This paper is the second part of a study conducted to investigate the dynamic behavior of a liquid propellant rocket engine. It is dedicated to complete the modeling, simulation and analysis of the dynamic behavior of the feeding system of a typical rocket engine. The elements involved are the gas generator, the turbo-pump assembly, and the combustion chamber. These individual elements are treated as separate units before dealing with the integrated system. The system incorporates the combustion chamber controller, the thrust controller, the gas generator controller, and the safety valve. Non-linear mathematical models and empirical relations have been deduced and used to develop computer simulation programs using MATLAB SIMULINK technique. The study was extended to investigate the static and dynamic behaviors of such components. The study showed that the thrust reaches always a new steady state value corresponding to pre-compression distance of the thrust controller spring and through regulating the combustion chamber pressure. The system, which has two power ratings, operates at a stable, self-regulated condition with slightly under-damped nature of settling time in switching from first to second power rating. The developed simulation programs could help investigate and analyze other similar liquid propellant rocket engines.