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. The specimens are representative of transport aircraft lower wing skin stiffened panels with end load capacities of 1.5 and 3 MN/m. Results prove that sheet thickness has a significant effect on crack propagation. Thinner gage materials exhibited slower crack propagation mainly because of greater retardation of crack growth after severe flights. The relevance of the results for the choice of advanced structural concepts and materials is discussed and a recommendation for further investigation is given.
The Effect of Sheet Thickness on Flight Simulation Fatigue Crack Propagation in 2024-T3, 7475-T761, and Mill Annealed Ti-6Al-4V
1979
28 pages
Report
No indication
English
ALUMINUM ALLOY SHEET 5.7Zn - 2.2Mg - 1.6Cu - 0.22Cr (7475-T761)
SAE Technical Papers | 1976
ALUMINUM ALLOY SHEET 5.7Zn - 2.2Mg - 1.6Cu - 0.22Cr (7475-T761)
SAE Technical Papers | 1978
ALUMINUM ALLOY SHEET, ALCLAD 5.7Zn - 2.2Mg - 1.6Cu - 0.22Cr (7475-T761)
SAE Technical Papers | 1979