The results of the development of a new generation pulsating engine – an ejector dual-circuit PuVRD capable of under certain conditions going into detonation combustion mode are presented. It is assumed that in the engines of this type, having a double bend duct, the transition to detonation combustion is performed by precessing vortex core separation zone. The possible cause of the failure of the self-oscillating process during the transition to detonation combustion mode is analyzed.

The idea of realization of the detonative combustion cycle in pulse jet engines appeared many years ago but in fact, it has not been realized in practice yet. Most investigations Óarried out both in our country and abroad have not been brought up to practical use because of various challenges. In most cases, technology demonstrator are described where the process of cyclic detonation is studied. But there are no engines which could realize detonative combustion of regular fuel in incoming air. As a rule, well known constructions need the controlled system of high-pressure fuel supply and fuels of special type.

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