{"created":"2023-06-20T15:13:49.658059+00:00","id":43799,"links":{},"metadata":{"_buckets":{"deposit":"a98a309d-3d6a-4332-b4d3-f9dbd1e7b8d8"},"_deposit":{"created_by":1,"id":"43799","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"43799"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00043799","sets":["1887:1893","1896:1898:1913:1916"]},"author_link":["465639","465643","465641","465640","465638","465642"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"An Estimation of Deflection Requirements of An Aero-Stable Solid Propellant Rocket Vehicle"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1972-02","bibliographicIssueDateType":"Issued"},"bibliographicPageStart":"36","bibliographicVolumeNumber":"216","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所資料"},{"bibliographic_title":"Technical Memorandum of National Aerospace Laboratory","bibliographic_titleLang":"en"}]}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"In this paper, are estimated the peak deflection angles and the total injectants required to control an aero-stable solid propellant rocket vehicle (the 1st stage) by SITVC (secondary injection thrust vector control) system. It is desirable to minimize those values under the given constraints; to minimize the aerodynamic load on the body, to minimize the flow rate capacity of the injection valves and to minimize the capacity of the injectants feed system. In order to realize the mini-mum deflection angles, the load relief auto-pilot method is used. A non-gravity-turn nominal trajectory is presented to reduce the effects of wind disturbance. The results of the computer simulation are discussed.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: NALTM0216000","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 TM-216","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":"0452-2982","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":"AN00314334","subitem_source_identifier_type":"NCID"}]},"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"},{"subitem_text_value":"航空宇宙技術研究所角田支所"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"大石, 晃"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"山中, 龍夫"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"冠, 昭夫"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"OOISHI, Akira","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"YAMANAKA, Tatsuo","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"KAMMURI, Akio","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":"2020-01-28"}],"displaytype":"detail","filename":"naltm00216.pdf","filesize":[{"value":"1.5 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltm00216.pdf","url":"https://jaxa.repo.nii.ac.jp/record/43799/files/naltm00216.pdf"},"version_id":"b7a45e44-6021-44ae-be3a-7ce7aeeabb00"}]},"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":"安定板を有する固体ロケットの操舵要求軽減法","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"安定板を有する固体ロケットの操舵要求軽減法"}]},"item_type_id":"3","owner":"1","path":["1893","1916"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"43799","relation_version_is_last":true,"title":["安定板を有する固体ロケットの操舵要求軽減法"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T22:07:40.511343+00:00"}