In order to accurately predict the typical burner nozzle in solid rocket engine working process of the whole structure of the temperature field and stress field distribution, established include thermal barrier and throat lining chamber nozzle integration model. Through Fluent fluid analysis software and ANSYS structural analysis software, the unsteady flow thermo-solid coupling numerical calculation was carried out. The simulation results show that solid rocket engine working process, as a result of the existence of thermal barrier, combustion chamber shell temperature rise is slow, upstream maximum heat flux density in the throat, throat area of convective heat transfer is most serious. Thermal stress peaks at the nozzle convergence and increases with time.