Flight simulation fatigue crack propagation tests were carried out on 2024-T3, 7475-T761, and mill annealed Ti-6Al-4V sheet in thicknesses up to 3 mm. These materials are representative of transport aircraft lower wing skin stiffened panels of end load capacities 1.5 and 3 MN/m. Results show that the performance of 2024-T3 is much superior, owing mainly to greater retardation of crack growth after severe flights. The effect of load truncation is also greater for 2024-T3. The significance of the results in the choice of advanced structural concepts and materials as well as in the choice of truncation level is discussed. A recommendation for further investigation is given.
Flight Simulation Fatigue Crack Propagation Evaluation of Candidate Lower Wing Skin Materials with Particular Consideration of Spectrum Truncation
1979
34 pages
Report
Keine Angabe
Englisch
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