Quasi-Stationary Mathematical Model of Hybrid Rocket Engine Combustion Chamber

Abstract

This paper presents a quasi-stationary one-dimensional mathematical model of the combustion chamber of a hybrid rocket engine. The model is based on stationary balance equations, considering time-varying input parameters. It makes it possible to quickly estimate the variability of parameters such as pressure, velocity, or temperature of gases inside the combustion chamber during engine operation. In addition, the assumption of a global paraffin oxidation reaction in nitrous oxide allows the determination of the composition of the exhaust gases. The results are consistent with numerical data from other researchers available in the literature.