Rotating Detonation Engine Performance Model for Rocket Applications

Airbreathing rotating detonation wave engine cycle analysis

Airbreathing rotating detonation wave engine cycle analysis" a r t i c l e i n f o a b s t r a c t A cycle analysis model for an airbreathing, rotating detonation wave engine (RDE) is presented. The engine consists of a steady inlet system with an isolator which delivers air into an annular combustor. A detonation wave continuously rotates around the combustor with side relief as the flow expan...

Analytical Models for the Thrust of a Rotating Detonation Engine

Twomodels are proposed for rotating detonation engine performance. The first model is motivated bymodels of pulse detonation engine performance which are based on the pressure-time history within the detonation tube. The present work extends those ideas to treat rotating detonation engines with a control volume analysis that considers the forces within the combustion chamber. The key scaling pa...

Large Class 1.3 Rocket Motor Detonation Character

Large explosive class 1.3 solid .propellant rocket motors utilizing polybutadiene binder, aluminum fuel, and ammonium perchlorate oxidizer are typically considered explosively vlsafell. That is, the required stimulus is so large that motor detonation is extremely unlikely, even when donored by a sizeable high explosive charge. Two large ground cratering events have occurred during recent years ...

The Blacklight Rocket Engine

Executive Summary This report summarizes the final project results for the period of May 1, 2002 through November 30, 2002 for the NIAC CP 01-02 Phase I study, "The BlackLight Rocket Engine". The objective of the Phase I study was to assess the potential of low pressure, mixed gas hydrogen plasmas (i.e. the BlackLight Process) toward the development of high performance space propulsion systems.

Rotating Combustion Chamber for Rocket Apparatus