Experimental investigations of material models for Ti-6A1-4V and 2024-T3
Experimental investigations of material models for Ti-6A1-4V and 2024-T3
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DOI：
10.2172/11977
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发表时间：
1999-05
期刊：
影响因子：
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通讯作者：
Don Lesuer;May
中科院分区：
文献类型：
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作者：
Don Lesuer;May
本文研究了Ti-6Al-4V和2024-T3铝合金的变形和破坏行为。数据是在高应变率和大应变下使用分离式霍普金森压杆技术获得的。这些信息，加上文献中的其他数据，被用来批判性地评估Johnson Cook材料模型在与发动机安全壳模拟和未包含的发动机碎片对飞机结构的影响相关的条件下表示Ti-6AMV和2024-T3的变形和故障响应的能力。该模型正在DYNA3D有限元代码中使用，该代码正在开发/验证中，用于根据联邦适航标准评估飞机/发动机设计，并改进缓解/遏制技术。本文报道的实验工作结果被用来定义一组新的材料常数，用于Ti-6Al-4V和2024-T3的Johnson Cook模型的强度分量。对该模型的性能和局限性进行了回顾。该模型能较准确地反映材料的应力应变响应。约翰逊-库克材料模型的主要问题是它能够准确地表示应变速率大于10{sup 3}-10{sup 4}S{sup{负}1}的应力-应变率响应。还需要额外的工作来充分解释剪切局部化破坏，这是两种材料在高应变率下的主要破坏模式。在未来的报告中将进一步考虑Ti-6Al-N和2024-T3的故障建模。
This report describes studies of the deformation and failure behavior of Ti-6Al-4V and 2024-T3 aluminum. Data was obtained at high strain rates and large strains using the split Hopkinson pressure bar technique. This information, plus additional data from the literature, was used to critically evaluate the ability of the Johnson Cook material model to represent the deformation and failure response of Ti-6AMV and 2024-T3 under conditions relevant to simulations of engine containment and the influence of uncontained engine debris on aircraft structures. This model is being used in the DYNA3D finite element code, which is being developed/validated for evaluating aircraft/engine designs relative to the federal airworthiness standards and for improving mitigation/containment technology. The results of the experimental work reported here were used to define a new set of material constants for the strength component of the Johnson Cook model for Ti-6Al-4V and 2024-T3. The capabilities and limitations of the model are reviewed. The model can accurately represent the stress-strain response of the materials. The major concern with the Johnson Cook material model is its ability to accurately represent the stress - strain rate response at strain rates greater than 10{sup 3}-10{sup 4} s{sup {minus}1}. Additional work is also needed to adequately account for failure via shear localization, which was the dominant failure mode at high strain rates in both materials. Failure modeling in both Ti-6Al-N and 2024-T3 will be considered further in future reports.