Results and Discussions for Case Studies
In this study, we will evaluate and compare the effectiveness of three
aerostructure repair techniques using the simulation framework BRSW
proposed in Section 2. Specifically, the comparisons are pertinent to
prediction of fatigue damage evolution, crack initiation and propagation
with service life estimation. The geometry under consideration is a
cracked aircraft pressured fuselage repair. The setup and conditions are
the same as in Ref. [20]. Without losing generality, the crack in
damaged skin structure is placed in an arbitrary angle, as shown in
Figure 5, even though cracks usually develop along rivet lines.