Abstract
Transverse cracking under tensile loading in Carbon/BMI (bismaleimide), G40-800/5260, and Carbon/Epoxy, T800H/3900-2, composite laminates with toughened-interlaminar layers is investigated experimentally. Laminate configurations used are [0/90]s, [0/902]s, [±45/90]s and [±45/902]s for G40-800/5260, while [0/90]s and [±45/90]s for T800H/3900-2. Damage mechanics analysis is used to predict transverse cracking based on both the energy and stress criteria. The present analysis can be used as a characterization method of transverse cracking resistance of a material, which will be helpful in ranking materials.
