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Verification Firings of End-Burning Type Hybrid Rockets

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Title: Verification Firings of End-Burning Type Hybrid Rockets
Authors: Nagata, Harunori Browse this author →KAKEN DB
Teraki, Hayato Browse this author
Saito, Yuji Browse this author
Kanai, Ryuichiro Browse this author
Yasukochi, Hiroyuki Browse this author
Wakita, Masashi Browse this author →KAKEN DB
Totani, Tsuyoshi 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: 1473
End Page: 1477
Publisher DOI: 10.2514/1.B36359
Abstract: The authors have previously proposed the concept of end-burning-type hybrid rockets, which would use cylindrical fuel grains consisting of an array of many small ports running in the axial direction, through which oxidizer gas would flow. Because of difficulty in manufacturing a fuel grain that satisfied requirements such as high volumetric filling rate (above 0.95) and microsized port intervals, the end-burning hybrid rocket had yet to be achieved. This paper reports the results of verification firing tests of a novel end-burning-type hybrid rocket made possible for the first time by recent progress in three-dimensional printing technology. The results clearly distinguish the initial transient and steady periods of the end-burning mode and prove that no oxidizer-to-fuel ratio shift occurs during firing. Because the initial transient is a period for the exit end face to attain a steady-state shape, an initial end-face shape being close to the steady-state shape can shorten this period. A firing test with fuel having tapered ports is shown to attain a steady-state shape in less than 1s, which is much shorter than the nontapered case of about 6 seconds.
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: 永田 晴紀

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