WEKO3
アイテム
{"_buckets": {"deposit": "4f7176e8-c46b-4817-9853-28063cead35e"}, "_deposit": {"created_by": 1, "id": "17256", "owners": [1], "pid": {"revision_id": 0, "type": "depid", "value": "17256"}, "status": "published"}, "_oai": {"id": "oai:jaxa.repo.nii.ac.jp:00017256", "sets": ["1709", "1891"]}, "author_link": ["156820", "156822", "156821", "156823"], "item_5_alternative_title_2": {"attribute_name": "その他のタイトル(英)", "attribute_value_mlt": [{"subitem_alternative_title": "Conditions for high efficiency flight of a pulse detonation engine"}]}, "item_5_biblio_info_10": {"attribute_name": "書誌情報", "attribute_value_mlt": [{"bibliographicIssueDates": {"bibliographicIssueDate": "2004-04", "bibliographicIssueDateType": "Issued"}, "bibliographicPageEnd": "104", "bibliographicPageStart": "101", "bibliographic_titles": [{"bibliographic_title": "宇宙輸送シンポジウム 平成15年度"}, {"bibliographic_title": "Proceedings of Space Transportation Symposium FY2003", "bibliographic_titleLang": "en"}]}]}, "item_5_description_17": {"attribute_name": "抄録(英)", "attribute_value_mlt": [{"subitem_description": "The performances of pulse detonation engine (PDE) were numerically estimated with detailed chemical reaction model. Flight altitude, flight Mach number, PDE-tube length and fuel-injection forms, i.e. equivalence ratio and distribution of equivalence ratio were altered as operational parameters. In consequence the following possibilities were suggested: The PDE-operation in the lower fuel quantity than stoichiometric mixture gave the higher performances; thrust per mass flowrate of fuel and specific impulse on fuel density, than those in stoichiometric mixture. Moreover, the partial fuel-injection PDE-operation under optimizing fuel-injection form; the equivalence ratio of the head-end side phi(sub closed) = 1.0, that of the open-end side phi(sub open) = 0.0 and the mean equivalence ratio in PDE-tube phi = 0.1, was anticipated to giving the highest-performances for various flight altitudes, and flight Mach numbers. In the same way thrust per mass flowrate of oxidizer, specific impulse on oxidizer, and thrust per unit area of PDE-tube were estimated.", "subitem_description_type": "Other"}]}, "item_5_description_32": {"attribute_name": "資料番号", "attribute_value_mlt": [{"subitem_description": "資料番号: AA0047118026", "subitem_description_type": "Other"}]}, "item_5_publisher_8": {"attribute_name": "出版者", "attribute_value_mlt": [{"subitem_publisher": "宇宙航空研究開発機構宇宙科学研究本部"}]}, "item_5_publisher_9": {"attribute_name": "出版者(英)", "attribute_value_mlt": [{"subitem_publisher": "Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS)"}]}, "item_5_text_20": {"attribute_name": "その他キーワード", "attribute_value_mlt": [{"subitem_text_value": "宇宙船の推進及び出力"}, {"subitem_text_value": "数値解析"}]}, "item_5_text_35": {"attribute_name": "JAXAカテゴリ", "attribute_value_mlt": [{"subitem_text_value": "JAXAカテゴリ: シンポジウム・研究会"}]}, "item_5_text_36": {"attribute_name": "JAXAカテゴリ2", "attribute_value_mlt": [{"subitem_text_value": "JAXAカテゴリ2: IS"}]}, "item_5_text_42": {"attribute_name": "シンポジウム区分", "attribute_value_mlt": [{"subitem_text_value": "シンポジウム区分: 013"}]}, "item_5_text_43": {"attribute_name": "DSpaceコレクション番号", "attribute_value_mlt": [{"subitem_text_value": "DSpaceコレクション番号: 7"}]}, "item_5_text_6": {"attribute_name": "著者所属", "attribute_value_mlt": [{"subitem_text_value": "名古屋大学 理工科学総合研究センター"}, {"subitem_text_value": "名古屋大学"}]}, "item_5_text_7": {"attribute_name": "著者所属(英)", "attribute_value_mlt": [{"subitem_text_language": "en", "subitem_text_value": "Nagoya University Center for Integrated Research in Science and Engineering"}, {"subitem_text_language": "en", "subitem_text_value": "Nagoya University"}]}, "item_access_right": {"attribute_name": "アクセス権", "attribute_value_mlt": [{"subitem_access_right": "metadata only access", "subitem_access_right_uri": "http://purl.org/coar/access_right/c_14cb"}]}, "item_creator": {"attribute_name": "著者", "attribute_type": "creator", "attribute_value_mlt": [{"creatorNames": [{"creatorName": "古川, 剛"}], "nameIdentifiers": [{"nameIdentifier": "156820", "nameIdentifierScheme": "WEKO"}]}, {"creatorNames": [{"creatorName": "藤原, 俊隆"}], "nameIdentifiers": [{"nameIdentifier": "156821", "nameIdentifierScheme": "WEKO"}]}, {"creatorNames": [{"creatorName": "Furukawa, Takeshi", "creatorNameLang": "en"}], "nameIdentifiers": [{"nameIdentifier": "156822", "nameIdentifierScheme": "WEKO"}]}, {"creatorNames": [{"creatorName": "Fujiwara, Toshitaka", "creatorNameLang": "en"}], "nameIdentifiers": [{"nameIdentifier": "156823", "nameIdentifierScheme": "WEKO"}]}]}, "item_keyword": {"attribute_name": "キーワード", "attribute_value_mlt": [{"subitem_subject": "パルスデトネーションエンジン", "subitem_subject_scheme": "Other"}, {"subitem_subject": "効率", "subitem_subject_scheme": "Other"}, {"subitem_subject": "飛行条件", "subitem_subject_scheme": "Other"}, {"subitem_subject": "数値解析", "subitem_subject_scheme": "Other"}, {"subitem_subject": "化学反応", "subitem_subject_scheme": "Other"}, {"subitem_subject": "燃料入射", "subitem_subject_scheme": "Other"}, {"subitem_subject": "質量流速", "subitem_subject_scheme": "Other"}, {"subitem_subject": "Euler運動方程式", "subitem_subject_scheme": "Other"}, {"subitem_subject": "pulse detonation engine", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "efficiency", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "flight condition", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "numerical analysis", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "chemical reaction", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "fuel injection", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "mass flow rate", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "Euler equation of motion", "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": "conference paper", "resourceuri": "http://purl.org/coar/resource_type/c_5794"}]}, "item_title": "Pulse detonation engineの高効率飛行条件", "item_titles": {"attribute_name": "タイトル", "attribute_value_mlt": [{"subitem_title": "Pulse detonation engineの高効率飛行条件"}]}, "item_type_id": "5", "owner": "1", "path": ["1709", "1891"], "permalink_uri": "https://jaxa.repo.nii.ac.jp/records/17256", "pubdate": {"attribute_name": "公開日", "attribute_value": "2015-03-26"}, "publish_date": "2015-03-26", "publish_status": "0", "recid": "17256", "relation": {}, "relation_version_is_last": true, "title": ["Pulse detonation engineの高効率飛行条件"], "weko_shared_id": -1}
Pulse detonation engineの高効率飛行条件
https://jaxa.repo.nii.ac.jp/records/17256
https://jaxa.repo.nii.ac.jp/records/172562e5071b6-baa9-4a81-b0fc-f43cc2b45e76
Item type | 会議発表論文 / Conference Paper(1) | |||||
---|---|---|---|---|---|---|
公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | Pulse detonation engineの高効率飛行条件 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | パルスデトネーションエンジン | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 効率 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 飛行条件 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 数値解析 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 化学反応 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 燃料入射 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 質量流速 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | Euler運動方程式 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | pulse detonation engine | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | efficiency | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | flight condition | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | numerical analysis | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | chemical reaction | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | fuel injection | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | mass flow rate | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Euler equation of motion | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_5794 | |||||
資源タイプ | conference paper | |||||
アクセス権 | ||||||
アクセス権 | metadata only access | |||||
アクセス権URI | http://purl.org/coar/access_right/c_14cb | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Conditions for high efficiency flight of a pulse detonation engine | |||||
著者 |
古川, 剛
× 古川, 剛× 藤原, 俊隆× Furukawa, Takeshi× Fujiwara, Toshitaka |
|||||
著者所属 | ||||||
名古屋大学 理工科学総合研究センター | ||||||
著者所属 | ||||||
名古屋大学 | ||||||
著者所属(英) | ||||||
en | ||||||
Nagoya University Center for Integrated Research in Science and Engineering | ||||||
著者所属(英) | ||||||
en | ||||||
Nagoya University | ||||||
出版者 | ||||||
出版者 | 宇宙航空研究開発機構宇宙科学研究本部 | |||||
出版者(英) | ||||||
出版者 | Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS) | |||||
書誌情報 |
宇宙輸送シンポジウム 平成15年度 en : Proceedings of Space Transportation Symposium FY2003 p. 101-104, 発行日 2004-04 |
|||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | The performances of pulse detonation engine (PDE) were numerically estimated with detailed chemical reaction model. Flight altitude, flight Mach number, PDE-tube length and fuel-injection forms, i.e. equivalence ratio and distribution of equivalence ratio were altered as operational parameters. In consequence the following possibilities were suggested: The PDE-operation in the lower fuel quantity than stoichiometric mixture gave the higher performances; thrust per mass flowrate of fuel and specific impulse on fuel density, than those in stoichiometric mixture. Moreover, the partial fuel-injection PDE-operation under optimizing fuel-injection form; the equivalence ratio of the head-end side phi(sub closed) = 1.0, that of the open-end side phi(sub open) = 0.0 and the mean equivalence ratio in PDE-tube phi = 0.1, was anticipated to giving the highest-performances for various flight altitudes, and flight Mach numbers. In the same way thrust per mass flowrate of oxidizer, specific impulse on oxidizer, and thrust per unit area of PDE-tube were estimated. | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0047118026 |