Experimental investigation on the performance of two-phase pulse detonation rocket engine

Utilizing liquid kerosene as the fuel, oxygen as oxidizer and nitrogen as purge gas, a series of multi-cycle detonation experiments were conducted to obtain the performance parameters of pulse detonation rocket engine (PDRE). The mass flow of liquid kerosene was measured by orifice meter and the mass flow of oxygen was measured based on the method of gas collection. The detonation chamber pressure traces were recorded by dynamic piezoelectric pressure transducers. Pulsed temperature test was employed to measure pulsed temperature at the exhaust plume of PDRE. A dynamic piezoelectric thrust transducer was used to record the transient thrust produced by PDRE. The average thrust and specific impulse of PDRE with different operation frequency were obtained by experiments. The experimental results indicated that detonation pressure and temperature were varied with the operation frequency of PDRE, and the fill fraction has a significant influence on the specific impulse of PDRE. With the strategy of partial filling in detonation tube, the specific impulse can be remarkably enhanced.