摘要
A time-resolved numerical computational approach, involving the combustion of double-base propellant is performed on thermal protection material for SRM nozzle. An implicit Navier-Stokes Solver is selected to simulate two-dimensional axial-symmetric unsteady turbulent flow of compressible fluid. The governing equations are discredited by using the finite Volume method. S-A turbulence model is employed. CFD scheme is implemented to investigate the temperature distribution causes at nozzle throat inserts composite material. Different parameters have been selected for the analysis to validate the temperature variation in the throat inserts and baking material of SRM nozzle. The advanced SRM nozzle composite material is also characterized for the high thermo stability and high thermo mechanical capabilities to make it more reliable, simpler and lighter.
A time-resolved numerical computational approach, involving the combustion of double-base propellant is performed on thermal protection material for SRM nozzle. An implicit Navier-Stokes Solver is selected to simulate two-dimensional axial-symmetric unsteady turbulent flow of compressible fluid. The governing equations are discredited by using the finite Volume method. S-A turbulence model is employed. CFD scheme is implemented to investigate the temperature distribution causes at nozzle throat inserts composite material. Different parameters have been selected for the analysis to validate the temperature variation in the throat inserts and baking material of SRM nozzle. The advanced SRM nozzle composite material is also characterized for the high thermo stability and high thermo mechanical capabilities to make it more reliable, simpler and lighter.
