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О.А. Ворожеева, Д.А. Ягодников
10
Инженерный журнал: наука и инновации
# 1·2017
Numerical study of the operating condition effect
on the thermal state of the structure of low thruster
on oxygen-methane propellant operating in pulsed mode
© O.A. Vorozheeva, D.A. Yagodnikov
Bauman Moscow State Technical University, Moscow, 105005, Russia
The article investigates the operating condition effect on the thermal state of the structure
elements of the model low thruster on oxygen-methane propellant operating in pulsed
mode using the unsteady-state conduction equations. The values of the maximum wall
temperature on the inner nozzle surface in the area of the critical section are considered
at various thruster operating conditions. Approximating multiparameter dependence al-
lowing determining the maximum temperature in the model low thruster structure for dif-
ferent values of combustion chamber pressure, the ratio of components, turn-on frequen-
cy and completion factor of pulse mode operation is obtained.
Keywords:
rocket engine, low thrust, pulse mode, thermal state, modeling.
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