ABSTRACT
This paper presents a part of study conducted to investigate the dynamic behavior of
a rocket propellant rocket engine. The part presented here concerns the modeling,
simulation and analysis of the dynamic behavior of the hydraulic control valves of the
feeding system of the studied rocket engine. The study involves the combustion
chamber, the gas generator controller, the thrust regulator, and the relief valve. For
the studied valves, non-linear mathematical models have been deduced and used to
develop computer simulation programs. The study was extended to investigate the
static and dynamic behaviors of the valves. The study showed that the combustion
chamber and gas generator controllers act to produce a feeding fuel pressure equal
to the oxidizer pressure. The thrust controller, through regulating the combustion
chamber pressure, could keep a fairly constant thrust of the rocket engine. The
developed simulation programs could be used for further investigation of the effect of
the valves constructional and operational parameters as well as the study of dynamic
behavior of the liquid propellant engine.