A Plane-Stress Damage Model for Vectran Laminated Composite

Abstract The aim of this paper is to present a plane-stress damage model based on the Classical Lamination Theory (CLT), developed for polymer fibre-based composite. proposed numerical utilises mechanics methodology coupled with fracture predict composite failure, particularly under quasi-static and dynamic loadings. In addition, constitutive equations consider single secant modulus describe its tensile compressive modulus, as opposed physically-proposed tier models fibres which possesses ‘skin–core’ structure. result element coupon-level modelling showed excellent correlation experimental results. It expected that will be able predict, up considerable accuracy, response low high velocity impact