抱负
发表于 2025-3-23 12:51:55
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珐琅
发表于 2025-3-23 15:08:09
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Grandstand
发表于 2025-3-23 19:21:11
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盖他为秘密
发表于 2025-3-23 22:45:15
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温和女孩
发表于 2025-3-24 04:41:39
High Cycle Fatigue and Fatigue Crack Growth Rate in Additive Manufactured Titanium Alloysecimen gauge section. Key findings are as follows. Presence of porosity did not affect the tensile strengths, however both ductility and fatigue strength were significantly reduced. Fatigue life could not be correlated by the applied stress, e.g. in terms of the .-. curves, owing to the different po
FEAT
发表于 2025-3-24 06:47:15
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保守党
发表于 2025-3-24 12:51:19
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ALIAS
发表于 2025-3-24 15:52:23
Assessment of Fatigue Behavior of Advanced Aluminum Alloys Under Complex Variable-Amplitude Loadingive load simulating landing in the spectrum crack growth M(T) testing. The special test method employed, results of the equivalency testing, and a comparison to the full-scale panel test results are covered.
mitten
发表于 2025-3-24 19:30:44
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Pseudoephedrine
发表于 2025-3-25 01:09:46
An Ultrafast Crack Growth Lifing Model to Support Digital Twin, Virtual Testing, and Probabilistic Doving aircraft design, safety, and reliability..Under Federal Aviation Administration (FAA) Funding, This methodology focused on the development of an ultrafast numerical crack growth algorithm that consists of: (a) a constant amplitude equivalent stress derived from a variable amplitude loading spe