{"created":"2023-06-20T15:12:45.031101+00:00","id":42625,"links":{},"metadata":{"_buckets":{"deposit":"ee6ea7c1-1b3a-4cc7-bc40-952ccc2fc956"},"_deposit":{"created_by":1,"id":"42625","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"42625"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00042625","sets":["1887:1893","1896:1898:1933:1934"]},"author_link":["502341","502340"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Orbital design to Ulysses-type solar polar orbit by solar electric propulsion system"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2002-02-28","bibliographicIssueDateType":"Issued"},"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":"日本の惑星科学分野において、2020年頃までの将来計画のビジョンを描く作業が進められており、太陽極軌道を実現して、黄道面から大きく離れた空間から太陽磁場、黄道光、星間塵、赤外線宇宙背景放射などを観測する事の有効性が認識されている。NASAとESAの共同ミッションとして1990年10月に打ち上げられたユリシーズ(Ulysses)の軌道は木星swingbyを利用して実現された太陽極軌道であり、黄道面から大きく離れる点で上記のミッションに適した軌道の1つである。本報告では、この軌道をユリシーズ型太陽極軌道と呼び、この軌道を電気推進系を使って効率的に実現する事を検討する。軌道計画法として、EΔV-EGA法(電気推進加速による地球重力アシスト法)を使用する。EΔV-EGA法は、地球swingby時の地球との相対速度が約6km/sまでの場合において効率が良い方法である。しかし、ユリシーズ型太陽極軌道を実現するためには、地球から直接木星に向かう場合、12km/s程度の地球出発時V(sub infinity)が必要となる。軌道計画の検討においては、地球重力アシストの効率を上げるために地球との相対速度をできるだけ抑える事、電気推進系の開発を容易にするために必要な推力を小さくする事、が重要となる。EΔV-EGA法により地球swingbyした後も電気推進系の最大噴射を利用する事で、ペイロード質量を減らす事なく、地球との相対速度を小さくでき、且つ電気推進系の必要な推力を小さくできる事を示した。C(sub 3)=0の軌道における初期質量500kgの場合、ペイロード質量が最大となるのは、日心距離1AUにおけるノミナル推力が約130mNの時であり、約219kgのペイロード質量をユリシーズ型太陽極軌道に投入できる結果を得た。必要な最大推力は約169mNとなる。この推力を実現できない場合、ノミナル推力90mNでも195kgのペイロード質量を投入でき、最大推力は118mNまで下がる。現在、日本において150mN推力のイオン・エンジンの研究開発が進められており、本報告の結果は、電気推進系を使用したユリシーズ型太陽極軌道の実現可能性を大きくするものである。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"In the field of planetary science in Japan, future vision up to about 2020 is being made. In that work, the observation of the solar magnetic field, the zodiacal light, the interstellar dusts, and the infrared cosmic background radiation from the points far away from the ecliptic plane is thought to be promising. The orbit of the Ulysses launched in 1990 as the joint mission between NASA and ESA is the solar polar orbit realized by the Jupiter swingby and is one of the adequate orbits, since the maximum deviation of the orbit from the ecliptic plane is large. This orbit is called the Ulysses-type solar polar orbit, and is investigated to realize this orbit efficiently by the solar electric propulsion system. The EDeltaV-EGA is applied as the method of orbital design. The EDeltaV-EGA is efficient when the relative velocity at infinity at Earth swingby is less than about 6km/s. In order to realize the Ulysses-type solar polar orbit, however, the starting relative velocity at infinity of about 12 km/s is required when the spacecraft goes directly to the Jupiter. In the orbital design, suppressing both the relative velocity to the Earth and the necessary thrust of the solar electric propulsion system is important. The former is for improving the efficiency at the Earth gravity assist, and the latter is for reducing the difficulty at the development of the solar electric propulsion system. It has been shown that suppressing both the relative velocity to the Earth and the necessary thrust of the solar electric propulsion system without reducing the payload mass is capable by thrusting even after the Earth gravity assist. In the initial spacecraft mass of 500 kg at the orbit of C(sub 3) = 0, the maximum payload mass of 219 kg was injected into the Ulysses-type solar polar orbit at the nominal thrust of 130 mN. 'Nominal' means the value at 1AU from the Sun. Required maximum thrust was 169 mN. When this thrust value cannot be realized, the nominal thrust of 90 mN can realize the payload mass of 195 kg. In that case, required maximum thrust becomes as small as 118 mN. Currently in Japan, the ion propulsion system with the thrust of 150 mN is being developed. The results of this report will enlarge the possibility of the realization of the Ulysses-type solar polar orbit by the solar electric propulsion system.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0033135000","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-010021","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"}]},"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 Office of Research and Department"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"歌島, 昌由"}],"nameIdentifiers":[{"nameIdentifier":"502340","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"Utashima, Masayoshi","creatorNameLang":"en"}],"nameIdentifiers":[{"nameIdentifier":"502341","nameIdentifierScheme":"WEKO"}]}]},"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":"33135000.pdf","filesize":[{"value":"4.1 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"33135000.pdf","url":"https://jaxa.repo.nii.ac.jp/record/42625/files/33135000.pdf"},"version_id":"7657b62d-c31d-4f5e-b031-50a242b2f10c"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"太陽極軌道","subitem_subject_scheme":"Other"},{"subitem_subject":"太陽電気推進","subitem_subject_scheme":"Other"},{"subitem_subject":"太陽磁場","subitem_subject_scheme":"Other"},{"subitem_subject":"Ulyssesミッション","subitem_subject_scheme":"Other"},{"subitem_subject":"スイングバイ技術","subitem_subject_scheme":"Other"},{"subitem_subject":"地球重力","subitem_subject_scheme":"Other"},{"subitem_subject":"推力","subitem_subject_scheme":"Other"},{"subitem_subject":"システムエンジニアリング","subitem_subject_scheme":"Other"},{"subitem_subject":"solar polar orbit","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"solar electric propulsion","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"solar magnetic field","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Ulysses mission","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"swingby technique","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Earth gravitation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"thrust","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"systems engineering","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":"電気推進系によるユリシーズ型太陽極軌道への軌道設計","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"電気推進系によるユリシーズ型太陽極軌道への軌道設計"}]},"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":"42625","relation_version_is_last":true,"title":["電気推進系によるユリシーズ型太陽極軌道への軌道設計"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T20:24:57.394282+00:00"}