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

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This study investigates the continuous transition from flame-spreading to stabilized combustion near the blow-off limit in opposed forced flow by using expanding solid fuel duct that makes distribution of oxidizer velocity in the axial direction. The stabilized combustion is a diffusion flame that appears in the Axial-Injection End-Burning Hybrid Rocket. The boundary between flame-spreading and stabilized combustion has not been investigated in detail. Polymethyl methacrylate (PMMA) rectangular ducts were used as a fuel, and gaseous oxygen was used as an oxidizer. All firing tests were conducted at atmospheric pressure. The diffusion flame traveled in the opposed-flow field where the oxidizer velocity increases continuously in the upstream direction. The combustion mode changed when oxidizer velocity at the flame tip exceeded a certain value. The oxidizer velocity used in this experiment ranges from 0.6 to 32.8 m/s. Experimental results show that a threshold oxidizer velocity of the transition can be determined. In this study, the threshold velocity was 26.4 m/s.

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