{"created":"2023-06-20T15:13:05.304772+00:00","id":42981,"links":{},"metadata":{"_buckets":{"deposit":"a69657ab-5f62-48f5-ae7b-0adb8cbd2929"},"_deposit":{"created_by":1,"id":"42981","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"42981"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00042981","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["461702","461705","461703","461701","461704","461706"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Transonic, supersonic and hypersonic wind tunnel tests of a lifting-body type reentry vehicle"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2003-08","bibliographicIssueDateType":"Issued"},"bibliographicVolumeNumber":"1468","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":"リフティングボディ型再突入機の空力特性を取得し、形状設計のためのデータや経験を蓄積するために、亜音速から極超音速の範囲で風洞試験を実施した。風試はM=0.5〜1.4についてはNAL 2m×2m遷音速風洞で実施し、M=1.4〜4.0についてはNAL 1m×1m超音速風洞で実施した。またM=10程度の極超音速域についてはNAL 1.27m極超音速風洞で実施した。風洞試験は基本形状の他、形状変更効果を見るために各種変更形状についてもデータを取得した。またエレボンやラダーなどの操舵面の効果を見るため、それぞれの操舵形態についてもデータを取得した。風洞試験の結果、遷音速における基本形状の空力特性は両外舷に取り付けたフィンによる非線形な傾向を示すことが分かった。またフィン前縁後退角を41度から60度へ大きくした場合や胴体上面後縁部を舵面操舵の様に20度切り上げることにより、空力特性の非線形な傾向が改善することも分かった。極超音速では、全形状についてピッチングモーメント特性について迎角範囲が15〜22度で頭下げの傾向が見られた(他の迎角範囲では頭上げ)。また極超音速域で胴体上面変更の効果はほとんどないがフィンキャント角を20度から45度へ変更した場合、高迎角では方向安定性が向上することも分かった。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"A series of wind tunnel tests from subsonic to hypersonic speeds were conducted to investigate the aerodynamic characteristics of a lifting-body type configuration for reentry vehicles and to accumulate knowledge and experience for the design of such vehicles. The tests were conducted at the NAL 2 m x 2 m Transonic Wind Tunnel for Mach numbers from 0.5 to 1.4 and at the NAL 1 m x 1 m Supersonic Wind Tunnel for numbers 1.4 to 4.0. For hypersonic speed of about Mach 10, the test was conducted at the 1.27 m Hypersonic Wind Tunnel. Data were obtained for the baseline configuration and several derived configurations to ascertain the effect of configuration modifications. The effectiveness of control surfaces such as elevons and rudders was also investigated. The test data indicated fin-induced nonlinear characteristics for the baseline configuration at transonic speeds. Data also indicated that enlarging the leading edge sweepback angle of the outboard fins from 41 deg. to 60 deg. or upsweeping the upper aft surface of the fuselage 20 deg., like an upward deflection of a control surface, improves the nonlinear characteristics. For the hypersonic test, a pitch down trend at angles of attack from 15 deg. to 22 deg. was observed for all configurations (with a pitch up trend for other angles of attack). No significant effect was observed for upper surface modification at hypersonic speeds, however, enlarging the fin cant angle from 20 deg. to 45 deg., improved the directional stability.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0047388000","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-1468","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":"航空宇宙技術研究所 宇宙輸送システムプロジェクトセンター"},{"subitem_text_value":"航空宇宙技術研究所 宇宙輸送システムプロジェクトセンター"},{"subitem_text_value":"航空宇宙技術研究所 宇宙輸送システムプロジェクトセンター"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Space Transportation Project Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Space Transportation Project Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Space Transportation Project Center"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"川戸, 博史"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"渡辺, 重哉"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"藤井, 謙司"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kawato, Hiroshi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Watanabe, Shigeya","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Fujii, Kenji","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":"2020-01-28"}],"displaytype":"detail","filename":"naltr0001468.pdf","filesize":[{"value":"3.4 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr0001468.pdf","url":"https://jaxa.repo.nii.ac.jp/record/42981/files/naltr0001468.pdf"},"version_id":"5e38aaf1-54f7-4ecc-887a-84cca1c632fa"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"風洞試験","subitem_subject_scheme":"Other"},{"subitem_subject":"亜音速流","subitem_subject_scheme":"Other"},{"subitem_subject":"極超音速流","subitem_subject_scheme":"Other"},{"subitem_subject":"リフティングボディ型再突入機","subitem_subject_scheme":"Other"},{"subitem_subject":"空力特性","subitem_subject_scheme":"Other"},{"subitem_subject":"超音速流","subitem_subject_scheme":"Other"},{"subitem_subject":"構造安定性","subitem_subject_scheme":"Other"},{"subitem_subject":"エレボン","subitem_subject_scheme":"Other"},{"subitem_subject":"ラダー","subitem_subject_scheme":"Other"},{"subitem_subject":"wind tunnel test","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"subsonic flow","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"hypersonic flow","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"lifting-body type reentry vehicle","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamic characteristic","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic flow","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"structural stability","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"elevon","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"rudder","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":"リフティングボディ型再突入機　遷音速、超音速及び極超音速風洞試験","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"リフティングボディ型再突入機　遷音速、超音速及び極超音速風洞試験"}]},"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":"42981","relation_version_is_last":true,"title":["リフティングボディ型再突入機　遷音速、超音速及び極超音速風洞試験"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T22:22:46.342038+00:00"}