Modeling Oscillated Combustion of NG/BTTN Based Heterogeneous Propellants

Addressing solid rocket motor (SRM) pressure oscillations is crucial for improving energy efficiency, thermal stress management, and thrust stability. This study presents an integrated framework combining experimental and numerical approaches to tackle this challenge. Experimentally, the propellant burning rate is analyzed under varying pressures, leading to the development of a macroscale SRM pressure oscillation model. A novel reaction kinetic mechanism is introduced for NEPE propellant reactions, integrating temperature-dependent condensed phase kinetics with semiglobal kinetic submodels to capture gas-phase reaction intricacies. The refined propellant microstructure is incorporated into the macroscale model, enhancing our understanding of the interaction between turbulent flow and reactive flow. The pressure oscillation is modeled as a sine form, providing a structured approach to study oscillations. This research examines transient flame evolution, dynamic temperature changes near the propellant surface, and unstable gas flow characteristics. The combustion response under varying pressure oscillation conditions is analyzed in detail, with simulation results accurately matching experimental data, providing robust theoretical support for enhancing propellant energy output efficiency.