{"created":"2023-06-20T15:02:54.184272+00:00","id":31992,"links":{},"metadata":{"_buckets":{"deposit":"66e5a31a-7871-479d-9f03-f22f56a72d5e"},"_deposit":{"created_by":1,"id":"31992","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"31992"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00031992","sets":["1887:1890","1896:1898:1899:1910"]},"author_link":["406918","406921","406919","406920"],"item_9_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Trajectory Optimization of Solar-electric Spacecrafts for Near-earth Mission : Considering the Radiation Damage of Solar Cells"}]},"item_9_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1968-04","bibliographicIssueDateType":"Issued"},"bibliographicIssueNumber":"2","bibliographicPageEnd":"324","bibliographicPageStart":"307","bibliographicVolumeNumber":"4","bibliographic_titles":[{"bibliographic_title":"東京大学宇宙航空研究所報告"}]}]},"item_9_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"ある軌道傾斜角をもった出発軌道上にある飛しょう体を,電気推進によるらせん飛しょう(準円軌道を仮定する)で徐々に軌道を拡大させると共に,軌道傾斜角を変化させて,赤道面上の静止英英軌道に遷移させるための最適遷移径路を求める.ただし飛しょう体の推力は一定とし,推力の軌道面内成分の方向が,速度ベクトルの方向と一致しているとき,与えられた初期重量から出発して,静止衛星軌道にのるペイロード重量が最大になるような飛しょう径路を見いだすことを最適化の対象とした.次に飛しょう体のエネルギー源を太陽熱とし,エネルギー変換器として太陽電池を使用した場合,太陽電池のふく射による劣化を考慮にいれて操舵の最適化を行なった.その際バンーアレン帯中の陽子のフラックス形状の近似式を作ると共に,太陽電池の表面に必要なカバーガラスの重量を,飛しょう体が全遷移期間中に沿びる放射線粒子の総個数に比例するとして,最適化問題にくりこんだ.結果は,太陽電池を用いた電気推進による軌道遷移においては,電池の耐性放射性がペイロード最大化という問題で果たす役割は比較的大きく,飛しょう体の操舵計画も耐性放射線によってかなり左右することを示している.","subitem_description_type":"Abstract"}]},"item_9_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"The transfer orbit of a solar powered spacecraft form an inclined parking orbit to the synchronous orbit is optimized to give the maximum payload weight, under the assumptions that the thrust magnitude is constant and that the in-plane thrust direction is tangential. In addition, the case is considered where the silicon solar cells are used for the energy converter, taking account of the influense of the radiation protector on the payload weight. In the computation, the simplified model of proton flux contours in the Van-Allen radiation belt is used and it is assumed that the degradation of the solar cell is proportional to the time-integrated flux during the mission time. The required protector weight is determined on the base of 25% degradation. The trajectory of the solar powered spacecraft must be optimized, taking account of the influence of the radiation protector weight.","subitem_description_type":"Other"}]},"item_9_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: SA0125073000","subitem_description_type":"Other"}]},"item_9_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"東京大学宇宙航空研究所"}]},"item_9_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"0563-8100","subitem_source_identifier_type":"ISSN"}]},"item_9_source_id_24":{"attribute_name":"書誌レコードID","attribute_value_mlt":[{"subitem_source_identifier":"AN00161914","subitem_source_identifier_type":"NCID"}]},"item_9_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"東京大学大学院"},{"subitem_text_value":"東京大学宇宙航空研究所"}]},"item_9_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Bulletin of the Institute of Space and Aeronautical Science University of Tokyo"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"上杉, 邦憲"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"長友, 信人"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"UESUGI, Kuninori","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"NAGATOMO, Makoto","creatorNameLang":"en"}],"nameIdentifiers":[{}]}]},"item_files":{"attribute_name":"ファイル情報","attribute_type":"file","attribute_value_mlt":[{"accessrole":"open_date","date":[{"dateType":"Available","dateValue":"2020-01-24"}],"displaytype":"detail","filename":"SA0125073.pdf","filesize":[{"value":"960.5 kB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"SA0125073.pdf","url":"https://jaxa.repo.nii.ac.jp/record/31992/files/SA0125073.pdf"},"version_id":"78ee1e7a-acb4-426e-9811-c15e18526d7e"}]},"item_language":{"attribute_name":"言語","attribute_value_mlt":[{"subitem_language":"jpn"}]},"item_resource_type":{"attribute_name":"資源タイプ","attribute_value_mlt":[{"resourcetype":"departmental bulletin paper","resourceuri":"http://purl.org/coar/resource_type/c_6501"}]},"item_title":"太陽熱ロケットにおける低推力飛しょう径路の最適化 : 太陽電池のふく射による劣化を考慮して","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"太陽熱ロケットにおける低推力飛しょう径路の最適化 : 太陽電池のふく射による劣化を考慮して"}]},"item_type_id":"9","owner":"1","path":["1890","1910"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"31992","relation_version_is_last":true,"title":["太陽熱ロケットにおける低推力飛しょう径路の最適化 : 太陽電池のふく射による劣化を考慮して"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T00:44:19.739049+00:00"}