Comprehensive Data Reduction for N<sub>2</sub>O/HDPE Hybrid Rocket Motor Performance Evaluation
Static firing tests of a hybrid rocket motor using liquid nitrous oxide (N<sub>2</sub>O) 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, characte...
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doaj-ea87a9d432724580b55d5793c89c21a32020-11-25T01:51:59ZengMDPI AGAerospace2226-43102019-04-01644510.3390/aerospace6040045aerospace6040045Comprehensive Data Reduction for N<sub>2</sub>O/HDPE Hybrid Rocket Motor Performance EvaluationLandon Kamps0Kazuhito Sakurai1Yuji Saito2Harunori Nagata3Department of Mechanical and Space Engineering, Hokkaido University, Sapporo 060-8628, JapanDepartment of Mechanical and Space Engineering, Hokkaido University, Sapporo 060-8628, JapanDepartment of Aerospace Engineering, Tohoku University, Sendai 980-8579, JapanFaculty of Engineering, Hokkaido University, Sapporo 060-8628, JapanStatic firing tests of a hybrid rocket motor using liquid nitrous oxide (N<sub>2</sub>O) 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 (<i>c</i><sup>∗</sup>) 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 <i>c</i><sup>∗</sup> efficiency histories of around 2.5 s, after which <i>c</i><sup>∗</sup> 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.https://www.mdpi.com/2226-4310/6/4/45ballistic reconstruction techniquefuel regressionnozzle erosion<i>c<sup>∗</sup></i> efficiency |
collection |
DOAJ |
language |
English |
format |
Article |
sources |
DOAJ |
author |
Landon Kamps Kazuhito Sakurai Yuji Saito Harunori Nagata |
spellingShingle |
Landon Kamps Kazuhito Sakurai Yuji Saito Harunori Nagata Comprehensive Data Reduction for N<sub>2</sub>O/HDPE Hybrid Rocket Motor Performance Evaluation Aerospace ballistic reconstruction technique fuel regression nozzle erosion <i>c<sup>∗</sup></i> efficiency |
author_facet |
Landon Kamps Kazuhito Sakurai Yuji Saito Harunori Nagata |
author_sort |
Landon Kamps |
title |
Comprehensive Data Reduction for N<sub>2</sub>O/HDPE Hybrid Rocket Motor Performance Evaluation |
title_short |
Comprehensive Data Reduction for N<sub>2</sub>O/HDPE Hybrid Rocket Motor Performance Evaluation |
title_full |
Comprehensive Data Reduction for N<sub>2</sub>O/HDPE Hybrid Rocket Motor Performance Evaluation |
title_fullStr |
Comprehensive Data Reduction for N<sub>2</sub>O/HDPE Hybrid Rocket Motor Performance Evaluation |
title_full_unstemmed |
Comprehensive Data Reduction for N<sub>2</sub>O/HDPE Hybrid Rocket Motor Performance Evaluation |
title_sort |
comprehensive data reduction for n<sub>2</sub>o/hdpe hybrid rocket motor performance evaluation |
publisher |
MDPI AG |
series |
Aerospace |
issn |
2226-4310 |
publishDate |
2019-04-01 |
description |
Static firing tests of a hybrid rocket motor using liquid nitrous oxide (N<sub>2</sub>O) 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 (<i>c</i><sup>∗</sup>) 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 <i>c</i><sup>∗</sup> efficiency histories of around 2.5 s, after which <i>c</i><sup>∗</sup> 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. |
topic |
ballistic reconstruction technique fuel regression nozzle erosion <i>c<sup>∗</sup></i> efficiency |
url |
https://www.mdpi.com/2226-4310/6/4/45 |
work_keys_str_mv |
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