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

  • Mechanics of Machines
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Abstract

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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Authors and Affiliations

  1. Blagonravov Institute of Mechanical Engineering, Russian Academy of Sciences, Moscow, 101830, Russia

    V. A. Kotel’nikov, M. V. Kotel’nikov & G. S. Filippov

  2. Moscow Aviation Institute (National Research University), Moscow, Russia

    V. A. Kotel’nikov, M. V. Kotel’nikov & G. S. Filippov

Authors
  1. V. A. Kotel’nikov
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  2. M. V. Kotel’nikov
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  3. G. S. Filippov
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Corresponding author

Correspondence to M. V. Kotel’nikov.

Additional information

Original Russian Text © V.A. Kotel’nikov, M.V. Kotel’nikov, G.S. Filippov, 2018, published in Problemy Mashinostroeniya i Nadezhnosti Mashin, 2018, No. 6.

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Kotel’nikov, V.A., Kotel’nikov, M.V. & Filippov, G.S. Electrical and Physical Parameters of Plasma Fluxes in Exhaust from a Liquid-Propellant Rocket Engine. J. Mach. Manuf. Reliab. 47, 488–494 (2018). https://doi.org/10.3103/S1052618818060067

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  • DOI: https://doi.org/10.3103/S1052618818060067

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