Optimized and Lightweight Rotating Detonation Rocket Engine

The complex nature of the spatio-temporal physics in a rotating detonation rocket engine (RDRE) makes it a difficult task to Figoptimize the thrust with only design thumb rules available for the geometry constraints. There is also ambiguity in the currently used methodologies in predicting engine performance and its loss mechanisms. In this research, we propose to bridge this technical gap with a rapid simulation strategy to assist the current NASA efforts on comprehensive RDRE performance plan. We offer a combination of an efficient design optimization simulation and a unique additive manufacturing concept for hot fire testing with the goal of reduction in the overall hardware mass. Phase I effort will focus on validating our approach in achieving better design with high performance. In the subsequent future research, our simulation method will assist in additively fabricating a lightweight RDRE. Using only passive radiative cooling, this hardware will consist of a smart combination of refractory material with significantly enhanced thermo-structural qualities.

We anticipate that our innovation will close the gap in the current methods and establish a useful optimization technique for high area ratio nozzle design. Our simulation strategy will assist in the additive manufacturing of RDRE with lightweight, compact, and robust material properties to support the current NASA efforts on comprehensive RDRE performance plan. Our optimization technique and reduced mass, high heat flux RDRE technology will find immediate interest for commercial Lunar and Martian exploration rocket propulsion systems.

This is early/mid-stage (TRL 2) — the most realistic path in is NASA SBIR/STTR, which funds small businesses and research institutions to develop technology aligned with NASA's needs (equity-free, phased funding). Check whether a current SBIR/STTR solicitation topic overlaps with this project's technology area, or contact the project directly (above) to ask.

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