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Completed TRL 3 (started at 2, targeting 4)
Project Objective
This work rapidly models Rotating Detonation Rocket Engine (RDRE) chamber and injector geometries to better understand how key design characteristics change the combustors operability.
Project Description
The goal of this work is to rapidly model varying design trades for the RDRE combustor to understand its operability limits. Many aspects of the injector design, chamber design, and nozzle design will be changed to understand how the detonation within the combustor will respond. The overall performance trends of the combustor will also be investigated and are the primary deliverables of this work. The combustion efficiency, Isp, and other properties of the combustion flowfield are all going to be evaluated from one design to another.
Project Results and Conclusions
The project team has successfully identified several key design criteria which govern the RDRE performance directly. These key criteria are being further investigated for their limitations in the design trade space.
Overall, this work is expected to yield a better understanding of how these engines operate and the limitations to their operability. The results will guide the ongoing design process of full scale hardware for the current Technology Demonstration Mission (TDM) being spearheaded through Marshall Space Flight Center.
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