Vasyliv S. Development of detonation devices to improve the efficiency of rocket engines

The thesis is devoted to development and substantiation of rocket engine circuit decisions with use of detonation process for increase of energy and mass characteristics of installation as a whole. The structure of the fuel component flow field in the annular detonation chamber of the combustion near the injector head is determined, which also affects the detonation front moving efficiency. Computer simulation of the mixture flow through the nozzles of different schemes for optimizing according the criterion of the turbulence minimum scale was conducted which in turn leads to decrease in the diffusion equalization time. Based on the obtained data, it was concluded that it is not possible to provide the optimal mixture for detonation in the existing schemes. The transition to the prechamber was proposed. The scheme of the detonation rocket engine with initiation of impulses by rotational detonation is developed. Based on it, a device for combustion of exhaust turbine gas in the detonation mode for the engine of type RD861K was developed. Experimental tests on this device element models for verification of technical decisions are carried out. A solid-fuel cord detonation engine has been developed to divert the wings of the main fairing separated from the rocket during flight in the surface dense layers of the atmosphere with supersonic speed. As a result of computer simulation of the wing flow by the oncoming flow, the effects contributed to the process of their separation and removal are revealed. Experimental studies of fuel compositions based on hydroxyl ammonium nitrate, which can be used for detonation devices in rocket technology, have been carried out.