Z.M. Huang/ Composites Science and Technology 64(2004)529-548 situ resin compressive strength for this lamina. As men- strengths were retrieved from its longitudinal an tioned earlier, the fiber and resin tensile strengths were transverse compressive strengths respectively. The used retrieved from the longitudinal tensile strengths of the resin tensile strength, 56. 5MPa, was higher than the D lamina, whereas the fiber and resin compressive resin tensile strength, 33 1 MPa, retrieved from the theory (initial failure, with thermal theory(final failure, with thermal 1000o Test results(final failure s theory(final failure, without I effect a200 8 600 1000 1400 y-direction stress(MPa) Fig. 6. Measured and predicted biaxial failure stresses for (90/+45/0] laminate subjected to combined orr and oxx. Material type: AS4/ 3501-6 1000 o Theory (y-strain, without thermal residual stresses) a Theory (x-strain, without thermal residual stresses Test results (y-strain) Test results(x-strain 800 theory (y-strain, with thermal residual stresses) Theory(x-strain, with thermal residual stresses) 折 (Predictions without thermal effect) 1 ply failure information SS=4463MPa, plies=(o), mode=MT SS=508MPa, plies=(45), mode=MT 3rd ply failure inforI SS=659MPa, plies=(90), mode=FT 0 Strain (% redicted oyy vs Eyy and oyy vS Exr curves for[900/=45 /0], laminate under uniaxial tension(oy/ oxx=1/0). Material type AS4/3501-6 Only the failure information without thermal effect is shown, in which"TT"=strength. ""MT"=resin tensile failure, and"FT"=fibersitu resin compressive strength for this lamina. As men￾tioned earlier, the fiber and resin tensile strengths were retrieved from the longitudinal tensile strengths of the UD lamina, whereas the fiber and resin compressive strengths were retrieved from its longitudinal and transverse compressive strengths respectively. The used resin tensile strength, 56.5MPa, was higher than the resin tensile strength, 33.1 MPa, retrieved from the Fig. 6. Measured and predicted biaxial failure stresses for [90
/45
/0
]s laminate subjected to combined
yy and
xx. Material type: AS4/3501-6. Fig. 7. Measured and predicted
yy vs. "yy and
yy vs. "xx curves for [90
/45
/0
]s laminate under uniaxial tension
yy=
xx ¼ 1=0
. Material type: AS4/3501-6. Onlythe failure information without thermal effect is shown, in which ‘‘TT’’ =strength, ‘‘MT’’=resin tensile failure, and ‘‘FT’’=fiber tensile failure. Z.-M. Huang / Composites Science and Technology 64 (2004) 529–548 533