Numerical modeling of hybrid rocket engine

Abstract

Recent development in space mission demands safer and more cost-effective space missions. Hybrid rocket engine technological advancements have prolonged a critical stage in their development and it is the better option for such space missions, as it has a lot of advantages over the solid rocket motor and liquid rocket engine. It is simple in design, has high thrust density, low weight, and is safer than a liquid rocket engine. It has restarted capability, safe, low explosion risk, and high specific impulse than a solid rocket motor. This paper shows the numerical analysis of a hybrid rocket engine. The paper highlights the initial boundary conditions in the analysis of a 300-N hybrid rocket engine. The process started with a chemical kinematic examination of engine-compatible fuels and oxidizers. This investigation provided the fundamental parameters required for the design and subsequent dimensioning of a hybrid rocket engine. It also produced a three-dimensional design model, performed numerical analysis using ANSYS software, and validated the findings using existing literature. Using the k–\(\varepsilon\) turbulence model and transient solver on 8 mm port diameter for analyzing. The computational fluid dynamics model offered the qualities of a real hybrid rocket engine and it will be helpful to researchers and the scientific community in the future.