Yu. V. Platova, A. I. Semenovb, and B. V. Filippova
a Pushkov Institute of Terrestrial Magnetism, Ionosphere, and Radiowave Propagation, Russian Academy of Sciences,
Kaluzhskoe shosse 4, Troitsk, Moscow oblast, 142190 Russia
b Obukhov Institute of Atmospheric Physics, Russian Academy of Sciences, Pyzhevskii per. 3, Moscow, 119017 Russia
e-mail: yplatov@izmiran.ru
Received June 5, 2012
Abstract—Condensation of water vapor and carbon dioxide in the jet exhausts of rocket engines during last
stages of Proton, Molniya, and Start launchers operating in the upper atmospheric with different types of fuels
is considered. Particle heating is taken into account with emission of latent heat of condensation and energy loss
due to radiation and heat exchange with combustion products. Using the solution of the heat balance and con-
densed particle mass equations, the temporal change in the temperature and thickness of the condensate layer
is obtained. Practically, no condensation of water vapor and carbon dioxide in the jet exhaust of a Start launcher
occurs. In plumes of Proton and Molniya launchers, the condensation of water vapor and carbon dioxide can
start at distances of 120–170 m and 450–650 m from the engine nozzle, respectively. In the course of conden-
sation, the thickness of the “water” layer on particles can exceed 100 Å, and the thickness of carbon dioxide
can exceed 60 Å.
DOI: 10.1134/S0016793214010125
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