{"created":"2023-06-19T12:44:25.317151+00:00","id":3899,"links":{},"metadata":{"_buckets":{"deposit":"78e10bac-0c3c-4c37-ade0-57ef46d87308"},"_deposit":{"created_by":3,"id":"3899","owners":[3],"pid":{"revision_id":0,"type":"depid","value":"3899"},"status":"published"},"_oai":{"id":"oai:tokyo-metro-u.repo.nii.ac.jp:00003899","sets":["1647:634:635"]},"author_link":["11868","11869","11870","11871","11872","11873"],"control_number":"3899","item_6_biblio_info_7":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2005","bibliographicIssueDateType":"Issued"},"bibliographicIssueNumber":"1","bibliographicPageEnd":"11","bibliographicPageStart":"1","bibliographicVolumeNumber":"21","bibliographic_titles":[{"bibliographic_title":"The Journal of Space Technology and Science"}]}]},"item_6_creator_2":{"attribute_name":"著者(ヨミ)","attribute_type":"creator","attribute_value_mlt":[{"nameIdentifiers":[{"nameIdentifier":"11870","nameIdentifierScheme":"WEKO"}]},{"nameIdentifiers":[{"nameIdentifier":"11871","nameIdentifierScheme":"WEKO"}]}]},"item_6_creator_3":{"attribute_name":"著者別名","attribute_type":"creator","attribute_value_mlt":[{"nameIdentifiers":[{"nameIdentifier":"11872","nameIdentifierScheme":"WEKO"}]},{"nameIdentifiers":[{"nameIdentifier":"11873","nameIdentifierScheme":"WEKO"}]}]},"item_6_description_4":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"To develop an experimental small hybrid rocket with a swirling gaseous oxygen flow type engine, we made a flight model engine. Burning tests of the engine showed that a maximum thrust of 692 N and a specific impulse of 263 s (at sea level) were achieved. We designed a small hybrid rocket with this engine. The rocket measured 1.8 m in length and 15.4 kg in mass. To confirm the flight stability of the rocket, wind tunnel tests using a 112-scale model of the rocket and simulations of the flight attitude and trajectory were carried out. A flight test was conducted at Taiki-cho, Hokkaido, Japan on March 2001. The rocket reached an altitude of about 600 m, thus recording the first successful flight of a hybrid rocket in Japan. For the next stage, future issues to develop larger hybrid rockets using a swirling liquid oxygen flow type engine are discussed, and preliminary burning tests of the engine have been carried out.","subitem_description_type":"Abstract"}]},"item_6_description_40":{"attribute_name":"資源タイプ","attribute_value_mlt":[{"subitem_description":"Article","subitem_description_type":"Other"}]},"item_6_publisher_33":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"日本ロケット協会"}]},"item_6_relation_43":{"attribute_name":"関係","attribute_value_mlt":[{"subitem_relation_type":"isVersionOf","subitem_relation_type_id":{"subitem_relation_type_id_text":"https://dx.doi.org/10.11230/jsts.21.1_1","subitem_relation_type_select":"DOI"}}]},"item_6_rights_13":{"attribute_name":"権利","attribute_value_mlt":[{"subitem_rights":"日本ロケット協会"}]},"item_6_source_id_10":{"attribute_name":"書誌レコードID","attribute_value_mlt":[{"subitem_source_identifier":"AA10925183","subitem_source_identifier_type":"NCID"}]},"item_6_source_id_8":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"0911-551X","subitem_source_identifier_type":"PISSN"}]},"item_6_version_type_16":{"attribute_name":"著者版フラグ","attribute_value_mlt":[{"subitem_version_resource":"http://purl.org/coar/version/c_ab4af688f83e57aa","subitem_version_type":"AM"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"Yuasa, Saburo","creatorNameLang":"en"},{"creatorName":"湯浅, 三郎","creatorNameLang":"ja"},{"creatorName":"ユアサ, サブロウ","creatorNameLang":"ja-Kana"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kitagawa, Koki","creatorNameLang":"en"},{"creatorName":"北川, 幸樹","creatorNameLang":"ja"},{"creatorName":"キタガワ, コウキ","creatorNameLang":"ja-Kana"}],"nameIdentifiers":[{}]}]},"item_files":{"attribute_name":"ファイル情報","attribute_type":"file","attribute_value_mlt":[{"accessrole":"open_date","date":[{"dateType":"Available","dateValue":"2016-08-04"}],"displaytype":"detail","filename":"10638-001.pdf","filesize":[{"value":"218.4 kB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"10638-001.pdf","url":"https://tokyo-metro-u.repo.nii.ac.jp/record/3899/files/10638-001.pdf"},"version_id":"fa5d653a-5f17-4ca7-b137-18490074429a"}]},"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":"journal article","resourceuri":"http://purl.org/coar/resource_type/c_6501"}]},"item_title":"Current status of rocket developments in universities -development of a small hybrid rocket with a swirling oxidizer flow type engine","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"Current status of rocket developments in universities -development of a small hybrid rocket with a swirling oxidizer flow type engine","subitem_title_language":"en"}]},"item_type_id":"6","owner":"3","path":["635"],"pubdate":{"attribute_name":"PubDate","attribute_value":"2013-12-24"},"publish_date":"2013-12-24","publish_status":"0","recid":"3899","relation_version_is_last":true,"title":["Current status of rocket developments in universities -development of a small hybrid rocket with a swirling oxidizer flow type engine"],"weko_creator_id":"3","weko_shared_id":-1},"updated":"2023-11-25T02:55:11.743182+00:00"}