{"created":"2023-06-20T14:35:53.011248+00:00","id":2163,"links":{},"metadata":{"_buckets":{"deposit":"8b84af77-a34a-455e-8ea9-dccb03183943"},"_deposit":{"created_by":1,"id":"2163","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"2163"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00002163","sets":["1887:1893","9:10:147:189"]},"author_link":["3883","3880","3885","3886","3881","3882","3889","3888","3884","3887"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Experimental study of a combined-cycle engine combustor in ejector-jet mode"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2008-02-29","bibliographicIssueDateType":"Issued"},"bibliographicVolumeNumber":"JAXA-RR-07-011","bibliographic_titles":[{"bibliographic_title":"宇宙航空研究開発機構研究開発報告"},{"bibliographic_title":"JAXA Research and Development Report","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"エジェクタージェットモードにおけるロケット-ラムジェット複合サイクルエンジンの燃焼器模型の実験を、静止大気条件下で実施した。模型はその内部に2基のロケットエンジンを有する。推進剤はガス水素とガス酸素である。燃焼器設計においては入口および出口の断面積、燃焼器長さ、燃料噴射位置、およびロケット作動条件を設定することが必要である。実験ではこれら要因の幾つかを変数として影響を検討した。実験を実施しその結果、設計作動状態をほぼ達成することができた。エジェクター効果により吸入した空気は入口スロート部でチョークし、超音速のロケット排気および空気流は拡大部において圧力の上昇を伴って減速し、燃焼ガスは模型出口のスロート部でチョークした。模型出口でのピトー圧測定およびガス分析から模型出口での平均燃焼効率は0.8であった。その他、以下の事柄が明らかとなった。ロケットの混合比の上昇によって吸込み性能は上昇した。上流平行部長さは模型内部の圧力レベルに影響を与えた。下流平行部長さまた燃料噴射位置は、燃焼状態に影響を与えなかった。下流平行部で噴射する燃料の増加は模型内部の圧力レベルの上昇をもたらした。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"A combustor model of a rocket-ramjet combined-cycle engine was tested in the ejector-jet mode under a sea-level, static condition. The model had two rockets in the duct. Propellants were gaseous hydrogen and oxygen. Design factors of the combustor were cross sections at the entrance and the exit, length of the combustor, fuel injection position and rocket operating conditions. In the tests, the designed operation of the ejector-jet was successfully attained, that is, breathed air was choked at the throat section. Supersonic rocket exhaust and air were decelerated in the divergent duct with an increase of the wall pressure. Combustion gas choked at the exit. The mean combustion efficiency was 0.8 according to pitot pressure measurement and gas sampling. Suction performance was increased with an increase of the mixture ratio of the rockets. Pressure level in the model was affected by the length of the upstream straight section. The combustion status was not affected by the length of the downstream straight section or the position of fuel injection. An increase of fuel caused an increase of the pressure.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0063821000","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: JAXA-RR-07-011","subitem_description_type":"Other"}]},"item_3_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"宇宙航空研究開発機構"}]},"item_3_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"Japan Aerospace Exploration Agency (JAXA)"}]},"item_3_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"1349-1113","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":"AA1192675X","subitem_source_identifier_type":"NCID"}]},"item_3_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"宇宙航空研究開発機構 宇宙基幹システム本部　宇宙輸送系推進技術研究開発センター"},{"subitem_text_value":"宇宙航空研究開発機構 宇宙基幹システム本部　宇宙輸送系推進技術研究開発センター"},{"subitem_text_value":"宇宙航空研究開発機構 宇宙基幹システム本部　宇宙輸送系推進技術研究開発センター"},{"subitem_text_value":"宇宙航空研究開発機構 宇宙基幹システム本部　宇宙輸送系推進技術研究開発センター"},{"subitem_text_value":"宇宙航空研究開発機構 宇宙基幹システム本部　宇宙輸送系推進技術研究開発センター"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency Space Transportation Propulsion Research and Development Center, Office of Space Flight and Operations"},{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency Space Transportation Propulsion Research and Development Center, Office of Space Flight and Operations"},{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency Space Transportation Propulsion Research and Development Center, Office of Space Flight and Operations"},{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency Space Transportation Propulsion Research and Development Center, Office of Space Flight and Operations"},{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency Space Transportation Propulsion Research and Development Center, Office of Space Flight and Operations"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"苅田, 丈士"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"加藤, 周徳"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"谷, 香一郎"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"工藤, 賢司"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"村上, 淳郎"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kanda, Takeshi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kato, Kanenori","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Tani, Koichiro","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kudo, Kenji","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Murakami, Atsuo","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":"2020-01-15"}],"displaytype":"detail","filename":"63821000.pdf","filesize":[{"value":"2.0 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"63821000.pdf","url":"https://jaxa.repo.nii.ac.jp/record/2163/files/63821000.pdf"},"version_id":"b40f577a-28b9-4f75-aa70-4501349b6abd"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"ロケット組込複合サイクルエンジン","subitem_subject_scheme":"Other"},{"subitem_subject":"エジェクター","subitem_subject_scheme":"Other"},{"subitem_subject":"ロケットエンジン設計","subitem_subject_scheme":"Other"},{"subitem_subject":"極超音速航空機","subitem_subject_scheme":"Other"},{"subitem_subject":"燃焼器","subitem_subject_scheme":"Other"},{"subitem_subject":"壁面圧","subitem_subject_scheme":"Other"},{"subitem_subject":"圧力分布","subitem_subject_scheme":"Other"},{"subitem_subject":"圧縮比","subitem_subject_scheme":"Other"},{"subitem_subject":"燃料燃焼","subitem_subject_scheme":"Other"},{"subitem_subject":"エジェクタージェットモード","subitem_subject_scheme":"Other"},{"subitem_subject":"rocket-based combined-cycle engine","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"ejector","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"rocket engine design","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"hypersonic aircraft","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"combustor","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wall pressure","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"pressure distribution","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"compression ratio","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"fuel combustion","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"ejector-jet mode","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":"エジェクターモードにおける複合サイクルエンジン燃焼器の実験","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"エジェクターモードにおける複合サイクルエンジン燃焼器の実験"}]},"item_type_id":"3","owner":"1","path":["189","1893"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"2163","relation_version_is_last":true,"title":["エジェクターモードにおける複合サイクルエンジン燃焼器の実験"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T09:27:33.221402+00:00"}