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Н.В. Быков, К.А. Бырдин, В.С. Макаренко
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Инженерный журнал: наука и инновации
# 2·2017
Effect of the injected jet pressure ratio
on rocket engine power characteristics
© N.V. Bykov
1,2
, K.A. Byrdin
1
, V.S. Makarenko
1
1
Bauman Moscow State Technical University, Moscow, 105005, Russia
2
Federal Research Centre for Computer Science and Control
of the Russian Academy of Sciences, Moscow, 119333, Russia
We studied how the pressure ratio of a jet being injected into the supercritical portion of
a rocket engine nozzle affects rocket engine performance and power characteristics. We
solved two test problems in order to verify the computation technique. We analysed the
potential of using a modelling software package to calculate how jets interact with a su-
personic flow. We used a modern hydrocode to model a supersonic jet being injected into
the supercritical nozzle portion. We obtained results of a series of numerical computa-
tions for various pressure ratios of the jet being injected, which allowed us to determine
the lateral control force as a function of the pressure ratio of the jet injected. The numer-
ical gas dynamics experiment technology presented may be useful for designing rocket
control and stabilisation systems.
Keywords
: injection thrust vectoring, asymmetrical injection, jet interaction, supersonic
flows, gas-dynamics flight controls
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