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Titlebook: Virtual Testing and Predictive Modeling; For Fatigue and Frac Bahram Farahmand Book 2009 Springer-Verlag US 2009 composite.composite materi

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發(fā)表于 2025-3-21 17:58:04 | 只看該作者 |倒序瀏覽 |閱讀模式
書目名稱Virtual Testing and Predictive Modeling
副標題For Fatigue and Frac
編輯Bahram Farahmand
視頻videohttp://file.papertrans.cn/984/983388/983388.mp4
概述Provides cost-effective and efficient approaches to obtain fatigue and fracture data.Describes virtual testing techniques that prove adequate life in manufactured structural parts.Written with a uniqu
圖書封面Titlebook: Virtual Testing and Predictive Modeling; For Fatigue and Frac Bahram Farahmand Book 2009 Springer-Verlag US 2009 composite.composite materi
描述Thematerialsusedinmanufacturingtheaerospace,aircraft,automobile,andnuclear parts have inherent aws that may grow under uctuating load environments during the operational phase of the structural hardware. The design philosophy, material selection, analysis approach, testing, quality control, inspection, and manufacturing are key elements that can contribute to failure prevention and assure a trouble-free structure. To have a robust structure, it must be designed to withstand the envir- mental load throughout its service life, even when the structure has pre-existing aws or when a part of the structure has already failed. If the design philosophy of the structure is based on the fail-safe requirements, or multiple load path design, partial failure of a structural component due to crack propagation is localized and safely contained or arrested. For that reason, proper inspection technique must be scheduled for reusable parts to detect the amount and rate of crack growth, and the possible need for repairing or replacement of the part. An example of a fail-sa- designed structure with crack-arrest feature, common to all aircraft structural parts, is the skin-stiffened design con guration
出版日期Book 2009
關鍵詞composite; composite material; continuum mechanics; damage; deformation; fatigue; fracture; fracture mechan
版次1
doihttps://doi.org/10.1007/978-0-387-95924-5
isbn_softcover978-1-4899-8370-1
isbn_ebook978-0-387-95924-5
copyrightSpringer-Verlag US 2009
The information of publication is updating

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R. Jones,D. Peng in schriftlicher, von den Kranken selbst verfa?ter Form oft inhaltlich reicher, aber dafür vielfach ph?nomenologisch unklarer, durch tendenzi?se Reflexionen entstellt sind. Wer selbst erlebte, findet am ehesten die treffende Schilderung. Der nur beobachtende Psychiater würde sich vergebens zu formu
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possible need for repairing or replacement of the part. An example of a fail-sa- designed structure with crack-arrest feature, common to all aircraft structural parts, is the skin-stiffened design con guration978-1-4899-8370-1978-0-387-95924-5
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Virtual Testing and Its Application in Aerospace Structural Parts,ing the data, obtaining the variation of fracture toughness versus part thickness, capturing data in the threshold region, and repeating the test in many cases due to invalid results make the virtual testing technique extremely helpful to overcome the time and cost related to the above-mentioned tes
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Predicting Creep and Creep/Fatigue Crack Initiation and Growth for Virtual Testing and Life Assessml uses a ductility exhaustion argument and constraint at the crack tip is able to predict, within a range of as much as a factor of ~30 crack initiation and growth at high temperatures, over the plane stress to plane strain regimes. By taking into account angular damage distribution around the crack
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Multiscale Modeling of Nanocomposite Materials,e tools for establishing structure–property relationships of composite materials made of combinations of polymers, metals, and ceramics. The objective of this chapter is to describe a general framework for multiscale modeling of composite materials. First, the fundamental aspects of efficient and ac
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