Numerical Analysis Of Solid Rocket Motor Ignition Transient

Although a very short-term process, the ignition transient plays a very important role in the normal work of a Solid Rocket Motor. Particularly for small and medium-sized Solid Rocket Motors, the small-sized structure, the short working time and the poor combustion stability make the ignition problems more prominent.On the basis of the proper simplification of the Solid Rocket Motor ignition transient, the mathematical model that facilitates the engineering application and numerical calculation is carried. And then the UDF (User Defined Function), k -εturbulent model, DO radiation model and PISO solver are utilized in this paper to simulate the ignition transient of the chosen Solid Rocket Motors.Firstly, a 2D ax-symmetric numerical analysis of ignition transient in the chosen Solid Rocket Motor with tube grain is progressed. The simulation results show the Pressure vs. Time curve and flow field property of the chamber. Besides, the impacts that design parameters (such as the igniter mass flow rate, burning rate of propellant, and opening pressure of the nozzle closure) play on the ignition pressurization course of the Solid Rocket Motor are analyzed.Secondly, according to the simulation results of the ignition transient in the 2D ax-symmetric model, the ignition transients of the two Solid Rocket Motors with star grain and conocyl and truncated cone grain separately are simulated. The simulation results of the ignition transient in each Solid Rocket Motor show the Pressure vs. Time curve, flame-spreading process and flow field at different time.