{"created":"2023-06-20T15:07:27.716315+00:00","id":36834,"links":{},"metadata":{"_buckets":{"deposit":"e8a532a6-b1c8-4216-8e37-093c6675d67e"},"_deposit":{"created_by":1,"id":"36834","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"36834"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00036834","sets":["1887:1891","1896:1898:1913:1915"]},"author_link":["425104","425101","425102","425103"],"item_5_alternative_title_1":{"attribute_name":"その他のタイトル","attribute_value_mlt":[{"subitem_alternative_title":"繊維/金属ラミネートの疲れ特性化"}]},"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1996-05","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"133","bibliographicPageStart":"125","bibliographicVolumeNumber":"31","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_5_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"将来の高性能航空機はさらに耐損傷性材料と最適設計を必要とする。超音速機(SST)の場合、高高度操縦における致命的な急減圧の防止が胴体の構造設計上のひとつの課題である。この要求を満たすために繊維/金属ラミネートをひとつの候補材料として考えた。繊維/金属ラミネートは亀裂成長が緩やかであるという魅力的な特色を示す。繊維/金属ラミネートを使用する場合の構造設計者にとってのひとつの問題は、亀裂成長の評価が複雑すぎて一般化が困難なことである。Glareによるクーポンテスト結果から新しい簡単な方法を提案した。モノリシック厚さとその厚みを通して表面亀裂が進行することを仮定して、基礎応力強度因子(ΔK)に補正因子(βfb)を乗じた補正応力強度因子(ΔKmod)を導入した。補正因子βfbは亀裂のサイズによって定義できる。アルミニウム合金に対する現在の解析方法は補正応力強度因子をもつ繊維/金属ラミネートに対して有効である。この方法は繊維/金属ラミネートの機能限界を理解するための実用的な方法であり、新しいタイプの繊維/金属ラミネートを開発に有効である。","subitem_description_type":"Abstract"}]},"item_5_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"High performance aircraft in the future need more damage tolerant materials and optimized designs. In SSTs (Supersonic Transport), the prevention of lethal rapid decompression in high altitude operations is one of the issues for the structural design of the fuselage. In meeting this requirement, fiber/metal laminates are considered as one of the candidates. Fiber/metal laminates show the attractive feature of slow crack growth. So far, one problem for structural designers in the application of fiber/metal laminates has been that the estimation of crack growth is too complex and has limited generality. A new simple approach is proposed with coupon test results with Glares. Assuming a monolithic thickness and that the surface cracks go through the thickness, the modified stress intensity factor (Delta K(sub mod)) is introduced with the basic stress intensity factor (Delta K) multiplied by the modification factor (beta(sub fb)). The modification factor beta(sub fb) can be defined by just the crack size. The current analytical practice for aluminum alloys is effective for fiber/metal laminates with Delta K(sub mod). This approach is a practical way to understand the performance limit of fiber/metal laminates and is effective in the development of new types of fiber/metal laminates.","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0000440011","subitem_description_type":"Other"}]},"item_5_description_33":{"attribute_name":"レポート番号","attribute_value_mlt":[{"subitem_description":"レポート番号: NAL SP-31","subitem_description_type":"Other"}]},"item_5_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"航空宇宙技術研究所"}]},"item_5_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"National Aerospace Laboratory (NAL)"}]},"item_5_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"0289-260X","subitem_source_identifier_type":"ISSN"}]},"item_5_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_5_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"富士重工業 航空宇宙技術本部"},{"subitem_text_value":"富士重工業 航空宇宙技術本部"}]},"item_5_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Fuji Heavy Industries, Ltd Aerospace Division"},{"subitem_text_language":"en","subitem_text_value":"Fuji Heavy Industries, Ltd Aerospace Division"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"戸井, 康弘"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"藤原, 康弘"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Toi, Yasuhiro","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Fujiwara, Yasuhiro","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":"nalsp0031011.pdf","filesize":[{"value":"1.0 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"nalsp0031011.pdf","url":"https://jaxa.repo.nii.ac.jp/record/36834/files/nalsp0031011.pdf"},"version_id":"d3125d7e-d073-4cca-962c-6681f1f42cf1"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"繊維/金属ラミネート","subitem_subject_scheme":"Other"},{"subitem_subject":"疲れ特性化","subitem_subject_scheme":"Other"},{"subitem_subject":"高性能航空機","subitem_subject_scheme":"Other"},{"subitem_subject":"耐損傷材料","subitem_subject_scheme":"Other"},{"subitem_subject":"最適設計","subitem_subject_scheme":"Other"},{"subitem_subject":"急減圧","subitem_subject_scheme":"Other"},{"subitem_subject":"胴体構造","subitem_subject_scheme":"Other"},{"subitem_subject":"構造設計","subitem_subject_scheme":"Other"},{"subitem_subject":"亀裂成長","subitem_subject_scheme":"Other"},{"subitem_subject":"ガラス繊維テープ/アルミニウム合金ラミネート","subitem_subject_scheme":"Other"},{"subitem_subject":"応力強度因子","subitem_subject_scheme":"Other"},{"subitem_subject":"アルミニウム合金","subitem_subject_scheme":"Other"},{"subitem_subject":"機能限界","subitem_subject_scheme":"Other"},{"subitem_subject":"fiber/metal laminate","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"fatigue characterization","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"high performance aircraft","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"damage tolerant material","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"optimized design","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"rapid decompression","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"fuselage structure","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"structural design","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"crack growth","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"fiberglass tape/aluminum alloy laminate","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"stress intensity factor","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aluminum alloy","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"performance limit","subitem_subject_language":"en","subitem_subject_scheme":"Other"}]},"item_language":{"attribute_name":"言語","attribute_value_mlt":[{"subitem_language":"eng"}]},"item_resource_type":{"attribute_name":"資源タイプ","attribute_value_mlt":[{"resourcetype":"conference paper","resourceuri":"http://purl.org/coar/resource_type/c_5794"}]},"item_title":"Fatigue characterization of fiber/metal laminates","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"Fatigue characterization of fiber/metal laminates","subitem_title_language":"en"}]},"item_type_id":"5","owner":"1","path":["1891","1915"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"36834","relation_version_is_last":true,"title":["Fatigue characterization of fiber/metal laminates"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T22:49:31.304078+00:00"}