{"created":"2023-06-20T15:10:02.244609+00:00","id":39634,"links":{},"metadata":{"_buckets":{"deposit":"6a8c7691-4955-45f2-b250-b3b00be78a0b"},"_deposit":{"created_by":1,"id":"39634","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"39634"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00039634","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["443676","443680","443675","443677","443678","443679"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Wing rock of delta wings with an analysis by the phase plane method"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1995-04","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"18","bibliographicPageStart":"1","bibliographicVolumeNumber":"1266","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":"異なる後退角(55度-85度)を持つ13枚の薄いデルタ翼のロール運動の実験を、自由回転法を用いて行った。一連の実験で、ロール機軸の迎角の変化に対して、デルタ翼が動的に安定、あるいは不安定になる領域を調べた。一方、デルタ翼のロール角を0度に保ったままデルタ翼の機軸の迎角を増加させた場合に、デルタ翼面上に非対称渦が発生する領域と、渦が崩壊する領域が実験的に調べられており、これらの静的実験の結果と、ここでの動的なロール不安定の実験結果とを比較した。その結果、静的な不安定領域は、動的に不安定名領域にほぼ平行して存在することが分かった。また、デルタ翼が一様流中で静止の状態からウィングロックに入る角運動の角度の時間的変化の測定を行い、ウィングロックの現象を支配する非線形なローリングモーメントを相平面法を用いて解析的に表現した。このローリングモーメントの解析的表現を用いて運動方程式を解くと、デルタ翼のウィングロックの実験から得られた角運動やリミットサイクルと一致する結果が得られた。このことは、この解析表現が実際に作用したモーメントをかなり忠実に表わしていることを示している。さらに、この解析的な表現を用いて、ウィングロックの力学的な特性、エネルギーの変化を明らかにすることが出来た。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Experimental investigation of the rolling motion of thin delta wings with varying sweep angles, using a free-to-roll method was conducted. The boundaries of dynamically stable and unstable regions of the delta wings were obtained and compared with vortex symmetry and vortex burst curves on a plane of angle of attack of the roll axis vs. delta wing sweep angle. An analytical expression of the rolling moment using a phase plane method was found to be satisfactory for generating the limit cycle similar to the one experimentally obtained. Using this expression, energy transfer in the unsteady motion was calculated.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0000005000","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-1266","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"}]},"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"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"楯, 篤志"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"野田, 順一"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"吉永, 崇"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Tate, Atsushi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Noda, Junichi","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":"naltr01266.pdf","filesize":[{"value":"2.3 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr01266.pdf","url":"https://jaxa.repo.nii.ac.jp/record/39634/files/naltr01266.pdf"},"version_id":"a43cb37f-28cf-494c-bd52-02b85cad48f2"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"空気力学","subitem_subject_scheme":"Other"},{"subitem_subject":"ウイングロック","subitem_subject_scheme":"Other"},{"subitem_subject":"デルタ翼","subitem_subject_scheme":"Other"},{"subitem_subject":"相平面法","subitem_subject_scheme":"Other"},{"subitem_subject":"高開始角度","subitem_subject_scheme":"Other"},{"subitem_subject":"ロール運動","subitem_subject_scheme":"Other"},{"subitem_subject":"自由回転法","subitem_subject_scheme":"Other"},{"subitem_subject":"渦","subitem_subject_scheme":"Other"},{"subitem_subject":"エネルギー移動","subitem_subject_scheme":"Other"},{"subitem_subject":"角運動量","subitem_subject_scheme":"Other"},{"subitem_subject":"リミットサイクル","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamics","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wing rock","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"delta wing","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"phase plane method","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"high angles of attack","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"rolling motion","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"free to roll method","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"vortex","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"energy transfer","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"angular momentum","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"limit cycle","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":"デルタ翼のウイングロックと相平面法による解析","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"デルタ翼のウイングロックと相平面法による解析"}]},"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":"39634","relation_version_is_last":true,"title":["デルタ翼のウイングロックと相平面法による解析"],"weko_creator_id":"1","weko_shared_id":1},"updated":"2023-06-20T19:20:09.696219+00:00"}