A numerical study on impact and compression after impact behaviour of variable angle tow laminates

Abstract

Recent developments of variable angled tow (VAT) technology have indicated that variable stiffness composite laminates offer a strong potential for structural tailoring. However, the design complexity requires use of numerical analysis and novel techniques for this type of structural composites. This paper addresses the problem of the impact and compression after impact (CAI) behavior prediction of variable stiffness composite laminates with emphasis on the effect of the interaction between fibre orientations, matrix-cracks and delaminations. An explicit finite element analysis using bilinear cohesive law-based interface elements and cohesive contacts is employed for the investigation. Examples are presented to illustrate the effectiveness of the current models for predicting the extent of impact damage and subsequent compression strength. The current study has improved the understanding of interactions between matrix-cracks and delaminations to clarify open questions on delamination initiation and how matrix cracks and fibre orientations interact.

Generalized Unified Formulation shell element for functionally graded Variable-Stiffness Composite Laminates and aeroelastic applications

“…[23] addressed the problem of impact and compression after impact of VSCLs with emphasis on the interaction between fiber orientations, matrix-crack and delaminations. The simulations were carried out using an explicit finite element analysis.…”

Delamination growth in composite laminates of variable stiffness

“…The impact behaviour of VSCL was carried out by TD Dang et al . in . They performed experimental tests and finite element simulations to investigate the effect of material orientation on the evolution of matrix cracking and delamination in impact damage.…”

Modelling VARTM process induced variations on bending performance of composite Omega beams

“…The cohesive zone method has been widely investigated for modelling composite delamination behaviour and was used for modelling fatigue delamination of composites [13], impact loading of UD laminate [14], compression after impact of UD laminate [15], soft impact of 3D woven composite [16], cantilever bending of 3D woven composites [17], and notched quasiisotropic laminate under tension [18]. Turon [19,20], Borg [21] and Harper [22] highlighted the sensitivity and the strategies in defining the cohesive properties.…”