Development of a Liquid-Propellant Rocket Powered by a Rotating Detonation Engine

This paper presents work on a demonstrator rocket powered by a rotating detonation engine (RDE) fed by liquid propellants. Key to the success of the project was the development of a suitably efficient and lightweight RDE. After selecting the propellants: nitrous oxide ([Formula: see text]) and propane ([Formula: see text]), laboratory tests were carried out on RDEs with different combustion chamber geometries. The conical geometry showed the best performance, and it was selected for further development; on this basis, the target RDE was designed and built in two versions: uncooled and regeneratively cooled. These were tested in laboratory conditions, but only the regeneratively cooled engine met the requirements. After successful laboratory testing of the engine, a demonstration rocket was designed and built. Static tests made in a vertical position confirmed that the rocket had sufficient operational performance (net thrust and total impulse). Ultimately, the liquid-propellant RDE-powered rocket made a successful flight. To the authors’ knowledge, it was the first liquid-fuel rocket in the world to take off and fly exclusively by means of RDE propulsion.