Abstract
The influence of different stress levels on the fatigue life and fracture behavior of laminated composites have been evaluated under compression-compression (C–C) loading conditions. Carbon/epoxy multidirectional (MD) laminate specimen was designed with eight layers [0°, ± 45°, 0°]s of unidirectional plies. The preforms were molded by a high-pressure resin transfer molding (HP-RTM) process. As part of the study, a static compression test was performed. The C–C fatigue loads were applied at −260 MPa, −280 MPa, −300 MPa, and −320 MP compression stress until failure or two million cycle loadings. The fatigue limit has been obtained at −265 MPa stress by stress-cycle number (S-N) curve analysis, which is 51.4 % of static compression strength. The damage behavior was identified after C–C fatigue tests. By using optical and scanning electron microscopy, fiber fracture, matrix cracking, and fiber/matrix interface debonding were observed. Under the C–C fatigue loading conditions, fiber fracture modes were characterized by rough cross-sections, shear, and line-shaped edges.
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