Analysis of adiabatic shearing failure mechanism for aluminum matrix composites based on experimental and numerical simulation

Abstract

Adiabatic shear behavior and the corresponding mechanism of TiB₂/Al composites were researched by split Hopkinson pressure bar (SHPB). Results show that the flow stresses of the TiB₂/Al composites exhibit softening tendency with the increasing of strain rates. All the composites fail in splitting and cutting with a 45 degree, and the phase transformed bands of molten aluminum are found on the adiabatic shear layers. The deformation behavior and shear localization of the TiB₂/Al composites specimens were simulated by finite element code MSC. Marc. The Johnson-Cook model was used to describe the thermo-viscoplastic response of the specimen material. There was unanimous between the numerical result and the experimental result on the location of the adiabatic shear band. From the numerical simulation and experiment, it was concluded that the instantaneous failure of the composite was ascribed due to the local low strength area where the formation of adiabatic shear band was, and the stress condition had significant effect on the initiation and propagation of adiabatic shear band (ASB).

Keywords

metal matrix composites / split Hopkinson pressure bar / high strain-rate / adiabatic shear band / Johnson-Cook model

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