Generative Design of Thermal Management Strategies for In-Space Detonation Propulsion assessed by Laser Absorption Spectroscopy

To meet NASAs objectives in lowering the cost of access to space and enabling larger scientific payloads, the weight reduction potential offered through the emerging field of generative design is proposed in conjunction with the theoretical weight-reducing properties of rotating detonation rocket engines (RDREs). RDREs, a low technology readiness level (low-TRL) technology, offer great theoretical potential to output the same amount of power as traditional liquid rocket engines while using less propellant and less upstream pressure, thus lowering overall propulsion system mass. Used together, these systems offer an even higher mass-reduction potential for existing chemical rocket engine architectures. These optimized systems can potentially see usage in gas generators or pre-burners upstream of existing thrust chambers in launch vehicles as well as implementation as standalone engines for in-space applications. A process is outlined to collect and analyze heat transfer data within a rotating detonation rocket engine (RDRE) through hot fire tests (using both coolant properties and laser measurements of exhaust gases), process the data using genetic programming with symbolic regression (GPSR) to develop a mathematical expression for the heat transfer in an RDRE, and to use generative design with the developed expression to realize the computationally efficient design of a mass-reduced, thermo-fluid-optimized RDRE thrust chamber. In addition to the milestones of collecting novel heat transfer data, developing a heat transfer correlation equation, and hot fire testing a generatively designed RDRE chamber, additional benefits of the proposed research include enabling propulsion designers to directly calculate the heat transfer in an RDRE for specific end-user applications (using the developed heat transfer correlation), and developing an outline of the thermo-fluid generative design process for use in any space technology that operates within the realms of thermodynamics and fluid mechanics, to realize further weight reduction potential for additional subsystems in future space missions.

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