{"created":"2023-06-20T15:11:32.065631+00:00","id":41215,"links":{},"metadata":{"_buckets":{"deposit":"9a1f8c58-95ae-4d77-839f-661dc8111618"},"_deposit":{"created_by":1,"id":"41215","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"41215"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00041215","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["451223","451215","451220","451216","451217","451219","451221","451218","451222","451212","451214","451213"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Aerodynamic characteristics of the orbital reentry vehicle experimental probe fins in a supersonic flow"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1994-04","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"16","bibliographicPageStart":"1","bibliographicVolumeNumber":"1232","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所報告"},{"bibliographic_title":"Technical Report of National Aerospace Laboatory","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"航空宇宙技術研究所(NAL)と宇宙開発事業団(NASDA)との共同研究として実施される軌道再突入実験において、実験機(OREX)の肩部に取り付けて再突入時の温度および電子密度の測定に使用されるプローブ(静電プローブおよび熱電対プローブ。ここではOREXフィンと呼ぶ、後退角60度、高さ70mm、および厚さ20mm)が開発されている。このプローブのOREX気体への取付角に誤差を生じると、OREXを機軸回りに回転させるモーメントが生じる。この値を推定するため、OREXフィン模型をAGARD-B模型の胴体に取り付けて揚力係数、抗力係数および縦揺れモーメント係数を測定した。試験は航空宇宙技術研究所の1m×1m吹出式超音速風動で実験した。試験の結果、揚力係数は小さな迎角(0度〜5度程度)の範囲内では、試験したすべてのマッハ数で迎角に対して直線性を示した。また迎角α=0度における揚力傾斜はマッハ数の増加とともに徐々に減少した。フィンの抗力係数はフィンの後退角が大きい方が小さく、マッハ数の増加とともに後退角の影響は小さくなった。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"The aerodynamic characteristics of probe fins with a sweep angle of 60 deg, which are equipped on the Orbital Reentry Experiment (OREX) vehicle to measure the surrounding ionized gas temperature and electron number density distributions in the high temperature communication black out regions, have been measured in the supersonic wind tunnel of the National Aerospace Laboratory and compared with those of the fins of 0 deg sweep angles. Since the probes are to be embeded in the boundary layer where the local Mach number is less than 2.5 over the OREX surface at a hypersonic flight speed, the aerodynamic characteristics in supersonic regions are needed to estimate the rolling moments of fins caused by the error of the installation angles. The lift coefficient slope of the probe fins decreases as the Mach number increases, being less than the values for the 0 deg sweep fins.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0004245000","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-1232","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":"航空宇宙技術研究所 空気力学部"},{"subitem_text_value":"航空宇宙技術研究所 空気力学部"},{"subitem_text_value":"航空宇宙技術研究所 空気力学部"},{"subitem_text_value":"航空宇宙技術研究所 空気力学部"},{"subitem_text_value":"航空宇宙技術研究所 空気力学部"},{"subitem_text_value":"航空宇宙技術研究所 空気力学部"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aerodynamics Division"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"渡辺, 光則"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"関根, 英夫"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"楯, 篤志"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"野田, 順一"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"井上, 安敏"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"吉永, 崇"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Watanabe, Mitsunori","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Sekine, Hideo","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Tate, Atsushi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Noda, Junichi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Inoue, Yasutoshi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Yoshinaga, Takashi","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":"2020-01-27"}],"displaytype":"detail","filename":"naltr01232.pdf","filesize":[{"value":"3.2 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr01232.pdf","url":"https://jaxa.repo.nii.ac.jp/record/41215/files/naltr01232.pdf"},"version_id":"c43ffbb6-f610-4330-981b-84003bf56972"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"超音速空力形状研究","subitem_subject_scheme":"Other"},{"subitem_subject":"超音速風洞試験","subitem_subject_scheme":"Other"},{"subitem_subject":"超音速空力特性","subitem_subject_scheme":"Other"},{"subitem_subject":"再突入物体空気力学","subitem_subject_scheme":"Other"},{"subitem_subject":"軌道再突入物体","subitem_subject_scheme":"Other"},{"subitem_subject":"再突入物体計測","subitem_subject_scheme":"Other"},{"subitem_subject":"イオン化気体温度プローブ","subitem_subject_scheme":"Other"},{"subitem_subject":"電子密度分布プローブ","subitem_subject_scheme":"Other"},{"subitem_subject":"後退角効果","subitem_subject_scheme":"Other"},{"subitem_subject":"通信途絶領域","subitem_subject_scheme":"Other"},{"subitem_subject":"取り付け誤差起源ローリングモーメント","subitem_subject_scheme":"Other"},{"subitem_subject":"OREX","subitem_subject_scheme":"Other"},{"subitem_subject":"軌道再突入実験機","subitem_subject_scheme":"Other"},{"subitem_subject":"揚力係数","subitem_subject_scheme":"Other"},{"subitem_subject":"抗力係数","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic configuration study","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic wind tunnel test","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic aerodynamic characteristics","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"reentry vehicle aerodynamics","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"orbital reentry vehicle","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"reentry body instrumentation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"ionized gas temperature probe","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"electron number density distribution probe","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"sweep angle effect","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"communication black out region","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"misalignment induced rolling moment","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"OREX","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"orbital reentry experiment","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"lift coefficient","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"drag coefficient","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":"超音速流中における軌道再突入実験機のプローブフィンの空力特性","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"超音速流中における軌道再突入実験機のプローブフィンの空力特性"}]},"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":"41215","relation_version_is_last":true,"title":["超音速流中における軌道再突入実験機のプローブフィンの空力特性"],"weko_creator_id":"1","weko_shared_id":1},"updated":"2023-06-20T19:11:57.571186+00:00"}