Numerical modelling of the damage modes in UD thin carbon/glass hybrid laminates

Abstract

This paper proposes a new FE-based approach for modelling all of the possible damage modes in glass/carbon UD hybrid laminates in tensile loading. The damage development is modelled by two sets of cohesive elements, (i) periodically embedded in the carbon layer for modelling carbon fibre failure and (ii) at the glass/carbon interface to capture delamination. The analysis is stopped when the glass layer failure is predicted by integrating the stress distribution over the glass layer to calculate an equivalent stress for unit volume of the glass. The proposed method is validated against the experimental results and then used to simulate the progressive damage process of other hybrid configurations and finally produce a damage-mode map for this material set. The method can easily be applied to other hybrids to assess their performance by producing damage-mode maps.

Fibre hybridisation in polymer composites: A review

“…Similar to Czél et al [13] and Jalalvand et al [129], Thysen achieved multiple fractures in the LE fibre layers, which are the glass fibres in this case. This only worked when the glass/steel ratio was low.…”

“…For their specific material combination, an upper limit of 84 µm for the carbon fibre layer thickness was determined both experimentally and theoretically. Further understanding of this phenomenon was performed by Jalalvand et al [129], who developed a finite element model for these thin ply hybrid composites. This led to the development of damage mode maps with relative thickness and absolute thickness on x and y-axis (see Fig.…”

Orientation-dispersed pseudo-ductile hybrid composite laminates – A new lay-up concept to avoid free-edge delamination

“…Assuming the mechanical properties for the USN020 thin carbon layer given in Ref. [24], E 1 ¼ 101.7 GPa, E2 ¼ 6 GPa, and G12 ¼ 2.4 GPa, we can compare the stiffness of the two laminates separating the two 0 carbon layers. The modulus of the [60 C /-60 C /-60 C /60 C ] sub-laminate along the 0 direction is 5880 MPa so the stiffness of this sub-laminate is 682 N/mm (E x multiplied by the thickness).…”

“…2 a Assumed to be equal to E-glass properties used in Ref. [24]. b This value is based on [36] as the fibre in the applied USN020A prepreg was different from that in Ref.…”

“…Four different types of failure processes have been recognised for Uni-Directional (UD) hybrid composites [24,25]: 1) premature high strain material failure after the first crack in the low strain material, 2) catastrophic delamination of the low strain material from the high strain material after the first crack in the low strain material, 3) fragmentation of the low strain material and 4) fragmentation of the low strain material followed by limited dispersed delamination. The first two failure modes are unfavourable and should be avoided because they result in catastrophic failure of the composite and lead to mechanical properties lower than the constituents.…”