{"created":"2023-06-20T15:03:09.436189+00:00","id":32282,"links":{},"metadata":{"_buckets":{"deposit":"58d9203c-4776-4116-b570-5b4a2b33b88a"},"_deposit":{"created_by":1,"id":"32282","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"32282"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00032282","sets":["1887:1890","1896:1898:1899:1910"]},"author_link":["408111","408109","408110","408113","408114","408112"],"item_9_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"On the extremum of the perigee height of a satellite orbit"}]},"item_9_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1971-07","bibliographicIssueDateType":"Issued"},"bibliographicIssueNumber":"3","bibliographicPageEnd":"708","bibliographicPageStart":"694","bibliographicVolumeNumber":"7","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":"人口衛星の打上げにおいては,現在制御されていない打上げロケットの受ける外乱のために予定軌道と異なっても,可能なかぎり衛星軌道に投入することが望ましく,このためには前段軌道および最終投ロケットモータによる速度増分が与えられたという条件で(最終段ロケットの)点火時刻および打出し方向とを制御して最終軌道の近地点高度を最大にすることが必要な場合がある.これは,数学的には単に前段軌道上の打出し位置および打出し方向との2変数の関数の極値問題に過ぎないが,仝変域について解析したものは見当らない様である.本文において最終軌道が円軌道になる場合を除き,この問題をすべての条件について検討した結果,遠近地点の極値は,いわゆる「Hohmann移行」か直線軌道となる場合のみに存在することが示された.これらの結果は,おのおのの条件に従って誘導される.また数値計算例は,この結果に矛盾のないことを示す.","subitem_description_type":"Abstract"}]},"item_9_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"At the launch of the satellite, it is desirable to put the satellite into an earth orbit as far as possible, even if the attained orbit may be different from the predetermined one because of the disturbance of the launch vehicles which cannot be controlled now. In order to attain this purpose, it is necessary to maximize the perigee height of the final orbit by controlling the ignition time and the direction of the final motor on the condition that the suborbit of the preceeding vehicle and the total impulse of the additional velocity obtained by the motor are given and estimated. Though it is mathematically a mere extremum problem of the function of two variables, position on the preceding suborbit and the launching direction of the final motor, it seems that this problem is not analysed in the full range of the variables due to the difficulties in the calculation containing the trigonometric function. In this paper, this problem is analyzed for all conditions except when the final orbit becomes circular one, and it is shown that the extremum of the perigee or apogee height exists only in the so-called 'Hohmann Transfer' or in the condition when the final orbit becomes linear one. These results are derived individually in each condition and some numerical example is computed, from which the validity of results is assured.","subitem_description_type":"Other"}]},"item_9_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: SA0125451000","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":"東京大学宇宙航空研究所"},{"subitem_text_value":"東京大学宇宙航空研究所"},{"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":"Institute of Space and Aeroautical Science University of Tokyo"},{"subitem_text_language":"en","subitem_text_value":"Institute of Space and Aeroautical Science University of Tokyo"},{"subitem_text_language":"en","subitem_text_value":"Institute of Space and Aeroautical Science University of Tokyo"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"浜崎, 襄二"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"石谷, 久"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"玉木, 康子"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"HAMASAKI, Joji","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"ISHITANI, Hisashi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"TAMAKI, Yasuko","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":"SA0125451.pdf","filesize":[{"value":"782.9 kB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"SA0125451.pdf","url":"https://jaxa.repo.nii.ac.jp/record/32282/files/SA0125451.pdf"},"version_id":"0779766a-7f5b-4d07-ae7c-684005f33a91"}]},"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":"速度インパルスによる軌道推移における達成軌道高度の極値について","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"速度インパルスによる軌道推移における達成軌道高度の極値について"}]},"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":"32282","relation_version_is_last":true,"title":["速度インパルスによる軌道推移における達成軌道高度の極値について"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T00:36:33.470936+00:00"}