{"created":"2023-06-20T15:11:26.956801+00:00","id":41106,"links":{},"metadata":{"_buckets":{"deposit":"7274d3ad-4b63-4ac7-a1d7-0634b50eb1bd"},"_deposit":{"created_by":1,"id":"41106","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"41106"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00041106","sets":["1887:1893","1896:1898:1933:1934"]},"author_link":["501582","501583"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"A study of flight trajectories to lunar orbits via low thrust propulsion and gravity capture"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1995-03-31","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"22","bibliographicPageStart":"1","bibliographic_titles":[{"bibliographic_title":"宇宙開発事業団技術報告"},{"bibliographic_title":"NASDA Technical Memorandum","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"通常イオンエンジンのような電気推進では3000秒以上の高い比推力が得られ、宇宙機の燃料重量比を大幅に低減することが可能である。たとえば、低高度の地球周回軌道から低高度の月周回軌道への飛行の場合、燃料重量比率は従来の化学ロケットではおおよそ80%程度であるが、イオンエンジンなどによる電気推進では20%程度となり、月や惑星の探査ミッションで高い比推力をもつイオンエンジンなどを利用することは小型の探査用宇宙機を実現する上で大変有望である。この報告書ではイオンエンジンなどのような極めて低い推進加速度で実現可能な飛行経路の成立条件と生成方法について報告し、これに基づく飛行経路の数値計算例を示した。検討結果は大きく5項目に分かれており、それぞれの項目の内容は次の通りである。(1)飛行経路の構成と生成条件:低推力飛行経路の概要と構成、螺旋軌道の性質と生成、月捕捉軌道の性質と生成、Q点半径の存在域、Q点に関する制約条件、月捕捉可能なQ点存在域の計算例、(2)低推力軌道変換:螺旋上昇軌道変換、軌道面変換、P遷移軌道における離心率増加、Q遷移軌道における離心率減少、螺旋降下軌道変換、(3)月捕捉軌道の数値計算例:極進入飛行経路、赤道進入飛行経路、(4)軌道制御:P遷移フェーズでの軌道制御、慣性飛行フェーズでの軌道制御、Q遷移フェーズでの軌道制御、(5)結論","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Usually high specific propulsion of not less than 3,000 sec. can be achieved from electric propulsion such as ion engines, and this can be utilized to substantially decrease the fuel/weight ratio of space vehicles. In case of flight from low earth orbit to low lunar orbit, for example, fuel/weight ratio of space vehicle is about 20 percent with ion engines, as compared to about 80 percent with conventional chemical engines. Use of ion engines with high specific propulsion is largely beneficial for lunar and planetary expedition vehicles, as smaller space vehicles can be utilized for those missions. This report presents consideration to achieve feasible flight path with low propulsion acceleration with ion engines and methods to obtain such flight path. Numerical calculations for the flight path are also presented.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0004125000","subitem_description_type":"Other"}]},"item_3_description_33":{"attribute_name":"レポート番号","attribute_value_mlt":[{"subitem_description":"レポート番号: NASDA-TMR-950006","subitem_description_type":"Other"}]},"item_3_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"宇宙開発事業団"}]},"item_3_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"National Space Development Agency of Japan (NASDA)"}]},"item_3_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"1345-7888","subitem_source_identifier_type":"ISSN"}]},"item_3_source_id_24":{"attribute_name":"書誌レコードID","attribute_value_mlt":[{"subitem_source_identifier":"AN00364784","subitem_source_identifier_type":"NCID"}]},"item_3_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"宇宙開発事業団 技術研究本部システム技術研究部"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"National Space Development Agency of Japan Systems Engineering Department, Office of Research and Development"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"山脇, 功次"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Yamawaki, Koji","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":"2020-02-10"}],"displaytype":"detail","filename":"04125000.pdf","filesize":[{"value":"1.9 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"04125000.pdf","url":"https://jaxa.repo.nii.ac.jp/record/41106/files/04125000.pdf"},"version_id":"27b773ca-be54-441d-a8f6-468e6c29f7e1"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"イオンエンジン","subitem_subject_scheme":"Other"},{"subitem_subject":"電気推進","subitem_subject_scheme":"Other"},{"subitem_subject":"比推力","subitem_subject_scheme":"Other"},{"subitem_subject":"燃料重量比","subitem_subject_scheme":"Other"},{"subitem_subject":"低高度地球周回軌道","subitem_subject_scheme":"Other"},{"subitem_subject":"低高度月周回軌道","subitem_subject_scheme":"Other"},{"subitem_subject":"化学ロケット","subitem_subject_scheme":"Other"},{"subitem_subject":"月探査ミッション","subitem_subject_scheme":"Other"},{"subitem_subject":"惑星探査ミッション","subitem_subject_scheme":"Other"},{"subitem_subject":"小型探査宇宙機","subitem_subject_scheme":"Other"},{"subitem_subject":"飛行経路","subitem_subject_scheme":"Other"},{"subitem_subject":"数値計算","subitem_subject_scheme":"Other"},{"subitem_subject":"低推力推進","subitem_subject_scheme":"Other"},{"subitem_subject":"重力捕捉","subitem_subject_scheme":"Other"},{"subitem_subject":"ion engines","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"electric propulsion","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"specific propulsion","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"fuel weight ratio","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"low earth orbit","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"low lunar orbit","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"chemical engines","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"lunar exploration mission","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"planetary exploration mission","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"small space vehicle","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"flight trajectory","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"numerical calculation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"low propulsion flight path","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"gravity capture","subitem_subject_language":"en","subitem_subject_scheme":"Other"}]},"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":"technical report","resourceuri":"http://purl.org/coar/resource_type/c_18gh"}]},"item_title":"低推力推進と重力捕捉による月飛行経路の検討","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"低推力推進と重力捕捉による月飛行経路の検討"}]},"item_type_id":"3","owner":"1","path":["1893","1934"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"41106","relation_version_is_last":true,"title":["低推力推進と重力捕捉による月飛行経路の検討"],"weko_creator_id":"1","weko_shared_id":1},"updated":"2023-06-20T19:13:54.896419+00:00"}