SAE J 1099-2002 Technical Report on Low Cycle Fatigue Properties Ferrous and Non-Ferrous of Materials《关于黑色金属和有色金属材料低周疲劳性能的技术报告》.pdf

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1、SAE Technical Standards Board Rules provide that: “This report is published by SAE to advance the state of technical and engineering sciences. The use of this report is entirelyvoluntary, and its applicability and suitability for any particular use, including any patent infringement arising therefro

2、m, is the sole responsibility of the user.”SAE reviews each technical report at least every five years at which time it may be reaffirmed, revised, or cancelled. SAE invites your written comments and suggestions.Copyright 2002 Society of Automotive Engineers, Inc.All rights reserved. No part of this

3、 publication may be reproduced, stored in a retrieval system or transmitted, in any form or by any means, electronic, mechanical, photocopying,recording, or otherwise, without the prior written permission of SAE.TO PLACE A DOCUMENT ORDER: Tel: 877-606-7323 (inside USA and Canada)Tel: 724-776-4970 (o

4、utside USA)Fax: 724-776-0790Email: custsvcsae.orgSAE WEB ADDRESS: http:/www.sae.orgSURFACEVEHICLE400 Commonwealth Drive, Warrendale, PA 15096-0001INFORMATIONREPORTJ1099REV.AUG2002Issued 1975-02Revised 2002-08Superseding J1099 JUN1998Technical Report on Low Cycle Fatigue PropertiesFerrous and Non-Fer

5、rous MaterialsForewordDesigning a component to avoid fatigue failure is one of the more important, yet difficult, tasks anengineer faces. Many factors are involved and the relationships between these factors are developed largelythrough empiricism. Fatigue failure is caused by repeated loading with

6、the number of loading cycles to failurebeing dependent upon the load range.Designing to avoid fatigue failure requires knowledge of the following:a. The expected load-time history (the local strain-time and stress-time history at the most critical locations).b. The geometry of the component and area

7、s of stress concentration (geometrical, metallurgical, surfacefinish, manufacturing variability, etc.)c. The nature of the environment in which the component is operated (wet, dry, corrosive, temperature, etc.)d. The properties of the material as it exists in the finished component at the most criti

8、cally stressed locations(“inherent” fatigue properties, residual stress effects, surface effects, sensitivity to corrosion, “cleanliness,”variability, etc.)Variability in fatigue life is another aspect of fatigue life evaluation and prediction that must be considered. Thisoften calls for statistical

9、 analysis. Circumstances dictate the degree of sophistication required in all aspects of anevaluation or prediction.1. ScopeInformation that provides design guidance in avoiding fatigue failures is outlined in this SAEInformation Report. Of necessity, this report is brief, but it does provide a basi

10、s for approaching complexfatigue problems. Information presented here can be used in preliminary design estimates of fatigue life, theselection of materials and the analysis of service load and/or strain data. The data presented are for the “lowcycle” or strain-controlled methods for predicting fati

11、gue behavior. Note that these methods may not beappropriate for materials with internal defects, such as cast irons, which exhibit different tension andcompression stress-strain behavior.SAE J1099 Revised AUG2002-2-2. References2.1 Applicable PublicationsThe following publications form a part of the

12、 specification to the extent specifiedherein. Unless otherwise indicated, the latest revision of SAE publications shall apply.1. Mitchell, M. R., Fundamentals of Modern Fatigue Analysis for Design, ASM, Vol. 19, Fatigue andFracture, 1997.2. Annual Book of ASTM Standards, MetalsMechanical Testing: El

13、evated and Low Temperature Tests;Metallography, Standard E 606-80, “Constant-Amplitude Low-Cycle Fatigure Testing,” Vol. 3.01,American Society for Testing and Materials, West Conshohocken, PA, 1996.3. Dowling, N.E., Mechanical Behavior of Materials; Engineering Methods for Deformation, Fracture, and

14、Fatigue, Prentice-Hall, 1993.4. Chernenkoff, R.A., Editor, Fatigue Research and Applications, SP-1009, Society of AutomotiveEngineers, Warrendale, PA, 1993.5. Rice, R. C., Editor, Fatigue Design Handbook (A-10), 1988, Society of Automotive Engineers, Inc., 400Commonwealth Drive, Warrendale, PA 15096

15、-0001.6. Boardman, B. E., Crack Initiation Fatigue-Data, Analysis, Trends and Estimation, Proceeding of theSAE Fatigue Conference, P109, Society for Automotive Engineers, Warrendale, PA, 1982.7. Wetzel, R. M., Editor, Fatigue Under Complex Loadings: Analysis and Experiments, AE-6, Society ofAutomoti

16、ve Engineers, Warrendale, PA, 1977.8. Bannantine, J., Comer, J., and Handrock, J., Fundamentals of Metal Fatigue Analysis, Prentice-Hall,1989.9. Multiaxial Fatigue; Analysis and Experiments, AE-14, Society of Automotive Engineers, Warrendale,PA, 1989.10. Fuchs, H. O. and Stephens, R. I., Metal Fatig

17、ue in Engineering, John Wiley and Sons, 1980.11. Bridgeman, P. W., Transactions of ASM, American Society for Metals, Vol. 32, p. 553, 1944; (alsoDieter, G. E. Mechanical Metallurgy, McGraw-Hill Book Co., Inc., 1961, New York, NY, pp. 250-254.12. Raske, D. T. and Morrow, JoDean, “Mechanics of Materia

18、ls in Low Cycle Fatigue Testing, Manual onLow Cycle Fatigue Testing,” ASTM STP 465, American Society for Testing and Materials, 1969, pp. 1-25.13. Landgraf, R. W., Morrow, JoDean, and Endo, T., “Determination of the Cyclic Stress-Strain Curve,”Journal of Materials, ASTM, Vol. 4, No. 1, March 1969, p

19、p. 176-188.14. Gallagher, J. P., “What the Designer Should Know About Fracture Mechanics Fundamentals,” Paper710151 presented at SAE Automotive Engineering Congress, Detroit, January 1971.15. Sinclair, G. M., “What the Designer Should Know About Fracture Mechanics Testing,” Paper 710152presented at

20、SAE Automotive Engineering Congress, January 1971.16. Ripling, E. J., “How Fracture Mechanics Can Help the Designer,” Paper 710153 presented at SAEAutomotive Engineering Congress, Detroit, January 1971.17. Campbell, J. E., Berry, W. E., and Fedderson, C. E., “Damage Tolerant Design Handbook,” MCIC H

21、B-01, Metal and Ceramics Information Center, Battelle Columbus Laboratories, Columbus, OH.18. Jaske, C. E., Fedderson, C. E., Davies, K. B., Rice, R. C., “Analysis of Fatigue, Fatigue CrackPropagation and Fracture Data,” NASA CR-132332, Battelle Columbus Laboratories, Columbus, OH,November 1973.19.

22、Moore, T. D., “Structural Alloys Handbook,” Mechanical Properties Data Center, BelFour Stulen, Inc.,Traverse City, MI.20. Wolf, J., Brown, W. F., Jr., “Aerospace Structural Metals Handbook,” Vol. 1-4, Mechanical PropertiesData Center, BelFour Stulen, Inc., Traverse City, MI.21. Raske, D. T., “Review

23、 of Methods for Relating the Fatigue Notch Factor to the Theoretical StresssConcentration Factor, Simulation of the Fatigue Behavior of the Notch Root in Spectrum LoadedNotched Members,” Chapter II, TAM Report No. 333-Department of Theoretical and AppliedMechanics, University of Illinois, Urbana, Ja

24、nuary 1970.22. Topper, T. H., Wetzel, R. M. and Morrow, JoDean, “Neubers Rule Applied to Fatigue of NotchedSpecimens,” Journal of Materials, ASTM, Vol. 4, No. 1, March 1969, pp. 200-209.SAE J1099 Revised AUG2002-3-23. Tucker, L. E., “A Procedure for Designing Against Fatigue Failure of Notched Parts

25、,” SAE Paper No.720265, Society of Automotive Engineers, New York, NY 10001.24. Dowling, N. E., “Fatigue Failure Predictions for Complicated Stress-Strain Histories,” J. Materials,ASTM, March 1972; (see also: Fatigue Failure Predictions for Complicated Stress-Strain Histories.TAM Report No. 337, The

26、oretical and Applied Mechanics Dept., University of Illinois, Urbana, 1970.25. Morrow, JoDean, “Cyclic Plastic Strain Energy and Fatigue of Metals,” Internal Friction, Damping, andCyclic Plasticity, ASTM STP 378, American Society for Testing and Materials, 1965, pp 45-87.26. Miller, G. A., and Reems

27、nyder, H. S., “Strain-Cycle Fatigue of Sheet and Plate Steels I: Test MethodDevelopment and Data Presentation,” SAE Paper No. 830175, 1983.27. Annual Book of ASTM Standards, MetalsMechanical Testing; Elevated and Low Temperature Tests;Metallography, Standard E 739-91, “Statistical Analysis of Linear

28、 or Linearized Stress-Life and Strain-Life Fatigue Data,” Vol. 3.01, American Society for Testing and Materials, West Conshohocken, PA,1995.3. Material Property TablesTables 2 to 4 list the monotonic and cyclic stress-strain properties and the fatigueproperties for selected materials. These tables a

29、re preceded by a brief introduction, definitions, discussion,and Table 1 which lists the abbreviations used in this document.The majority of the properties listed in the Tables have been contributed by members of the SAE Fatigue,Design, and Evaluation Committee and are the property of SAE Internatio

30、nal, Warrendale, PA, 15096.Researchers are encouraged to contribute their data and may do so by contacting the Fatigue Design andEvaluation Committee through the SAE.For several materials commonly used in the as-received condition, there are numerous data sets available.These have been reported as a

31、 single value or a range and are identified as to which data were involved. Asdefined, these properties are from specimens tested in ambient environments and, therefore, do not includesuch influences as environmental effects (wet or corrosive conditions, elevated temperature, etc.), surfaceroughness

32、 effects, mean stress effects, notch effects, etc.There are many procedures for using this information for design purposes. They are too lengthy to be includedin this report; however, there are a number of publications which discuss these procedures. Several keyreferences 1-27 that discuss fatigue p

33、roperties, methods for determining fatigue properties, and illustrate theuse of these data for making design decision are listed in Section 2.4. Monotonic Stress-Strain Properties4.1 Monotonic stress-strain properties are generally determined by testing a smooth polished specimen underaxial loading.

34、 The load, diameter and/or strain on the uniform test section is measured during the test in orderto determine the materials stress-strain response as illustrated in Figures 1 and 2. Properties, most of whichare discrete points on the stress-strain curve, can be defined to describe the behavior of a

35、 material.4.2 Ultimate Tensile Strength (Su)The engineering stress at maximum load. In a ductile material, it occurs atthe onset of necking in the specimen.(Eq. 1)where:Pmax = maximum loadAo = original cross sectional areaSu Pmax Ao=SAE J1099 Revised AUG2002-4-4.3 True Fracture Strength (f)The “true

36、” tensile stress required to cause fracture.(Eq. 2)where:Pf = load at failureAf = minimum cross sectional area after failureThe value f must be corrected for the effect of triaxial stress present due to necking. One such correctionsuggested by Bridgeman 11 is illustrated in Figure 3. In this figure,

37、 the ratio of the corrected value to theuncorrected value (f/(Pf/Af) is plotted against true tensile strain.4.4 Tensile Yield Strength (Sys, ys )The stress to cause a specified amount of inelastic strain, usually 0.2%. Itis usually determined by constructing a line of slope E (modulus of elasticity)

38、 through 0.2% strain and zerostress. The stress where the constructed line intercepts the stress-strain curve is taken as the yield strength.4.5 Percentage Reduction of Area (% RA)The percentage of reduction in cross sectional area after fracture.(Eq. 3)4.6 True Fracture Ductibility (f)The “true” pl

39、astic strain after fracture.(Eq. 4)4.7 Monotonic Strain Hardening Exponent (n)The power to which the “true” plastic strain must be raised to bedirectly proportional to the “true” stress. It is generally taken as the slope of log versus log p plot as shownin Figure 2.(Eq. 5)4.8 Monotonic Strength Coe

40、fficient (K)The “true” stress at a “true” plastic strain of unity as shown in Figure 2.If the value of the true fracture ductility is less than 1.0, it is necessary to extrapolate. (see Equation 5).4.8.1 Monotonic tension properties of a material can be classed into two groups, engineering stress-st

41、rainproperties and “true” stress-strain properties. Engineering properties are associated with the original crosssectional area of the test specimen, and “true” values relate to actual area while the specimen is under load.The difference between “true” and engineering values is insignificant in the

42、low strain region, less than orequal to 2% strain.4.8.2 Until the test bar begins to locally neck, some simple relationships exist between engineering and “true”stress-strain values. Equation 6 gives the relationship between engineering and true strain.(Eq. 6)where: = “true” straine = engineering st

43、rainf Pf Af=%RA = 100 Ao Af Ao()f ln (Ao Af)ln 100100%RA()= Kpn= ln 1 e+()=SAE J1099 Revised AUG2002-5-Similarly, Equation 7 relates true stress to engineering stress.(Eq. 7)where: = “true” stressS = engineering stressThese relationships do not apply after onset of necking.4.8.2.1 A more detailed di

44、scussion and derivation of monotonic stress-strain properties can be found in ASTMSTP 465 12. Figures 1 and 2 graphically illustrate a majority of these properties.5. Cyclic Stress-Strain Properties5.1 Cyclic stress-strain properties are determined by testing smooth polished specimens under axial cy

45、clic straincontrol conditions. The cyclic stress-strain curve is defined as the locus of tips of stable “true” stress-strainhysteresis loops each obtained from a constant amplitude test specimen. A typical stable hysteresis loop isillustrated in Figure 4 and a set of stable loops with a cyclic stres

46、s-strain curve down through the loop tips isillustrated in Figure 5. As illustrated, the height of the loop from tip-to-tip is defined as the stress range. Forcompletely reversed testing, one-half of the stress range is generally equal to the stress amplitude while one-half of the width from tip-to-

47、tip is defined as the strain amplitude. Plastic strain amplitude is found bysubtracting the elastic strain amplitude from the strain amplitude as indicated in Equations 8, 9, and 10.(Eq. 8)According to Hookes law,(Eq. 9)where:E = modulus of elasticity(Eq. 10)5.2 A more complete discussion of the cyc

48、lic stress-strain curve and other methods of obtaining the curve aregiven in STP 465 12 and 4.5.3 Cyclic Yield Strength (0.2% ys)The stress to cause 0.2% inelastic strain as measured on a cyclic stress-strain curve. It is usually determined by constructing a line parallel to the slope of the cyclic

49、stress-strain curveat zero stress through 0.2% strain. The stress where the constructed line intercepts the cyclic stress-straincurve is taken as the 0.2% cyclic yield strength.5.4 Cyclic Strain Hardening Exponent (n)The power to which “true” plastic strain amplitude must be raised tobe directly proportional to “true” stress amplitude. It is taken as the slope of the log /2 versus log p/2 plot,where /2 and p/2 are measured from cyclically stable hysteresis loops.(Eq. 11)where:p/2 = “true” plastic strain amplitude S 1 e+(