Issue 17

V. Crupi et alii, Frattura ed Integrità Strutturale, 17 (2011) 32-41; DOI: 10.3221/IGF-ESIS.17.04 36 Figure 4 : CT analysis of an honeycomb panel ( d =3 mm). Figure 5 : CT analysis of an AFS Schunk panel. Figure 6 : CT analysis of a polymeric sandwich composite. Figure 7 : CT analysis of a laminated composite. The impact damage mechanisms of composites with Kevlar fiber layers are distinctly different from those of GFRP. X-ray CT images of two laminated specimens subjected to 126 J impact energy are shown in Fig. 8. In particular, the images show a comparison between a fiber-glass laminated composite (upper images of Fig. 8) and a hybrid Kevlar/fiber-glass