Design and Analysis of a LH2-LOX Rotating Detonation Propulsion System

Rotating detonation rocket engines (RDREs) are believed to have a higher thermal efficiency than Brayton cycle rocket engines. In this study, we designed a LH2-LOX upper stage propulsion system utilizing rotating detonative combustion. A thrust chamber with efficient injectors and aerospike nozzle designed based on C-J theory and gas dynamics principles. In addition, an expander cycle system was developed. Equilibrium calculations for the propulsion system were conducted by coupling the feed systems with the thrust chamber. Parametric studies were conducted to compare and analyse the characteristics of different chamber. The focus was on the system equilibrium and propulsion system performance. The results indicate that the system requires a lower outlet pressure from the pump across a range of varying conditions, and the propulsion system experiences no significant performance loss under low operating conditions. This effectively reduces the required power for the pump, leading to a decrease in the overall weight of the system and obtaining a wider adjustment range. This research demonstrates the feasibility of using rotating detonative combustion for upper stage propulsion systems, providing a reference for rocket applications of rotating detonation engines.