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首页> 外文会议>Annual AHS international forum and technology display >Development of Techniques for Composite Parts Failure Analysis in Static and Fatigue Mode -Application on Thermoset and Thermoplastic Materials for Rotorcraft Main Rotor Hub Analysis
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Development of Techniques for Composite Parts Failure Analysis in Static and Fatigue Mode -Application on Thermoset and Thermoplastic Materials for Rotorcraft Main Rotor Hub Analysis

机译：静态和疲劳模式下复合零件失效分析技术的发展-在旋翼飞机主旋翼毂分析的热固性和热塑性材料中的应用

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摘要

A model defined at the ply scale to predict the failure of laminated composites for static or fatigue loading is proposed. The model describes the loss of strength in the fiber direction for a significant level of transverse damage. This meso-scale model has been characterized on woven ply laminates used for rotorcraft dynamic components, such as glass/epoxy of Starflex~®, carbon fiber/epoxy, and carbon fiber/PEEK of H160 main rotor hub. Failure behavior prediction at coupon level has been validated regarding static and fatigue failure mode in tension for epoxy resin woven ply laminates. Characterizations have been also provided for PEEK resin in balanced woven ply laminate, regarding static or fatigue failure mode. Those activities are crucial to increase the level of confidence in failure model, to rely on virtual testing at coupons level, and to better predict damage and failure at component level. This work intends to support the building block approach during development and certification of such critical applications for rotorcraft.
机译：提出了在帘布层上定义的模型，以预测层压复合材料在静态或疲劳载荷下的破坏。该模型描述了在纤维水平方向上的强度损失，从而造成了相当大的横向损伤。该中尺度模型的特征在于用于旋翼飞机动力组件的编织层板层压板，例如Starflex®的玻璃/环氧树脂，H160主旋翼毂的碳纤维/环氧树脂和碳纤维/ PEEK。关于环氧树脂编织层合层压板在拉伸时的静态和疲劳失效模式，已验证了试样片级别的失效行为预测。关于静态或疲劳破坏模式，还提供了平衡编织层片中PEEK树脂的特性。这些活动对于提高对故障模型的置信度，依赖于优惠券级别的虚拟测试以及更好地预测组件级别的损坏和故障至关重要。这项工作旨在为旋翼航空器的此类关键应用的开发和认证过程中的构建模块方法提供支持。

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