The out-of-plane displacement fields for a cross-ply laminate [03/903]s with impact damage under axial compression are investigated using carrier electronic speckle pattern interferometry (carrier-ESPI) in this paper. The compression after impact (CAI) test is conducted on rectangular specimen 65mm × 87.5mm in size using an anti-buckling fixture. In order to apply a uniform load to the top of composite laminate, a self-designed device insures that an accurate loading is given. The experimental results reveal the deformation characteristics of laminate under CAI test.
References
1.
FinnS.R., HeY.F., and SpringerG.S., Composite Structures, 23 (1993) 191–204.
2.
SanchezS.S., BarberoE., ZaeraR., and NavarroC., Composites Science and Technology, 65 (2005) 1911–1919.
3.
AslanZ., and SahinM., Composite Structures, 90 (2009) 382–390.
4.
AndrewT.R., DavidM., and RichardB., Composites Part A, 42 (2010) 1056–1065.
5.
LeifE.A., NilssonS., and SunilS., Composites Part A, 32 (2001) 1229–1235.
6.
NaikN.K., and RamasimhaR., Composite Structure, 52 (2001) 199–204.
7.
CairnsD.S., MinguetP.J., and AbdallahM.G., Composite Structures, 24 (1994) 431–437.
8.
FedericoB., JohnB., MauroF., and PhilippeG., Composite Science and Technology, 62 (2002) 41–54.
9.
SunP., Optics Communications, 275 (2007) 305–310.
10.
AymerichF., and PrioloP., International Journal of Impact Engineering, 35 (2008) 591–608.
