Fatigue Behaviour of Hat Section Stringer Stiffened Panels Compressed in the Post-Buckling Range.
Final technical rept.,
PISA UNIV (ITALY) INST OF AERONAUTICS
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The report presents results of research on the fatigue behaviour of riveted hat section stringer stiffened panels which buckle under constant amplitude fatigue loading. Panels made with 2024-T3 as well as 7075-T6 Aluminum alloys were tested, and cracks were found to develop systematically in the stringer top plate along the rivet lines. It was demonstrated that the tensile bending stresses which take place in the stringer when the sheet cover buckles are responsible for crack initiation. The fatigue cracked panels were statically tested. Results are discussed.
- Metallurgy and Metallography