Мақаланы E-mail арқылы жіберу Electrical and Physical Parameters of Plasma Fluxes in Exhaust from a Liquid-Propellant Rocket Engine
- Авторлар: Kotel’nikov V.A.1,2, Kotel’nikov M.V.1,2, Filippov G.S.1,2
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Мекемелер:
- Blagonravov Institute of Mechanical Engineering
- Moscow Aviation Institute (National Research University)
- Шығарылым: Том 47, № 6 (2018)
- Беттер: 488-494
- Бөлім: Mechanics of Machines
- URL: https://journals.rcsi.science/1052-6188/article/view/194039
- DOI: https://doi.org/10.3103/S1052618818060067
- ID: 194039
Дәйексөз келтіру
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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.
Авторлар туралы
V. Kotel’nikov
Blagonravov Institute of Mechanical Engineering; Moscow Aviation Institute (National Research University)
Email: mvk_home@mail.ru
Ресей, Moscow, 101830; Moscow
M. Kotel’nikov
Blagonravov Institute of Mechanical Engineering; Moscow Aviation Institute (National Research University)
Хат алмасуға жауапты Автор.
Email: mvk_home@mail.ru
Ресей, Moscow, 101830; Moscow
G. Filippov
Blagonravov Institute of Mechanical Engineering; Moscow Aviation Institute (National Research University)
Email: mvk_home@mail.ru
Ресей, Moscow, 101830; Moscow
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