Testing and modelling of tension after impact of a thin ply textile composite

• This paper presents an experimental and numerical study of impact response, damage and tension after impact of thin ply HTS45/RTM6 carbon/epoxy laminates, manufactured via resin transfer moulding. A plain weave from carbon fibre spread-tow bands was used in a quasi-isotropic layup. Finite element simulations were performed using layered shell elements accounting for in-plane damage mechanics, with cohesive surfaces between a few layers of shell elements to account for delamination. The damage was found to include a combination of fibre damage and delaminations, in contrast to a previous study on similar cross-ply laminates, where fibre damage dominated. The rate of decrease in tensile strength after impact was similar to prepreg laminates with conventional ply thickness, but the impacted strength was slightly higher due to a higher undamaged strength for thin ply laminates.

Nyckelord

Damage tolerance

Finite element model

Impact

Testing

Thin plies

Carbon fibers

Composite materials

Delamination

Finite element method

Laminated composites

Laminates

Paper laminates

Resin transfer molding

Tensile strength

Weaving

Carbon/epoxy laminates

Cross-ply laminate

Experimental and numerical studies

Finite element simulations

Layered shell element

Prepreg laminates

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