@inproceedings{oai:jaxa.repo.nii.ac.jp:00016654,
 author = {岸田, 佳晃 and 真島, 悠樹 and 堀澤, 秀之 and Kishida, Yoshiaki and Mashima, Yuki and Horisawa, Hideyuki},
 book = {宇宙輸送シンポジウム: 講演集録, Proceedings of Space Transportation Symposium},
 month = {Jan},
 note = {平成21年度宇宙輸送シンポジウム(2010年1月14日-15日, 宇宙航空研究開発機構宇宙科学研究本部), Space Transportation Symposium (January 14-15, 2010. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)),  Sagamihara, Kanagawa Japan, Experimental investigation of impulse-bit and propellant consumption rate, or mass shot, per single pulse discharge was conducted to characterize the thrust performance of the rectangular laser-electromagnetic hybrid acceleration thruster with various propellant materials. From the result, alumna propellant showed significantly superior performance. The largest values of the measured impulse-bit, specific impulse and thrust efficiency were 49 microNsec, 6,200 sec and 22%, respectively., 形態: カラー図版あり, 形態: CD-ROM1枚, Physical characteristics: Original contains color illustrations, Note: One CD-ROM, 資料番号: AA0064741084},
 publisher = {宇宙航空研究開発機構宇宙科学研究本部, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)},
 title = {矩形型レーザ・電磁加速複合推進機の作動特性評価},
 volume = {平成21年度},
 year = {2010}
}