896 C Dong, L Davies/Materials and Design 54 (2014)893-899 0 -0.375 r0.750.875 lass/epoxy Carbon/ 60 Fig. 5. A hybrid composite specimen in three point bending. Span-to-depth ratio Table 2 ig. 8. Effect of span-to-depth ratio on flexural modulus Levels used in 3 factorial design. Low Vh(i 50 -0--Tensilc 60 [OscI [02G/06c] 0c/0c 0c0c] [0s/0c] 00c] 0.8 Fig. 6. Stacking configurations of carbon fibre(C)and glass fibre(G) plies. Hybrid ratio Fig. 9. Flexural modulus at S/h=64 and tensile modulus versus hybrid ratio for 120 FEA .O--CLT 0.8 Hybrid ratio Fig. 7. Comparison of FEA and CLT for the flexural moduli at S/h=64 when Vee=50% It is shown from Eq(7)that the hybrid ratios for the full carbon/ V-30% and V =50 us at Sh=64 and tensile modulus versus hybrid ratio for Fig. 10. Flexural mod m-1%,画%+E(--)It is shown from Eq. (7) that the hybrid ratios for the full carbon/ epoxy and full glass/epoxy laminates are 0 and 1, respectively. The tensile modulus can be obtained using the rule of mixtures (ROM) as: ET ¼ hfc h EfcVfc þ hfg h EfgVfg þ Em 1 hfc h Vfc hfg h Vfg ð8Þ Fig. 5. A hybrid composite specimen in three point bending. Table 2 Levels used in 32 factorial design. Low Middle High Vfc (%) 30 50 70 Vfg (%) 30 50 70 Fig. 6. Stacking configurations of carbon fibre (C) and glass fibre (G) plies. Fig. 7. Comparison of FEA and CLT for the flexural moduli at S/h = 64 when Vfc = 50% and Vfg = 50%. Fig. 8. Effect of span-to-depth ratio on flexural modulus. Fig. 9. Flexural modulus at S/h = 64 and tensile modulus versus hybrid ratio for Vfc = 30% and Vfg = 30%. Fig. 10. Flexural modulus at S/h = 64 and tensile modulus versus hybrid ratio for Vfc = 30% and Vfg = 50%. 896 C. Dong, I.J. Davies / Materials and Design 54 (2014) 893–899