cycles during the design lifetime and predicted number of cycles to failure. The total damage is calculated under the assumption of linear cumulative damage, i.e., Palmgren-Miner rule [17], which equals the summation of the ratio between the reference number of cycles, ni, and the predicted number of cycles, Ni, for all stress range classes.(2)D=∑i=1niNi.In order to achieve all stress ranges, the rainflow cycle counting originally proposed by Matsuishi and Endo is selected as the only counting procedure [18, 19], and the approach has been widely adopted and considered to be the most efficient counting method.


## 2.2. Damage Equivalent Theory

In general, it is convenient to introduce damage equivalent, constant amplitude stress range, which can be regarded as a concise description of fatigue damage. It should be noted that the principle of equal damage must be followed. For a constant slopeS-N curve, equivalent stress range depends only on the slope parameter m, the material parameter K, the range of cycles, and an arbitrary reference number of cycles. For example, the damage with the number of stress cycles, k, in a stress time history can be equivalent to the damage with only one stress cycle with respect to the reference number of cycles, nr, namely, by(3)∑i=1kniNi=nrNΔσeqThe equivalent stress range can be then obtained by the union of (2) and (3) as(4)Δσeq=1nr·∑i=1kni·Δσim1/m,where NΔσeq denotes the number of cycles to failure for the equivalent stress range, Δσeq, and Δσi is the stress range for class i.


## 3. Damage Superposition Methods during the Fatigue Analysis

### 3.1. Arithmetic Superposition of Stress Range

A simplistic formula is proposed for calculating the combined fatigue loading which is based on the arithmetic summation superposition of the equivalent stress range.(5)Δσeq=ΔσL+ΔσHUnder combined low cycle and high cycle loading, low cycle loading induced fatigue damageDL and high cycle loading induced fatigue damage DH can be calculated, separately, according to (1) and (2):(6)DL=ΔσLmnLK(7)DH=ΔσHmnHKWith respect to damage equivalent theory,DL can be equivalent to the damage produced by a stress range of Δσeq,H and the number of cycles nH.(8)DL=ΔσLmnLK=Δσeq,HmnHKΔσeq,H can then be derived as(9)Δσeq,H=ΔσL·nLnH1/mAccording to (5), the equivalent stress range of combined cycle loading can be obtained:(10)Δσeq,LH=Δσeq,H+ΔσHBy incorporating (1), (2), (6), and (7) with (10), a combined damage formula can be obtained:(11)Dc=DL1/m+DH1/mm


### 3.2. Quadratic Superposition of Stress Range

Another superposition method is based on the quadratic superposition of the equivalent stress range. The formula is as follows:(12)Δσeq,LH=Δσeq,L2+Δσeq,H2According to a similar process with (11), another combined damage formula can be obtained:(13)Dc=DL2/m+DH2/mm/2Equation (13) will be used to calculate the combined fatigue damage due to low cycle loading and high cycle loading.


### 3.3. DNV Method

Fatigue damage is increased by assuming that the high cycle loading can be added to that of the low cycle loading to get a stress rangeΔσL+ΔσH and the number of cycles nL. Then fatigue damage from the high cycle loading can be increased with a stress range ΔσH and the number of cycles nH-nL. Hence, the total fatigue damage as DNV method can be obtained as follows:(14)DDNV=ΔσL+ΔσHmK·nL+ΔσHmKnH-nL,where ΔσL is the stress range of low cycle loading, nL is the number of cycles of low cycle loading, ΔσH is the stress range of high cycle loading, and nH is the number of cycles of high cycle loading.


### 3.4. Quadratic Superposition of Fatigue Damage

Temple depicted an approach of the combined fatigue damage based on the quadratic superposition of the separate fatigue contributions, which has been applied to the calculation of fatigue damage in the Utgrunden offshore wind farm [20].(15)DTemple=DL2+DH2


## 3.1. Arithmetic Superposition of Stress Range

A simplistic formula is proposed for calculating the combined fatigue loading which is based on the arithmetic summation superposition of the equivalent stress range.(5)Δσeq=ΔσL+ΔσHUnder combined low cycle and high cycle loading, low cycle loading induced fatigue damageDL and high cycle loading induced fatigue damage DH can be calculated, separately, according to (1) and (2):(6)DL=ΔσLmnLK(7)DH=ΔσHmnHKWith respect to damage equivalent theory,DL can be equivalent to the damage produced by a stress range of Δσeq,H and the number of cycles nH.(8)DL=ΔσLmnLK=Δσeq,HmnHKΔσeq,H can then be derived as(9)Δσeq,H=ΔσL·nLnH1/mAccording to (5), the equivalent stress range of combined cycle loading can be obtained:(10)Δσeq,LH=Δσeq,H+ΔσHBy incorporating (1), (2), (6), and (7) with (10), a combined damage formula can be obtained:(11)Dc=DL1/m+DH1/mm


## 3.2. Quadratic Superposition of Stress Range

Another superposition method is based on the quadratic superposition of the equivalent stress range. The formula is as follows:(12)Δσeq,LH=Δσeq,L2+Δσeq,H2According to a similar process with (11), another combined damage formula can be obtained:(13)Dc=DL2/m+DH2/mm/2Equation (13) will be used to calculate the combined fatigue damage due to low cycle loading and high cycle loading.


## 3.3. DNV Method

Fatigue damage is increased by assuming that the high cycle loading can be added to that of the low cycle loading to get a stress rangeΔσL+ΔσH and the number of cycles nL. Then fatigue damage from the high cycle loading can be increased with a stress range ΔσH and the number of cycles nH-nL. Hence, the total fatigue damage as DNV method can be obtained as follows:(14)DDNV=ΔσL+ΔσHmK·nL+ΔσHmKnH-nL,where ΔσL is the stress range of low cycle loading, nL is the number of cycles of low cycle loading, ΔσH is the stress range of high cycle loading, and nH is the number of cycles of high cycle loading.


## 3.4. Quadratic Superposition of Fatigue Damage

Temple depicted an approach of the combined fatigue damage based on the quadratic superposition of the separate fatigue contributions, which has been applied to the calculation of fatigue damage in the Utgrunden offshore wind farm [20].(15)DTemple=DL2+DH2


## 4. Numerical Validation

Trapezoidal wave is generally used to replace the low cycle loading in experimental study and numerical simulations. However, trapezoidal wave is not consistent with the actual loading. Relatively, sine wave is close to the practical situation and is thus adopted in this paper. Simplified HCL and LCL can be seen in Figure2. Assuming that ΔσH and ΔσL are the stress range of two sine waves, fH and fL are the individual frequency. Two new parameters are defined as follows:(16)Rσ=ΔσHΔσLRf=fHfLFigure 2
Schematic view of LCL, HCL, and combined cycle loading.The ratio of loadingRσ and the ratio of frequency Rf, as well asS-N curve parameter m, are considered as the main factor which influences the fatigue damage obtained from previously mentioned methods. In numerical simulations, the value of Rσ is 4:1, 3:1, 2:1, 1:1, 1:2, 1:3, and 1:4. The value of Rf is 10, 50, 100, and 300. m is defined from 1 to 20 with an increment of 1.Time-domain rainflow damage in a sufficiently long time series can be used as a reference solution and is compared with estimations by arithmetic superposition of stress range method, quadratic superposition of stress range method, DNV method, and quadratic superposition of fatigue method. Presented results in all figures are given in terms of the fatigue damage ratio which is defined in (17):(17)ρ=D¯DRFC,where DRFC is the fatigue damage from numerical simulations; it can be calculated through rainflow cycle counting for combined stress time series, associating withS-N curve and Palmgren-Miner rule. D¯ is the theoretical damage estimate computed by each of the methods previously proposed. It is defined that when ρ>1, the fatigue damage estimation is conservative. On the contrary, when ρ<1, the fatigue damage estimation is not conservative.Figure3 plots the damage estimation by the arithmetic summation of equivalent stress range. When Rσ>1, the factor ρ increases with the increasing of m; when Rσ≤1, the factor ρ firstly increases and then tends to steadiness with the increasing of m. Keeping m and Rf fixed, the factor ρ decreases with the decreasing of Rσ. In addition, by comparison with Figures 3(a), 3(b), 3(c), and 3(d), the factor ρ is raised with the increasing of Rf. Overall, when m is equal to 3, 4, and 5 or the value of Rσ and Rf is very low, this method provides reasonably conservative fatigue damage prediction.Figure 3
Damage estimation by the arithmetic summation of equivalent stress range in the case of (a)Rf=10, (b) Rf=50, (c) Rf=100, and (d) Rf=300.
(a) (b) (c) (d)Figure4 shows the damage estimation by DNV method. The value of Rf almost has no effect on the factor ρ. Only when Rσ<1 and m<6, the factor ρ is a little higher. In other cases, very good agreement between DNV method and numerical simulations can be observed.Figure 4
Damage estimation by DNV method in the case of (a)Rf=10, (b) Rf=50, (c) Rf=100, and (d) Rf=300.
(a) (b) (c) (d)Figure5 exhibits the damage estimation by quadratic superposition of stress range method. In most cases, the method highly underestimates the combined fatigue damage. Only when m≤5, the method can give an accurate fatigue damage estimation.Figure 5
Damage estimation by direct quadratic superposition of equivalent stress ranges method in the case of (a)Rf=10, (b) Rf=50, (c) Rf=100, and (d) Rf=300.
(a) (b) (c) (d)Similarly to quadratic superposition of stress range method, quadratic superposition of fatigue damage method can provide good damage results only in a small range. In other cases, it cannot give precise damage evaluation (as seen in Figure6).Figure 6
Damage estimation by Temple method in the case of (a)Rf=10, (b) Rf=50, (c) Rf=100, and (d) Rf=300.
(a) (b) (c) (d)


## 5. Experimental and Numerical Validation of Superposition Approaches

### 5.1. Experimental Validation Based on Smooth Round-Type Specimens

#### 5.1.1. Test Setup

A high strength marine structural steel named DH36 is used in this paper, which is widely used for constructions of ships and marine structures. The design of specimens follows the American Society for Testing and Materials (ASTM) [21]. Figure 7 exhibits size of smooth round-type specimens and the machined specimens, respectively. The left side in Figure 8 is the electrohydrautic servo fatigue test machine; the right side is the control interface.Figure 7
Designed specimens.Figure 8
Test setup.


#### 5.1.2. Test ofS-N Curve

According to test requirements ofS-N curve, complete rupture of specimens is defined as failure criterion. Six-grade stress levels are adopted in the test, and for every grade stress level one specimen is used to conduct a fatigue test until the failure criterion is attained. If the test data is abnormal, repeated test should be carried out for another specimen. The load is a symmetrical sine wave with a mean amplitude of zero. During the test, the value of loads and the number of cycles to failure for each specimen are recorded. The experimental data were then fitted using the least squares method as shown in Figure 9, with a variance of 97.3644%, which proved that the reliability of the test data, and the fittedS-N curve expression is as follows:(18)lg⁡N=54.27057563816-19.83042291007∗lg⁡SFigure 9
Test data ofS-N curve.From the above equation, two important parameters related to calculation of fatigue damage can be implied, namely, bym=19.83042291007, lg⁡K=54.27057563816.


#### 5.1.3. Grouping of Test Load

As previously mentioned, the ratio of loads and the ratio of frequencies are the main factors which have a significant effect on fatigue damage. Based on that, five groups of loads are selected for experimental test, as shown in Table1, and the first three groups (groups 1-3) represent the combination of low frequency plus small loads and high frequency plus large loads; the last two groups (groups 4-5) denote the combination of low frequency plus large loads and high frequency plus small loads.Table 1
Group of loads.
Group load Amplitude/KN Ratio of loads Frequency Ratio of frequencies 1 F 1 5.498 3.857 0.125 2.667 F 2 21.206 0.333  2 F 1 5.498 3.857 0.125 1.143 F 2 21.206 0.143  3 F 1 5.498 3.857 0.0625 16 F 2 21.206 1  4 F 1 21.206 0.259 0.125 1.143 F 2 5.498 0.143  5 F 1 21.206 0.259 0.0625 16 F 2 5.498 1Note that the ratio of loads is equal to that of stress ranges considering the linear relationship between loads and stress for test specimens,(19)S=Fπ·r2,where r is the diameter of specimens in the beeline part.The fact that fatigue life has no concern with the loading path is widely accepted; thus triangle waves are adopted during the test instead of sine waves after the condition that they have the same peak and trough is fulfilled. The combined loading process can be seen as in Figure10.Figure 10
Detailed loading of combined process.Different combinations have quite distinct time-domain characteristics, as seen in Figure11.Figure 11
Simulated time history of combined process for experimental cases.


### 5.2. Discussion of Experimental Results

For five load combinations, the number of test specimens is 4, 4, 5, 4, and 1, respectively. The parts of ruptured test specimens after fatigue test are illustrated in Figure12. The number of cycles to failure for each test specimen is recorded and then transformed into fatigue damage plotted in Figure 13. What is more, fatigue damage is calculated by the numerical simulations and some superposition formulae, based on the result ofS-N curve test. After that, the overall accuracy of all methods was studied.Figure 12
Ruptured specimens.Figure 13
Fatigue damage result for different approaches.First of all, fatigue damage based on time-domain simulations with rainflow counting is compared with results provided by the experiment. As can be seen in Figure13, time-domain rainflow damage based on a one slopeS-N curve is basically the same as the results obtained from the experiment in most cases. However, in the case of Rσ=3.857, Rf=16, time-domain rainflow results are visibly lower than the experimental results for five test specimens in group 3. By this token, we infer that fatigue damage estimation from numerical simulations in this situation is inexact.In addition, four superposition approaches including arithmetic superposition of stress range method, quadratic superposition of stress range method, DNV method, and quadratic superposition of fatigue damage method are compared with numerical results as seen in Figure13.Arithmetic superposition of stress range method can always provide highly conservative fatigue damage estimation. DNV method also gives conservative fatigue damage prediction in four test load cases, but nonconservative in the third load case.Quadratic superposition of stress range method and quadratic superposition of fatigue damage method give quite close fatigue damage results. However, both exhibit a tendency for a highly nonconservative results whatever the value ofRσ and Rn is, and the clear error of approximate to −100% is unfavorable to estimation of the combined fatigue damage.


## 5.1. Experimental Validation Based on Smooth Round-Type Specimens

### 5.1.1. Test Setup

A high strength marine structural steel named DH36 is used in this paper, which is widely used for constructions of ships and marine structures. The design of specimens follows the American Society for Testing and Materials (ASTM) [21]. Figure 7 exhibits size of smooth round-type specimens and the machined specimens, respectively. The left side in Figure 8 is the electrohydrautic servo fatigue test machine; the right side is the control interface.Figure 7
Designed specimens.Figure 8
Test setup.


### 5.1.2. Test ofS-N Curve

According to test requirements ofS-N curve, complete rupture of specimens is defined as failure criterion. Six-grade stress levels are adopted in the test, and for every grade stress level one specimen is used to conduct a fatigue test until the failure criterion is attained. If the test data is abnormal, repeated test should be carried out for another specimen. The load is a symmetrical sine wave with a mean amplitude of zero. During the test, the value of loads and the number of cycles to failure for each specimen are recorded. The experimental data were then fitted using the least squares method as shown in Figure 9, with a variance of 97.3644%, which proved that the reliability of the test data, and the fittedS-N curve expression is as follows:(18)lg⁡N=54.27057563816-19.83042291007∗lg⁡SFigure 9
Test data ofS-N curve.From the above equation, two important parameters related to calculation of fatigue damage can be implied, namely, bym=19.83042291007, lg⁡K=54.27057563816.


### 5.1.3. Grouping of Test Load

As previously mentioned, the ratio of loads and the ratio of frequencies are the main factors which have a significant effect on fatigue damage. Based on that, five groups of loads are selected for experimental test, as shown in Table1, and the first three groups (groups 1-3) represent the combination of low frequency plus small loads and high frequency plus large loads; the last two groups (groups 4-5) denote the combination of low frequency plus large loads and high frequency plus small loads.Table 1
Group of loads.
Group load Amplitude/KN Ratio of loads Frequency Ratio of frequencies 1 F 1 5.498 3.857 0.125 2.667 F 2 21.206 0.333  2 F 1 5.498 3.857 0.125 1.143 F 2 21.206 0.143  3 F 1 5.498 3.857 0.0625 16 F 2 21.206 1  4 F 1 21.206 0.259 0.125 1.143 F 2 5.498 0.143  5 F 1 21.206 0.259 0.0625 16 F 2 5.498 1Note that the ratio of loads is equal to that of stress ranges considering the linear relationship between loads and stress for test specimens,(19)S=Fπ·r2,where r is the diameter of specimens in the beeline part.The fact that fatigue life has no concern with the loading path is widely accepted; thus triangle waves are adopted during the test instead of sine waves after the condition that they have the same peak and trough is fulfilled. The combined loading process can be seen as in Figure10.Figure 10
Detailed loading of combined process.Different combinations have quite distinct time-domain characteristics, as seen in Figure11.Figure 11
Simulated time history of combined process for experimental cases.


## 5.1.1. Test Setup

A high strength marine structural steel named DH36 is used in this paper, which is widely used for constructions of ships and marine structures. The design of specimens follows the American Society for Testing and Materials (ASTM) [21]. Figure 7 exhibits size of smooth round-type specimens and the machined specimens, respectively. The left side in Figure 8 is the electrohydrautic servo fatigue test machine; the right side is the control interface.Figure 7
Designed specimens.Figure 8
Test setup.


## 5.1.2. Test ofS-N Curve

According to test requirements ofS-N curve, complete rupture of specimens is defined as failure criterion. Six-grade stress levels are adopted in the test, and for every grade stress level one specimen is used to conduct a fatigue test until the failure criterion is attained. If the test data is abnormal, repeated test should be carried out for another specimen. The load is a symmetrical sine wave with a mean amplitude of zero. During the test, the value of loads and the number of cycles to failure for each specimen are recorded. The experimental data were then fitted using the least squares method as shown in Figure 9, with a variance of 97.3644%, which proved that the reliability of the test data, and the fittedS-N curve expression is as follows:(18)lg⁡N=54.27057563816-19.83042291007∗lg⁡SFigure 9
Test data ofS-N curve.From the above equation, two important parameters related to calculation of fatigue damage can be implied, namely, bym=19.83042291007, lg⁡K=54.27057563816.


## 5.1.3. Grouping of Test Load

As previously mentioned, the ratio of loads and the ratio of frequencies are the main factors which have a significant effect on fatigue damage. Based on that, five groups of loads are selected for experimental test, as shown in Table1, and the first three groups (groups 1-3) represent the combination of low frequency plus small loads and high frequency plus large loads; the last two groups (groups 4-5) denote the combination of low frequency plus large loads and high frequency plus small loads.Table 1
Group of loads.
Group load Amplitude/KN Ratio of loads Frequency Ratio of frequencies 1 F 1 5.498 3.857 0.125 2.667 F 2 21.206 0.333  2 F 1 5.498 3.857 0.125 1.143 F 2 21.206 0.143  3 F 1 5.498 3.857 0.0625 16 F 2 21.206 1  4 F 1 21.206 0.259 0.125 1.143 F 2 5.498 0.143  5 F 1 21.206 0.259 0.0625 16 F 2 5.498 1Note that the ratio of loads is equal to that of stress ranges considering the linear relationship between loads and stress for test specimens,(19)S=Fπ·r2,where r is the diameter of specimens in the beeline part.The fact that fatigue life has no concern with the loading path is widely accepted; thus triangle waves are adopted during the test instead of sine waves after the condition that they have the same peak and trough is fulfilled. The combined loading process can be seen as in Figure10.Figure 10
Detailed loading of combined process.Different combinations have quite distinct time-domain characteristics, as seen in Figure11.Figure 11
Simulated time history of combined process for experimental cases.


## 5.2. Discussion of Experimental Results

For five load combinations, the number of test specimens is 4, 4, 5, 4, and 1, respectively. The parts of ruptured test specimens after fatigue test are illustrated in Figure12. The number of cycles to failure for each test specimen is recorded and then transformed into fatigue damage plotted in Figure 13. What is more, fatigue damage is calculated by the numerical simulations and some superposition formulae, based on the result ofS-N curve test. After that, the overall accuracy of all methods was studied.Figure 12
Ruptured specimens.Figure 13
Fatigue damage result for different approaches.First of all, fatigue damage based on time-domain simulations with rainflow counting is compared with results provided by the experiment. As can be seen in Figure13, time-domain rainflow damage based on a one slopeS-N curve is basically the same as the results obtained from the experiment in most cases. However, in the case of Rσ=3.857, Rf=16, time-domain rainflow results are visibly lower than the experimental results for five test specimens in group 3. By this token, we infer that fatigue damage estimation from numerical simulations in this situation is inexact.In addition, four superposition approaches including arithmetic superposition of stress range method, quadratic superposition of stress range method, DNV method, and quadratic superposition of fatigue damage method are compared with numerical results as seen in Figure13.Arithmetic superposition of stress range method can always provide highly conservative fatigue damage estimation. DNV method also gives conservative fatigue damage prediction in four test load cases, but nonconservative in the third load case.Quadratic superposition of stress range method and quadratic superposition of fatigue damage method give quite close fatigue damage results. However, both exhibit a tendency for a highly nonconservative results whatever the value ofRσ and Rn is, and the clear error of approximate to −100% is unfavorable to estimation of the combined fatigue damage.


## 6. Conclusions

This paper studied the fatigue damage under combined high cycle and low cycle loading. Several methods are proposed for considering the interaction of high cycle and low cycle loading. The accuracy of new methods is validated with numerical simulations and experimental test. Some conclusions are as follows:(1)
Quadratic superposition of stress range method and DNV method can provide good fatigue damage results that are very close to simulated rainflow damage with a maximum error of about 20% when1≤m≤5 and Rσ>1.(2)
WhenS-N curve parameter m is larger, four superposition methods provide unsatisfactory fatigue damage estimation with a maximum negative error of 100% when m=20.(3)
Fatigue predictions from numerical simulations produce negative 50% compared with experimental results in some cases. In future work, experimental study on welded structures should be carried out to obtain typicalS-N curve parameter m (usually m=3, 4, and 5) in ship and offshore structures.(4)
Overall, fatigue damage estimation error from different superposition methods increases with the increasing of the load ratio, the frequency ratio, andS-N curve parameter.



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*Source: 9045658-2018-07-12.xml*