2007 by Taykr&Francis Group. TABLE 4.3 Tensile Test Data and Failure Modes of Several Symmetric Carbon Fiber-Reinforced Epoxy Laminates Secant Modulus Transverse at Low Failure Stress, Failure Ply Strain Laminate Type Strain,GPa MPa Strain Cracking Failure Modes (in Sequence) [04/90Ls 122 1620 0.0116 0.0065 Small transverse ply cracks in 90 plies,transverse cracks growing [04/902s 109 1340 0.011 0.004 in number as well as in length up to 0 plies,delamination at 0/90 04/90小s 1230 0.0114 0.0035 interfaces,0 ply failure 104/90sls 2 930 0.0115 0.003 [±45s 17.3 126 0.017 Edge crack formation,edge cracks growing across the width parallel [+452/-452小s 19 135 0.0117 to fiber direction,delamination at the +45/-45 interfaces,single [+453/-45s 14 89 0.01 or multiple ply failure [+45/-452/4s 18.2 152 0.016 [(+45/-452s 17 125 0.014 [±45/902/02ls 64.2 690 0.014 0.0028 Transverse microcracks in 90 plies,longitudinal or angled cracks [±45/02/902ks 61.2 630 0.014 0.0022 in 90 plies in the first three laminates,a few edge cracks in 45 plies. 02/±45/902s 56.4 640 0.012 0.0016 delamination(45/90,0/90,+45,and 45/0 interfaces in ascending 02/902/士±45s 59.1 670 0.012 0.0035 order of threshold strain),longitudinal ply failure Source:Adapted from Harrison,R.P.and Bader,M.G.,Fibre Sci.Technol.,18.163,1983.TABLE 4.3 Tensile Test Data and Failure Modes of Several Symmetric Carbon Fiber-Reinforced Epoxy Laminates Laminate Type Secant Modulus at Low Strain, GPa Failure Stress, MPa Failure Strain Transverse Ply Strain Cracking Failure Modes (in Sequence) [04=90]S [04=902]S [04=904]S [04=908]S 122 109 93 72 1620 1340 1230 930 0.0116 0.011 0.0114 0.0115 0.0065 0.004 0.0035 0.003 Small transverse ply cracks in 908 plies, transverse cracks growing in number as well as in length up to 08 plies, delamination at 0=90 interfaces, 08 ply failure [±45]S [þ452=452]S [þ453=453]S [þ45=452=45]S [(þ45=45)2]S 17.3 19 14 18.2 17 126 135 89 152 125 0.017 0.0117 0.01 0.016 0.014 — — — — — Edge crack formation, edge cracks growing across the width parallel to fiber direction, delamination at the þ45=45 interfaces, single or multiple ply failure [±45=902=02]S [±45=02=902]S [02=±45=902]S [02=902=±45]S 64.2 61.2 56.4 59.1 690 630 640 670 0.014 0.014 0.012 0.012 0.0028 0.0022 0.0016 0.0035 Transverse microcracks in 908 plies, longitudinal or angled cracks in 908 plies in the first three laminates, a few edge cracks in 458 plies, delamination (45=90, 0=90, ±45, and 45=0 interfaces in ascending order of threshold strain), longitudinal ply failure Source: Adapted from Harrison, R.P. and Bader, M.G., Fibre Sci. Technol., 18, 163, 1983.
2007 by Taylor & Francis Group, LLC.