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 those used in transport aircraft lower wing skin stiffened panels with end load capacitied of 1.5 and 3 MN/m. The performance of 2024-T3 was much superior to the others, owing mainly to greater retardation of crack growth after severe flights. The effect of load truncation was also greater for 2024-T3. The significance of the results of the choice of advanced structural concepts and materials, and the choice of truncation level is discussed. A recommendation for further investigation is given.
Gust Spectrum Fatigue Crack Propagation in Candidate Skin Materials
1978
32 pages
Report
No indication
English
Aircraft , Nonferrous Metals & Alloys , Airframe materials , Crack propagation , Fatigue (Materials) , Skin (Structural member) , Aluminum alloys , Titanium alloys , Gust loads , Fatigue tests , Structural design criteria , Wing panels , Aluminum alloy 2024 , Aluminum alloy 7475 , Titanium alloy 6Al 4V , Aircraft panels