{"created":"2023-06-20T14:40:38.620510+00:00","id":7563,"links":{},"metadata":{"_buckets":{"deposit":"5f30cac5-517a-4a67-b27f-c6dfbd97376f"},"_deposit":{"created_by":1,"id":"7563","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"7563"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00007563","sets":["1543:1544:1557","1887:1891"]},"author_link":["40494","40491","40493","40492"],"item_5_alternative_title_1":{"attribute_name":"その他のタイトル","attribute_value_mlt":[{"subitem_alternative_title":"木星探査における低弾道エアロキャプチャの可能性"}]},"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2007-03","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"370","bibliographicPageStart":"362","bibliographic_titles":[{"bibliographic_title":"第16回アストロダイナミクスシンポジウム講演後刷り集　2006"},{"bibliographic_title":"Proceedings of 16th Workshop on JAXA Astrodynamics and Flight Mechanics","bibliographic_titleLang":"en"}]}]},"item_5_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"エアロキャプチャは、従来の化学推進による手段と比較して、軌道投入に要する推進剤を減らすことが可能であると知られている。 突入飛行経路角のウィンドウや空力加熱環境などの厳しい条件から、これまで実現されたことはなかった。しかし、軽量かつ大面積の膜面を利用した低弾道エアロキャプチャならば、そのようなリスクを避け、実現可能性がある。JAXA将来ミッションとして計画されているソーラセイルミッションでは、母船から分離される小型オービタの木星周回軌道への投入も計画されている。そこで、ソーラセイルに使用された母船の膜面の1部を小型オービタの軌道投入に再利用するとした仮定のもと、エアロキャプチャの木星における実現可能性について検討を行った。","subitem_description_type":"Abstract"}]},"item_5_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"The aerocapture is known to be an orbit insertion technique around planetary body at a fraction of the propellant of the traditional chemical propulsive technique. Severe aerocapture conditions such as the very narrow entry corridor and the aerodynamic heating environment have prevented us from putting it into practical use in a planetary exploration mission. However, the low-ballistic-coefficient aerocapture where an orbiter is connected to the light and wide membrane decelerator has the potential to reduce the risk of the aerocapture. In the Solar Sail mission which is planed as one of the future missions of JAXA, the orbit insertion around Jupiter of the small orbiter which is separated from the mother spacecraft is included. In this paper, we investigated the feasibility of the aerocapture at Jupiter, assuming that a fraction of the Solar Sail membrane of the mother spacecraft was reused in order to insert the separated orbiter into the orbit around Jupiter.","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0063481062","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":"東京大学 大学院工学系研究科"},{"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":"University of Tokyo School of Engineering"},{"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":"古川, 宗孝"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"安部, 隆士"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Furukawa, Munetaka","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Abe, Takashi","creatorNameLang":"en"}],"nameIdentifiers":[{}]}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"エアロキャプチャ","subitem_subject_scheme":"Other"},{"subitem_subject":"ソーラーセイル","subitem_subject_scheme":"Other"},{"subitem_subject":"軌道挿入","subitem_subject_scheme":"Other"},{"subitem_subject":"軌道解析","subitem_subject_scheme":"Other"},{"subitem_subject":"空気力","subitem_subject_scheme":"Other"},{"subitem_subject":"弾道係数","subitem_subject_scheme":"Other"},{"subitem_subject":"ソーラーセイル再利用","subitem_subject_scheme":"Other"},{"subitem_subject":"膜温度限界","subitem_subject_scheme":"Other"},{"subitem_subject":"木星","subitem_subject_scheme":"Other"},{"subitem_subject":"再利用","subitem_subject_scheme":"Other"},{"subitem_subject":"空力加熱","subitem_subject_scheme":"Other"},{"subitem_subject":"計算機シミュレーション","subitem_subject_scheme":"Other"},{"subitem_subject":"モンテカルロ法","subitem_subject_scheme":"Other"},{"subitem_subject":"aerocapture","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"solar sail","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"orbit insertion","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"trajectory analysis","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamic force","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"ballistic coefficient","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"reusing solar sail","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"membrane temperature limit","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Jupiter","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"reuse","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamic heating","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"computerized simulation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Monte Carlo method","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":"Feasibility assessment of low-ballistic-coefficient aerocapture for Jupiter exploration","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"Feasibility assessment of low-ballistic-coefficient aerocapture for Jupiter exploration","subitem_title_language":"en"}]},"item_type_id":"5","owner":"1","path":["1557","1891"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"7563","relation_version_is_last":true,"title":["Feasibility assessment of low-ballistic-coefficient aerocapture for Jupiter exploration"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T07:37:33.597924+00:00"}