{"created":"2023-06-20T15:05:09.247931+00:00","id":34410,"links":{},"metadata":{"_buckets":{"deposit":"1e14270f-b74b-4356-b93e-93ffc5591da5"},"_deposit":{"created_by":1,"id":"34410","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"34410"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00034410","sets":["1887:1890","1896:1898:1899:1992"]},"author_link":["419555"],"item_9_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1968-11","bibliographicIssueDateType":"Issued"},"bibliographicIssueNumber":"12","bibliographicPageEnd":"347","bibliographicPageStart":"309","bibliographicVolumeNumber":"33","bibliographic_titles":[{},{"bibliographic_title":"ISAS report/Institute of Space and Aeronautical Science,University of Tokyo","bibliographic_titleLang":"en"}]}]},"item_9_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"A theoretical study for initiation of high-frequency combustion oscillation in the premixed gas rocket was conducted. A generalized wave equation which governs the behavior of pressure disturbances in a chemically reacting flow field was derived through the linearization of the fundamental equations. It was shown that the behavior of pressure disturbances depends only on the variation in heat release rate, being independent of the individual chemical reaction processes through which this variation is provided. It was also shown that the equation can be used for the analysis of heat-driven oscillation when the response of heat source to flow disturbances is known. The space conditon for the occurrence of heat-driven oscillation was found to depend upon the way of response of heat source to flow disturbances, while the time condition was found to be independent of it. For the occurrence of high-frequency combustion oscillation in the premixed gas rocket, a simplified analytical model of heat-driven oscillation with an insensitive time delay was postulated on the basis of the previous experimental studies. The incipient amplification rate of the oscillation was calculated as the function of propellant equivalence ratio and combustion chamber length. The calculated oscillation boundary was found to correlate very well with the experimentally observed boundary.","subitem_description_type":"Other"}]},"item_9_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: SA2400608000","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_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"Institute of Space and Aeronautical Science,University of Tokyo"}]},"item_9_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"0372-1418","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":"AA00675986","subitem_source_identifier_type":"NCID"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"TAKENO, Tadao","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":"SA2400608.pdf","filesize":[{"value":"3.0 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"SA2400608.pdf","url":"https://jaxa.repo.nii.ac.jp/record/34410/files/SA2400608.pdf"},"version_id":"7fb7a984-fe39-448f-8640-7c13d8c750b4"}]},"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":"departmental bulletin paper","resourceuri":"http://purl.org/coar/resource_type/c_6501"}]},"item_title":"A Theoretical Study for Initiation of High-Frequency Combustion Oscillation in Premixed Gas Rocket","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"A Theoretical Study for Initiation of High-Frequency Combustion Oscillation in Premixed Gas Rocket","subitem_title_language":"en"}]},"item_type_id":"9","owner":"1","path":["1890","1992"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"34410","relation_version_is_last":true,"title":["A Theoretical Study for Initiation of High-Frequency Combustion Oscillation in Premixed Gas Rocket"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T23:42:37.175141+00:00"}