Rocket Test Facility Design, Modelling, and Simulation

Abstract

At present, rocket testing remains a challenge due to the complexity of safety aspects involved and the associated costs. Despite these challenges, testing is a crucial aspect of a rocket engine's lifecycle. To address this, the current study aims to design a model, simulate, and control a test facility for chemical propulsion systems. For this particular study, two distinct bi-propellant systems were examined. The first system involved the design of a liquid-propellant feeding system, while the second focused on a 500 N lab-scale bi-propellant rocket, equipped with both an engine and a feeding system. The research incorporated real-time monitoring via a control system dashboard, using PID controllers to adjust propellant pressure and flow rate. To assess the system's sensitivity response, a parametric study was conducted, examining variations in the oxidizer-to-fuel ratio as well as in the fuel and oxidizer pressures. This systematic investigation revealed correlations between these dynamic variables and crucial rocket parameters, such as thrust, characteristic velocity, specific impulse, heat release from fuel combustion, and nozzle expansion. The system was validated within acceptable error tolerances. This validation enabled comprehensive modelling for the parametric study. The study offers a validated, well-established, and robust platform for rocket design advancements. In short, the study provides a useful foundation for improving the reliability and understanding of rocket engine testing.