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TECHNICAL PAPERS

Control of Damage in Composite Laminates by Ply-Stacking Designs: Characteristic Failure Signatures and Safety Criteria

[+] Author and Article Information
Vasyl Michael Harik

ICASE, MS 132C, NASA Langley Research Center, Hampton, VA 23681-2199

J. Eng. Mater. Technol 125(4), 385-393 (Sep 22, 2003) (9 pages) doi:10.1115/1.1605771 History: Received January 10, 2003; Revised June 17, 2003; Online September 22, 2003
Copyright © 2003 by ASME
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References

Chang, F.-K., ed., 2000, “Structural Health Monitoring 2000,” Proceedings 2nd Int. Workshop on Structural Health Monitoring, September 8–10, 1999, Stanford University, Stanford, CA.
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Chamis, C. C., 1996, “Failure Criteria for Filamentary Composites,” Testing and Design, ASTM STP 490, American Society for Testing and Materials, West Conshohocken, PA, pp. 336–460.
Ochoa, O., and Reddy, J. N., 1992, Finite Element Analysis of Composite Laminates, Kluwer Academic Publishers, Dordrecht, The Netherlands.
Sun, C. T., Quinn, B. J., Tao, J., and Oplinger, D. W., 1996, “Comparative Evaluation of Failure Analysis Methods for Composite Laminates,” Technical Report DOT/FAA/AR-95/109, Washington, D.C.
Soden,  P. D., Hinton,  M. J., and Kaddour,  A. S., 1998, “A Comparison of the Predictive Capabilities of Current Failure Theories for Composite Laminates,” Compos. Sci. Technol., 58(7), pp. 1225–1254.
Sleight, D. W., 1999, “Progressive Failure Analysis Methodology for Laminated Composite Structures,” NASA/TP-1999-209107, NASA Langley Research Center, Hampton, VA.
Hinton, M. J., Kaddour, A. S., and Soden, P. D., 2001, “Predicting Failure in Fibre Composites: Lessons Learned from the World-Wide Failure Exercise,” Proceed. ICCM-13, July 11–13, Beijing, China.
Bogetti, T. A., Harik, V. M., and Hoppel, C. P. R., 2000, “3D Analysis of Progressive Damage in Thick Composite Laminates,” Proc. 8th Int. Conf. Nuclear Engng., ICONE-8, Baltimore, 2–6 April; ASME CD, Philadelphia, PA, pp. 1–10.
Bogetti,  T. A., Harik,  V. M., Hoppel,  C. P. R., Newill,  J., and Burns,  B., 2003, “Prediction of the Nonlinear Response and Progressive Failure of Composite Laminates,” Compos. Sci. Technol., in press.
Bogetti,  T. A., Hoppel,  C. P. R., Harik,  V. M., Newill,  J., and Burns,  B., 2003, “Prediction of the Nonlinear Response and Progressive Failure of Composite Laminates: Correlation With Experimental Results,” Compos. Sci. Technol., in press.
Harik,  V. M., 2001, “Optimization of Structural Designs for a Safe Failure Pattern: Layered Material Systems,” Mater. Des., 22(4), pp. 317–324.
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Christensen, R. M., 1979, “Effective Moduli of Cylindrical and Lamellar Systems,” in Mechanics of Composite Materials, Wiley, New York, NY, pp. 73–105.
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O’Brien,  T. K., 1985, “Interlaminar Fracture of Composites,” J. Aeronaut. Soc. India,37(1), pp. 61–71.
Reifsnider, K. L., 1977, “Some Fundamental Aspects of the Fatigue and Fracture Response of Composite Materials,” Proc. 14th SES Annual Meeting, Bethlehem, PA.
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Figures

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A schematic for the incremental loading strategy and a generic failure signature with the associated load-drop sequence during a progressive failure of a composite laminate
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An example of the initial and final bi-axial failure envelopes (σx versus τxy) for a [90/+30/−30]s glass/epoxy laminate and the associated damage modes in the failed plies
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An example of a bi-axial failure envelope (σy versus σx) for the initial and final failures of the [0/+45/−45/90]s AS4 graphite/epoxy composite laminate and the associated damage modes
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The stress-strain curves with damage modes for a [0/+45/−45/90]s AS4 graphite/epoxy composite under bi-axial loading (σyx=2:1, after 12)
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The stress-strain curves for a [0/90]s laminate under a tensile loading, where theoretical predictions are shown by two solid lines, while experimental data is represented by dots 10
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A schematic of the cross-ply structure in a [02/90]s composite laminate
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A quarter of the unit cell for an E-glass/MY epoxy cross-ply composite 891011 shown with the original contour and a deformed mesh of finite elements (a) and a field of displacement vectors (b) for a tensile loading (Rf=1,H/Rf=8, and w/Rf=2)
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The tensile strain (εx) distribution (a), and the compressive Poisson’s strain, εy (b), in an MY epoxy matrix around an E-glass fiber predicted by the micromechanical FE model for a tensile loading (the dotted line is the original boundary, while Rf=1,H/Rf=8, and w/Rf=2)
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Distribution of the shear strain in an MY epoxy matrix around an E-glass fiber of a cross-ply composite subjected to a tensile loading (the dotted line is the original boundary, while Rf=1,H/Rf=8, and w/Rf=2)

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