Email this article Electrical and Physical Parameters of Plasma Fluxes in Exhaust from a Liquid-Propellant Rocket Engine
- Authors: Kotel’nikov V.A.1,2, Kotel’nikov M.V.1,2, Filippov G.S.1,2
-
Affiliations:
- Blagonravov Institute of Mechanical Engineering
- Moscow Aviation Institute (National Research University)
- Issue: Vol 47, No 6 (2018)
- Pages: 488-494
- Section: Mechanics of Machines
- URL: https://journals.rcsi.science/1052-6188/article/view/194039
- DOI: https://doi.org/10.3103/S1052618818060067
- ID: 194039
Cite item
Open Access
Access granted
Subscription Access
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.
About the authors
V. A. Kotel’nikov
Blagonravov Institute of Mechanical Engineering; Moscow Aviation Institute (National Research University)
Email: mvk_home@mail.ru
Russian Federation, Moscow, 101830; Moscow
M. V. Kotel’nikov
Blagonravov Institute of Mechanical Engineering; Moscow Aviation Institute (National Research University)
Author for correspondence.
Email: mvk_home@mail.ru
Russian Federation, Moscow, 101830; Moscow
G. S. Filippov
Blagonravov Institute of Mechanical Engineering; Moscow Aviation Institute (National Research University)
Email: mvk_home@mail.ru
Russian Federation, Moscow, 101830; Moscow
Supplementary files
