Determination of breaking load of plates with hole

Determining the failure load of aircraft components is a critical aspect of aircraft design and operation. Flight safety, component durability and economic efficiency of operation directly depend on the strength characteristics of materials and structures. In this connection, the problem of numerical and analytical calculation of destructive load is considered. The program implementing the algorithm of destructive load determination using the finite element method in Ansys package has been developed. Validation of the algorithm is performed on plates with a circular hole. Homogeneous plates made of D 16T and B 95 alloys, as well as combined specimens consisting of two plates, one of which is made of D 16T alloy and the other of B 95 alloy, were investigated. In the combined specimens, in the tensile region where the plates are in contact, it is assumed that the friction occurring between their surfaces has little effect on the solution results, i.e., there is no assignment of any contact conditions. In the gripping region,the plates are strongly pressed against each other and rigidly fixed in the gripping devices. The elastic-plastic parameters of the materials determined from tensile tests of smooth specimens without holes are used in the calculations. A satisfactory agreement between the experimental data and the calculation results is obtained