{"created":"2023-06-20T15:15:00.310673+00:00","id":45036,"links":{},"metadata":{"_buckets":{"deposit":"f49335f0-f1f1-40e2-9557-5d5480ab55db"},"_deposit":{"created_by":1,"id":"45036","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"45036"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00045036","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["472598","472599"],"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1983-08","bibliographicIssueDateType":"Issued"},"bibliographicPageStart":"27","bibliographicVolumeNumber":"778T","bibliographic_titles":[{},{"bibliographic_title":"Technical Report of National Aerospace Laboratory TR-778T","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"微小推力を用いて,地球周回円軌道からスパイラル・レイジング(spiral raising)により脱出軌道速度を達成し,それ以後太陽の中心力場を飛行して目標惑星の公転軌道に到達する最適(最短時間)軌道遷移問題を設定した。新たに開発した3次元探索アルゴリズムを適用して,大型電子計算機により数値解を得た。本問題は,初期時刻t0=0において初期値(出発軌道の位置,速度),途中の時刻t1において総エネルギーE,終端時刻tf(=t1+t2)において終端値(目標惑星公転軌道の位置,速度)の拘束条件を有しており,通常の2点境界値問題ではなく,3点境界値問題に帰着する。質点としての宇宙船の運動は,同一平面内とし,地球引力圏脱出までは地球の中心力場のみ,それ以後は太陽の中心力場のみを考慮するそれぞれ二体問題として扱った。こうした単純化にも拘らず,本問題は,運動方程式が時刻t1で切換り,同時に座標系も切換えるので,位置,速度などの状態変数に見かけ上不連続が生ずるなどの複雑さを含んでいる。推力の大きさ,燃料消費率は一定と仮定しているので,本最適問題のパラメタは操舵角uの探索方向の長さα及びtf,t1の修正分Δtf,Δt1の3つである。この為,3つのパラメタを変動させて評価関数の極値を求めていく3次元探索アルゴリズムを新たに開発して,本問題に適用した。ところで,惑星間飛行の最短時間問題は数多くの研究者によって扱われており,その解t2*はよく知られている。最短時間地球引力圏脱出問題の解t1*は,今回,参考文献3と同様の方法で得られた。数値計算の結果,t1 > t1*,t2 < t2*であるが,t1*とt2*の和よりも短いtf(=t1+t2)が得られた。操舵角の履歴は,引力圏脱出部分で最適脱出問題の解とは極めて異なった,又惑星間飛行部分では類似の特徴をそれぞれ示す。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"A numerical analysis has been carried out on minimum-time low-thrust Earth-Mars transfer including Earth escape spiral trajectory. This is a three-point boundary-value problem with a constraint at the interior point t=t1 when the hyperbolic velocity is attained in the geocentric force field, and the terminal constraints at the final time t=tf(=t1+t2). Minimal time t1* for the Earth escape problem is obtained here by the authors in a manner similar to that in Ref. 3, and t2* for the Earth-Mars heliocentric transfer problem is well-known(e.g., Ref.2, 16). A three-dimensional search procedure using Δt1, Δtf, and the control correction length α as three parameters is developed to solve the present complicated problem numerically. The obtained total mission time tf is slightly shorter than the sum of t1* and t2*. The control history in the escape portion is quite different from that in an optimal escape problem, but in the interplanetary portion it is similar to that in an optimal interplanetary transfer problem.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: NALTR0778000","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: NAL TR-778T","subitem_description_type":"Other"}]},"item_3_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"航空宇宙技術研究所"}]},"item_3_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"National Aerospace Laboratory(NAL)"}]},"item_3_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"0389-4010","subitem_source_identifier_type":"ISSN"}]},"item_3_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"航空宇宙技術研究所宇宙研究グループ"},{"subitem_text_value":"航空宇宙技術研究所宇宙研究グループ"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Space Technology Research Group, National Aerospace Laboratory(NAL)"},{"subitem_text_language":"en","subitem_text_value":"Space Technology Research Group, National Aerospace Laboratory(NAL)"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"YOSHIMURA, Shoichi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"YAMANAKA, Tatsuo","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":"2020-01-29"}],"displaytype":"detail","filename":"naltr0778t.pdf","filesize":[{"value":"1.9 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr0778t.pdf","url":"https://jaxa.repo.nii.ac.jp/record/45036/files/naltr0778t.pdf"},"version_id":"7f50e3b1-f114-43d9-bb06-f8b008828d5a"}]},"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":"technical report","resourceuri":"http://purl.org/coar/resource_type/c_18gh"}]},"item_title":"OPTIMAL LOW-THRUST INTERPLANETARY ORBIT TRANSFER INCLUDING EARTH ESCAPE SPIRAL TRAJECTORY","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"OPTIMAL LOW-THRUST INTERPLANETARY ORBIT TRANSFER INCLUDING EARTH ESCAPE SPIRAL TRAJECTORY","subitem_title_language":"en"}]},"item_type_id":"3","owner":"1","path":["1893","1917"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"45036","relation_version_is_last":true,"title":["OPTIMAL LOW-THRUST INTERPLANETARY ORBIT TRANSFER INCLUDING EARTH ESCAPE SPIRAL TRAJECTORY"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:46:26.775619+00:00"}