Correlation and Spectral Analysis of Combustion Products Electrophysical Characteristics of Rocket Engines

Abstract

The results of firing tests of a model liquid-propellant rocket engine on the fuel components kerosene and gaseous oxygen are presented. In the process of firing tests, electromagnetic field oscillations of ionized combustion products in the frequency range of 0.01–56 kHz were recorded. The technique of secondary signal processing from an electromagnetic sensor is presented. This technique makes it possible to diagnose the combustion process in the liquid-propellant rocket engine. As a result of the mutual (correlation) analysis of the electromagnetic sensor signal and the combustion chamber pressure, the linear relationship has been established in the range of pressure variation of 0.87–1.95 MPa. In the spectral analysis of the electromagnetic sensor signal during fuel combustion, discrete frequencies are determined, which coincide with the frequencies of acoustic vibrations in the combustion chamber of the model liquid-propellant rocket engine.