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首页> 外文期刊>Journal of the American Helicopter Society >Progressive Fatigue Damage Simulation in Laminated Composites Based on Explicit Finite Element Formulation
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Progressive Fatigue Damage Simulation in Laminated Composites Based on Explicit Finite Element Formulation

机译：基于显式有限元公式的层合复合材料渐进疲劳损伤模拟

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Advanced polymeric composites are playing a major role in designing high-performance and lightweight vertical lift structures. However, uncertain residual strength and remaining useful life of the composite rotor and airframe structures due to complexity of failure mechanisms and susceptibility to manufacturing irregularities, which may be precursors to structural damage, impose risks that cannot be mitigated exclusively by time-consuming and costly experimental iterations. Validated analysis techniques accelerating design, certification, and qualification of composite structures are needed. Our team has been taking essential steps toward improving confidence in material qualification for laminated composites. The first step started with our reduced lamina test methods, short-beam shear, and small-plate twist based on digital image correlation measuring as a subset the standard material properties and, in addition, key properties that cannot be currently measured using any standard test methods. The lamina properties provide essential material input data for laminate analysis. The laminate analysis was the second step increasing confidence in material qualification. A known weakness of the existing progressive damage analysis methods is the lack of effective techniques to predict ultimate failure. The newly developed methodology relies on explicit finite element modeling and eliminates convergence issues in the ply-level progressive damage analysis methods due to severe nonlinear discontinuities after propagation of damage beyond detectable size. This work shows results of applying this methodology to nanosilica-toughened IM7/PMT-F3GHT open-hole tension strength/fatigue, open-hole compression strength/fatigue, and bearing strength multidirectional laminate configurations. The ability to predict progression of damage from initiation to ultimate strength and fatigue for advanced material systems including IM7/PMT-F3GHT carbon/epoxy reinforced by nanosilica has been demonstrated for the first time.
机译：先进的聚合物复合材料在设计高性能和轻型垂直举升结构中起着重要作用。但是，由于故障机理的复杂性和制造不规则性的敏感性，复合材料旋翼和机身结构的剩余强度以及剩余使用寿命尚不确定，这可能是结构损坏的先兆，这带来了无法通过耗时且昂贵的实验来完全缓解的风险迭代。需要经过验证的分析技术来加速复合结构的设计，认证和鉴定。我们的团队一直在采取重要步骤来提高对层压复合材料的材料鉴定的信心。第一步始于我们减少的层板测试方法，短梁剪切和基于数字图像相关性的小板扭曲，将标准材料性能以及目前无法使用任何标准测试测量的关键性能作为子集进行测量方法。层板特性为层压板分析提供了必不可少的材料输入数据。层压板分析是提高材料鉴定信心的第二步。现有渐进式损伤分析方法的一个已知缺点是缺乏预测最终失效的有效技术。新开发的方法依赖于显式的有限元建模，并消除了在层级渐进式损伤分析方法中由于损伤传播超出可检测的尺寸后出现严重的非线性不连续性而导致的收敛问题。这项工作显示了将该方法应用于纳米二氧化硅增韧的IM7 / PMT-F3GHT开孔拉伸强度/疲劳，开孔压缩强度/疲劳以及轴承强度多向层压板配置的结果。首次证明了对先进材料系统（包括由纳米二氧化硅增强的IM7 / PMT-F3GHT碳/环氧树脂）预测从破坏到最终强度和疲劳发展的能力。

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  • 来源
    《Journal of the American Helicopter Society》 |2019年第2期|022004.1-022004.12|共12页
  • 作者

    Nikishkov Yuri; Seon Guillaume; Makeev Andrew;

  • 作者单位

    Univ Texas Arlington, Adv Mat & Struct Lab, Arlington, TX 76019 USA;

    Univ Texas Arlington, Adv Mat & Struct Lab, Arlington, TX 76019 USA;

    Univ Texas Arlington, Adv Mat & Struct Lab, Arlington, TX 76019 USA;

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