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Relationship between Scatter of Fatigue Life and S-N Curve of 2024-T4 Aircraft Structural Aluminum Alloy Specimens with a Sharp Notch (Kt=8.25) Under a Constant Temperature and Humidity Condition
https://jaxa.repo.nii.ac.jp/records/44661
https://jaxa.repo.nii.ac.jp/records/4466150ef709f-010c-40c2-958e-704af7f45bf4
名前 / ファイル | ライセンス | アクション |
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naltr0412t.pdf (1.1 MB)
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Item type | テクニカルレポート / Technical Report(1) | |||||
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公開日 | 2015-03-26 | |||||
タイトル | ||||||
言語 | en | |||||
タイトル | Relationship between Scatter of Fatigue Life and S-N Curve of 2024-T4 Aircraft Structural Aluminum Alloy Specimens with a Sharp Notch (Kt=8.25) Under a Constant Temperature and Humidity Condition | |||||
言語 | ||||||
言語 | eng | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_18gh | |||||
資源タイプ | technical report | |||||
著者 |
下河, 利行
× 下河, 利行× 浜口, 泰正× SHIMOKAWA, Toshiyuki× HAMAGUCHI, Yasumasa |
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著者所属 | ||||||
航空宇宙技術研究所機体第二部 | ||||||
著者所属 | ||||||
航空宇宙技術研究所機体第二部 | ||||||
著者所属(英) | ||||||
en | ||||||
Second Airframe Division, National Aerospace Laboratory(NAL) | ||||||
著者所属(英) | ||||||
en | ||||||
Second Airframe Division, National Aerospace Laboratory(NAL) | ||||||
出版者 | ||||||
出版者 | 航空宇宙技術研究所 | |||||
出版者(英) | ||||||
出版者 | National Aerospace Laboratory(NAL) | |||||
書誌情報 |
航空宇宙技術研究所報告 en : Technical Report of National Aerospace Laboratory TR-412T 巻 412T, p. 13, 発行日 1977-10 |
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抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | 本研究は疲労寿命のばらつきとS-N曲線の関係を一種の誤差論の立場から検討したものである。ある一定条件下の疲労試験で得られたS-N曲線を考えてみると,この一定条件に対し,応力側の誤差に換算して考えることのできる因子が新たに加われば,これは当初に予想した寿命からの偏差を生みだし,この偏差大きさはS-N曲線の傾きと形状に依存することが容易に理解できる。そこで,疲労寿命のばらつきの原因として考えられる因子の効果すべてを総合し.設定応力の誤差に換算して考え,設定応力との和を換算応力と定義する。この考えをもとに,温度およぴ湿度を一定にした実験室で,航空機構造用アルミニウム合金2024-T4の鋭い切欠き(Kt=8.25)を有する板状試験片によって行った疲労試験の結果について,換算応力分布,中央S-N曲線,および疲れ寿命分布の相互関係について調べた。この結果,換算応力の分布形はほぼ正規分布であり,標準偏差も応力によらず,ほぼ一定(0.256~0.375 kg/mm2)であった。このため,疲労寿命分布は中央S-N曲線の傾きと形状に大きく影響されていると結論された。 | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | This paper presents an investigation of the relationship between fatigue life scatter and S-N curve from the standpoint of a kind of error theory. When a new factor serving like an error in applied stress is added to an identical condition under which an S-N curve has been obtained, it produces a deviation from the expected fatigue life and the amount of the deviation depends on the slope of the S-N curve. In this study, the accumulated effect of all factors producing fatigue life scatter, which is found in a fatigue test by nominally identical specimens subjected to nominally identical repeated stresses, is regarded as an error in applied stress. Equivalent stress is defined as the sum of applied stress and the error in applied stress. This concept is used for analyzing the results of a series of fatigue tests on 2024-T4 aircraft structural aluminum alloy specimens with a sharp notch (Kt=8.25) under a constant temperature and humidity condition. The inter-relationship between scatter of equivalent stress, S-N curve, where N is the median fatigue life, and fatigue life scatter is discussed. It became clear that equivalent stresses are distributed in almost normal distribution and their standard deviation is nearly constant (0.256 to 0375 kg/mm2) regardless of stress level, and that fatigue life distribution has a strong Correlation to the slope and shape of S-N curve. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0389-4010 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: NALTR0412T000 | |||||
レポート番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | レポート番号: NAL TR-412T |