@inproceedings{oai:jaxa.repo.nii.ac.jp:00016253,
 author = {齋藤, 翔平 and 浅井, 健太 and 栗田, 哲志 and 福成, 雅史 and 山口, 敏和 and 小紫, 公也 and 小田, 靖久 and 梶原, 健 and 高橋, 幸司 and 坂本, 慶司 and Saito, Shohei and Asai, Kenta and Kurita, Satoshi and Fukunari, Masafumi and Yamaguchi, Toshikazu and Komurasaki, Kimiya and Oda, Yasuhisa and Kajiwara, Ken and Takahashi, Koji and Sakamoto, Keishi},
 book = {平成24年度宇宙輸送シンポジウム: 講演集録, Proceedings of Space Transportation Symposium: FY2012},
 month = {Jan},
 note = {平成24年度宇宙輸送シンポジウム (2013年1月17日-1月18日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)), 相模原市, 神奈川県, Space Transportation FY2012 (January 17-18, 2013. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, Microwave rocket is one of BEP (Beamed Energy Propulsion) systems. It is expected as a future low cost transportation system for large-scale infrastructure constructions like SSPS (Space Solar Power System). Microwave rocket can realize high payload ratio because it can use the atmospheric air as a propellant during its flight in atmosphere. However, a launch experiment with a kg class thruster was not conducted in the past study. The reason for this is impulse decrement due to refilling problem and low power density due to long distance beam transmission. In this study, these problems are resolved and the launch experiment with a kg class thruster is conducted., 形態: カラー図版あり, 形態: PDF, Translation title: Launch experiment results of kg class microwave rocket, Physical characteristics: Original contains color illustrations, Physical characteristics: PDF, 資料番号: AA0061856117, レポート番号: STEP-2012-034},
 pages = {1--5},
 publisher = {宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS), Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)},
 title = {kg級マイクロ波ロケットの打上げ実証実験報告},
 year = {2013}
}