Отправить статью по E-mail Electrical and Physical Parameters of Plasma Fluxes in Exhaust from a Liquid-Propellant Rocket Engine
- Авторы: Kotel’nikov V.A.1,2, Kotel’nikov M.V.1,2, Filippov G.S.1,2
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Учреждения:
- Blagonravov Institute of Mechanical Engineering
- Moscow Aviation Institute (National Research University)
- Выпуск: Том 47, № 6 (2018)
- Страницы: 488-494
- Раздел: Mechanics of Machines
- URL: https://journal-vniispk.ru/1052-6188/article/view/194039
- DOI: https://doi.org/10.3103/S1052618818060067
- ID: 194039
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Аннотация
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.
Об авторах
V. Kotel’nikov
Blagonravov Institute of Mechanical Engineering; Moscow Aviation Institute (National Research University)
Email: mvk_home@mail.ru
Россия, Moscow, 101830; Moscow
M. Kotel’nikov
Blagonravov Institute of Mechanical Engineering; Moscow Aviation Institute (National Research University)
Автор, ответственный за переписку.
Email: mvk_home@mail.ru
Россия, Moscow, 101830; Moscow
G. Filippov
Blagonravov Institute of Mechanical Engineering; Moscow Aviation Institute (National Research University)
Email: mvk_home@mail.ru
Россия, Moscow, 101830; Moscow
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