Targeting 3-D dual-burning rate solid rocket motor(SRM)

the erosive burning rate

burning surface temperature

mass source

momentum source

energy source and igniter inlet boundary condition were investigated to aid in the ignition transient flow field simulation with erosive burning

using the user defined function module of commercial CFD code. The focus was put on the analysis of simulation results and comparison between simulation and test results indicate that: in the initial stage of ignition

the flow structure is highly complicated and the pressure varies drastically in the head-ending region; the open of nozzle closure leads to a negative pressure gradient and the shake of pressure gradient; the calculated results are consistent with the experiments showing

it is appropriate to compute the 3-D burning surface temperature using 1-D unsteady heat transfer equation for the solid phase

and the calculated approach is accurate and valid.