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

Material type: 文書・図像類

Author: 和田, 明哲ほか

Publisher: 宇宙航空研究開発機構(JAXA)

Publication date: 2021-02-12

Material Format: Digital

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Note (General)：: In order to obtain the exploration flexibility by the propulsion control technology of the micro-spacecraft, it is important to optimize the propulsio...

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Material Type: 文書・図像類
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
Author/Editor: 和田, 明哲
飯塚, 俊明
佐原, 宏典
各務, 聡
渡邊, 裕樹
船瀬, 龍
羽生, 宏人
WADA, Asato
IIZUKA, Toshiaki
SAHARA, Hironori
KAKAMI, Akira
WATANABE, Hiroki
FUNASE, Ryu
HABU, Hiroto
Author Heading: 和田, 明哲
飯塚, 俊明
佐原, 宏典
各務, 聡
渡邊, 裕樹
船瀬, 龍
羽生, 宏人
WADA, Asato
IIZUKA, Toshiaki
SAHARA, Hironori
KAKAMI, Akira
WATANABE, Hiroki
FUNASE, Ryu
HABU, Hiroto
Publication, Distribution, etc.: 宇宙航空研究開発機構(JAXA)
Publication Date: 2021-02-12
Publication Date (W3CDTF): 2021-02-12
Alternative Title: Trade-Off Evaluation of the Integration Propulsion Systems for Space Explorations
Periodical title: 宇宙航空研究開発機構研究開発報告: 将来深宇宙探査に向けた革新的超小型推進系研究グループ 2020年度研究成果報告書 = JAXA Research and Development Report: Technical Report of the Research Activity for Innovative Micro Propulsion Systems for Future Deep Space Explorations (2020)
No. or year of volume/issue: JAXA-RR-20-008
Volume: JAXA-RR-20-008
Pages: 13-19
ISSN (Periodical Title): ISSN : 2433-2216
Text Language Code: jpn
Subject Heading: Micro-Propulsion
Integration Propulsion System
Micro-spacecraft
Deep Space Exploration
Target Audience: 一般
Note (General): 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
DOI: 10.20637/00047358
Access Restrictions: 限定公開
Data Provider (Database): 国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
https://irdb.nii.ac.jp
Original Data Provider (Database): 宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ