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Research Papers

A Comparison of Constitutive Equations for the Energy-Based Lifing Method

[+] Author and Article Information
M.-H. Herman Shen

e-mail: shen.1@osu.edu
The Department of Mechanical and Aerospace Engineering,
The Ohio State University,
Columbus, OH 43210

Charles Cross

Air Force Research Laboratory,
Wright-Patterson AFB, OH 45433

1Corresponding author.

Contributed by the Materials Division of ASME for publication in the JOURNAL OF ENGINEERING MATERIALS AND TECHNOLOGY. Manuscript received September 4, 2012; final manuscript received March 27, 2013; published online May 8, 2013. Assoc. Editor: Irene Beyerlein.

J. Eng. Mater. Technol 135(3), 031008 (May 08, 2013) (7 pages) Paper No: MATS-12-1225; doi: 10.1115/1.4024116 History: Received September 04, 2012; Revised March 27, 2013

Alternatives to quasi-static and dynamic constitutive relationships have been investigated with respect to a previously developed energy-based fatigue lifing method for various load profiles, which states: the total strain energy dissipated during both a quasi-static process and a dynamic process are equivalent and a fundamental material property. Specifically, constitutive relationships developed by Ramberg–Osgood and Halford were modified for application to the existing energy-based framework and were compared to the lifing method originally developed by Stowell. Extensive experimentation performed on Titanium 6Al-4V (Ti-64) combined with experimental data generated for Aluminum (Al) 6061-T6 at various temperatures were utilized in support of this investigation. This effort resulted in considerable improvements to the accuracy of the lifing prediction for materials with an endurance limit through application of a modified-Halford approach. Additionally, the relative equality in predictive accuracy between the modified-Stowell approach the modified-Ramberg–Osgood approach was demonstrated.

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References

Figures

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Fig. 1

(a) Validation of predictions, axial/shear, room-temperature, Al 6061-T6, R = −1 [15,16] and (b) validation of predictive capabilities, axial, elevated temperature, Al 6061-T6, R = −1 [18]

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Fig. 2

(a) Idealized schematic of quasi-static strain energy density [19] and (b) idealized schematic of dynamic strain energy density [11,19]

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Fig. 3

Specimen design, dimensions in millimeter

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Fig. 4

Representative quasi-static curve

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Fig. 5

Experimental fatigue data

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Fig. 6

(a) Fracture surface, specimen 1006 and (b) fracture surface, specimen 1007

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Fig. 7

Dynamic frequency evaluation results

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Fig. 8

Normalized energy-dissipation history: abscissa normalized by total number of cycles to failure and ordinate normalized by maximum cyclic strain energy

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Fig. 9

(a) Fatigue life prediction, MSA versus MHA versus MROA, Ti-64, 298 K and (b) accuracy comparison, MSA versus MHA versus MROA, Ti-64, 298 K

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Fig. 10

(a) Fatigue life prediction, MSA versus MHA versus MROA, Al-6061 T6, 298 K and (b) accuracy comparison, MSA versus MHA versus MROA, Al-6061 T6, 298 K

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Fig. 11

(a) Fatigue life prediction, MSA versus MHA versus MROA, Al-6061 T6, 348 K and (b) accuracy comparison, MSA versus MHA versus MROA, Al-6061 T6, 348 K

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Fig. 12

(a) Fatigue life prediction, MSA versus MHA versus MROA, Al-6061 T6, 373 K and (b) accuracy comparison, MSA versus MHA versus MROA, Al-6061 T6, 373 K

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Fig. 13

(a) Fatigue life prediction, MSA versus MHA versus MROA, Al-6061 T6, 398 K and (b) accuracy comparison, MSA versus MHA versus MROA, Al-6061 T6, 398 K

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