Date of Award
2026
Document Type
Thesis
Degree Name
Master of Science in Engineering (MSE)
Department
Mechanical and Aerospace Engineering
Committee Chair
John Bennewitz
Committee Member
George Nelson
Committee Member
Robert Frederick
Research Advisor
John Bennewitz
Subject(s)
Rockets (Aeronautics)--Fuel, Rocket engines Propulsion systems, Water--Electrolysis, Rotating detonation rocket engine (RDRE)
Abstract
This work explores the potential benefits and practical feasibility of a rotating detonation rocket engine (RDRE) spacecraft thruster using water electrolysis for propellant generation. Such a thruster can enable the use of liquid water as an easily storable and chemically inert propellant, as well as the volume and efficiency benefits associated with detonation combustion. A thermodynamic model is first developed to demonstrate the compounding advantages of both water electrolysis propellant generation and detonation combustion when compared to conventional isobaric combustion cycles. Comparisons are also drawn to alternative water-powered propulsion methods and the advantages of chemical propulsion are observed. The representative water electrolysis RDRE thrusters can more than double the specific impulse using propellants derived from water compared to alternative water-powered propulsion methods, and they can reduce the propellant volume requirement by multiple orders of magnitude compared to compressed gas propellants in some cases. Then, the suitability of water electrolysis generated hydrogen and oxygen propellants for detonation propulsion at size scales relevant for small spacecraft is shown through the construction of a laboratory-scale propellant generation system and successful hot-fire testing using a 15 mm outer diameter RDRE. Successful rotating detonation operation is observed at all operating conditions tested, and performance parameters including thrust and specific impulse are comparable to performance observed in engine tests using industrial-grade propellants, with approximately 20% reduced chamber pressure and 40% reduced thrust attributed to impurities in the electrolyzed propellants. The system-level analysis and experimental demonstration serves as strong motivation for the further development of such propulsion systems.
Recommended Citation
Byers, Justin M., "System-level analysis and experimental testing of a rotating detonation rocket engine with water electrolysis propellants" (2026). Theses. 854.
https://louis.uah.edu/uah-theses/854