High-fidelity laser-based imaging of mixing effects on rotating detonation combustion for space propulsion

An experimental and computational study of a modular rocket RDE operating at various mixing conditions, from non-premixed to fully premixed is proposed. The combustor will be designed to allow for optical access to the flow passages and accurate modeling of the flow field at low computational expense. MHz-rate Acetone PLIF and kHz-rate hybrid fs/ps CARS will be performed inside the combustion chamber for reliable time-resolved fuel mixture fraction imaging and point thermometry. The data will be used in a collaboration with NASA to create a CFD model that reflects the combustor geometry to understand the effects of propellant mixing on wave speeds and detonation structure. This work will help to determine the mixing and combustion physics behind the wave speed discrepancy between experiments and simulations. With this knowledge in hand, modeling efforts can focus on improving RDE design for pressure gain, longer-term operation, stable combustion, efficient power extraction, and propulsion for rocket applications.

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