Method for Determining Nozzle-Throat-Erosion History in Hybrid Rockets

Kamps, Landon; Saito, Yuji; Kawabata, Ryosuke et al.

Journal of propulsion and power, 2017, 33(6), 1369-1377

Permalink : https://hdl.handle.net/2115/67733

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アクセス権
open access
URI
https://hdl.handle.net/2115/67733
タイトル
Method for Determining Nozzle-Throat-Erosion History in Hybrid Rockets
著者
Kamps, Landon ; Saito, Yuji ; Kawabata, Ryosuke ; Wakita, Masashi ; Totani, Tsuyoshi ; Takahashi, Yusuke ; Nagata, Harunori
著者名
Kamps, Landon
著者名
Saito, Yuji
著者名
Kawabata, Ryosuke
e-Rad_Researcher
80451441
著者名
Wakita, Masashi
e-Rad_Researcher
00301937
著者名
Totani, Tsuyoshi
e-Rad_Researcher
40611132
著者名
Takahashi, Yusuke
e-Rad_Researcher
40281787
著者名
Nagata, Harunori
言語
英語
発行日
2017-11
出版者
The American Institute of Aeronautics and Astronautics
収録物名
Journal of propulsion and power
巻(号)
33(6)
ページ
1369-1377
抄録
The authors of this paper introduce a new reconstruction technique titled nozzle-throat reconstruction technique to estimate nozzle-throat-erosion history and oxidizer-to-fuel-mass-ratio history in hybrid rockets. Nine static-firing tests were carried out on a 2kN-class cascaded multistage impinging-jet-type hybrid-rocket motor under varying oxidizer-flow rates to evaluate the accuracy of reconstructed results. Nozzle-throat-erosion histories calculated by the nozzle-throat reconstruction technique agreed well with measured values for initial nozzle-throat radius, and successfully reconstructed the case, in which no measurable amount of nozzle-throat erosion occurred. For equivalence ratios 0.6-1.4, the relationship between nozzle-throat-erosion rate and equivalence ratio of reconstructed results displays a trend consistent with chemical-kinetic-limited heterogeneous-combustion theory, as well as predictions made by previous researchers.
資源タイプ
学術雑誌論文
出版タイプ
Accepted Manuscript
PISSN
0748-4658
関連情報 (isVersionOf)
出版社版DOI
https://doi.org/10.2514/1.B36390