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Thermal strength of retention compartment interacting with exhaust gas

The thermal strength of the retention compartment is calculated to analyze the possibility of multiple use for a rocket start. The transient heat field of the retention compartment, which is induced by the interaction of the exhaust gas with the retention compartment, is analyzed. The part of the retention compartment undergoes significant heat action with a high-temperature gradient when the rocket is started. This heat action essentially changes in time. This leads to the generation of significant transient stress fields. The aim of the present paper is the calculation of the maximal values of stresses induced by the heat field. We analyze the stress state induced by the steady-state heat field. This field corresponds to the transient heat field at the time when the maximal temperature gradient is observed. The upper bound of stresses in the retention compartment is obtained by the suggested method.