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

2016-07-B36390.R2 - SOURCE FILE.pdf1.05 MBPDF見る/開く

タイトル: Method for Determining Nozzle-Throat-Erosion History in Hybrid Rockets
著者: Kamps, Landon 著作を一覧する
Saito, Yuji 著作を一覧する
Kawabata, Ryosuke 著作を一覧する
Wakita, Masashi 著作を一覧する
Totani, Tsuyoshi 著作を一覧する
Takahashi, Yusuke 著作を一覧する
Nagata, Harunori 著作を一覧する
発行日: 2017年11月
出版者: The American Institute of Aeronautics and Astronautics
誌名: Journal of propulsion and power
巻: 33
号: 6
開始ページ: 1369
終了ページ: 1377
出版社 DOI: 10.2514/1.B36390
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.
資料タイプ: article (author version)
出現コレクション:雑誌発表論文等 (Peer-reviewed Journal Articles, etc)

提供者: Kamps Landon Thomas


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