{"created":"2023-06-20T15:03:09.572259+00:00","id":32285,"links":{},"metadata":{"_buckets":{"deposit":"aa02ffe4-303d-4121-b5b8-89ba6f1cf305"},"_deposit":{"created_by":1,"id":"32285","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"32285"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00032285","sets":["1887:1890","1896:1898:1899:1910"]},"author_link":["408136","408135","408133","408134"],"item_9_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Fatigue Fracture and Crack Propagation in Aluminum Alloys (1)"}]},"item_9_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1971-10","bibliographicIssueDateType":"Issued"},"bibliographicIssueNumber":"4","bibliographicPageEnd":"760","bibliographicPageStart":"745","bibliographicVolumeNumber":"7","bibliographic_titles":[{"bibliographic_title":"東京大学宇宙航空研究所報告"}]}]},"item_9_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"航空機に用いられる代表的なアルミニウム合金である2024合金の疲労に関する研究を行なった.実験は平板試験片に対して,一軸方向に繰返し荷重を加える方法を用いた.2024合金と同時に純アルミニウムについても同様な実験を行なって,疲労に伴う挙動を比較した.実験の結果,S-N曲線に関しては,材料の力学的性質の異方性,試験片の寸法効果などによる差はほとんど認められない.平均応力が引張状態になるほど疲労に対する寿命は短かくなる.疲労破断面は,2024合金の場合は主応力面に近い面になるが,純アルミニウムの場合は主せん断応力面に近い面になる.疲労に伴うクラックの発生と伝ぱは,荷重の加え方によって異なる.片振り荷重の場合は1本のクラックが発生し,これが成長して破断に至るが,両振り荷重の場合は多数の微小クラックが発生し,これがしだいにつながって破断に至る.クラックの成長は,片振り荷重の場合はクラックの長さの対数が繰返し数に対して直線関係を示すが,両振り荷重の場合は直線関係は認められない,などの結論が得られた.さらにクラックの発生に関して,金属組織的な観察も行なった.","subitem_description_type":"Abstract"}]},"item_9_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Fatigue behaviours in aluminum and 2024-T 3 aluminum alloy were investigated. The fatigue test was carried out with a sheet specimen loaded repeatedly at various stress levels. It has been found that the direcrional change in mechanical properties of the tested sheet materials and the change in size of a fatigue specimen have no appreciable effects on the S-N curves. It has been observed that fatigue cracks propagate along the principal stress plane in 2024-T 3 aluminum alloy, but along the principal shear stress plane in pure aluminum. In the case of repeated stress cycle test at tension levels, a single crack was nucleated and grew to fracture, however, in the case of reversed cycle test a number of small cracks were nucleated, and then a single crack was formed linking them. The length of propagating fatigue crack was related exponentially to the number of stress cycles in the repeated stress cycle test, but no simple relationship was found in the reversed stress cycle test. Metallographic observations also have been made to investigate the inception of fatieue cracks.","subitem_description_type":"Other"}]},"item_9_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: SA0125457000","subitem_description_type":"Other"}]},"item_9_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"東京大学宇宙航空研究所"}]},"item_9_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"0563-8100","subitem_source_identifier_type":"ISSN"}]},"item_9_source_id_24":{"attribute_name":"書誌レコードID","attribute_value_mlt":[{"subitem_source_identifier":"AN00161914","subitem_source_identifier_type":"NCID"}]},"item_9_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"東京大学宇宙航空研究所"},{"subitem_text_value":"東京大学宇宙航空研究所"}]},"item_9_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Institute of Space and Aeroautical Science University of Tokyo"},{"subitem_text_language":"en","subitem_text_value":"Institute of Space and Aeroautical Science University of Tokyo"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"小原, 嗣朗"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"武藤, 範雄"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"KOHARA, Shiro","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"MUTO, Norio","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":"2020-01-24"}],"displaytype":"detail","filename":"SA0125457.pdf","filesize":[{"value":"2.2 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"SA0125457.pdf","url":"https://jaxa.repo.nii.ac.jp/record/32285/files/SA0125457.pdf"},"version_id":"0b948a85-d070-40eb-9611-4bc277236624"}]},"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":"departmental bulletin paper","resourceuri":"http://purl.org/coar/resource_type/c_6501"}]},"item_title":"航空機用アルミニウム合金の疲労によるクラックの発生と伝ぱ(1)","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"航空機用アルミニウム合金の疲労によるクラックの発生と伝ぱ(1)"}]},"item_type_id":"9","owner":"1","path":["1890","1910"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"32285","relation_version_is_last":true,"title":["航空機用アルミニウム合金の疲労によるクラックの発生と伝ぱ(1)"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T00:36:28.970769+00:00"}