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Е.А. Андреев, А.В. Новиков, О.Е. Шацкий
24
Инженерный журнал: наука и инновации
# 4·2017
Computational and experimental study of
reliability
of rocket-engine firing and starting operation
of low thruster on the gaseous components
oxygen + methane with electric spark ignition
© E.A. Andreev, A.V. Novikov, O.E. Shatskiy
Bauman Moscow State Technical University, Moscow, 105005, Russia
Expansion of the domestic rocket raw material base, as well as increased environmental
requirements involve the use of cryogenic methane as a fuel component in space and aer-
ospace propulsion systems. The problem of creating thrusters on non-hypergolic compo-
nents for use in the spacecraft orientation and stabilization systems becomes urgent. Thus
there is a need to determine the conditions of a reliable ignition of gaseous fuel compo-
nents oxygen + methane for different structures of ignition units with varying ignition
unit power. The article analyzes the electrical ignition system capable of providing mul-
tiple engine firing, shows the results of theoretical and experimental studies of the low
thruster with the zonal component feeding in a wide range of geometrical and operation-
al parameters. Practical recommendations for the designing the combustion chambers
are presented.
Keywords:
rocket engine, low thruster, electric ignition systems, reliable ignition, bench
tests
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