Post-Impact Investigation of CFRP Laminated Plate
DOI:
https://doi.org/10.11113/jt.v71.3723Keywords:
CFRP, Impact, permanent indentation, delaminationAbstract
This paper deals with low-velocity impact and quasi-static indentation tests on carbon fibre reinforced plastic (CFRP) laminates that classically used in aeronautical applications. The aim is to carry out post-impact analysis using Vic 3-D digital image correlation to investigate the behaviour of permanent indentation which is an important condition for the damage tolerance justification in composite. Result shows the indentation depth decreased with the time due to relaxation of the specimen until at certain position. The microscopic observations were carried out to understand the phenomenon. Besides that, the post-mortem analyses on the impacted plate were also carried out through microscopic observation to determine the delamination area at each interface which is normally difficult to extract from the C-Scan result. The observations were made at three different sections cut (0°, 90° and 45°). The results of delamination area obtained from both microscopic and C-scan analysis is compared and there are rather satisfying to each other.
References
D. Zheng. 2007. Low Velocity Impact Analysis of Composite Laminated Plates. University of Akron. Ohio. PhD Thesis.
N. Hongkarnjanakul, C. Bouvet, S. Rivallant. 2013. Validation of low velocity impact modelling on different stacking sequences of CFRP laminates and influence of fibre failure. Compos Struct. 106: 549–559.
D. Coutellier, J.C. Walrick, P. Geoffroy. 2006. Presentation of a methodology for delamination detection within laminated structures. Compos Sci Technol. 66: 837–845
R.C. Alderliesten. 2008. Damage tolerance of bonded aircraft structures. Int J Fatigue. 1: 1–10
R. Dilger, H. Hickethier, M.D. Greenhalgh. 2009. Eurofighter a safe life aircraft in the age of damage tolerance. Int J Fatigue. 31(6):1017–1023
A.A. Elias, C. Bouvet, R. Samuel, B. Broll, J.J. Barrau. 2009. Experimental analysis of damage creation and permanent indentation on highly oriented plate. Compos Sci Technol. 69: 1238–1245
K. Henkhaus. 2003. Overview of research on composite material impact behaviour. 16thEngineering Mechanics Conference, American Society of Civil Engineers, University of Washington, Seattle.
M. Aktas, C. Atas, M.I. Bϋlent, K. Ramazan. 2008. An experimental investigation of the impact response of composite laminate. Compos Struct. 87: 307–313
J.F.M. Wiggenraad, R. Aoki, M. Gädke, E. Greenhalg, D. Hachenberg, K. Wolf, R. Bübl. 1997. Damage propagation in composite structural elements - Analysis and experiments on structures. Compos Struct. 36: 173–186.
S. Petit, C. Bouvet, A. Bergerot, J.J. Barrau. 2007. Impact and compression after impact experimental study of a composite laminate with a cork thermal shield. Compos Sci Technol. 67: 3286–3299
B. Broll. 2008. Experimental Studies On The Damage Mechanisms of CFRP-Structures. Master Thesis. ISAE.
C. Bouvet, S. Rivallant, J.J. Barrau. 2012. Low velocity impact modeling in composite laminates capturing permanent indentation. Compos Sci Technol. 72(16): 1977–88
W. He, Z. Guan, X. Li. 2013. Prediction of permanent indentation due to impact on laminated composites based on an elasto-plastic model incorporating fiber failure. Compos Struct. 96: 232–242.
ASTM D7136/D7136M. 2007. Standard Test Method for Measuring the Damage Resistance of a Fiber- Reinforced Polymer Matrix Composite to a Drop-Weight Impact Event.
H. A. Israr. 2014. Experimental and Numerical Investigation of CFRP Composite Laminates under Crushing. Université de Toulouse: ISAE, INSA, UPS, Emac; ICA (Institut Clement Ader). Phd Thesis.
S.S. Suh, N.L. Han, J.M. Yang, H.T. Hahn. 2003. Compression behavior of stitched stiffened panel with clearly visible stiffener impact damage. Compos Struct. 62: 213–221.
G. Belingardi, R. Vadori. 2003. Influence of the laminate thickness in low velocity impact behavior of composite material plate. Compos Struct. 62: 27–38.
A.T. Nettles, A.J. Hodge. 1997. The impact response of carbon/epoxy laminates. NASA/TM-97-206317.
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