Conceptual Design of a Continuous Wave (Rotating Detonation) Engine for Suborbital Flight Vehicles

Rotating Detonation Engines (RDEs) operate on continuous detonation waves, offering superior thermodynamic efficiency and compactness compared to traditional deflagration-based combustion systems. This study investigates the feasibility of RDEs for suborbital and hypersonic cruise flight vehicles through a combined theoretical and computational approach. A fractional-factorial Design of Experiments (DoE) method is applied to evaluate the influence of key parameters such as propellant type (methane, acetylene), thrust, and thermal stability. The performance impact of nozzle geometry, particularly aerospike configurations, is also assessed. A two-dimensional computational fluid dynamics (CFD) simulation in ANSYS Fluent is used to visualize detonation wave propagation, pressure rise, and flow field dynamics. Results show that detonation wave characteristics are highly sensitive to specific impulse and nozzle geometry, with CFD confirming hypersonic wave speeds and effective detonation front propagation. The study demonstrates the potential of RDEs as efficient, compact propulsion systems for suborbital applications. Future work will focus on real-gas effects, improved cooling strategies, and enhancing detonation stability under variable flow conditions.