PSI - Issue 35

Jarmil Vlach et al. / Procedia Structural Integrity 35 (2022) 132–140 Author name / Structural Integrity Procedia 00 (2019) 000 – 000

137

6

5. Impact test 5.1. Model description

After calibration, the FE model was prepared as prescribed by ASTM D7316. The model of test specimens was created by the ply-by- ply method as reported by Šedek and Bělský (2017). The laminate layers were joined by cohesive contact. The elasticity parameters for the fibre volume fraction of 53.3 % are given in Table 3. Regarding the elastic properties and the speed of calculation in relation to accuracy, an element size of 1.5 mm was chosen. The strength and failure parameters of the laminate are shown in Table 4 and 5. The strength characteristics of the cohesive contact, which consider the angle at which the adjacent layers intersect, are shown in Table 6. The parameters for the development of layer debonding are shown in Table 7. The impact simulation was performed for 11.06 J energy at speed 10 m/s. A visual representation of the impact tests and the result of the calculation is shown in Fig. 5.

a

b

c

Fig. 5. Damage caused by impact, (a) Photography; (b) C-Scan; (c) ABAQUS/Explicit simulation.

The size of debonded zones of the layers after the impact is shown in Fig. 6a and Fig. 6b. On the left side the finite elements with released surfaces are displayed. On the right side the real sample after impact is shown. The mean value of the deflection rate of the sample under the impactor is shown in Table 5.

a

b

Fig. 6. Debonded zones, (a) Horizontal cross-section; (b) Vertical cross-section.