{"created":"2023-06-20T15:03:11.185523+00:00","id":32320,"links":{},"metadata":{"_buckets":{"deposit":"be6fdaa0-756b-4d63-af82-072440721a05"},"_deposit":{"created_by":1,"id":"32320","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"32320"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00032320","sets":["1887:1890","1896:1898:1899:1910"]},"author_link":["408310","408309","408312","408311"],"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"}]},"item_9_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1972-06","bibliographicIssueDateType":"Issued"},"bibliographicIssueNumber":"2_B","bibliographicPageEnd":"418","bibliographicPageStart":"408","bibliographicVolumeNumber":"8","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":"航空機の構造別材料である2024アルミニウム合金の高温における疲労の研究を行なった.疲労試験は平板試験片を用い,一輪方向に繰返し応力を加えた.試験温度は100 - 250℃である.疲労強さぱ,荷重の大きさおよび加え方によって変わるが,時効に伴う合金の硬さの変化に対応している.したがって疲労強さはある温度で最大になる.一方,丸穴をあけた試験片でぱ,室温の疲労強さが最大で,温度が上るほど低下する.破断面の方向は,一般に最大士応力面に沿っているが,軟化した状態でぱ,最大剪断応力面に沿う方向に変わる.疲労に伴うクラックの発生は,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,雨振り荷重の場合は,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成長し,破断に至る.","subitem_description_type":"Abstract"}]},"item_9_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Fatigue behaviors of 2024 aluminum alloy at high temperatures have been investigated. The fatigue test was carried out with a sheet specimen loaded repeatedly, and heated by a small furnace during the test. The temperature range investigated was 100 - 250℃. It was found that the fatigue strength varied with the change in hardness of specimen, so the fatigue strength showed the maximum value at the temperature range of 200 - 225℃. In the case of rectangular specimen with a hole at the center, however, the fatigue strength was the highest at room temperature and decrased with temperature. Fatigue crack propagated along the principal stress plane for hardened specimens, but along the maximum shear stress pine for softened specimens. A single crack appeared and grew to fracture in repeated tension test, but a number of small cracks appeared and then a single crack was formed linking them in tension-compression test.","subitem_description_type":"Other"}]},"item_9_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: SA0125506000","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":"SA0125506.pdf","filesize":[{"value":"1.3 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"SA0125506.pdf","url":"https://jaxa.repo.nii.ac.jp/record/32320/files/SA0125506.pdf"},"version_id":"bebd585c-cbd3-4ef2-a4c4-12b391165588"}]},"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(2)","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(2)"}]},"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":"32320","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(2)"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T00:35:26.123567+00:00"}