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

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Title: Method for Determining Nozzle-Throat-Erosion History in Hybrid Rockets
Authors: Kamps, Landon Browse this author
Saito, Yuji Browse this author
Kawabata, Ryosuke Browse this author
Wakita, Masashi Browse this author →KAKEN DB
Totani, Tsuyoshi Browse this author →KAKEN DB
Takahashi, Yusuke Browse this author →KAKEN DB
Nagata, Harunori Browse this author →KAKEN DB
Issue Date: Nov-2017
Publisher: The American Institute of Aeronautics and Astronautics
Journal Title: Journal of propulsion and power
Volume: 33
Issue: 6
Start Page: 1369
End Page: 1377
Publisher DOI: 10.2514/1.B36390
Abstract: 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.
Type: article (author version)
Appears in Collections:工学院・工学研究院 (Graduate School of Engineering / Faculty of Engineering) > 雑誌発表論文等 (Peer-reviewed Journal Articles, etc)

Submitter: Kamps Landon Thomas

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