@inproceedings{oai:jaxa.repo.nii.ac.jp:00016230,
 author = {小林, 直人 and 常松, 春霞 and 浅沼, 和貴 and 人見, 亮輔 and 堀澤, 秀之 and 船木, 一幸 and Kobayashi, Naoto and Tsunematsu, Haruka and Asanuma, Kazuki and Hitomi, Ryosuke and Horisawa, Hideyuki and Funaki, Ikko},
 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, Observation of the micro-nozzle discharges was conducted, and a new thruster with extended nozzle structure for which each electrode element was electrically isolated from nearby elements was developed. The typical values of the thrust, specific impulse and averaged per nozzle element of the 6x6 micro-plasmajet array thruster operated at 27 W with 37.5 mg/sec of propellant mass flow per nozzle element were 39 mN, 107 sec, 33 % respectively., 形態: カラー図版あり, 形態: PDF, Physical characteristics: Original contains color illustrations, Physical characteristics: PDF, 資料番号: AA0061856094, レポート番号: STEP-2012-011},
 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 = {マイクロ・マルチ・プラズマジェット・アレイ推進機の高性能化},
 year = {2013}
}