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TECHNICAL PAPERS

On the Characterization of Fatigue Crack Growth in a Plate With a Single-Sided Repair

[+] Author and Article Information
C. N. Duong

The Boeing Company, 5301 Bolsa Avenue, MC H013-A316, Huntington Beach, CA 92647-2099

C. H. Wang

Defence Science & Technology Organization, 506 Lorimer Street, Fishermans Bend 3207, Australia

J. Eng. Mater. Technol 126(2), 192-198 (Mar 18, 2004) (7 pages) doi:10.1115/1.1647129 History: Received May 12, 2003; Revised September 26, 2003; Online March 18, 2004
Copyright © 2004 by ASME
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References

Baker, A. A., Jones, R., Rose, F., and Rao, K. J., 2002, Advances in the Bonded Composite Repair of Metallic Aircraft Structures, Elsevier Publisher, The Netherlands.
Ratwani,  M. M., 1979, “Analysis of Cracked, Adhesively Bonded Laminate Structures,” AIAA J., 17, pp. 988–994.
Rose, L. R. F., 1988, “Theoretical Analysis of Crack Patching,” in Bonded Repair of Aircraft Structures, A. A. Baker and R. Jones, eds., Martinus Nijhoff, New York.
Ratwani,  M. M., 1980, “A Parametric Study of Fatigue Crack Growth Behavior in Adhesively Bonded Metallic Structures,” ASME J. Eng. Mater. Technol., 100, pp. 46–51.
Arendt, C., and Sun, C. T., 1994, “Bending Effects of Unsymmetric Adhesively Bonded Composite Repairs on Cracked Aluminum Panels,” Proceedings of FAA/NASA International Symposium on Advanced Structural Integrity Methods for Airframe Durability and Damage Tolerance, NASA Conference Publication 3274, Part 1, pp. 33–48.
Wang,  C. H., Rose,  L. R. F., and Callinan,  R., , 1998, “Analysis of Out-of-Plane Bending in One-Sided Bonded Repair,” Int. J. Solids Struct., 35, pp. 1653–1675.
Wang,  C. H., and Rose,  L. R. F., 1999, “A Crack Bridging Model for Bonded Plates Subjected to Tension and Bending,” Int. J. Solids Struct., 36, pp. 1985–2014.
Beom,  H. G., and Earmme,  Y. Y., 1999, “The Elastic Field of an Elliptic Cyclindrical Inclusion in a Laminate With Multiple Isotropic Layers,” ASME J. Appl. Mech., 66, pp. 165–171.
Duong,  C. N., and Yu,  J., 2003, “Analysis of a Plate Containing a Polygon-Shaped Inclusion With a Uniform Eigencurvature,” ASME J. Appl. Mech., 70, pp. 404–407.
Duong,  C. N., and Yu,  J., 2003, “Thermal Stresses in a One-Sided Bonded Repair: An Approximate Geometrically Nonlinear Analysis,” Theor. Appl. Fract. Mech. J., 40, pp. 197–209.
Duong,  C. N., 2004, “An Engineering Approach to Geometrically Nonlinear Analysis of a One-Sided Bonded Repair Under Thermo-Mechanical Loading,” Compos. Struct., 64, pp. 13–21.
Duong, C. N., 2003, Composite Repair of Aircraft Structures, Program Report, Volume III: Tests and Method Validations, prepared for USAF Air Force Research Laboratory.
De Koning, A. U., 1980, “A Simple Crack bClosure Model for Prediction of Fatigue Crack Growth Rates Under Variable Amplitude Loading,” NRL MP 80006.

Figures

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Two-stage analytical procedure for determining the stress intensity factor in a plate with a single-sided repair: (a) the original problem; (b) stage I analysis; and (c) stage II analysis
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da/dN versus ΔKeff for Al 7075-T6 3.175 mm thick sheet
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da/dN versus ΔKeff for Al 7075-T6 1.27 mm thick sheet
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Analytical predictions versus test results of crack growth in specimen configuration 1
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Analytical predictions versus test results of crack growth in specimen configuration 2
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Analytical predictions versus test results of crack growth in specimen configuration 3
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Analytical predictions versus test results of crack growth in specimen configuration 4
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Analytical predictions versus test results of crack growth in specimen configuration 5. Since the relative humidity condition (RH) in this particular test varies quite significantly from one specimen to another, RH condition of the specimen is also indicated in the figure’s legend with low and high meaning low and high value of RH.
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Analytical predictions versus test results of crack growth in specimen configuration 6
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Analytical predictions versus test results of crack growth in specimen configuration 7
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Analytical predictions versus test results of crack growth in specimen configuration 8
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Analytical predictions versus test results of crack growth in specimen configuration 9

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