This paper presents a brief overview of experimental studies performed at the Institute of Thermophysics of the Siberian Branch of the Russian Academy of Sciences 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 liquid film 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.

中文翻译：

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真空室中航天器定向推进器喷气机的建模

本文简要概述了在俄罗斯科学院西伯利亚分院热物理研究所进行的实验研究，该研究对用作航天器（包括国际空间站）的控制和定向推进器的低推力液体火箭发动机的射流进行建模。为用于喷嘴冷却的气流和近壁液膜的参数制定了建模标准。描述了近壁液膜与超音速喷嘴内的并流气流相互作用以及射流膨胀到真空过程中的实验装置、诊断方法和实验结果。讨论了尽量减少导致航天器外表面污染的回流问题。