Detonation characteristic on kerosene/oxygen pulse detonation rocket engine

Unlike conventional steady-state rocket engines, which use constant pressure combustion, PDREs utilize the high-energy release rate and thermodynamic characteristics of detonation waves to produce thrust. This enables PDREs to operate at higher thermodynamic efficiencies. In this paper, the PDRE test model utilized kerosene as the fuel, oxygen as oxidizer, and nitrogen as purge gas. Solenoid valves were employed to control intermittent supplies of kerosene, oxygen, and purge gas. The spark plug igniter used in these experiments had ignition energy of only around 50 mJ. Solenoid valves and spark plug are controlled by the control and ignition system. DDT enhancement device Shchelkin spiral was used in the test model. Six pressure transducers placed on the detonation tube at different locations from the thrust wall were used to measure pressure trace. Detonation characteristic on kerosene/oxygen PDRE was experimentally investigated.