Sage Journals: Discover world-class research

Abstract

Composite pressure vessel design requires the prediction of failure given large-scale damage. Cracks in composite laminates are known to develop a damage zone that exhibits strain-softening. This investigation sought to develop a computational model that simulates progressive damage and predicts failure of complex laminated shell structures subject to combined tension and flexure. The model assumed a macroscopic definition of orthotropic damage that was allowed to vary linearly through the shell thickness. It was further proposed that nonlocal plate strain and curvature act to force damage growth according to a set of uniaxial criteria. Damage induced strain softening is exhibited by degradation of laminate stiffness. An expression for the damage reduced laminated plate stiffness was derived which assumed the familiar laminated plate [ABD] stiffness matrix format. The model was implemented in a finite element shell program for simulation of fracture and evaluation of damage tolerance. A combined tension plus flexure fracture test was developed for characterizing damage. Analysis was performed on a section of pressurized composite fuselage containing a large crack. Good agreement was found between calculations and test results.

Get full access to this article

View all access options for this article.

References

1. Awerbuch, J. and Madhukar, M.S. 1985. "Notched Strength of Composite Laminates: Predictions and Experiments-A Review." Journal of Reinforced Plastics and Composites, 4(1):1-159.

2. Kennedy, T. and Nahan, M. 1996. "A Simple Nonlocal Damage Model for Predicting Failure of Notched Laminates." Composite Structures, 35:29-236.

3. Walker, T.H. , Avery, W.B. , Ilcewicz, L.B. , Poe, C.C. and Harris, C.E. 1991. "Tension Fracture of Laminates for Transport Fuselage-Part 1: Material Screening." Second NASA Advanced Technology Conference, NASA CP 3154, 197-238.

4. Walker, T.H. , Ilcewicz, L.B. , Polland, D.R. and Poe, C.C. 1992. "Tension Fracture of Laminates for Transport Fuselage-Part 2: Large Notches." Third NASA Advanced Technology Conference, NASA CP 3178, 727-758.

5. Nahan, M. 1997. "A Nonlocal Damage Theory for Laminated Plate with Application to Aircraft Damage Tolerance." Dissertation, Oregon State University.

6. Ilcewicz, L.B. , Walker, T.H. , Murphy, D.P. , Dopker, B. and Scholz, D.B. 1993. "Tension Fracture of Laminates for Transport Fuselage-Part 4: Damage Tolerance Analysis." Fourth NASA Advanced Technology Conference, NASA CP 3229, 264-298.

7. Hillerborg, A. 1983. "Analysis of One Single Crack." Fracture Mechanics of Concrete, Ed. Wittmann, F.H. , Publ. Elsevier Science, 223-249.

8. Bazant, Z.P. 1984a. "Size Effect in Blunt Fracture: Concrete, Rock, Metal." J. Eng Mech., 110:4:518-535.

9. Pijaudier-Cabot, G. and Bazant, Z.P. 1987. "Nonlocal Damage Theory." J. Eng. Mech., 113:2:1512-1533.

10.

10. Dopker, B. , Murphy, D.P. , Ilcewicz, L. and Walker, T. 1994. "Damage Tolerance Analysis of Composite Transport Fuselage Structure."

35th AIAA/ASME/ACSE1AMS/ASC Structures, Structural Dynamics and Materials Conf

11.

11. Voyiadjis, G.Z. and Kattan, P.I. 1993. "Damage of Fiber-Reinforced Composite Materials with Micromechanical Characterization." Int. J. Solids Structures, 30:20:2757-2778.

12.

12. Shahid, I. , Sun, H.-T. and Chang, F.-K. 1995b. "Predicting Scaling Effect on the Notched Strength of Prepreg and Fiber Tow-Placed Laminated Composites." J. Composite Materials, 29:8:1063-1095.

13.

13. Kennedy, T. and Nahan, M. 1997. "A Simple Nonlocal Damage Model for Predicting Failure in a Composite Shell Containing a Crack." Composite Structures, 39(1-2):85-91.

14.

14. Jones, R.M. 1975. Mechanics of Composite Materials, Hemisphere Publishing Corp., New York, 147-156.

15.

15. Cordebois, J.L. and Sidoroff, F. 1979. "Damage Induced Elastic Anisotropy." Mechanical Behavior of Anisotropic Solids, Colloque Euromech 115, ed. Boehler, J.-P. , Martinus Nijhoff Publishers, 761-774.

16.

16. Bazant, Z.P. and Cedolin, L. 1991. Stability of Structures: Elastic, Inelastic Fracture and Damage Theories, Oxford University Press, New York.

17.

17. Walker, T. , Scholz, Flynn B. , Dopker, B.D.B. , Bodine, J. , Ilcewicz, L.B. , Rouse, M. , McGowan, D. and Poe C.C. 1996."Damage Tolerance of Composite Fuselage Structure." Sixth NASA/DOD/ARPA Advanced Composite Technology Conference, NASA CP-3326.