1.19.4 Dynamic shear failure of a single-edge notch simulated using XFEM

Product: Abaqus/Standard  

Problem description

This example verifies and illustrates the use of the extended finite element method (XFEM) in Abaqus/Standard to predict dynamic crack propagation of a plate with an edge crack. The specimen is subjected to a high rate shear impact loading. The crack paths and crack initiation angles presented are compared to the experimental results of Kalthoff and Winkler (1987).

Geometry and model

A plate with a single edge crack is studied. The specimen, shown in Figure 1.19.4–1, has dimensions L = 0.003 m and W = 0.0015 m and an initial crack with length a = 0.0015 m. The lower part of the specimen is subjected to an impulse load along the horizontal direction, which is modeled as a prescribed velocity:

where = 25 m/s and = 1.0 × 10–7 s.

Material

The material data for the bulk material properties in the enriched elements are = 3.24 GPa, = 1190  kg/m3, and = 0.35.

The response of cohesive behavior in the enriched elements in the model is specified. The maximum principal stress failure criterion is selected for damage initiation, and an energy-based damage evolution law based on a power law fracture criterion is selected for damage propagation. The relevant material data are as follows: = 100.0 MPa, = 700 N/m, = 700 N/m, = 700 N/m, = 1.0, = 1.0, and = 1.0.

Results and discussion

Figure 1.19.4–2 shows the crack profile when = 6.0 × 10–6 s. The crack propagates at an angle of 62°, which is in reasonable agreement with the experimental result of 65°.

Input file

crackprop_shear_xfem_3d_dyn.inp

Three-dimensional brick model with reduced integration under shear impact loading.

Python script

Reference

  • Kalthoff,  J. K., and S. Winkler, Failure Mode Transition at High Rates of Loading,Proceedings of the International Conference on Impact Loading and Dynamic Behavior of Materials 185–195, 1987.

  • Figures

    Figure 1.19.4–1 Model geometry of the plate with an edge crack subjected to shear impact loading.

    Figure 1.19.4–2 Crack profile at = 6.0 × 10–6 s.