{"created":"2023-06-20T15:02:44.180722+00:00","id":31819,"links":{},"metadata":{"_buckets":{"deposit":"f332855c-b084-4459-9c43-0bcfe3e59af9"},"_deposit":{"created_by":1,"id":"31819","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"31819"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00031819","sets":["1887:1890","1896:1898:1899:1910"]},"author_link":["406340","406339"],"item_9_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"On the Aeroelastic Characteristics of SSR Rocket"}]},"item_9_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1966-06","bibliographicIssueDateType":"Issued"},"bibliographicIssueNumber":"2_B","bibliographicPageEnd":"569","bibliographicPageStart":"562","bibliographicVolumeNumber":"2","bibliographic_titles":[{"bibliographic_title":"東京大学宇宙航空研究所報告"}]}]},"item_9_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"In this report, the body divergence speed and the nutter speed of tail fins of rocket SSR under the actual flight conditions are analysed. The calculational results show that the flutter margin of tail fins is minimum at about M=l.0, which is about 70% of atmosphere value, and that the body divergence margin becomes to minimum at about 5 seconds after launching, not at the maximum flight speed, which is about 50% of atmosphere value. Both the aeroelastic instabilities did not occur in flight testing.","subitem_description_type":"Other"}]},"item_9_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: SA0124874000","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航空力学部"}]},"item_9_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"the Institute of Space and Aeronautical Science University of Tokyo"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"富田, 文治"}],"nameIdentifiers":[{"nameIdentifier":"406339","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"TOMITA, Bunji","creatorNameLang":"en"}],"nameIdentifiers":[{"nameIdentifier":"406340","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":"2020-01-24"}],"displaytype":"detail","filename":"SA0124874.pdf","filesize":[{"value":"471.2 kB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"SA0124874.pdf","url":"https://jaxa.repo.nii.ac.jp/record/31819/files/SA0124874.pdf"},"version_id":"52192fab-8f57-44bd-9baa-9d9222cf31ef"}]},"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":"II.1.2 シングルステップロケットの空力弾性特性(1 機体および構造)(II.関連研究)","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"II.1.2 シングルステップロケットの空力弾性特性(1 機体および構造)(II.関連研究)"}]},"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":"31819","relation_version_is_last":true,"title":["II.1.2 シングルステップロケットの空力弾性特性(1 機体および構造)(II.関連研究)"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T00:49:38.088413+00:00"}