DETONATION ROCKET ENGINES PROCESSES INVESTIGATION

Abstract

The article focuses on the problems of the detonation engines specific characteristics increasing. The schemes that are known have several disadvantages, so despite the seventy years history they are still at the experimentation stage.To improve the performance of detonation engines the solutions are suggested. The new scheme provides the initiation of the engine in pulse detonation tubes using rotating detonation wave. It is distributed in channel located between the spray head and a circular tubular combustion chamber. The advantage of the new scheme is the fact that batch filling of the combustion chamber is not needed anymore, initiation of detonation of each cycle and a high part of fuel detonates in the axial direction.Experimental studies were conducted in order to test the operability of the scheme. For this purpose, two models and test-banch were developed.Also, one of the tasks of the experiments was to test the possibility of passing deflagration and detonation fronts through the mesh barriers. For this pyrpose, the mesh is installed between the main channel and offshoot. Moments of launches including the velocity of fronts are illustrated in the figures.The results showed that the detonation and deflagration are distributed through offshoot, but their speed drops more than 2 times. This result is expected, and described in publications. The mesh cell size that blocks deflagration and detonation fronts in a mixture of propane air is determined. Thus, the workability of the proposed scheme of detonation rocket engine with initiation impulses rotating detonation wave was confirmed experimentally.