{"created":"2023-06-20T15:15:20.997636+00:00","id":45424,"links":{},"metadata":{"_buckets":{"deposit":"a0016db0-d65e-4931-b675-d75153694fd1"},"_deposit":{"created_by":1,"id":"45424","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"45424"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00045424","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["474719","474721","474724","474718","474723","474720","474717","474722","474716","474715"],"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2002-01","bibliographicIssueDateType":"Issued"},"bibliographicPageStart":"28","bibliographicVolumeNumber":"1440T","bibliographic_titles":[{"bibliographic_title":"独立行政法人航空宇宙技術研究所報告"},{"bibliographic_title":"Technical Report of National Aerospace Laboratory TR-1440T","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"スクラムジェットのスペースプレーン機体への組込み方法には大別して以下の３とおりが挙げられる。（1）エンジン全体を機体下面の予圧縮面に取り付ける、（2）下流で機軸に平行になった機体下面にエンジンを取り付ける、（3）インレットは機体下面の予圧縮面に取付け、エンジン下流部は機軸と平行になった面に取り付ける。組込み方法がエンジン性能に与える影響について調べるために数種類のインレット模型をマッハ４風洞で試験し、その結果に基づきスクラムジェットエンジンの性能を計算し、スペースプレーンの飛行シミュレーションを行った。実験によって（1）および（3）の組込み状態で良好な空気捕獲率が得られた。（2）の形態では、機体下面での予圧縮効果がエンジン入口での膨張波によって打ち消された。どの形態でもほぼ同じ運動エネルギー効率が得られた。エンジン性能計算では（3）の形態での推力が最大で、最小の抗力となった。（2）の形態ではペイロードは負となった。エンジンの機体組込み方法としては、インレットは予圧縮面取付け、その下流のエンジン部はカウル抗力を減らして外部ノズル推力を増やすために機軸と平行とすべきであることが示された。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"There are three typical configurations for integrating the scramjet into the airframe of aerospace planes. They are (1) the whole engine is on the windward ramp surface of the airframe, (2) the engine is located downstream of the forebody ramp where the surface of the airframe is parallel to the airframe axis, and (3) the inlet entrance is on the ramp surface with the following engine parts parallel to the airframe axis. To examine the effect of the integrating forms on the engine performance, several types of the inlet models were tested in a wind tunnel, and simulations of the scramjet engine and the flight of the aerospace plane were conducted. The experimental results showed that the first and the third configurations showed better mass capture. In the second configuration, the pre-compression effect was neutralized by the expansion fan from the corner of the downstream end of the ramp. All configurations showed similar levels of kinetic energy efficiencies. The simulation based on the experimental results showed that the third configuration produced the best engine thrust and the least airframe drag. On the other hand, in the second configuration, the payload became negative. Thus, it is recommended that the inlet should be located on the windward ramp surface of the vehicle to inhale the pre-compressed air, and the following engine components should be parallel to the airframe axis to reduce the cowl drag and to increase the thrust at the external nozzle.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: NALTR1440000","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-1440T","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":"1347-4588","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":"AN00311347","subitem_source_identifier_type":"NCID"}]},"item_3_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"トヨタ自動車株式会社"},{"subitem_text_value":"元・東北大学大学院"},{"subitem_text_value":"航空宇宙技術研究所ラムジェット推進研究センター"},{"subitem_text_value":"航空宇宙技術研究所ラムジェット推進研究センター"},{"subitem_text_value":"航空宇宙技術研究所ラムジェット推進研究センター"},{"subitem_text_value":"東北大学工学部機械航空学科"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Toyota Motor Corporation"},{"subitem_text_language":"en","subitem_text_value":"Former Graduate school, Tohoku University."},{"subitem_text_language":"en","subitem_text_value":"Ramjet Propulsion Research Center, National Aerospace Laboratory(NAL)"},{"subitem_text_language":"en","subitem_text_value":"Ramjet Propulsion Research Center, National Aerospace Laboratory(NAL)"},{"subitem_text_language":"en","subitem_text_value":"Ramjet Propulsion Research Center, National Aerospace Laboratory(NAL)"},{"subitem_text_language":"en","subitem_text_value":"Department of Aeronautics and Space Engineering, Tohoku University"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"秋久, 大輔"}],"nameIdentifiers":[{"nameIdentifier":"474715","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"苅田, 丈士"}],"nameIdentifiers":[{"nameIdentifier":"474716","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"谷, 香一郎"}],"nameIdentifiers":[{"nameIdentifier":"474717","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"工藤, 賢司"}],"nameIdentifiers":[{"nameIdentifier":"474718","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"升谷, 五郎"}],"nameIdentifiers":[{"nameIdentifier":"474719","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"AKIHISA, Daisuke","creatorNameLang":"en"}],"nameIdentifiers":[{"nameIdentifier":"474720","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"KANDA, Takeshi","creatorNameLang":"en"}],"nameIdentifiers":[{"nameIdentifier":"474721","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"TANI, Kouichiro","creatorNameLang":"en"}],"nameIdentifiers":[{"nameIdentifier":"474722","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"KUDO, Kenji","creatorNameLang":"en"}],"nameIdentifiers":[{"nameIdentifier":"474723","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"MASUYA, Goro","creatorNameLang":"en"}],"nameIdentifiers":[{"nameIdentifier":"474724","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":"2020-01-29"}],"displaytype":"detail","filename":"naltr0001440t.pdf","filesize":[{"value":"9.2 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr0001440t.pdf","url":"https://jaxa.repo.nii.ac.jp/record/45424/files/naltr0001440t.pdf"},"version_id":"c38eb1c6-b889-4100-bb19-e051983bdaeb"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"scramjet, inlet, mass capture, aerospace plane","subitem_subject_language":"en","subitem_subject_scheme":"Other"}]},"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":"technical report","resourceuri":"http://purl.org/coar/resource_type/c_18gh"}]},"item_title":"Effect of Integration of Scramjet into Airframe on Engine Performance and Payload","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"Effect of Integration of Scramjet into Airframe on Engine Performance and Payload","subitem_title_language":"en"}]},"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":"45424","relation_version_is_last":true,"title":["Effect of Integration of Scramjet into Airframe on Engine Performance and Payload"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:39:43.659722+00:00"}