Chemically Reacting Flow Modeling of a Hybrid Rocket

This study investigates simulation strategies for chemically reacting flows in hybrid rocket systems, which leverage the advantages of both gas and solid-fueled propulsion. Gaseous nitrous oxide (N₂O) is utilized as the oxidizer and solid acrylonitrile butadiene styrene (ABS) is utilized as the fuel grain. Simulations are tailored to an experimental setup designed for thrust levels below 100 pounds and accommodating dual gas oxidizer configurations. The Uintah: MPMICE Computational Framework is employed to simulate chemically reacting flow dynamics, multiphase phenomena, and fluid-structure interactions. Fuel regression rates are quantified using an Arrhenius-type equation and a two-phase chemistry model specific to ABS, calibrated with limited experimental data. The study assesses how surface gasification and combustion models influence fuel grain regression rates, emphasizing validation against experimental measurements for accuracy and reliability.