Evaluation pulse detonation rocket engines using ethanol and oxygen

This study includes both a theoretical and an experimental investigation of a pulse detonation rocket engine using ethanol and oxygen. The motivation for using ethanol is shown by ignition delay time calculations. The longer ignition delay time of ethanol in comparison to hydrocarbon liquid fuels, such a heptane, at below 900 K is expected to prevent premature ignition of the propellant in a multiple cycle operation. In the experimental study, the oxygen is used to atomize the ethanol and form the mixture, which is subsequently ignited using a spark plug and transitions to detonation. Continuous operation was demonstrated an thrust was measured using a pendulum. Thrust and propellant flow rate measurements show that the specific impulse of the engine is 300 seconds, which is 20% higher than obtainable with the same propellant in a conventional rocket engine.