Thermal Structure Strength Analysis of Nozzle of Solid Rocket Motor with the Coupled Algorithm

In order to achieve the thermal structural integrity analysis of solid rocket motor nozzle accurately and efficiently, multifield (flow-thermal-mechanical) coupled numerical investigation was carried out based on mesh-based parallel code interface. The simulation process finite element model algorithm engineering were obtained, while physical simplified appropriately. interface parameters, internal flow field, temperature stress field compared with results, effectiveness accuracy validated. investigations shown that both obtained by slightly lower than which algorithm. These considered be impacted Bartz empirical formula one-dimensional isentropic assumption. Further experimental exterior surface strain throat much closer further verified