ROTATING DETONATION ROCKET DESIGN AND LAUNCH

Abstract

The goal of this project is to fire the first Rotating Detonation Engine powered sounding rocket in the United States. The scope of this project includes all systems in a rocket excluding the engine itself and the nozzle, which will be sponsor-provided. This includes but is not limited to propulsion systems, electronics bay and recovery systems, airframe, and Ground/Launch equipment. Rotating Detonation Engines (RDEs) are the next frontier of rocket propulsion. RDE's use pressure gain combustion to increase efficiencies within a smaller package by utilizing sustained supersonic combustion. Higher efficiency propulsion allows for reduced fuel use, allowing for greater performance and lower emissions for rocket aerospace systems. In the past few years, the major challenges underlying the design of these engines have been solved, and now the technology has matured to the point of use for flight systems. The goal of this project is to develop a platform to demonstrate that technological maturity. A full static fire would prove that this rocket system would be ready for a launch. This final report illustrates the motivation of design through functional requirements and system requirements, a technical data package, and the verification of system requirements validating the operation of our design.