Advanced Particulate Sub-Models for Rocket Motor Exhaust Plumes

IllinoisRocstar LLC will develop and commercialize an innovative multiscale computational framework that predicts the behavior of aluminum particles as they evolve from the grain surface, combust, pass through the nozzle, and into the plume exhaust. Based on high-fidelity, physics-based simulations of complete SRM internal ballistics using our Rocstar Simulation Suite, a continuous probability distribution sub-model for the particulates entering the SRM nozzle will be developed. Highly resolved, three-dimensional simulations will be performed to understand the effects of turbulent inlet conditions on the nozzle particle field, as well as the effects of nozzle vectoring on the particle behavior. Accurate characterization of the particle field entering and leaving the nozzle is critical to capturing the particulate evolution in the exhaust plume and ultimately the plume signature. Our strategy will produce results with better fidelity than those generated using current industry practice, and will provide important insights into multiphase issues for plume signatures of importance to MDA and other DoD mission agencies. The SBIR product following Phase II will be commercial-quality software modules suitable for incorporation in MDA and other plume signature codes. Further, we will continue the validation of the IllinoisRocstar Rocstar Simulation Suite.