宇宙エネルギー利用システムの研究:フォーメーションフライトにより構成されるSSPS

Material type: 文書・図像類

Author: 武市, 昇ほか

Publisher: 宇宙航空研究開発機構

Publication date: 2004-10-29

Material Format: Digital

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Note (General)：: This paper presents a new concept of a solar power satellite system configured by formation flying (Formation-Flying Solar Power Satellite: FF-SPS). I...

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Material Type: 文書・図像類
Title: 宇宙エネルギー利用システムの研究:フォーメーションフライトにより構成されるSSPS
Author/Editor: 武市, 昇
上野, 浩史
小田, 光茂
Takeichi, Noboru
Ueno, Hiroshi
Oda, Mitsushige
Author Heading: 武市, 昇
上野, 浩史
小田, 光茂
Takeichi, Noboru
Ueno, Hiroshi
Oda, Mitsushige
Publication, Distribution, etc.: 宇宙航空研究開発機構
Publication Date: 2004-10-29
Publication Date (W3CDTF): 2004-10-29
Alternative Title: A study of the space energy utilization: Solar power satellite system configured by formation flying
Periodical title: 宇宙航空研究開発機構研究開発資料: 平成15年度総合技術研究本部宇宙領域研究成果報告書:先行研究等 = JAXA Research and Development Memorandum: FY15 Annual Report of Research & Development on Space Technology in the Institute of Space Technology and Aeronautics: Advanced Technology
No. or year of volume/issue: JAXA-RM-04-011
Volume: JAXA-RM-04-011
Pages: 7-12
ISSN (Periodical Title): ISSN : 1349-1121
Text Language Code: jpn
Subject Heading: 宇宙エネルギー利用
太陽発電
太陽光
太陽発電衛星
編成飛行
反射板
FEM
マイクロ波
space energy utilization
solar generator
sunlight
solar power satellite
formation flying
reflector
microwave
Target Audience: 一般
Note (General): This paper presents a new concept of a solar power satellite system configured by formation flying (Formation-Flying Solar Power Satellite: FF-SPS). In this concept, the solar power satellite system consists of sunlight reflectors and an Earth-pointing segment. The Earth-pointing segment is on a common GEO, and the reflectors are placed on the north and south by using solar pressure to raise their orbits from GEO. Therefore, the orbits of the reflectors and that of the Earth-pointing segment make three parallel GEOs. The feasibility is also discussed focusing on the orbital and attitude mechanics of the reflector. Through some analyses, it is shown that the required propellant for the control of the formation flying SPS is about a few 10 percent larger than that for previous concepts. The structural feasibility is also discussed through FEM analyses. It is revealed that it is possible to assemble the lightweight reflector structure with sufficient stiffness using deployable structures based on current technologies. Although FF-SPS requires more control propellant than previous concepts, its feasibility is technologically equivalent to previous ones. FF-SPS is the first concept that has both Earth-pointing and Sun-pointing segments without any single point of failure.
資料番号: AA0048129002
レポート番号: JAXA-RM-04-011
Access Restrictions: 限定公開
Periodical Title (NCID): AA11983593
https://ci.nii.ac.jp/ncid/AA11983593
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