Numerical Modelling of Carbon/Epoxy Laminated Plate Impact Damage

Abstract:

• Periodical: Key Engineering Materials (Volumes 230-232)
• Pages: 533-536
• DOI: https://doi.org/10.4028/www.scientific.net/KEM.230-232.533
• Online since: October 2002
• Authors: Nuno Ferreira Rilo, Luís Manuel Silva Ferreira, José Maria Osório Sousa Cirne, Rogério Augusto da Costa Pereira Leal
• Keywords: ADINA, Carbon/Epoxy Composites, Damage, Delamination, Finite Element Model (FEM), Impact

References

[1] Bathe, K. J., Finite Element Procedures, Prentice Hall, Englewood Cliffs, NJ, (1996)

[2] Kwon, Y. S. and Sankar, B. V.; Indentation-Flexure and Low-Velocity Impact Damage in Graphite/Epoxy Laminates; NASA Contrator Report 187624, Grant NAG1-826, March 1992.

[3] Sankar, B. V. and Nguyen, P. T., Nondimensional Impact Models for Composite Laminates, Proceedings of the American Society for Composites 5 th Technical Conference, E. Lansing, Michigan, June, pp.600-610, June 1990.

[4] Lakshminarayana, H. V., Boukhili, R. and Gauvin, R., Impact response of laminated composite plates: Prediction and verification, Composite Structures, 28, 61-72, 1994.

DOI: 10.1016/0263-8223(94)90006-x

[5] Lakshminarayana, H. V., Boukhili, R. and Gauvin, R., Finite element simulation of impact tests of laminated composite plates, Composite Structures, 28, 47-59, 1994.

DOI: 10.1016/0263-8223(94)90005-1

[6] ADINA - Automatic Dynamic Incremental Nonlinear Analysis, Theory and Modeling Guide, ARD 00-7, Watertown, MA 02472, USA 1.00 0.75 0.50 0.25 0 Load (P/P )máx 0 2 3 4 5 6 7 Central Displacement W/h 1 0 Nonlinear Static Analysis Linear Static Analysis h = 1 mm P = 200 kg máx R= 25.4 mm r= 1.257 mm 16 layers (0°,90°)8s R x a P y z,w h r 1.00 0.75 0.50 0.25 0 0 2 3 4 5 6 7 Central Displacement W 1 0 x/a Nonlinear Static Analysis Linear Static Analysis e y/a Along X Along y Along x Along y 8 16 layers (0°) h = 1 mm P = 200 kgmáx R= 25.4 mm r= 1.257 mm R x a P y z,w h r

DOI: 10.1088/0026-1394/60/1a/04006