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Comprehensive Data Reduction for N2O/HDPE Hybrid Rocket Motor Performance Evaluation

1
Department of Mechanical and Space Engineering, Hokkaido University, Sapporo 060-8628, Japan
2
Department of Aerospace Engineering, Tohoku University, Sendai 980-8579, Japan
3
Faculty of Engineering, Hokkaido University, Sapporo 060-8628, Japan
*
Author to whom correspondence should be addressed.
These authors contributed equally to this work.
Aerospace 2019, 6(4), 45; https://doi.org/10.3390/aerospace6040045
Received: 31 January 2019 / Revised: 15 April 2019 / Accepted: 15 April 2019 / Published: 17 April 2019
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Abstract

Static firing tests of a hybrid rocket motor using liquid nitrous oxide (N2O) as the oxidizer and high-density polyethylene (HPDE) as the fuel are analyzed using a novel approach to data reduction that allows histories for fuel mass consumption, nozzle throat erosion, characteristic exhaust velocity (c) efficiency, and nozzle throat wall temperature to be determined experimentally. This is done by firing a motor under the same conditions six times, varying only the burn time. Results show that fuel mass consumption was nearly perfectly repeatable, whereas the magnitude and timing of nozzle throat erosion was not. Correlations of the fuel regression rate result in oxidizer port mass flux exponents of 0.62 and 0.76. There is a transient time in the c efficiency histories of around 2.5 s, after which c efficiency remains relatively constant, even in the case of excessive nozzle throat erosion. Although nozzle erosion was not repeatable, the erosion onset factors were similar between tests, and greater than values in previous research in which oxygen was used as the oxidizer. Lastly, nozzle erosion rates exceed 0.15 mm/s for chamber pressures of 4 to 5 MPa. View Full-Text
Keywords: ballistic reconstruction technique; fuel regression; nozzle erosion; c efficiency ballistic reconstruction technique; fuel regression; nozzle erosion; c efficiency
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Kamps, L.; Sakurai, K.; Saito, Y.; Nagata, H. Comprehensive Data Reduction for N2O/HDPE Hybrid Rocket Motor Performance Evaluation. Aerospace 2019, 6, 45.

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