TY - JOUR
T1 - Comprehensive data reduction for N 2 O/HDPE hybrid rocket motor performance evaluation
AU - Kamps, Landon
AU - Sakurai, Kazuhito
AU - Saito, Yuji
AU - Nagata, Harunori
N1 - Funding Information:
The authors would like to recognize the hard work of the students of the Hokkaido University hybrid rocket systems research team Erika Uchiyama, Taku Inoue, Hanako Ikeda, Seiji Itoh, Lisa Kageyama, and Terutaka Okuda in assisting in the experiments conducted for this study. Furthermore, this research relied heavily on the expert technical support of Kato of the Hokkaido University workshop. This research is supported by the Grant-in-Aid for Japan Society for the Promotion of Science (JSPS) fellows 18J2087708, as well as by a matching fund program of Centers for Inter-University Collaboration from ISAS (Institute of Space and Astronautical Science), JAXA (Japan Aerospace Exploration Agency)
Funding Information:
Funding: This research is supported by the Grant-in-Aid for Japan Society for the Promotion of Science (JSPS) fellows 18J2087708, as well as by a matching fund program of Centers for Inter-University Collaboration from ISAS (Institute of Space and Astronautical Science), JAXA (Japan Aerospace Exploration Agency).
Publisher Copyright:
© 2019 by the authors.
PY - 2019/4/1
Y1 - 2019/4/1
N2 - Static firing tests of a hybrid rocket motor using liquid nitrous oxide (N 2 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 (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.
AB - Static firing tests of a hybrid rocket motor using liquid nitrous oxide (N 2 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 (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.
KW - Ballistic reconstruction technique
KW - C efficiency
KW - Fuel regression
KW - Nozzle erosion
UR - http://www.scopus.com/inward/record.url?scp=85065429572&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=85065429572&partnerID=8YFLogxK
U2 - 10.3390/aerospace6040045
DO - 10.3390/aerospace6040045
M3 - Article
AN - SCOPUS:85065429572
VL - 6
JO - Aerospace
JF - Aerospace
SN - 2226-4310
IS - 4
M1 - 45
ER -