Characterization of Combustion in a Hybrid Rocket Motor Paraffin-Based

Date
2014-07-13
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Publisher
44th International Conference on Environmental Systems
Abstract

A hybrid rocket motor is an intermediate choice between solid and liquid propulsion systems. The use of paraffin as fuel increases the regression rate because of the formation of droplets originated from a process of hydrodynamic instability on the oxidant-fuel interface. Chamber pressure is measured in a laboratory test with a hybrid configuration that uses paraffin and gaseous oxygen. In addition, a numerical solution of the continuity equation is applied to the combustion chamber, using an algorithm that takes into account physical and thermo chemical properties of the propellants as well as the internal geometry of the motor. Finally, numerical and experimental results are compared.

Description
Tucson, Arizona
The 44th International Conference on Environmental Systems was held in Tuscon, Arizona, USA on 13 July 2014 through 17 July 2014.
Saulo A. Gómez, Instituto Tecnologico de Aeronáutica, USA
Shirley Pedreira, Instituto Tecnologico de Aeronáutica, USA
Pedro Lacava, Instituto Tecnologico de Aeronáutica, USA
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