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首页> 外文期刊>Journal of Composites Technology & Research >Strength and Fatigue Life Modeling of Bonded Joints in Composite Structure
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Strength and Fatigue Life Modeling of Bonded Joints in Composite Structure

机译：复合结构粘结节点的强度和疲劳寿命建模

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摘要

The aerospace industry lacks a validated, practical analysis method for the strength, durability, and damage tolerance evaluation of composite bonded joints. This paper presents the results of a combined strength and fracture analysis approach applied to typical bonded joint configurations found in rotorcraft composite structures. The analysis uses detailed 2-D non-linear finite element models of the local bondline. Strength-of-materials failure criteria are used to predict critical damage initiation loads and locations. A fracture mechanics approach is used to predict damage growth and failure under static and cyclic loads based on test data for static fracture toughness (G_(Ic), G_(IIc)) and crack growth rate (da/dN). Results are presented from the application of the analysis approach to two joint configurations: 1) a skin-stiffener T-joint and; 2) a bonded repair lap joint. The results show that the proposed approach can be used to predict critical failure modes, damage initiation loads and locations, crack and/or delamination stability, static strength, residual strength, and fatigue life. Discussion is also included on how this approach can be applied in damage tolerance evaluations of composite bonded joints.
机译：航空航天工业缺乏对复合粘结接头的强度，耐久性和损伤耐受性评估的经过验证的实用分析方法。本文介绍了结合强度和断裂分析方法的结果，该方法应用于旋翼航空器复合结构中的典型粘结接头构型。分析使用局部键合线的详细二维非线性有限元模型。材料强度破坏准则用于预测关键破坏的初始载荷和位置。基于静态断裂韧性（G_（Ic），G_（IIc））和裂纹扩展率（da / dN）的测试数据，采用断裂力学方法来预测在静态和循环载荷下的损伤增长和破坏。通过将分析方法应用于两种关节结构，可以得出结果：1）皮肤增强T型接头;以及2）搭接修复搭接接头。结果表明，所提出的方法可用于预测关键失效模式，损伤起始载荷和位置，裂纹和/或分层稳定性，静态强度，残余强度和疲劳寿命。还讨论了如何将此方法应用于复合粘结接头的损伤容限评估。

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