ICCM19 paper PN GZ 13-06-2013 Second Draft.pdf (515.6 kB)
Experimental study of impact damage resistance and tolerance of composite sandwich panels
conference contribution
posted on 2014-07-17, 13:36 authored by Peter Nash, Gang ZhouGang Zhou, S. Gahlay, M. BurtAn 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 MaterialsVolume
2Pages
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
2013Notes
This is a conference paper. Deposited with kind permission from the Canadian Association for Composite Structures and Materials [http://www.cacsma.ca/].Language
- en