A numerical analysis of unsteady motions in solid rocket motors has been conducted. A fully coupled
implicit scheme based on a dual time-stepping integration algorithm has been adopted to solve the governing
equations and associated boundary conditions. A narrow pressure pulse is imposed at the head end to
simulate unsteady acoustic oscillations in the combustion chamber. Pressure increases when the front of the
pulse reaches near the nozzle area. Self-generated oscillations with frequency of standing wave propagates
upstream in the combustion chamber. Investigation of transient response of gas-phase dynamics to traveling
pressure wave and its effects on propellant combustion reveals several aspects: Combustion responses have
a strong relationship with vorticity fluctuations in case of high turbulent intensity on the propellant surface.
Temperature fluctuations of the propellant surface in the head end region seem to be very unstable and
independent of the pressure wave. Surface temperature without turbulence effect looks more sensitive to
temperature fluctuations in the primary flame zone. Stability of surface temperature is strongly related to
turbulent intensity on the propellant surface
