Comprehensive data reduction for N 2 O/HDPE hybrid rocket motor performance evaluation

Landon Kamps, Kazuhito Sakurai, Yuji Saito, Harunori Nagata

研究成果: Article査読

13 被引用数 (Scopus)

抄録

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.

本文言語English
論文番号45
ジャーナルAerospace
6
4
DOI
出版ステータスPublished - 2019 4月 1

ASJC Scopus subject areas

  • 航空宇宙工学

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