Dr. D. Suslov
The work conducted by this department revolves around combustion chamber processes and technologies for liquid rocket propulsion with cryogenic propellants LOX/hydrogen, LOX/methane, and storable propellants.
For experimental studies, research combustion chambers are developed and used to explore combustion chamber processes under typical apogee or booster stage propulsion conditions. The combustion chamber pressures in test runs range from just a few bar to 330 bar, the fluid temperatures ranging from 40 K to 3500 K.
We aim to explain fundamental combustion chamber phenomena and to gather quantitative data to validate numerical analysis tools.
This fundamental research aims at detailed testing of chemical and molecular processes, as occurring in: