A dynamic simulation approach to optimize thrust regulation in electric pump-fed rocket engines

This study presents a dynamic simulation framework to optimize thrust regulation in an electric pump-fed rocket engine using liquid oxygen-liquid methane propellants. The engine operates across a 20–100% thrust range. A comprehensive system model simulates transient interactions among electric pumps and injectors. It focuses on actuation timing effects on thrust control efficiency. The model integrates pump dynamics, combustion, and two-phase flow. It uses a time-stepped numerical method. Results show that synchronized pump actuation minimizes regulation time. Delays extend it. The oxidizer pump predominantly influences chamber pressure and mixture ratio due to its faster response. Pre-actuation of components modulates performance. Oxidizer pump adjustments reduce mixture ratio during thrust decrease. Injector pre-actuation elevates pressure ratios. An optimized timing sequence mitigates fluctuations in mixture ratio and injector pressure during deep-thrust transitions. Validation against experimental data confirms accuracy. Errors are below 1.2% for chamber pressure and mass flow rate. This methodology elucidates electric pump-fed engine dynamics. It offers a scalable tool for refining thrust regulation. It advances propulsion system design through computational modeling.