Fatigue Behavior of Hat Section Stringer Stiffened Panels Compressed in the Post-Buckling Range.
Final technical rept. Apr 71-Mar 72,
PISA UNIV (ITALY) INST OF AERONAUTICS
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This report includes the analytical and experimental research results of work conducted during the period of performance of the contract. Panels which were constructed using current aircraft construction techniques were subjected to compressive loads until buckling occurred. Both static and dynamic tests were performed. Strain gauge measurements were made on 29 panels constructed of 2024-T3 or 7075-T6 aluminum to determine the maximum allowable load and then to assess the fatigue damage on each panel. A statistical analysis of the static test results was made to determine the distribution of the maximum tensile stresses measured. Author