Study on Damage Modes of a Sandwich Panel Impacted Repeatedly

Article Preview

Abstract:

This paper describes an experimental investigation for determining the damage modes under low energy impact-fatigue of sandwich panels consisting of aluminum skins supported by honeycomb core made of aluminum. Square samples of 125mm by 125mm sides and 10mm thickness (skin of 0.6mm and 8.8mm of core) were subjected to impact fatigue loading using a testing machine at four different energy levels (2J, 3J, 5J and 7J). The square plates are clamped in a fixture system over a 100mm diameter hole. Three different diameters of impactor head (15mm, 25mm and 35mm) are used to study their influence on life duration of the sandwich plates. Results showed that damage area at impacted face and propagation of multi-cracks at rear face are greatly affected by energy level and impactor diameter.

You might also be interested in these eBooks

Info:

Periodical:

Pages:

147-151

Citation:

Online since:

June 2014

Export:

Price:

Permissions CCC:

Permissions PLS:

Сopyright:

© 2014 Trans Tech Publications Ltd. All Rights Reserved

Share:

Citation:

* - Corresponding Author

[1] C.C. Foo, L.K. Seah, G.B. Chai, Low-velocity impact failure of aluminium honeycomb sandwich panels, Composite Structures. 85(1) (2008) 20-28.

DOI: 10.1016/j.compstruct.2007.10.016

Google Scholar

[2] V. Crupi, G. Epasto, E. Guglielmino, Collapse modes in aluminium honeycomb sandwich panels under bending and impact loading, International Journal of Impact Engineering. 43 (2012) 6-15.

DOI: 10.1016/j.ijimpeng.2011.12.002

Google Scholar

[3] L. Aktay, A.F. Johnson, M. Holzapfel, Prediction of impact damage on sandwich composite panels, Computational Materials Science. 32(3-4) (2005) 252-260.

DOI: 10.1016/j.commatsci.2004.09.044

Google Scholar

[4] K.W. Jeon, K.B. Shin, An experimental investigation on low-velocity impact responses of sandwich panels with the changes of impact location and the wall partition angle of honeycomb core, International Journal of Precision Engineering and Manufacturing. 13(10) (2012).

DOI: 10.1007/s12541-012-0235-8

Google Scholar

[5] R.C. Moody, A.J. Vizzini, Test and analysis of composite sandwich panels with impact damage, In: U.S. Federal Aviation Administration, Office of Aviation Research, Washington, 2002, p.6.

Google Scholar

[6] T.E. Plam, Impact resistance and residual compression strength of composite sandwich panels, In: Proc 8th bat Conf on Composite Mat. (ICCM/8), Honolulu, 1991, pp.1-13.

Google Scholar

[7] T. Gottesman, Criticality of impact damage in composite sandwich structures, In: Proc of 6th lnt Conf on Comp Mat Combined with the 2nd European Conf on Comp Mat, London, 1987, p.3. 27-3. 35.

Google Scholar

[8] J.S. Tomblin, Impact damage characterization and damage tolerance of composite sandwich airframe structures - Phase II, In: U.S. Federal Aviation Administration, Office of Aviation Research, Washington, 2002, pp.4-6.

Google Scholar

[9] K. Azouaoui, Z. Azari, G. Pluvinage, Evaluation of impact fatigue damage in glass/epoxy composite laminate, International Journal of Fatigue. 32(2) (2010) 443-452.

DOI: 10.1016/j.ijfatigue.2009.09.005

Google Scholar

[10] X.L. Fan, T.J. Wang, Q. Sun, Damage evolution of sandwich composite structure using a progressive failure analysis methodology, Procedia Engineering. 10 (2011) 530-535.

DOI: 10.1016/j.proeng.2011.04.089

Google Scholar