{"created":"2023-06-20T15:11:01.094134+00:00","id":40600,"links":{},"metadata":{"_buckets":{"deposit":"8bffc11a-2caa-4748-a425-1285bd602f08"},"_deposit":{"created_by":1,"id":"40600","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"40600"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00040600","sets":["1887:1893","1896:1898:1913:1916"]},"author_link":["448799","448802","448798","448800","448801","448803"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Effects of propellant property on vehicle structure and velocity gain of a space transportation system"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1999-05","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"12","bibliographicPageStart":"1","bibliographicVolumeNumber":"739","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所資料"},{"bibliographic_title":"Technical Memorandum of National Aerospace Laboratory","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"宇宙輸送機の構造特性を表す指標として機体の乾燥質量と増進剤タンクの容積から定義される機体乾燥平均密度を導入した。同時に、ミッション性能を検討する際の利便性を考慮し、機体の乾燥質量にペイロードを含めた修正機体乾燥平均密度も示した。既存の航空輸送機とロケット輸送機を評価した結果、機体乾燥平均密度はロケットで35〜115kg/立法メートル、航空機で145〜270kg/立法メートルの水準にあることが分かった。単段(SSTO)式ロケット輸送機について推進剤の密度、比推力および修正機体乾燥平均密度の相互関係を検討し、ミッションの成立限界を示す修正機体乾燥平均密度の許容値を求めた。また、推進剤が高密度になるほど比推力が低下するような特性を持つ場合でも、推進剤密度と比推力の関係が適切であれば、速度増分あるいは修正機体乾燥平均密度の許容値が極大となる点が存在することを示した。いくつかの実用的な推進剤を用いて検討した結果、ロケットSSTO機用推進剤としては液化酸素/液化メタン(LOX/LCH4)が比較的に優れていることが分かった。すなわち、軌道到達質量を一定とした比較によれば、強度が大きくコンパクトな機体を実現するのに適している。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Dry vehicle bulk density, defined as the vehicle dry mass divided by the propellant tank volume, was adopted as the structure evaluation index of a space transportation vehicle. The modified dry vehicle bulk density, which includes the payload mass effect, was also shown for convenience of flight performance analysis. These indices proved to be useful for estimating the effects of propellant properties on the mission ability of the space transportation vehicle. Dry vehicle bulk density is in the range from 35 to 115 kg/cu m for existing rocket vehicles, and in the range from 145 to 270 kg/cu m for existing air freighters. If the mutual relationship between the specific impulse and the propellant density is pertinent, the mission ability of the space transportation vehicle will be of peak value. The permissible value of dry vehicle bulk density for the mission achievement may be determined from the specific impulse, propellant density, and the required velocity gain. For practical use, a combination of liquid oxygen and liquid methane is suitable for SSTO (Single Stage To Orbit) vehicles. Namely, the use of such propellants will result in the smallest and most robust airframe for the SSTO vehicle.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0001964000","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 TM-739","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":"0452-2982","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":"AN00314334","subitem_source_identifier_type":"NCID"}]},"item_3_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"航空宇宙技術研究所 角田宇宙推進技術研究センター"},{"subitem_text_value":"航空宇宙技術研究所 角田宇宙推進技術研究センター"},{"subitem_text_value":"航空宇宙技術研究所 角田宇宙推進技術研究センター"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Kakuda Research Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Kakuda Research Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Kakuda Research Center"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"小野, 文衛"}],"nameIdentifiers":[{"nameIdentifier":"448798","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"若松, 義男"}],"nameIdentifiers":[{"nameIdentifier":"448799","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"苅田, 丈士"}],"nameIdentifiers":[{"nameIdentifier":"448800","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"Ono, Fumiei","creatorNameLang":"en"}],"nameIdentifiers":[{"nameIdentifier":"448801","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"Wakamatsu, Yoshio","creatorNameLang":"en"}],"nameIdentifiers":[{"nameIdentifier":"448802","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"Kanda, Takeshi","creatorNameLang":"en"}],"nameIdentifiers":[{"nameIdentifier":"448803","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":"naltm0000739.pdf","filesize":[{"value":"270.7 kB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltm0000739.pdf","url":"https://jaxa.repo.nii.ac.jp/record/40600/files/naltm0000739.pdf"},"version_id":"db0c3f72-b4fc-44ad-bd42-3a3e3c28faac"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"宇宙輸送システム","subitem_subject_scheme":"Other"},{"subitem_subject":"エアロスペースプレーン","subitem_subject_scheme":"Other"},{"subitem_subject":"液体推進剤","subitem_subject_scheme":"Other"},{"subitem_subject":"宇宙輸送機推進","subitem_subject_scheme":"Other"},{"subitem_subject":"機体構造","subitem_subject_scheme":"Other"},{"subitem_subject":"増速性能","subitem_subject_scheme":"Other"},{"subitem_subject":"機体乾燥平均密度","subitem_subject_scheme":"Other"},{"subitem_subject":"SSTO機","subitem_subject_scheme":"Other"},{"subitem_subject":"単1段機","subitem_subject_scheme":"Other"},{"subitem_subject":"宇宙輸送機","subitem_subject_scheme":"Other"},{"subitem_subject":"比推力","subitem_subject_scheme":"Other"},{"subitem_subject":"推進剤","subitem_subject_scheme":"Other"},{"subitem_subject":"地球低軌道","subitem_subject_scheme":"Other"},{"subitem_subject":"space transportation system","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aerospace plane","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"liquid propellant","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"space transport propulsion","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"vehicle structure","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"velocity increment performance","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"dry vehicle bulk density","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"SSTO vehicle","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Single Stage to orbit vehicle","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"space transportation vehicle","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"specific impulse","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"propellant","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"low earth orbit","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":"推進剤が宇宙輸送機の構造と増速性能に及ぼす影響","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"推進剤が宇宙輸送機の構造と増速性能に及ぼす影響"}]},"item_type_id":"3","owner":"1","path":["1893","1916"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"40600","relation_version_is_last":true,"title":["推進剤が宇宙輸送機の構造と増速性能に及ぼす影響"],"weko_creator_id":"1","weko_shared_id":1},"updated":"2023-06-20T19:14:59.408221+00:00"}