{"created":"2023-06-20T15:10:02.655074+00:00","id":39642,"links":{},"metadata":{"_buckets":{"deposit":"01da8579-b9bf-4e93-b5f4-6e75792def4a"},"_deposit":{"created_by":1,"id":"39642","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"39642"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00039642","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["443726","443721","443719","443725","443723","443717","443718","443720","443724","443722"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Combustion characteristics of LOX-hydrogen with high mixture ratio, 1"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1995-09","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"15","bibliographicPageStart":"1","bibliographicVolumeNumber":"1278","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所報告"},{"bibliographic_title":"Technical Report of National Aerospace Laboratory","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"単段式宇宙往還機(SSTO)に用いるデュアル混合比液体酸素(LOX)-水素エンジンを提案した。このエンジンは、離陸時には高混合比で作動させてブースタモードで高い密度比推力を得、高空では低い混合比で作動させて高い比推力を得る。SSTOのペイロードをかなり増加させるために、このエンジンのSSTOへの応用が期待される。ここでは、デュアル混合比LOX-水素燃焼器の燃焼特性と熱伝達特性を調べた。3つの同軸型噴射器(従来のストレート燃料アニュラーを用いたひとつの配置と角度燃料アニュラーを用いた2つの配置)を用いて実験を行った。単一要素燃焼器を用いて4.5MPaの燃焼室圧力および4.6-17の混合比でデータを得た。燃焼室の軸方向の圧力分布データを直接使用する簡単化直接法により1次元定常状態方程式を解き、これにより燃焼試験結果を解析した。この解析により、各インゼクタのLOX噴射の蒸発に必要な距離を得た。角度燃料アニュラーは燃焼性能を改善する場合に有効であることを示した。各インゼクタに対して観測した熱伝達特性も、ここで提案した簡単化モデルにより説明した。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"A dual mixture ratio LOX-hydrogen engine is proposed for application to the Single-Stage-To-Orbit vehicles (SSTO). The engine operates at a high mixture ratio, providing a high thrust-to-weight ratio in the booster mode; at a low mixture ratio, it provides a high specific impulse in the high altitude operation. The application of this engine to the SSTO is expected to remarkably increase the payload of the vehicle. The present study investigated the combustion and heat transfer characteristics of dual mixture ratio LOX-hydrogen combustors. Experiments were conducted with three coaxial injectors: one configuration with a conventional straight fuel annulus and two configurations with an angular fuel annulus. The data were obtained at a chamber pressure of 4.5 MPa and an oxidant to fuel ratio from 4.6 to 17 with single-element combustors. The combustion test results were analyzed by using a 'simplified direct' method which directly uses pressure distribution data along the chamber axis to solve one-dimensional steady-state equations. By using the analysis, the distances required to vaporize the LOX spray for each injector were obtained. It was shown that the angular fuel annulus is effective in improving the combustion performance. Some of the heat transfer characteristics observed for each injector were also explained by the proposed simplified model.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0000013000","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 TR-1278","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":"0389-4010","subitem_source_identifier_type":"ISSN"}]},"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 角田宇宙推進技術研究センター"},{"subitem_text_value":"航空宇宙技術研究所 角田宇宙推進技術研究センター"},{"subitem_text_value":"航空宇宙技術研究所 角田宇宙推進技術研究センター"},{"subitem_text_value":"航空宇宙技術研究所 角田宇宙推進技術研究センター"},{"subitem_text_value":"航空宇宙技術研究所 角田宇宙推進技術研究センター"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Kakuda Research Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Kakuda Research Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Kakuda Research Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Kakuda Research Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Kakuda Research Center"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"坂本, 博"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"佐々木, 正樹"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"高橋, 守"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"佐藤, 和雄"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"田村, 洋"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Sakamoto, Hiroshi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Sasaki, Masaki","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Takahashi, Mamoru","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Sato, Kazuo","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Tamura, Hiroshi","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":"2020-01-27"}],"displaytype":"detail","filename":"naltr01278.pdf","filesize":[{"value":"1.4 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr01278.pdf","url":"https://jaxa.repo.nii.ac.jp/record/39642/files/naltr01278.pdf"},"version_id":"b5a6d151-7b20-4f89-bdaa-18357cde1c9a"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"デュアル混合比","subitem_subject_scheme":"Other"},{"subitem_subject":"液体ロケット燃料","subitem_subject_scheme":"Other"},{"subitem_subject":"液体酸素／水素燃焼器","subitem_subject_scheme":"Other"},{"subitem_subject":"熱伝達特性","subitem_subject_scheme":"Other"},{"subitem_subject":"燃焼効率","subitem_subject_scheme":"Other"},{"subitem_subject":"液体ロケットエンジン","subitem_subject_scheme":"Other"},{"subitem_subject":"噴射器","subitem_subject_scheme":"Other"},{"subitem_subject":"燃焼圧依存性","subitem_subject_scheme":"Other"},{"subitem_subject":"混合比依存性","subitem_subject_scheme":"Other"},{"subitem_subject":"ストレート流路","subitem_subject_scheme":"Other"},{"subitem_subject":"テーパ付き流路","subitem_subject_scheme":"Other"},{"subitem_subject":"燃焼圧分布","subitem_subject_scheme":"Other"},{"subitem_subject":"1次元解析モデル","subitem_subject_scheme":"Other"},{"subitem_subject":"流出係数","subitem_subject_scheme":"Other"},{"subitem_subject":"特性速度効率","subitem_subject_scheme":"Other"},{"subitem_subject":"dual mixture ratio","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"liquid rocket fuel","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"liquid oxygen/hydrogen combustor","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"heat transfer characteristic","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"combustion efficiency","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"liquid rocket engine","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"injector","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"combustion pressure dependence","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"mixture ratio dependence","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"straight fuel annulus","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"tapered fuel annulus","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"combustion pressure distribution","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"one dimensional analytical model","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"discharge coefficient","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"characteristic velocity efficiency","subitem_subject_language":"en","subitem_subject_scheme":"Other"}]},"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":"デュアル混合比液酸/水素燃焼器の燃焼・熱負荷特性　1","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"デュアル混合比液酸/水素燃焼器の燃焼・熱負荷特性　1"}]},"item_type_id":"3","owner":"1","path":["1893","1917"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"39642","relation_version_is_last":true,"title":["デュアル混合比液酸/水素燃焼器の燃焼・熱負荷特性　1"],"weko_creator_id":"1","weko_shared_id":1},"updated":"2023-06-20T19:20:00.875654+00:00"}