Journal of Machinery Manufacture and Reliability

, Volume 47, Issue 6, pp 488–494 | Cite as

Electrical and Physical Parameters of Plasma Fluxes in Exhaust from a Liquid-Propellant Rocket Engine

  • V. A. Kotel’nikov
  • M. V. Kotel’nikovEmail author
  • G. S. Filippov
Mechanics of Machines


The structure of the disturbed area near the internal surface of the nozzle of a liquid-propellant rocket engine (LPRE) and also the distribution of the electrical and physical parameters in the flux of dense weakly ionized plasma are examined by means of mathematical simulation. The results of probe measurements of charged particle concentration in combustion products in the exhaust from the nozzle of a liquid-propellant rocket engine under real conditions at the moment of rocket lift-off from the launching site are presented.


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Copyright information

© Allerton Press, Inc. 2018

Authors and Affiliations

  • V. A. Kotel’nikov
    • 1
    • 2
  • M. V. Kotel’nikov
    • 1
    • 2
    Email author
  • G. S. Filippov
    • 1
    • 2
  1. 1.Blagonravov Institute of Mechanical EngineeringRussian Academy of SciencesMoscowRussia
  2. 2.Moscow Aviation Institute (National Research University)MoscowRussia

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