{"created":"2023-06-20T15:11:32.698001+00:00","id":41226,"links":{},"metadata":{"_buckets":{"deposit":"fdd64d76-d2db-446c-b1f6-90ac9dfcfe73"},"_deposit":{"created_by":1,"id":"41226","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"41226"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00041226","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["451294","451295"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Development test of a liquid apogee engine for the ETS-6"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1994-10","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"21","bibliographicPageStart":"1","bibliographicVolumeNumber":"1250","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":"1994年度にH-2ロケットで打ち上げが予定されている2000kg級大型技術試験衛星ETS-6のアポジエンジン(衛星をトランスファ軌道からドリフト軌道に軌道変換させる)には貯蔵性推進薬を用いた2液式液体アポジエンジンが用いられる。このエンジンには高性能、高信頼性が要求され、比推力325秒を目標として開発研究を行った。現在実用化されている液体アポジエンジンの比推力が310秒であることから、実現すれば世界でもトップクラスの性能を有するエンジンとなる。この目標達成のために我々は、(1)推進薬として酸化剤に4酸化2窒素、燃料には高エネルギであるヒドラジンを用いる。(2)高膨張ノズル(開口比200-300)の採用。(3)システムの単純化による信頼性の向上を図るためブローダウン方式を採用することとした。1983年から基礎実験を開始し、ハードスタート、ポップ、熱制御など種々の課題を乗り越え、1990年度に本エンジンが完成した。エンジンの最終仕様は以下の通りとなった。エンジン作動範囲;燃焼圧0.97-0.63(MPa),混合比0.85-1.05,推力;1980-1280(N),ブローダウン平均比推力;320.0±2.7(秒),連続燃焼可能時間;2900(秒)である。比推力は当初目標に達しなかったがそれでも世界トップクラスの性能を持ったエンジンである。本報告書では主に、インジェクタの開発を中心に述べる。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"A pressure-fed, full-blowdown, Nitrogen Tetroxide (NTO)/hydrazine (N2H4) bipropellant liquid apogee propulsion system was selected for Engineering Test Satellite-6 (ETS-6), a 2000-kg Japanese engineering test satellite. This 2000-kg mass geostationary satellite is scheduled to be launched by an H-2 rocket in 1994. The apogee engine required a high reliability and a relatively high performance for a pressure fed system. In the preliminary development phase of the apogee engine, a peak vacuum specific impulse Ispv of 325 s was set as the initial development target. This performance requirement of the apogee engine is greater than that of the bipropellant engine using NTO/Monomethyl Hydrazine (MMH). To meet such high performance requirements, a NTO/N2H4 propellant system instead of NTO/MMH propellant was employed and a very large area ratio nozzle (nozzle area ratio is 200 to 300) was used. To enhance the reliability of the apogee propulsion system, a pressure-fed, full-blowdown system was selected. Fundamental studies including hard-start, pop and thermal problems were also conducted during the development series of apogee engine started in 1983. Performance characteristics of apogee engine developed in 1990 was as follows; chamber pressure Pc = 0.97-0.63 MPa, mixture ratio MR = 0.85-1.05, vacuum thrust = 1980-1280 N, mean vacuum specific impulse Ispv = 320.0 +/- 2.7 s, and total burn time = 2900 s. Delivered peak Ispv was less than the initial development target, however, the engine performance was higher than that of the engine for NTO/MMH propellant. This paper describes mainly the development studies of the injectors used in the apogee engine.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0004257000","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-1250","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":"液体アポジエンジン研究開発チーム"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Rocket Propulsion Research Division"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"液体アポジエンジン研究開発チーム"}],"nameIdentifiers":[{"nameIdentifier":"451294","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"Rocket Propulsion Research Division","creatorNameLang":"en"}],"nameIdentifiers":[{"nameIdentifier":"451295","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":"2020-01-27"}],"displaytype":"detail","filename":"naltr01250.pdf","filesize":[{"value":"2.2 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr01250.pdf","url":"https://jaxa.repo.nii.ac.jp/record/41226/files/naltr01250.pdf"},"version_id":"4829bd65-cff5-4b16-987b-6c42c8cd1e8f"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"技術試験衛星6","subitem_subject_scheme":"Other"},{"subitem_subject":"ETS-6","subitem_subject_scheme":"Other"},{"subitem_subject":"2液推進アポジエンジン","subitem_subject_scheme":"Other"},{"subitem_subject":"インジェクタ特性","subitem_subject_scheme":"Other"},{"subitem_subject":"H-2ロケット","subitem_subject_scheme":"Other"},{"subitem_subject":"トランスファ軌道","subitem_subject_scheme":"Other"},{"subitem_subject":"ドリフト軌道","subitem_subject_scheme":"Other"},{"subitem_subject":"貯蔵性推進薬","subitem_subject_scheme":"Other"},{"subitem_subject":"比推力","subitem_subject_scheme":"Other"},{"subitem_subject":"4酸化2窒素","subitem_subject_scheme":"Other"},{"subitem_subject":"ヒドラジン","subitem_subject_scheme":"Other"},{"subitem_subject":"高膨張ノズル","subitem_subject_scheme":"Other"},{"subitem_subject":"吹き出しシステム","subitem_subject_scheme":"Other"},{"subitem_subject":"engineering test satellite 6","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"ETS 6","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"bipropellant apogee engine","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"injector characteristic","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"H 2 rocket","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"transfer orbit","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"drift orbit","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"storable propellant","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"specific impulse","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"nitrogen tetroxide","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"hydrazine","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"high expansion nozzle","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"blow down system","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":"ETS-6用液体アポジエンジンの研究開発(インジェクタ特性)","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"ETS-6用液体アポジエンジンの研究開発(インジェクタ特性)"}]},"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":"41226","relation_version_is_last":true,"title":["ETS-6用液体アポジエンジンの研究開発(インジェクタ特性)"],"weko_creator_id":"1","weko_shared_id":1},"updated":"2023-06-20T19:11:43.784332+00:00"}