抄録
Considering the space environment, it is important to study the effects of thermal cycling on the mechanical properties in CFRP laminates. In the present study, thermal cycling induced matrix cracking in CFRP laminates is investigated experimentally. Two kinds of carbon/epoxy systems, T800H/3631 and T300/2500, are used. Laminate configurations are (0/90)_s and (90/0)_s for both material systems. The specimens are thermally cycled between -196℃ and 100℃. Thermal cycling tests are performed up to 1000 cycles. In T800H/3631 (0/90)_s, (90/0)_s and T300/2500 (0/90)_s, (90/0)_s laminates, matrix cracking is observed in 90°ply by thermal cycling. Tensile tests after thermal cycling are also performed. The effect of thermal cycling on matrix cracking under tension is evaluated by the change in the critical energy release rate and the critical stress.
