Design and characterization of a lab-scale hybrid rocket test stand
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© 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. Hybrid rockets have unique advantages over their pure solid or liquid counterparts, but low regression rates and comparatively low combustion efficiencies limit their potential. Innovative and novel fuel formulations are needed to solve these problems and are being developed at Texas A&M University. In the current paper, a theoretical hybrid rocket model was developed and utilized to size fuel grains, a combustion chamber, injector, and nozzle. The combustion chamber can accommodate fuel grains of 5-12 cm in length with initial combustion port diameters of 2-20 mm. Data reduction procedures were developed and utilized to analyze preliminary motor firings of plain hydroxyl terminated polybutadiene (HTPB) burning in gaseous oxygen (GOX). Regression rate data from preliminary motor firings at moderate oxidizer mass fluxes (2-12 g/cm2-s) agree well with literature after accounting for the effects of motor scale. The lab-scale hybrid rocket facility will prove an effective tool for evaluating novel fuel formulations.
author list (cited authors)
Thomas, J. C., Stahl, J. M., Morrow, G. R., & Petersen, E. L.