Numerical Simulation of Low Velocity Impact on Pin-Reinforced Foam Core Sandwich Panel

Abstract

The use of sandwich structures is well established in industrial sectors where high stiffness and strength combined with lightweight are required, like in marine, wind turbine and railway applications. However, the vulnerability of sandwich structures to low-velocity impacts limits its use in primary aircraft structures. Pin reinforcement of the foam core enhances the out-of-plane properties and the damage tolerance of the foam core. In this paper, a finite element model is proposed to predict the impact behaviour of pin-reinforced sandwich structure. An approach based on the building block approach was used to develop the model. Multi-scale modelling in the impact region that considers the delamination of the face sheet using cohesive zone elements was employed to increase the accuracy of the simulation. Impact tests were performed to validate the numerical model. A good agreement between numerical and experimental results in terms of contact-force displacement history and failure mode was found.

Mechanical Behaviour of Pin-Reinforced Foam Core Sandwich Panels Subjected to Low Impact Loading

“…The main application of composite sandwich panels is in structures that are under low or high impact loading regarding lightweight design. In other words, composite sandwich panels should be designed for impact-resistant applications [17]. Therefore, understanding the dynamic behaviour and responses of a composite structure in the form of sandwich panels, and the prediction of mechanical strength is important to generate an optimum sandwich panel.…”

“…Numerical models and especially finite element model is a reliable tool to evaluate the structural integrity of the sandwich panel. Damage initiation, damage propagation, and failure are three stages of damage [17,22,23] that can be observed in a sandwich panel under low impact loading. To evaluate the foam core sandwich (FCS) structures many FE models have been reported by previous research [19,24,25].…”