@article{oai:jaxa.repo.nii.ac.jp:00021655,
 author = {小林, 弘明 and 杵淵, 紀世志 and 更江, 渉 and 梅村, 悠 and 藤本, 圭一郎 and 薮崎, 大輔 and 杉森, 大造 and 姫野, 武洋 and 佐藤, 哲也 and 北古賀, 智史 and 角, 悠輝 and 坂本, 勇樹 and 野中, 聡 and 藤田, 猛 and Kobayashi, Hiroaki and Kinefuchi, Kiyoshi and Sarae, Wataru and Umemura, Yutaka and Fujimoto, Keiichiro and Yabusaki, Daisuke and Sugimori, Daizo and Himeno, Takehiro and Sato, Tetsuya and Kitakoga, Satoshi and Sumi, Yuki and Sakamoto, Yuki and Nonaka, Satoshi and Fujita, Takeshi},
 issue = {5},
 journal = {日本航空宇宙学会論文集, Journal of the Japan Society for Aeronautical and Space Sciences},
 month = {Oct},
 note = {The Japan Aerospace Exploration Agency launched the S-310-43 sounding rocket from the Uchinoura Space Center on Aug. 04, 2014 for the purpose of investigating such behavior as boiling and flow of cryogenic liquid rocket propellant in an environment simulating coasting flight on orbit by using the sounding rocket's sub-orbital ballistic flight. In the low-gravity state, the cryogenic fluid (liquid nitrogen) was introduced into the test sections of similar shapes to the flow channels in the cryogenic propulsion systems. The boiling of liquid nitrogen inside the test-sections and the transition of flow regimes from gas/liquid two-phase flow to liquid mono-phase flow were visualized. The temperatures, pressures and void fractions of each channels were measured as well. Development of the experimental equipment for S-310-43 sounding rocket is described in this paper., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: DS1540301003},
 pages = {188(14)--196(22)},
 title = {ロケット慣性飛行中の二相流挙動および熱伝達特性の観測実験: 実験装置部の開発},
 volume = {63},
 year = {2015}
}