Abstract
The paper considers the thermal stress state of the module for retaining the rocket during firing. The high-temperature gas flow leaves the cruise propulsion system and flows around the retention module. As a result, it heats up. The temperature field, which is nonstationary with large gradients, causes the elastoplastic deformation of the structure. A procedure is proposed to determine the stress-strain state, which consists of two stages. In the first stage, the temperature field of the retention module is calculated. To this end, the high-temperature supersonic flow leaving the cruise propulsion system is numerically investigated. The flow parameters are used in a semiempirical procedure, by which the temperature field in the retention module is determined. At the second stage, the stress-strain state caused by the temperature field is calculated. The elastoplastic deformation of the material is described by a bilinear deformation curve and is calculated by the finite element method, which is implemented in the ANSYS software. As a result of a numerical simulation, it has been found that the most dangerous stress state is observed in the lower part of longitudinal reinforcement, where plastic strains occur.
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