Ignition process of a 3-D dual-burning rate solid rocket motor with erosive burning

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.