{"created":"2023-06-20T15:11:44.389989+00:00","id":41459,"links":{},"metadata":{"_buckets":{"deposit":"55c117c2-d2f6-4ccf-b17d-87226decd72c"},"_deposit":{"created_by":1,"id":"41459","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"41459"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00041459","sets":["1887:1893","1896:1898:1913:1915"]},"author_link":["490117","490118","490116","490121","490120","490119"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Fatigue test of fuselage scale model under synchronized pressure and bending loading"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2000-10","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"96","bibliographicPageStart":"93","bibliographicVolumeNumber":"50","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所特別資料"},{"bibliographic_title":"Special Publication of National Aerospace Laboratory","bibliographic_titleLang":"en"}]}]},"item_3_description_14":{"attribute_name":"会議概要（会議名, 開催地, 会期, 主催者等）","attribute_value_mlt":[{"subitem_description":"4 Oct. 2000","subitem_description_type":"Other"}]},"item_3_description_15":{"attribute_name":"会議概要（会議名, 開催地, 会期, 主催者等）（英）","attribute_value_mlt":[{"subitem_description":"4 Oct. 2000","subitem_description_type":"Other"}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"航空機胴体構造疲労強度に及ぼす曲げ荷重の効果を評価するために、与圧サイクルで同期させた曲げ荷重試験を航空機胴体スケールモデルに適用した。与圧力サイクル約45,000回後、胴体左右のトップ列継ぎ手のリベット孔縁から約1mmの疲労割れを検出した。与圧サイクル79,515回において、不安定フラッピング破壊を観察した。曲げ荷重を重ね負荷しなかった事前の試験と疲労挙動を比較した。き列の開始から最終破壊までの本研究におけるサイクル数は、それぞれ事前試験のほぼ1/2と2/3であった。組合せ荷重でもたらされる主応力を考慮することで、この短寿命について納得のいく理解ができた。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Bending loads synchronized with pressurization cycles were applied to the fuselage scale model structure to evaluate the effect of bending load on fatigue behavior of fuselage structure. About 1 mm fatigue cracks were detected from the rivets of the top row fastener of the right and left side of the body after approximately 45,000 pressure cycles. Unstable flapping failure was observed at 79,515 pressure cycles. Fatigue behavior was compared with that of the previous test, where bending loads were not superposed. Number of cycles to crack initiation and final failure of the present test were approximately 1/2 and 2/3 of those of the previous test, respectively. This shorter life was reasonably comprehended by taking account of the principal stress induced by combined loads.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0028639008","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 SP-50","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":"0289-260X","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":"AN10097345","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"},{"subitem_text_value":"航空宇宙技術研究所"},{"subitem_text_value":"航空宇宙技術研究所"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory"}]},"item_access_right":{"attribute_name":"アクセス権","attribute_value_mlt":[{"subitem_access_right":"metadata only access","subitem_access_right_uri":"http://purl.org/coar/access_right/c_14cb"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"寺田, 博之"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"岡田, 孝雄"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"デイブスキー, パブロ"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Terada, Hiroyuki","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Okada, Takao","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Dybskiy, Pavel","creatorNameLang":"en"}],"nameIdentifiers":[{}]}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"航空機胴体スケールモデル","subitem_subject_scheme":"Other"},{"subitem_subject":"リベット継手疲労","subitem_subject_scheme":"Other"},{"subitem_subject":"組合せ荷重","subitem_subject_scheme":"Other"},{"subitem_subject":"与圧・曲げ疲労試験","subitem_subject_scheme":"Other"},{"subitem_subject":"き裂成長","subitem_subject_scheme":"Other"},{"subitem_subject":"フラッピング破壊","subitem_subject_scheme":"Other"},{"subitem_subject":"主応力","subitem_subject_scheme":"Other"},{"subitem_subject":"疲労寿命","subitem_subject_scheme":"Other"},{"subitem_subject":"fuselage scale model","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"riveted joint fatigue","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"combined load","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"pressure bend fatigue test","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"crack growth","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"flapping failure","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"principal stress","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"fatigue life","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":"航空機胴体構造スケールモデルの与圧・曲げ疲労試験","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"航空機胴体構造スケールモデルの与圧・曲げ疲労試験"}]},"item_type_id":"3","owner":"1","path":["1893","1915"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"41459","relation_version_is_last":true,"title":["航空機胴体構造スケールモデルの与圧・曲げ疲労試験"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T20:59:49.314087+00:00"}