{"created":"2023-06-20T14:39:48.967884+00:00","id":6621,"links":{},"metadata":{"_buckets":{"deposit":"026ba88b-e0a9-40d7-9b82-2522289b6723"},"_deposit":{"created_by":1,"id":"6621","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"6621"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00006621","sets":["1887:1891","9:789:1085:1366"]},"author_link":["33907","33909","33908","33900","33904","33903","33902","33901","33906","33905"],"item_5_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Rocket engine dynamic simulator (REDS)"}]},"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2004-03-25","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"112","bibliographicPageStart":"107","bibliographicVolumeNumber":"JAXA-SP-03-002","bibliographic_titles":[{"bibliographic_title":"宇宙航空研究開発機構特別資料: 航空宇宙数値シミュレーション技術シンポジウム2003論文集"},{"bibliographic_title":"JAXA Special Publication: Proceedings of Aerospace Numerical Simulation Symposium 2003","bibliographic_titleLang":"en"}]}]},"item_5_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"The Rocket Engine Dynamic Simulator (REDS) has been developed. REDS is a kind of simulation tool to simulate and examine unsteady behavior of a rocket engine. A rocket engine is modeled as a system of pipes with various hydraulic elements such as turbopumps, turbines, valves, orifices, etc. Flows of fuel oxidizer and combustion gas are simulated by solving conservative equations with calculations of their phase changes and physical properties. The motion of turbopumps and turbines are solved coupling with flow equations. The heat exchange between fluid and walls is also calculated and incorporated into the energy state of fluids. In the present version of REDS, the simulation code has been developed to simulate the unsteady behavior such as a startup and a shutdown of a staged combustion cycle engine, which has been applied to Japanese launch vehicles H-2 and H-2A. The validity of REDS has been checked by comparing with the combustion test data, and the results showed high capability in reproduction of unsteady response in startup and shutdown and steady state working condition. REDS has been constructed with flexibility to apply to any configuration of a rocket engine and is expected to contribute to research and development of a next generation rocket engine.","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0047427020","subitem_description_type":"Other"}]},"item_5_description_33":{"attribute_name":"レポート番号","attribute_value_mlt":[{"subitem_description":"レポート番号: JAXA-SP-03-002","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"}]},"item_5_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"Japan Aerospace Exploration Agency (JAXA)"}]},"item_5_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"1349-113X","subitem_source_identifier_type":"ISSN"}]},"item_5_source_id_24":{"attribute_name":"書誌レコードID","attribute_value_mlt":[{"subitem_source_identifier":"AA11984031","subitem_source_identifier_type":"NCID"}]},"item_5_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"航空宇宙技術研究所"},{"subitem_text_value":"航空宇宙技術研究所"},{"subitem_text_value":"航空宇宙技術研究所"},{"subitem_text_value":"航空宇宙技術研究所"},{"subitem_text_value":"宇宙開発事業団"}]},"item_5_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory"},{"subitem_text_language":"en","subitem_text_value":"National Space Development Agency of Japan"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"木村, 俊哉"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"高橋, 政浩"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"若松, 義男"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"長谷川, 恵一"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"山西, 伸宏"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kimura, Toshiya","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Takahashi, Masahiro","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Wakamatsu, Yoshio","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Hasegawa, Keiichi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Yamanishi, Nobuhiro","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":"2020-01-16"}],"displaytype":"detail","filename":"47427020.pdf","filesize":[{"value":"1.6 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"47427020.pdf","url":"https://jaxa.repo.nii.ac.jp/record/6621/files/47427020.pdf"},"version_id":"ee48409e-aefe-43aa-99b7-ef2070da95c1"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"ロケットエンジンシミュレータ","subitem_subject_scheme":"Other"},{"subitem_subject":"非定常流体力学","subitem_subject_scheme":"Other"},{"subitem_subject":"数値シミュレーション","subitem_subject_scheme":"Other"},{"subitem_subject":"液体推薬ロケットエンジン","subitem_subject_scheme":"Other"},{"subitem_subject":"LE-7","subitem_subject_scheme":"Other"},{"subitem_subject":"H-2A","subitem_subject_scheme":"Other"},{"subitem_subject":"非定常挙動","subitem_subject_scheme":"Other"},{"subitem_subject":"宇宙機信頼性","subitem_subject_scheme":"Other"},{"subitem_subject":"rocket engine simulator","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"unsteady aerodynamics","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"numerical simulation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"liquid propellant rocket engine","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"LE-7","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"H-2A","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"unsteady behavior","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"spacecraft reliability","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 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