Dynamics modeling and simulation analysis of a reusable high-pressure staged combustion LOX/kerosene variable thrust rocket engine

Abstract

Reusable liquid propellant rocket engines are critical propulsion systems for future space launches and, with the increasing diversity of space missions, have become a prominent research focus in the aerospace field. To address the unclear response characteristics of a reusable high-pressure staged combustion LOX/kerosene variable-thrust rocket engine, a simulation platform was established for a specific engine model. This platform comprehensively considers the effects of the turbopump, valves, gas generator, thrust chamber, and regenerative cooling channels. Simulations were conducted under single-point operating conditions to investigate the system’s response characteristics across different operating conditions, the variation of system performance parameters with thrust levels, and the effects of ignition timing gaps and start-up acceleration valves on the engine start-up process. The results indicate that reducing the ignition timing gap between the gas generator and the combustion chamber effectively decreases the risk of over-temperature and over-pressure in the gas generator. Additionally, during rapid start-up with the use of an acceleration valve, the fuel valve opening for the gas generator should be minimized to prevent fuel accumulation, which could lead to over-temperature conditions.