Comparison of the characteristics of modern aluminum alloys

The results of experimental studies of the static strength, fatigue and crack resistance of modern improved aluminum alloys 1163ATV, 1163RDTV, 1441RT1, 1163T, 1163T7, 1161T, V95ochT2, B96-3pchT12., 1973T2 developed at the All-Russian Scientific Research Institute for Aviation Materials (VIAM, Russia); and 2524-T3, 6013-T6 HDT, 2324-T39, C433-T351, 7055-T7751 developed at ALCOA (USA) are presented. Those materials are used in the construction of modern operated and designed aircraft. The experimental data were obtained in testing standard specimens on electro-hydraulic machines MTS (USA), Instron (Great Britain) and Schenk (FRG). The tested specimens were cut from semi-products manufactured according to serial technologies. The mechanical properties of materials under tension (σ_b, σ_0.2, δ), fatigue characteristics, fatigue crack growth rate, stress crack propagation curves under static loading (R-curves), conditionally critical stress intensity factors are determined according to domestic standards. To ensure high weight efficiency combined with a high resource and high performance characteristics of the aircraft structures, aluminum alloys must have the following set of necessary characteristics: high resistance to variable loads, low rate of fatigue cracks growth, required residual strength, and good corrosion resistance. The obtained results of experimental studies clearly demonstrate the advantages and disadvantages of the strength properties of the materials under study. The results of experimental studies provide the possibility to compare the strength properties of the materials under study to optimize their use for the specific zone of the structure and thus increase the life and safety of the aircraft design.

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