TY - GEN
T1 - Solid fuel regression measurements rate using an optical hybrid rocket engine
AU - Over, Dillon J.
AU - Ianuzzi, Makayla L.L.
AU - Moore, Jeffrey D.
AU - Risha, Grant A.
N1 - Funding Information:
The authors wish to thank the Penn State Altoona Research and Sponsored Programs Office and Mr. Corey Griffin for sponsoring this internally funded effort. Special thanks to Mr. Tim Deibler and Deibler Machining, LLC for machining of the entire optical hybrid rocket engine and components.
Publisher Copyright:
© 2019 by American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2019
Y1 - 2019
N2 - The focus of this research work was to develop an optical hybrid rocket engine that regression rates, various flame characteristics, and other chamber characteristics can be measured using conventional cinematography. For the current experimental series, hydroxyl-terminated polybutadiene (HTPB) or nylon PA66 fuels and gaseous oxygen were the reactants. Images of both the plume and the chamber interior were ascertained since the chamber was equipped with quartz and Plexiglas windows at capture rates from 2000 to 4000 frames per second. From the fourteen experimental test fires, the quartz windows were used for five tests and sustained the combustion event while maintaining a steady-state pressure of approximately 1.0 to 3.5 MPa. The gaseous oxygen was delivered at mass flow rates of 35 to 75 g/s and the thrust levels produced were 130 to 300 N.
AB - The focus of this research work was to develop an optical hybrid rocket engine that regression rates, various flame characteristics, and other chamber characteristics can be measured using conventional cinematography. For the current experimental series, hydroxyl-terminated polybutadiene (HTPB) or nylon PA66 fuels and gaseous oxygen were the reactants. Images of both the plume and the chamber interior were ascertained since the chamber was equipped with quartz and Plexiglas windows at capture rates from 2000 to 4000 frames per second. From the fourteen experimental test fires, the quartz windows were used for five tests and sustained the combustion event while maintaining a steady-state pressure of approximately 1.0 to 3.5 MPa. The gaseous oxygen was delivered at mass flow rates of 35 to 75 g/s and the thrust levels produced were 130 to 300 N.
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U2 - 10.2514/6.2019-4069
DO - 10.2514/6.2019-4069
M3 - Conference contribution
AN - SCOPUS:85095978841
SN - 9781624105906
T3 - AIAA Propulsion and Energy Forum and Exposition, 2019
BT - AIAA Propulsion and Energy Forum and Exposition, 2019
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Propulsion and Energy Forum and Exposition, 2019
Y2 - 19 August 2019 through 22 August 2019
ER -