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 2a ≈ 610 mm, maximum mode I stress intensity factors of 160 MPa√m 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.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
