@techreport{oai:jaxa.repo.nii.ac.jp:00047371,
 author = {和田, 明哲 and 飯塚, 俊明 and 佐原, 宏典 and 各務, 聡 and 渡邊, 裕樹 and 船瀬, 龍 and 羽生, 宏人 and WADA, Asato and IIZUKA, Toshiaki and SAHARA, Hironori and KAKAMI, Akira and WATANABE, Hiroki and FUNASE, Ryu and HABU, Hiroto},
 month = {Feb},
 note = {In order to obtain the exploration flexibility by the propulsion control technology of the micro-spacecraft, it is important to optimize the propulsion system. The objective of this paper is evaluated the trade-off of the chemical propulsion (CP) systems, the electric propulsion (EP) systems, and the combined CP and EP systems with shared propellant for 100 kg-class micro-spacecraft. As a result, it was confirmed that the effectiveness of combined CP and EP system with shared the high energetic propellant was clarified. In addition, at the higher thruster operation ratio for reaction control, it is necessary that the thruster performance is improved by using the higher thermal potential propellant. At the higher delta-V for orbit maneuver, it was confirmed that the integration propulsion systems of the higher thrust density are validity., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA2030017003, レポート番号: JAXA-RR-20-008},
 title = {宇宙探査に向けた統合型推進システムのトレードオフ評価},
 year = {2021}
}