Damage Tolerance of Metallic Aircraft Structures by Sérgio M. O. Tavares & Paulo M. S. T. de Castro

Author:Sérgio M. O. Tavares & Paulo M. S. T. de Castro
Language: eng
Format: epub
ISBN: 9783319701905
Publisher: Springer International Publishing

5.2.1 Structural Analyses

As an example of the need for analyses of increasing complexity, bulging effects in cracked fuselage are now mentioned. A basic study of the longitudinal through crack in a circular cylindrical vessel subjected to internal pressure is shown in Fig. 5.4a, where ABAQUS FEM is compared with solutions from Anderson [35], Tada et al. [36], Folias [37], and Zahoor [38]. Consideration of a cracked hole leads to the analysis documented in Fig. 5.4b with the notation a—physical length of crack, D—hole diameter, using the relationships and .

Fig. 5.4SIF for cracked pressurized cylinder, a through crack in axial direction, b circular hole with through crack in axial direction, c deformed shape and bulging effect of a cracked cylinder

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