A recent study led by Haodong He from the School of Astronautics has shed light on the static equilibrium characteristics of a cutting-edge rocket propulsion system known as the full-flow staged combustion cycle (FFSC) engine. This research, published in the International Journal of Aerospace Engineering, explores how different propellants—specifically liquid oxygen and liquid hydrogen (LOX-LH2), liquid oxygen and liquid methane (LOX-LCH4), and liquid oxygen and kerosene (LOX-kerosene)—affect the engine’s performance.
The FFSC engine is gaining attention in the aerospace industry due to its ability to achieve a high specific impulse, which translates into more efficient propulsion. He’s research utilized a sophisticated equilibrium model and the discrete Newton iteration method to analyze how these propellants influence the engine’s performance. One of the key findings was that the engine exhibited similar equilibrium results on the oxidizer side, but significant differences emerged on the fuel side.
He noted, “The regulation range of LOX-LH2 was wider than that of LOX-LCH4 primarily because of the variance in the molecular weight of the fuel-rich gas.” This implies that LOX-LH2 could offer more operational flexibility, potentially making it a preferred choice for future rocket designs. In contrast, LOX-kerosene showed the narrowest regulatory range, which was attributed to a low oxidizer excess coefficient. This indicates that while LOX-kerosene is a common choice, it may limit the operational parameters of the engine.
The implications of this research extend beyond aerospace engineering. As the industry moves towards more sustainable and efficient rocket technologies, understanding the characteristics of different propellants can lead to advancements in commercial space travel and satellite launches. With the growing interest in space exploration and satellite deployment, optimizing rocket propulsion systems can significantly reduce costs and improve mission success rates.
Moreover, the study highlights the importance of temperature regulation in preburners, which is critical for maintaining engine performance. He emphasized that managing the oxidizer excess coefficient requires precise adjustments to various valve components, including the main fuel valve and oxidizer preburner fuel valve. This technical insight could pave the way for innovations in engine design and control systems, ultimately benefiting the energy sector as it seeks to enhance propulsion technologies.
As the aerospace industry continues to evolve, research like that of Haodong He offers valuable insights that could redefine propulsion systems and open up new commercial opportunities. The findings from this study, published in the International Journal of Aerospace Engineering, contribute to the ongoing dialogue about optimizing rocket propulsion for a more sustainable future in space exploration.
