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Torsion fatigue behavior of unidirectional carbon/epoxy and glass/epoxy composites

机译：单向碳/环氧树脂和玻璃/环氧树脂复合材料的扭转疲劳行为

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摘要

This paper presents results of the feasibility of carbon/epoxy composites (CFRP) as a future helicopter flexbeam material. Torsional behaviors of unidirectional CFRP and glass/epoxy composites (GFRP) with the same resin matrix were investigated. The initial torsional rigidity of CFRP was almost identical to that of GFRP. The torsional rigidities calculated using finite element analyses (FEA) agreed with the experimental results: the torsional rigidities are governed mainly by the material's shear stiffness. Torsion fatigue tests were also conducted by controlling the angle of twist of the sinusoidal wave under a constant tensile axial load. No catastrophic failure occurred with either GFRP or CFRP, although decreased amplitudes of torque and torsional rigidities were observed according to the number of cycles. Results of X-ray CT inspections and numerical calculation by FEA revealed that degradation of a torsional rigidity is caused mainly by splitting crack propagation along the fiber direction. The torsion fatigue life of CFRP was superior to that of GFRP. Consequently, results confirmed that CFRP exhibits excellent properties as a torsional element of a helicopter flexbeam in terms of torsional rigidity and tension-torsion fatigue behaviors.
机译：本文介绍了碳/环氧复合材料（CFRP）作为未来直升机柔性梁材料的可行性的结果。研究了具有相同树脂基体的单向CFRP和玻璃/环氧树脂复合材料（GFRP）的扭转行为。 CFRP的初始扭转刚度与GFRP几乎相同。使用有限元分析（FEA）计算的抗扭刚度与实验结果一致：抗扭刚度主要由材料的剪切刚度决定。在恒定的轴向拉伸载荷下，通过控制正弦波的扭转角也进行了扭转疲劳试验。 GFRP或CFRP均未发生灾难性故障，尽管根据循环次数观察到扭矩幅值和扭转刚度减小。 X射线CT检查的结果和FEA的数值计算表明，扭转刚度的下降主要是由于沿纤维方向的裂纹扩展引起的。 CFRP的扭转疲劳寿命优于GFRP。因此，结果证实，就抗扭刚度和拉伸-扭转疲劳行为而言，CFRP作为直升机挠性梁的扭转元件具有优异的性能。

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  • 来源
    《Composite Structures》 |2009年第4期|482-489|共8页
  • 作者

    Toshio Ogasawara; Keiji Onta; Shinji Ogihara; Tomohiro Yokozeki; Eiichi Hara;

  • 作者单位

    Aerospace Research and Development Directorate (ARD), Japan Aerospace Exploration Agency (JAXA), 6-13-1, Ohsawa, Mitaka-shi, Tokyo 181-0015, Japan;

    Department of Mechanical Engineering, Tokyo University of Science, 2641 Yamazaki, Noda-shi, Chiba-ken 278-8510, Japan;

    Department of Mechanical Engineering, Tokyo University of Science, 2641 Yamazaki, Noda-shi, Chiba-ken 278-8510, Japan;

    Department of Aeronautics and Astronautics, University of Tokyo, 7-3-1 Hongo, Bunkyo-ku, Tokyo 113-8656, Japan;

    Foundation for Promotion of Japanese Aerospace Technology (JAST), 6-13-1, Ohsawa, Mitaka-shi, Tokyo 181-0015, Japan;

  • 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

    A. carbon fiber; A. class fiber; B. fatigue; B. matrix cracking;

    机译：A.碳纤维;A.类纤维;B.疲劳;B.基体开裂;

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