{"created":"2023-06-20T15:03:12.022366+00:00","id":32339,"links":{},"metadata":{"_buckets":{"deposit":"f5f361e0-5d6e-4988-8f44-85ca9c6d12dc"},"_deposit":{"created_by":1,"id":"32339","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"32339"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00032339","sets":["1887:1890","1896:1898:1899:1910"]},"author_link":["408423","408421","408419","408424","408420","408422"],"item_9_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"RADIO GUIDANCE CONCEPT. PART I."}]},"item_9_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1972-07","bibliographicIssueDateType":"Issued"},"bibliographicIssueNumber":"3_A","bibliographicPageEnd":"701","bibliographicPageStart":"665","bibliographicVolumeNumber":"8","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":"人工衛星の打上げにおいて,現在は最終段ロケットの打出し姿勢角のみがあらかじめ設定された方向へ制御されているが,それまでに受ける外乱が大きいため,達成軌道は予定値からずれる可能性がある.この外乱は追跡レーダにより実時間で算定されるので,この情報をもとに最終段ロケットを制御することにより軌道精度をあげる可能性がある.現在の打上げ方式は,前段の弾道軌道頂点で,局地水平方向に最終段ロケットを打出すため,頂点に達するまでかなりの時間がある.したがって,打出しまえに,弾道軌道を推定し,最終段ロケットの最適制御則を求め,これらの結果を飛しょう体へ指令することが可能であり,電波誘導方式は比較的簡単な装置およびプログラムで実現される.","subitem_description_type":"Abstract"}]},"item_9_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"At the present launch of the satellite, only the attitude of the final stage motor is controlled to the predetermined direction, and attained orbit of the satellite may differ from the nominal value because of the disturbances suffered before. Since these disturbances can be known by a real time tracking radar, there are some possibilities to improve the accuracy of the orbit by controlling the final motor according to that information. At present, the final motor is injected to the local horizontal direction at the apogee point of the preceding suborbit and there are considerably a lot of time for the vehicle to reach the apogee. Therefore, it is possible to estimate the suborbital parameters, solve the optimum control law for the final motor and command these results to the vehicle before the injection, and the radio guidance system is realized with relatively simple software and hardware. In this paper, the basic concepts and criterion of the guidance system are discussed from a practical viewpoint, and the algorithm are obtained to get the optimum direction and ignition time for the motor that optimize the orbit of the satellite on the condition that the preceding suborbit is estimated with sufficient accuracy. The adaptability of the algorithm for practical experiments is assured by the numerical examples applied to some typical flight test data previously obtained.","subitem_description_type":"Other"}]},"item_9_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: SA0125535000","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":"石谷, 久"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"前田, 行雄"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"玉木, 康子"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"ISHITANI, Hisashi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"MAEDA, Yukio","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":"SA0125535.pdf","filesize":[{"value":"2.4 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"SA0125535.pdf","url":"https://jaxa.repo.nii.ac.jp/record/32339/files/SA0125535.pdf"},"version_id":"de5edf89-883e-4ca9-b532-622600dd4962"}]},"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":"電波誘導方式(I)","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"電波誘導方式(I)"}]},"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":"32339","relation_version_is_last":true,"title":["電波誘導方式(I)"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T00:34:55.212347+00:00"}