| Article ID | Journal | Published Year | Pages | File Type |
|---|---|---|---|---|
| 7171609 | International Journal of Fatigue | 2018 | 23 Pages |
Abstract
Based on biaxial tests with cruciform specimens, the scenario of fatigue cracks in the upper fuselage section between the wings and the tail unit of a commercial single aisle aircraft has been studied. Two different types of specimen were designed, namely for the scenario of a circumferential crack across a broken stringer and for a longitudinal crack parallel to the stringers. With crack length up to 2aâ¯ââ¯610â¯mm, maximum mode I stress intensity factors of 160â¯MPaâm were obtained for the commercial aluminum alloys AA2024-T351 and AA5028-H116. All experiments were supported by digital image correlation to obtain the actual deformation fields of the specimens. Based on these data stress intensity factors and J integrals were computed with a line integral procedure. Furthermore, plastic zone and crack closure effects were studied.
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Authors
Eric Breitbarth, Michael Besel, Stefan Reh,