PSI - Issue 5

Jan Raška et al. / Procedia Structural Integrity 5 (2017) 225–232 Jan Raška / Structural Integrity Procedia 00 (2017) 000 – 000

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Fig. 8. File organization structure [3]

Fig. 9. Final result functions: stress intensity factor vs. crack length [3]

4. Application

An example of the software application is demonstrated on the figure 10. The shown structure is the real airplane wing box section, compound of spars, ribs, panels and others pieces.

Fig. 10. Application structure

The crack initiation is supposed on the edge of the intrados integrated panel (it means on the skin, integrated with the stringers), and the crack is growing across the profile – see figure 11. On the same figure, the resulting function – stress intensity factor K I vs. crack length is represented. As for the peaks and valleys that can be seen on the graph, it is correlated with the passage of the crack through the stringers across the panel. Another applications are realized in [10] and [11].