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Experimental and Analytical Study of Mode II Interlaminar Failure of Bolted and Bonded Composite Structures.

机译:螺栓连接和键合复合结构的模式II层间破坏的实验和分析研究。

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摘要

The capability of a fastener to arrest and stabilize pure Mode II interlaminar failure in composite structures has been investigated both experimentally and analytically. A novel pure Mode II three-beam axially loaded specimen was designed specifically for the study. Test specimens were manufactured with [(0/45/90/-45)3]S quasi-isotropic carbon fiber composite laminates for each beam. Teflon inserts were installed as initial cracks, and several variations of plies and bonding techniques were used at the crack interface. Testing showed that crack initiation loads depended on the plies at the crack interface and the bonding technique used. The fracture toughness of the bond in several configurations resulted in the crack initiation loads being higher that the load at which filled-hole tension failure of the laminates occurred; in such cases the full arrestment capability of the fasteners was not able to be captured, but post failure C-scans showed that the presence of a fastener did provide more crack arrestment than without a fastener. However, the testing of other specimens with lower fracture toughness of crack interface bonds displayed the capability of the fastener to arrest and stabilize a crack before filled-hole tension failure.;An analytical model and solution were developed to simulate crack growth in the three-beam specimen. The analytical solution was verified using FEM, and showed very good agreement of the results. The analytical model was used to determine the critical Mode II strain energy release rate, G IIC, of each specimen configuration. Also, the analytical model was used to perform a series of parametric analysis of the three-beam specimen to study the effect that changing specimen parameters, such as laminate layup and thickness, had on the crack propagation behavior of the specimen. It was advised that the analytical model be used to aid in the design of alternate specimen configurations for further study.
机译:已经通过实验和分析研究了紧固件阻止和稳定复合结构中纯的II型层间破坏的能力。专门为研究设计了一种新颖的纯II型三光束轴向载荷标本。对于每个梁,用[(0/45/90 / -45)3] S准各向同性碳纤维复合材料层压板制造测试样品。将特氟隆插件安装为初始裂缝,并在裂缝界面处使用了多种板层和粘结技术。测试表明,裂纹萌生载荷取决于裂纹界面处的层和所使用的粘结技术。在几种构型中,粘接剂的断裂韧性导致裂纹萌生载荷高于层压板发生填充孔拉伸破坏时的载荷。在这种情况下,无法捕获紧固件的全部止动能力,但是失效后的C扫描显示,紧固件的存在比没有紧固件的情况下确实提供了更多的止裂性。但是,对其他裂纹界面粘结断裂韧性较低的试样进行的测试表明,紧固件具有在填充孔张力失效之前阻止并稳定裂纹的能力。梁标本。使用FEM对分析溶液进行了验证,结果显示出很好的一致性。分析模型用于确定每个样品配置的临界II型应变能释放速率G IIC。此外,该分析模型还用于对三束试样进行一系列参数分析,以研究改变试样参数(如层压板叠置和厚度)对试样的裂纹扩展行为的影响。建议使用分析模型来辅助设计替代标本配置,以供进一步研究。

著录项

  • 作者

    Gray, Phillip.;

  • 作者单位

    University of Washington.;

  • 授予单位 University of Washington.;
  • 学科 Engineering Aerospace.
  • 学位 M.S.
  • 年度 2012
  • 页码 68 p.
  • 总页数 68
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

  • 入库时间 2022-08-17 11:42:28

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