Fuel Regression Characteristics of Axial-Injection End-Burning Hybrid Rocket Using Nitrous Oxide

Abstract

This study is an investigation of fuel regression characteristics in an axial-injection endburning hybrid rocket using nitrous oxide. Experiments were conducted using ϕ 38 mm cylindrical fuel grains with an array of 0.8 mm ports made from curable. Previous studies of end-burning hybrid rockets used gaseous oxygen as the oxidizer. Nitrous oxide may be more suitable than the gaseous oxygen for use in space-based missions because of the weight savings associated with the oxidizer storage vessels, supply system, and motor mass. In this study, two types of nozzle closures were employed to increase the initial chamber pressure and promote

Modelling of Hybrid Rocket Flow-Fields with Computational Fluid Dynamics

“…Every regression rate is regarded as the crucial parameter which has the consequences of the first order on the engine design and thus on the engine performance [14,15]. The regression rate is dependent on the oxidizer mass flux rate, indicating that the rate at which the fuel burns is proportional to the amount of oxidizer flowing through the port, according to the governing equation for hybrid rocket combustion.…”