High-Fidelity Numerical Simulations of Rotating Detonation Rocket Engines

Rotating detonation rocket engines are considered the next generation of space propulsion technology. However, existing high-fidelity numerical tools for design and optimization of these revolutionary engines require substantial computational costs and fail in accurately predicting the detonation wave speed, stability, and operating regimes. In the current research, we developed a variety of new calibration procedures of simplified single-step and two-step chemical kinetics models for arbitrary mixtures, including mixtures relevant for space rocket propulsion applications. The newly developed chemical kinetics models are able to capture all the important detonation properties, including the detonation cellular structure, and reduce the required computational cost of numerical simulations by more than an order of magnitude. We extensively test, verify, and validate the newly suggested numerical approach against results from the literature. The research outcomes provide the Israeli aerospace industries a unique numerical tool for design and optimization of highly accurate simple chemical kinetics model that can capture realistic detonation properties. Thus, advancing Israel towards cutting-edge technological advancements in space rocket detonation-based propulsion systems.