Open AccessOn the question of solid-propellant rocket engine design preventing unstable operation in the combustion chamber
Author(s) -
Г. А. Глебов,
С. А. Высоцкая
Publication year - 2017
Publication title -
vestnik koncerna vko «almaz - antej»
Language(s) - English
Resource type - Journals
ISSN - 2542-0542
DOI - 10.38013/2542-0542-2017-4-63-72
Subject(s) - propellant , combustion chamber , rocket engine , chamber pressure , aerospace engineering , combustion , solid fuel rocket , liquid propellant rocket , mechanics , rocket (weapon) , materials science , engineering , physics , chemistry , organic chemistry
The paper presents results of a numerical investigation concerning the effect that the flow duct shape and combustion rate equation have on the gas dynamic vortex flow pattern and self-excited pressure oscillations in the combustion chamber of a solid-propellant rocket engine. We provide guidelines on upgrading solid-propellant rocket engines in order to decrease the magnitude of pressure pulses in the case of pulsating combustion.