ICCM19 paper PN GZ 13-06-2013 Second Draft.pdf (515.6 kB)
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Experimental study of impact damage resistance and tolerance of composite sandwich panels

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conference contribution
posted on 17.07.2014, 13:36 by Peter Nash, Gang ZhouGang Zhou, S. Gahlay, M. Burt
An experimental study of in-plane compressive behaviour of carbon/epoxy-skinned and E-glass/epoxy-skinned sandwich panels was conducted. For the former, two carbon/epoxy skin thickness combinations were 8/6 plies and 16/12 plies. Both cross ply (CP) and quasi-isotropic (QI) lay-ups were used in each combination. For the latter, two E-glass/epoxy skin thickness combinations of 8/8 and 16/16 plies were used with both being in a cross ply lay-up. The majority of sandwich panels were impact-damaged with their dominant damage mechanisms being characterised. All impact-damaged and baseline panels were in-plane compression tested. The effects of impact damage, lacking symmetry, skin thickness, skin lay-up and core density on CAI strength were examined.

History

School

  • Aeronautical, Automotive, Chemical and Materials Engineering

Department

  • Aeronautical and Automotive Engineering

Published in

19th International Conference on Cmoposite Materials

Volume

2

Pages

2844 - 2851 (8)

Citation

NASH, P. ... et al., 2013. Experimental study of impact damage resistance and tolerance of composite sandwich panels. IN: Van Hoa, S. and Hubert, P. (eds.) 19th International Conference on Composite Materials (ICCM-19), Montreal, Canada, 28 July - 2 August 2013, 2, pp. 2844 - 2851.

Publisher

© Canadian Association for Composite Structures and Materials (CACSMA)

Version

AM (Accepted Manuscript)

Publication date

2013

Notes

This is a conference paper. Deposited with kind permission from the Canadian Association for Composite Structures and Materials [http://www.cacsma.ca/].

Language

en

Location

Montreal