Modeling of space vehicle orientation thruster jets in vacuum chambers

This paper presents a brief overview of experimental studies performed at the Institute of Thermophysics SB RAS to model jets of low-thrust liquid rocket engines used as control and orientation thrusters of spacecrafts, including the International Space Station. Modeling criteria are formulated for the parameters of both the gas flow and the near-wall film of the liquid used for nozzle cooling. The experimental setup, diagnostic methods, and experimental results on the interaction of the near-wall liquid film with co-current gas flow inside the supersonic nozzle and during jet expansion into vacuum are described. The problem of minimizing backflows leading to contamination of the spacecraft external surfaces is discussed.