3-D Simulations of Ignition Transients in the RSRM

Abstract

Although many of the older analyses used reduced geometries and empirically-based physical models, they were often able to match the pressure history of the RSRM to a fairly high degree of accuracy. However, reliance on calibration to fit experimental data greatly reduces the confidence one may have in the predictive capability of a simulation. More detailed multi-physics coupled simulations using the full 3-D geometry are required to understand all of the important phenomena taking place during the ignition of a large solid rocket motor. The goal of the Center for Simulation of Advanced Rockets (CSAR) is to perform fully-coupled, 3-D, detailed simulations of solid propellant rockets using science-based models whenever possible 7 . This paper describes the Center's code in considerable detail and presents results for RSRM ignition simulations. Verification and validation of Rocstar 3 is described elsewhere. 8 Rocstar 3 has recently been applied to a variety of other rocket- related problems, including propellant slumping in the Titan IV SRMU