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

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.

Automated summary

This study presents the results of firing tests on a liquid-propellant rocket engine using kerosene and gaseous oxygen as fuel components. Electromagnetic field oscillations of the ionized combustion products were recorded during the tests in the frequency range of 0.01-56 kHz. The study introduces a technique for secondary signal processing from an electromagnetic sensor to diagnose the combustion process in the engine. The analysis shows a linear relationship between the electromagnetic sensor signal and the combustion chamber pressure within a certain range of pressure variation. Spectral analysis of the sensor signal during fuel combustion reveals discrete frequencies that coincide with the acoustic vibrations in the combustion chamber.