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.