The exhaust and thrust properties of a high frequency pulse detonation rocket engine

To investigate the exhaust and thrust properties of a high frequency pulse detonation rocket engine (PDRE), experimental and numerical investigations were carried out. High speed camera was utilized to capture the shadowgraph and ame graph of the exhaust process. A numerical model of a single cycle PDRE was designed to study the exhaust process and thrust of the engine. The results indicated that the PDRE was ignited near the open end and the detonation wave propagated to the closed end. The detonation wave propagated to the open end and started the first exhaust process. The compression wave which reected from the closed end propagated to the open end and started the second exhaust process. The impulses obtained from each exhaust process were nearly the same.