Abstract
This article describes a method for choosing the shape of structurally-similar elements made of polymer composite ma-terials and the scheme of their loading during fatigue tests. These tests are an important step of the complex of efforts to prevent fatigue failure of aviation critical structures made of polymer composite materials. The shape of structurally- similar elements and the loading scheme must be substantiated by a series of preliminary calculations. When testing such samples, the deformation field in the critical zone of the part must be re-produced. The ability to achieve fatigue failure of specimens on the selected equipment shall be verified. The application of the proposed approach to the justification of the choice of structure and loading of structurally similar elements is demonstrated on the example of a typical aircraft structure.
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