The use of a Rotating Detonation Engine (RDE) as a gas-generator or pre-combustor to power the turbopump in a conventional rocket cycle will enable a system level improvement of the full rocket engine cycle. The detonation cycle is fundamentally more efficient than a comparable constant pressure Brayton cycle and generates less entropy and more pressure. The RDE captures a detonation wave in an annular chamber for continuous operation. Estimates of basicperformance improvement range from 5-10% or greater, depending on the operating pressure.In accordance with Topic No. AF182-064, New Cycle Engineering LLC proposes to build a subscale demonstration rocket engine RDE powered turbopump. This Phase I proposal covers a planning and basic research program to construct a detailed program for the design, build and test of the demonstrator in Phase II. The plan consists of a matrix of multiple factors such as fuel choice, scale, thermal strategies, injection design, and baseline reference engine. The plan will also cover Phase III and recommend a strategy for transitioning to commercial use.Pressure gain combustion, rotating detonation engine, Advanced Rocket Engine Technology, gas generator, Pre-Combustor, turbopump
