It is shown that the finite-element 3D model of the cohesive zone developed in the ANSYS® software for the sample in the form of DCB, delaminated according to mode I, is applicable for evaluation of crack resistance of layered reinforced polymer composite materials that are perspectiv for use in aerospace engineering. The results of numerical modeling correlate well with experimentally obtained data. Using in the model for two different in structure and composition reinforced polymer composite laminates based on carbon and glass fibers and pseudo-brittle thermoplastic matrices - polyetheretherketone and polycaproamide, the length of the cohesive zone, calculated according to experimentally determined parameters of interlayer crack resistance (intensity of elastic energy release during crack growth and local cohesive strength of the material), the minimum required size and number of interface (cohesive) elements were selected that provide a sufficiently high accuracy in the calculation of the main crack resistance parameters, while minimizing amount of computations.
$^1$Moscow State Aviation University (MAI)
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