Numerical simulation of thermal elastic behavior of the output unit of SPRE with account of influence of mass velocity of composite material carry-over

Abstract

Reliability and energy mass perfection of solid propellant rocket engine (SPRE) is largely determined by the correct choice of materials and design of a thermal barrier coating. To adequately evaluate the results of fault detection of a thermal barrier coating after firing test bench, you need to be able to "restore" the depth of the thermal degradation of the coating corresponding to the end of the solid propellant. Basic requirements for coatings are reduction of the temperature conductivity coefficient, increase of erosion resistance, increase of safety margins of bearing structural parts of SPRE. In this connection there is an urgent task of the thermal elastic behavior of the nozzle of SPRE with the influence of the mass-loss velocity of composites. The aim of this work is to develop a computational algorithm that can adequately simulate the thermal elastic behavior of the nozzle block in unsteady gas dynamic and high-loading taking into account the effect of chemical ablation of composite materials.