...
  • 主题
高级搜索  >
历史搜索 清空历史
首页> 外文期刊>Composites Science and Technology >Effect of stitch density and stitch thread thickness on compression after impact strength and response of stitched composites
【24h】

Effect of stitch density and stitch thread thickness on compression after impact strength and response of stitched composites

机译：线迹密度和线迹厚度对冲击强度和复合材料响应后压缩的影响

获取原文
获取原文并翻译 | 示例
           
页面导航
  • 摘要
  • 著录项
  • 相似文献
  • 相关主题

摘要

In this paper, the damage failure and behaviour of stitched composites under compression after impact (CAI) loading are experimentally investigated. This study focuses on the effect of stitch density and stitch thread thickness on the CAI strength and response of laminated composites reinforced by through-thickness stitching. Experimental findings show that stitched composites have higher CAI failure load and displacement, which corresponds to higher energy absorption during CAI damage, mainly attributed to greater energy consumption by stitch fibre rupture. The coupling relationships between CAI strength, impact energy, stitch density and stitch thread thickness are also revealed. It is understood that the effectiveness of stitching has high dependency on the applied impact energy. At low impact energy range, CAI strength is found to be solely dependent on stitch density, showing no influence of stitch thread thickness. It is however observed that stitch fibre bridging is rendered ineffective in moderately stitched laminates during compressive failure, as local buckling occurs between stitch threads, resulting in unstitched and moderately stitched laminates have similar CAI strength. The CAI strength of densely stitched laminates is much higher due to effective stitch fibre bridging and numerous stitch thread breakages. At high impact energy level, CAI strength is discovered to be intimately related to both stitch density and stitch thread thickness. Since CAI failure initiates from impact-induced delamination area, stitch fibre bridging is considerable for all specimens due to the relatively large delamination area present. Stitch threads effectively bridge the delaminated area, inhibit local buckling and suppress delamination propagation, thus leading to increased CAI strength for laminates stitched with higher stitch density and larger stitch thread thickness. Fracture mechanisms and crack bridging phenomenon, elucidated by X-ray radiography are also presented and discussed. This study reveals novel understanding on the effectiveness of stitch parameters for improving impact tolerance of stitched composites.
机译：本文通过实验研究了缝合复合材料的冲击破坏（CAI）后的破坏破坏和行为。这项研究的重点是针迹密度和针迹线厚度对通过厚度缝合增强的层压复合材料的CAI强度和响应的影响。实验结果表明，缝合的复合材料具有更高的CAI破坏载荷和位移，这对应于CAI破坏过程中的更高能量吸收，这主要归因于缝合纤维断裂所消耗的能量更多。还揭示了CAI强度，冲击能量，线迹密度和线迹厚度之间的耦合关系。可以理解，缝合的效果高度依赖于所施加的冲击能量。在低冲击能量范围内，发现CAI强度仅取决于针迹密度，而对针迹线厚度没有影响。然而，观察到在压缩破坏期间，缝制纤维桥接在中等缝制的层压体中无效，因为在缝制线之间发生局部弯曲，导致未缝制和中等缝制的层压体具有相似的CAI强度。由于有效的缝合纤维桥接和大量的缝合线断裂，致密缝合的层压材料的CAI强度要高得多。在高冲击能水平下，发现CAI强度与线迹密度和线迹厚度密切相关。由于CAI破坏是从冲击引起的分层区域开始的，因此，由于存在相对较大的分层区域，因此缝制纤维对所有样品的桥接都相当大。缝合线有效地桥接了分层区域，抑制了局部弯曲并抑制了分层的传播，从而提高了以较高针迹密度和较大针迹线厚度缝合的层压板的CAI强度。还介绍和讨论了X射线射线照相所阐明的断裂机理和裂纹桥接现象。这项研究揭示了针迹参数对改善针刺复合材料耐冲击性有效性的新颖理解。

著录项

  • 来源
    《Composites Science and Technology》 |2012年第5期|p.587-598|共12页
  • 作者

    K.T. Tan; N. Watanabe; Y. Iwahori; T. Ishikawa;

  • 作者单位

    School of Aeronautics and Astronautics, Purdue University, Armstrong Hall, West Lafayette, IN 47907, USA;

    Department of Aerospace Engineering, Tokyo Metropolitan University, 6-6 Asahigaoka, Hino, Tokyo 191-0065, Japan;

    Advanced Composite Technology Centre, Japan Aerospace Exploration Agency, 6-13-1 Osawa, Mitaka, Tokyo 181-0015, Japan;

    Aerospace Research and Development Directorate, Aviation Program Croup, Japan Aerospace Exploration Agency, 7-44-1 Jindaiji, Higashi, Chofu, Tokyo 182-8522, Japan;

  • 收录信息
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

    b. delamination; b. impact behaviour; c. damage tolerance; c. fibre bridging; stitched composites;

    机译：b。分层b。冲击行为;C。破坏容忍度C。光纤桥接缝合复合材料;

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱：kefu@zhangqiaokeyan.com

京公网安备：11010802029741号 ICP备案号：京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有

  • 客服微信

  • 服务号