Orbit Verification Results of the De-Orbit Mechanism Demonstration CubeSat FREEDOM, Trans. Jpn. Soc. Aerinaut. Space Sci

• 資料種別: 記事
• タイトル: Orbit Verification Results of the De-Orbit Mechanism Demonstration CubeSat FREEDOM, Trans. Jpn. Soc. Aerinaut. Space Sci
• 著者標目: UTO Hiroki; KUWAHARA Toshinori; HONDA Tomoyuki
• 出版年月日等: 2019
• 出版年（W3CDTF）: 2019
• タイトル（掲載誌）: TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN
• 巻号年月日等（掲載誌）: 17 3
• 掲載巻: 17
• 掲載号: 3
• 掲載ページ: 295-300
• 掲載年月日（W3CDTF）: 2019
• ISSN（掲載誌）: 18840485
• ISSN-L（掲載誌）: 18840485
• 出版事項（掲載誌）: THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
• 本文の言語コード: en
• 件名標目: De-Orbit Mechanism; Space Debris; CubeSat; International Space Station
• 対象利用者: 一般
• イベントの日付、場所: International Symposium on Space Technology and Science
• DOI: 10.2322/tastj.17.295; https://doi.org/10.2322/tastj.17.295
• オンライン閲覧公開範囲: インターネット公開
• 関連情報（URI）: http://hdl.handle.net/10097/00132012; https://tohoku.repo.nii.ac.jp/records/134622; https://www.jstage.jst.go.jp/article/tastj/17/3/17_17.295/_pdf
• 参照: Attitude control of spin-type space membrane structures using electromagnetic force in earth orbit; https://cir.nii.ac.jp/crid/1360298337105203840; System Design, Development and Ground Verification of a Separable De-Orbit Mechanism for the Orbital Manoeuvre of Micro-Satellite ALE-1; https://cir.nii.ac.jp/crid/1390287907269899264; Time-of-Flight Monitoring Camera System of the De-orbiting Drag Sail for Microsatellite ALE-1; https://cir.nii.ac.jp/crid/1390289302760263424; Proposal of Deployable Membrane Coil Effective for Deorbiting of Small Satellites from Low-Earth Orbit; https://cir.nii.ac.jp/crid/1390300700249455744; 地球低軌道における電磁力を用いた宇宙展開膜面構造物の展開; https://cir.nii.ac.jp/crid/1390571106619513984; Space Demonstration of Boom Extension and De-orbit Sail Deployment of the Separable De-orbit Mechanism of Micro-satellite ALE-1; https://cir.nii.ac.jp/crid/1390575971012516608; On-Board Computers for Micro-Satellites; https://cir.nii.ac.jp/crid/1390851553098921216
• 参照: Kibo’s contribution to broadening the possibilities for Micro-Satellite; https://cir.nii.ac.jp/crid/1360011146611804160; NRLMSISE‐00 empirical model of the atmosphere: Statistical comparisons and scientific issues; https://cir.nii.ac.jp/crid/1361137045175448832
• 連携機関・データベース: 国立情報学研究所 : CiNii Research; https://cir.nii.ac.jp/
• 提供元機関・データベース: Japan Link Center; https://japanlinkcenter.org/top; 学術機関リポジトリデータベース; https://irdb.nii.ac.jp; Crossref; https://www.crossref.org; CiNii Articles
• NII論文ID: 130007642476

• 要約等: <p>Nakashimada Engineering Works, Ltd. and Tohoku University have developed a 1U-size CubeSat “FREEDOM”. The mission of FREEDOM is to demonstrate a thin film deployment mechanism called the De-Orbit Mechanism (DOM) for space debris prevention, and includes deployment of the thin film, early de-orbiting, and tracking of its orbit transition. FREEDOM was released into low Earth orbit from the International Space Station using the robotic arm of the Japanese Experiment Module “Kibo” on January 16, 2017. The initial altitude of FREEDOM was approximately 410 km. The transition of the orbit of FREEDOM was monitored by obtaining the publicly available two line elements. FREEDOM fell below an altitude of 250 km on February 6, 2017 and is considered to have re-entered into the Earth atmosphere approximately one day later. FREEDOM stayed in orbit approximately 22 days. This result agrees with the numerical estimates and proves that FREEDOM succeeded in the deployment of the film and early de-orbiting.</p>
• DOI: 10.2322/tastj.17.295
• オンライン閲覧公開範囲: インターネット公開
• 連携機関・データベース: 科学技術振興機構 : J-STAGE; http://www.jstage.jst.go.jp

• オンライン閲覧公開範囲: インターネット公開
• 関連情報: 出版社サイト; https://www.jstage.jst.go.jp/article/tastj/17/3/17_17.295/_article/-char/ja/
• 関連情報（DOI）: 10.2322/tastj.17.295; https://doi.org/10.2322/tastj.17.295
• 連携機関・データベース: 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
• 提供元機関・データベース: 東北大学 : 東北大学機関リポジトリ TOUR