• 主题
高级搜索  >
历史搜索 清空历史
首页> 外文会议>PVP-vol.493; American Society of Mechanical Engineers(ASME) International Mechanical Engineering Congress and Exposition; 20051105-11; Orlando,FL(US) >PERFORMANCE EVALUATION OF UNSTITCHED, STITCHED AND Z-PINNED TEXTILE COMPOSITES UNDER STATIC LOADING
【24h】

PERFORMANCE EVALUATION OF UNSTITCHED, STITCHED AND Z-PINNED TEXTILE COMPOSITES UNDER STATIC LOADING

机译：静态载荷下未缝合，缝合和Z钉纺织复合材料的性能评估

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

Advances in conventional tape laminates and textile composites provide aircraft manufacturers important technology, but the industry lacks the confidence to use these composites to manufacture wing and fuselage structures due to high cost and low damage tolerance. In order to overcome the high cost and to improve the damage tolerance of composites, researchers have developed new through-the-thickness reinforcement techniques, such as stitching through the thickness. This reinforcement technique can be used to join the skin, stiffeners, ribs and spars to form an integral structure. The structures are typically more damage tolerant, contain fewer fasteners and are less expensive to manufacture than conventional composite or metallic structures. Furthermore, stitching reduces the manufacturing time and labor compared to drilling holes for fasteners, and may eliminate the problems of fatigue and/or corrosion from galvanic reactions with metal fasteners. Woven composites with through the thickness reinforcements such as stitching have good properties not only in mutually orthogonal directions but also in the transverse direction and more balanced properties than traditional tape laminates. They are also expected to have better fatigue and impact resistance due to the interlacing. Another benefit is reduced manufacturing cost by reducing part count. Because of these potential benefits, these composites are being considered for various applications including primary/secondary components for aerospace structures. The objective of this effort is to develop experimental tools for comparing the performance of these composites reinforced by stitching to unstitched composites. Identification of damage mechanisms and forces available to grow damage is essential for identifying the primary parameters that determine performance. Accurate determination of the driving forces will require extensive manufacturing and experimentation. However, once the reinforcement techniques are well understood, it is anticipated that simplified experiments can be developed that could be used routinely by designers to evaluate the effects of the reinforcements on damage tolerance. This paper specifically addresses the performance evaluation of stitched low cost manufactured composites subjected to static loading. Static tension and compression testing was conducted to determine the Ultimate Tensile and Compressive Strengths, Young's Moduli and Poisson's Ratio. Two different stitch patterns or stitch densities were used for comparison. The first density was five rows of stitching per inch of width, with eight stitches per inch over the entire length. The second density was three rows of stitching per inch of width, with four stitches per inch over the entirelength.
机译：常规胶带层压板和纺织品复合材料的进步为飞机制造商提供了重要的技术，但是由于成本高且损害容忍度低，业界缺乏使用这些复合材料制造机翼和机身结构的信心。为了克服高成本和提高复合材料的损伤耐受性，研究人员开发了新的贯穿厚度的增强技术，例如通过厚度进行缝合。这种加固技术可用于将蒙皮，加劲肋，肋骨和梁连接起来以形成整体结构。与传统的复合材料或金属结构相比，该结构通常更耐损伤，包含较少的紧固件，并且制造成本较低。此外，与紧固件的钻孔相比，缝合减少了制造时间和劳动，并且可以消除与金属紧固件的电反应引起的疲劳和/或腐蚀问题。具有诸如缝合之类的厚度增强材料的机织复合材料不仅在相互正交的方向上而且在横向方向上都具有良好的性能，并且比传统的胶带层压板具有更平衡的性能。由于隔行，它们还有望具有更好的抗疲劳性和抗冲击性。另一个好处是通过减少零件数量来降低制造成本。由于这些潜在的好处，这些复合材料正被考虑用于各种应用，包括航空航天结构的主要/次要组件。这项工作的目的是开发一种实验工具，以比较通过缝合增强的复合材料与未缝合的复合材料的性能。识别损坏机制和增加损坏的力对于确定决定性能的主要参数至关重要。准确确定驱动力将需要大量的制造和试验。但是，一旦对加固技术有了很好的了解，可以预见的是，可以开发出简化的实验，设计人员可以常规使用这些实验来评估加固对损伤容限的影响。本文专门针对静态负载下缝合的低成本人造复合材料的性能评估。进行了静态拉伸和压缩测试，以确定极限拉伸和压缩强度，杨氏模量和泊松比。比较中使用了两种不同的针迹样式或针迹密度。第一密度是每英寸宽度五行针，在整个长度上每英寸八针。第二密度是每英寸宽度三排针，在整个长度上每英寸四针。

著录项

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