In order to reduce the run-up distance for deflagration-to-detonation transition process, and increase the operating frequency of a pulse detonation rocket engine, a specific experimental system was designed. A tube closed at one end and open at the other end was employed as the detonation tube. The detonable mixtures were injected into the detonation tube periodically in the middle of the tube through a rotary valve and ignited near the open end. Detonation waves can be obtained when the deflagration waves propagate to the closed end. Varieties of experiments were carried out in the pulse detonation rocket engine system utilizing ethylene as fuel and oxygen-enriched air as oxidizer. Fully developed detonation waves were obtained, and a steady operating frequency of 200 Hz was successfully achieved. Higher operating frequency can be expected when the supplying flow rate is improved or smaller tube is utilized.
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