Research and development of bidimentional mathematical models of pulsing detonation engines for perspective flying devices

In the present paper the design procedure of parameters and performances of the pulsing detonation engine with a diffuser and the ejector on different conditions and stages of its operation develops. Construction of numerical methods of a solution of a commitment by definition parameters of flow of yields of a knocking and air to the detonation engine in different instants is carried on. Determining of a general pulse of the detonation engine with a diffuser and the ejector for one clock tick of operation. Trial accounts of a mathematical model of the detonation engine with a diffuser and the ejector at different stages of his operation are conducted.