Abstract
Aviation construction subjected to cyclic load, in consequence of which, near stress concentrators (rivet holes), emerge and develop fatigue cracks. The development of fatigue crack reduces the residual strength of the structure and further, its destruction. This work describes the selection of the sample to assess multi-site damage. Technique drilling rivet holes. Mounting the sample on the test machine. Processing of the results of the experiment. The data for crack growth in the aviation alloy D16AT. The coefficients C and n equations Paris Law that characterize properties of the material. The dependence of the crack growth rate of the stress intensity factor (SIF). The rate of crack growth and the number of cycles until a crack of specified length. According to experimental data obtained prediction of fatigue cracks. о� ����� �Ĺ �о экспериментальным данным получен прогноз развития усталостных трещин.
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