Thermal Delamination Modelling and Evaluation of Aluminium-Glass Fibre-Reinforced Polymer Hybrid.

Zhen Pei Chow,Seyed Saeid Rahimian Koloor,Zaini Ahmad,King Jye Wong,Michal Petrů

doi:10.3390/polym13040492

Zhen Pei Chow, Seyed Saeid Rahimian Koloor + Show 3 more

Open Access

https://doi.org/10.3390/polym13040492

Copy DOI

Abstract

This paper aims to propose a temperature-dependent cohesive model to predict the delamination of dissimilar metal–composite material hybrid under Mode-I and Mode-II delamination. Commercial nonlinear finite element (FE) code LS-DYNA was used to simulate the material and cohesive model of hybrid aluminium–glass fibre-reinforced polymer (GFRP) laminate. For an accurate representation of the Mode-I and Mode-II delamination between aluminium and GFRP laminates, cohesive zone modelling with bilinear traction separation law was implemented. Cohesive zone properties at different temperatures were obtained by applying trends of experimental results from double cantilever beam and end notched flexural tests. Results from experimental tests were compared with simulation results at 30, 70 and 110 °C to verify the validity of the model. Mode-I and Mode-II FE models compared to experimental tests show a good correlation of 5.73% and 7.26% discrepancy, respectively. Crack front stress distribution at 30 °C is characterised by a smooth gradual decrease in Mode-I stress from the centre to the edge of the specimen. At 70 °C, the entire crack front reaches the maximum Mode-I stress with the exception of much lower stress build-up at the specimen’s edge. On the other hand, the Mode-II stress increases progressively from the centre to the edge at 30 °C. At 70 °C, uniform low stress is built up along the crack front with the exception of significantly higher stress concentrated only at the free edge. At 110 °C, the stress distribution for both modes transforms back to the similar profile, as observed in the 30 °C case.

Highlights

Fibre metal laminates (FMLs) are increasingly used in aeronautical and marine applications for their combination of advantages from two different materials
Slopes and peak load between experimental and simulation results are compared to demonstrate the feasibility of models by percentage agreements
Separate temperature-adjusted material models are applied for the aluminium, effects delamination aluminium and aAfter

Summary

Introduction

Fibre metal laminates (FMLs) are increasingly used in aeronautical and marine applications for their combination of advantages from two different materials. FMLs involve adhesively bonding alternating metal and composite layers to form a laminated sandwich structure. The hybrid nature of the FML allows beneficial properties from both metal and composite counterparts, including lighter weight, ductility, fatigue resistance and damage tolerance [1,2,3]. The multiple layers of the FML structure prevent crack propagation from damaged layers to subsequent layers via crack bridging and prevent catastrophic failure that would otherwise occur unimpeded in monolithic materials. Multiple alternating laminates are capable of suppressing the spread of thermal and moisture absorption across the layers that allow potential applications of FMLs in

Objectives

Results

Conclusion