@article{oai:muroran-it.repo.nii.ac.jp:00008565,
 author = {笹木, 康平 and SASAKI, Kohei and 飯島, 明日香 and IIJIMA, Asuka and 中田, 大将 and NAKATA, Daisuke and 湊,  亮二郎 and MINATO, Ryojiro and 棚次,  亘弘 and TANATSUGU, Nobuhiro and 杉岡,  正敏 and SUGIOKA, Masatoshi and 東野,  和幸 and HIGASHINO, Kazuyuki and 石本, 真二 and ISHIMOTO, Shinji and 東,  伸幸 and AZUMA, Nobuyuki},
 journal = {室蘭工業大学紀要, Memoirs of the Muroran Institute of Technology},
 month = {Mar},
 note = {application/pdf, The feasibility of GG cycle reusable rocket engine is examined in this study based on the requirements of JAXA reference mission. Bioethanol is used as fuel and LOX is used as oxidizer. The combustion chamber pressure, the expansion ratio and the fuel injection temperature are set to 7 MPaA, 25 and 390 K. As a result, 0.6 in its turbine/pomp efficiency and 0.954 in its Isp efficiency are needed to satisfy the mission requirements. Besides, the experimental study was conducted to confirm the validity of anticorrosion coating on A6061 alloy in high-pressure and high-temperature ethanol., 特集 : 航空宇宙機システム研究センターにおける開発研究2 : 1. オオワシII飛行にむけて並びに関連技術の研究開発（推進系）},
 pages = {3--8},
 title = {将来輸送系リファレンスシステムの推進系に関する基礎検討},
 volume = {64},
 year = {2015},
 yomi = {ササキ, コウヘイ and イイジマ, アスカ and ナカタ, ダイスケ and ミナト, リョウジロウ and タナツグ, ノブヒロ and スギオカ, マサトシ and ヒガシノ, カズユキ and イシモト, シンジ and アズマ, ノブユキ}
}