PSI - Issue 28

A.M. Al-Mukhtar / Procedia Structural Integrity 28 (2020) 124–131 Author name / Structural Integrity Procedia 00 (2019) 000–000

128

5

d)

c)

Fig.4. Crack

path from one hole grows toward the notches.

3.2. Final Fracture The current FE models are in good agreement with the experimental 2D model does not able to show the direction of the the real case study (Fig. 5b). In addition, the rupture turn into outside due to the internal pressure. fracture opening (Fig. 5a); the crack path has been

literature, see Fig. 5. However, the current

verified with

a)

b)

Fig 5. Comparison of the final failure during the biaxial loading

by performing the LEFM

4. Conclusions The process of the crack opening in the contributes to the crack propagation. The local stress increasing dramatically under the cyclic load (sequences of pressurizing and weakened after the numbers of cycles of pressurization and depressurization. The cracks appea

fuselage is highly concerned. The fracture mechanics is concentrated due to the notches. The stress concentration depressurizing). The fuselage alloys r in outer aluminum approach is are