NUMERICAL AND EXPERIMENTAL RESEARCH IN TO CONTACT STRESS OF STRUCTURAL ELEMENTS IN SPRM
The strength of the "flange-cover" structure of a solid propellant rocket engine (SPRM) was determined numerically using the finite element method and telemetry data. Its performance has been experimentally confirmed. The results of numerical modeling of the contact elastic-plastic boundary value problem and visualization of the readings of the measuring equipment in terms of the stress-strain state of this structure are presented. In accordance with the results of the computational experiment and telemetry data after the autonomous tests (AT), the optimization of the overall mass characteristics of structural elements in solid propellant rocket motors was carried out.