The present work is focused on experimental study of the kinetics of damage accumulation in aircraft alloy D16T and steel 15HSND for symmetric cycle (stress-controlled test). The evaluation of the material damage on the basis of an analysis of the elasticity modulus variation for different values of the loading cycle amplitudes was carried out. Experimental damage accumulation curves were obtained. The "healing parameter" for given loading regime of the materials under study was determined. This parameter can be used for an approximate estimation of the total damage value for the full loading cycle. The concept of initial and critical damage parameter is considered and analytical dependencies for their determination were presented. A method for durability calculation, based on the results of the carried out studies, was proposed. The error of this method in relation to the experimental data was estimated.
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