Numerical study of the hybrid rocket engine

Abstract

Hybrid rocket engines have gathered significant attention due to their ease of use, safety, and affordability associated with traditional chemical propulsion systems. They offer the advantage of on-demand throttle and thrust adjustments. The performance of hybrid rocket engines depends on the regression rate, which is the transition of the solid fuel grain to flammable gas. Unlike solid and liquid engines, hybrids experience varying oxidizer-to-fuel (O/F) ratios over time. Factors such as changes in oxidizer flow and fuel port diameter contribute to this fluctuation, leading to incomplete combustion and reduced efficiency. To enhance hybrid rocket engine performance, ongoing research explores various methods. One approach is increasing the oxidizer flow velocity over the burning fuel surface. This paper employs analytical and numerical techniques to determine the effective oxidizer/fuel ratio for a single-port fuel grain in a hybrid rocket engine. Ultimately, the research aims to optimize performance, allowing this secure and efficient propulsion technology to mature.