{"created":"2023-06-20T14:40:32.359706+00:00","id":7438,"links":{},"metadata":{"_buckets":{"deposit":"24c3cefd-e18e-4fbd-9698-2521366559ca"},"_deposit":{"created_by":1,"id":"7438","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"7438"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00007438","sets":["1543:1544:1556","1887:1891"]},"author_link":["39562","39554","39565","39564","39558","39555","39556","39560","39561","39557","39559","39563"],"item_5_alternative_title_1":{"attribute_name":"その他のタイトル","attribute_value_mlt":[{"subitem_alternative_title":"はやぶさ地球帰還フェーズの軌道決定"}]},"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2008-03","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"5","bibliographicPageStart":"1","bibliographic_titles":[{"bibliographic_title":"第17回アストロダイナミクスシンポジウム講演後刷り集　2007"},{"bibliographic_title":"Proceedings of 17th Workshop on JAXA Astrodynamics and Flight Mechanics","bibliographic_titleLang":"en"}]}]},"item_5_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"「はやぶさ(MUSES-C: Asteroid Sample-return Spacecraft)」は、2005年12月に小惑星を離脱した直後に発生した燃料流出のトラブルにより、地球帰還の予定を2010年6月に変更して航行中である。使用可能なホイールは既に1台のみとなっているため、「はやぶさ」は姿勢制御のために、IES(Ion Engine System)を連続運転して姿勢制御をするか、セーフホールドを維持することが必要である。したがって往路で行ったような軌道決定のために電気推進を一時停止する「3パスコースティング」の手法は姿勢喪失の危険を伴うことになる。本報告では、地球帰還フェーズにおける「はやぶさ」の軌道決定について、小惑星離脱から2007年のIES運用終了までの結果について述べる。","subitem_description_type":"Abstract"}]},"item_5_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Hayabusa (MUSES-C: Asteroid Sample-return Spacecraft) lost its all chemical fuels, and two of three momentum wheels do not work anymore. Under this severe condition, Hayabusa is cruising using its ion engine to get back to the earth in June, 2010. In order to control spacecraft's attitude under only one momentum wheel, Hayabusa has to operate ion engine controlling thrust directions with gimbals continuously, or keep low spin safe-hold. Therefore, it became difficult to make a short ballistic flight for orbit determination among ion engine operations. On the other hand, continuous stable ion engine operation causes less modeling error on ion engine acceleration. In this report, orbit determination after the departure from the target asteroid is described focusing on two point of view; orbit prediction under long term ion engine operation, and orbit determination under low spin safe hold mode.","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0063718001","subitem_description_type":"Other"}]},"item_5_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"宇宙航空研究開発機構宇宙科学研究本部"}]},"item_5_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS)"}]},"item_5_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"富士通"},{"subitem_text_value":"宇宙航空研究開発機構 宇宙科学研究本部"},{"subitem_text_value":"宇宙航空研究開発機構 宇宙科学研究本部"},{"subitem_text_value":"宇宙航空研究開発機構 宇宙科学研究本部"},{"subitem_text_value":"宇宙航空研究開発機構 宇宙科学研究本部"},{"subitem_text_value":"宇宙航空研究開発機構 宇宙科学研究本部"}]},"item_5_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Fujitsu Limited"},{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency Institute of Space and Astronautical Science"},{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency Institute of Space and Astronautical Science"},{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency Institute of Space and Astronautical Science"},{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency Institute of Space and Astronautical Science"},{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency Institute of Space and Astronautical Science"}]},"item_access_right":{"attribute_name":"アクセス権","attribute_value_mlt":[{"subitem_access_right":"metadata only access","subitem_access_right_uri":"http://purl.org/coar/access_right/c_14cb"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"大西, 隆史"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"吉川, 真"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"加藤, 隆二"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"竹内, 央"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"市川, 勉"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"川口, 淳一郎"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Onishi, Takafumi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Yoshikawa, Makoto","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kato, Takaji","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Takeuchi, Hiroshi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Ichikawa, Tsutomu","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kawaguchi, Junichiro","creatorNameLang":"en"}],"nameIdentifiers":[{}]}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"軌道計算","subitem_subject_scheme":"Other"},{"subitem_subject":"軌道決定","subitem_subject_scheme":"Other"},{"subitem_subject":"はやぶさ","subitem_subject_scheme":"Other"},{"subitem_subject":"MUSES-C","subitem_subject_scheme":"Other"},{"subitem_subject":"小惑星探査機","subitem_subject_scheme":"Other"},{"subitem_subject":"姿勢制御","subitem_subject_scheme":"Other"},{"subitem_subject":"測距","subitem_subject_scheme":"Other"},{"subitem_subject":"衛星追尾","subitem_subject_scheme":"Other"},{"subitem_subject":"衛星軌道","subitem_subject_scheme":"Other"},{"subitem_subject":"予測","subitem_subject_scheme":"Other"},{"subitem_subject":"IESデルタV計画","subitem_subject_scheme":"Other"},{"subitem_subject":"イオンエンジン","subitem_subject_scheme":"Other"},{"subitem_subject":"セーフホールドモード","subitem_subject_scheme":"Other"},{"subitem_subject":"精度","subitem_subject_scheme":"Other"},{"subitem_subject":"軌道","subitem_subject_scheme":"Other"},{"subitem_subject":"orbit calculation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"orbit determination","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Hayabusa","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"MUSES-C","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Asteroid Sample-return Spacecraft","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"attitude control","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"rangefinding","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"satellite tracking","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"satellite orbit","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"prediction","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"IES delta-V plan","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"ion engine","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"safe hold mode","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"accuracy","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"trajectory","subitem_subject_language":"en","subitem_subject_scheme":"Other"}]},"item_language":{"attribute_name":"言語","attribute_value_mlt":[{"subitem_language":"eng"}]},"item_resource_type":{"attribute_name":"資源タイプ","attribute_value_mlt":[{"resourcetype":"conference paper","resourceuri":"http://purl.org/coar/resource_type/c_5794"}]},"item_title":"Hayabusa orbit determination after the departure from Itokawa","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"Hayabusa orbit determination after the departure from Itokawa","subitem_title_language":"en"}]},"item_type_id":"5","owner":"1","path":["1556","1891"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"7438","relation_version_is_last":true,"title":["Hayabusa orbit determination after the departure from Itokawa"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T07:39:31.988774+00:00"}