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Multi-level experimental and numerical analysis of composite stiffener debonding. Part 1: Non-specific specimen level

机译：复合材料加劲肋剥离的多层次实验与数值分析。第1部分：非特定标本水平

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摘要

A multi-level analysis of skin/stiffener debonding is used for the fuselage design of future aircraft during postbuckling. The specimens composed of a laminate (the skin) to which an over-thickness (the flange) had been added were subjected to four-point bending, which led to interface failure between the flange and the skin. These tests were performed with several configurations and parameters, such as the orientation of the plies located at the interface, temperature (-50, 20 and 70℃), ageing and manufacturing mode: co-cured or co-bonded. The flange shape (tapered or not) and thickness were also considered. Test data are presented and analyzed and critical configurations are identified. Finite element models were developed and the flange debonding loads computed, firstly by use of cohesive models and then through a fracture mechanics approach (Virtual Crack Closure Technique). In both cases, the Benzeggagh-Kenane criterion was selected and proved its efficiency but the fracture mechanics approach was an order of magnitude less time consuming, which will enable future modelling to include larger sizes.
机译：在后屈曲过程中，将对蒙皮/加劲肋剥离进行多层次分析，以用于未来飞机的机身设计。对由添加了厚度过大（凸缘）的层压板（皮肤）组成的样品进行四点弯曲，这会导致凸缘和皮肤之间的界面破坏。这些测试是通过几种配置和参数进行的，例如位于界面处的帘布层的方向，温度（-50、20和70℃），老化和制造模式：共固化或共粘合。还考虑了法兰的形状（是否为锥形）和厚度。提供并分析测试数据，并确定关键配置。开发了有限元模型，并首先通过使用内聚模型，然后通过断裂力学方法（虚拟裂缝闭合技术），计算了法兰的脱粘载荷。在这两种情况下，均选择了Benzeggagh-Kenane准则并证明了其有效性，但断裂力学方法的耗时减少了一个数量级，这将使将来的建模能够包含更大的尺寸。

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  • 来源
    《Composite Structures》 |2009年第4期|381-391|共11页
  • 作者

    Julien Bertolini; Bruno Castanie; Jean-Jacques Barrau; Jean-Philippe Navarro;

  • 作者单位

    Airbus France, 316 Route de Bayonne, F-31000 Toulouse, France;

    Universite de Toulouse, UPS, LGMT (Laboratoire de Genie Mecanique de Toulouse), Bat3PN, 118, route de Narbonne, F-31062 Toulouse, France;

    Universite de Toulouse, UPS, LGMT (Laboratoire de Genie Mecanique de Toulouse), Bat3PN, 118, route de Narbonne, F-31062 Toulouse, France;

    Airbus France, 316 Route de Bayonne, F-31000 Toulouse, France;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

    skin/stiffener debonding; fracture mechanics; finite element analysis;

    机译：皮肤/增硬剂脱胶;断裂力学有限元分析;

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