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首页> 外文期刊>Composite Structures >Finite-element simulation for modeling composite plates subjected to soft-body, high-velocity impact for application to bird-strike problem of composite fan blades
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Finite-element simulation for modeling composite plates subjected to soft-body, high-velocity impact for application to bird-strike problem of composite fan blades

机译：有限元模拟对软高速度冲击下的复合板进行建模，以解决复合风扇叶片的鸟击问题

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摘要

We presented a numerical simulation to address the impact-induced deformation and damage of composite plates subjected to soft-body, high-velocity impacts for application to the bird-strike problem of composite fan blades. A new stabilized contact algorithm was developed based on the Lagrange multiplier method to predict appropriate impact forces applied to the plate, in order to solve soft-body impact at high velocity without causing severe numerical instabilities. The bird-strike impact on composite fan blade was simply modeled by discussing the damage characteristics of a unidirectional composite plate. Combining the model of a soft-body impactor with an appropriate contact algorithm, we could capture the transition from the global bending mode at low velocity to the local deformation mode at high velocity, enabling a discussion of the ballistic limit using the damage analysis of the laminate. As the impact velocity increased, the damage in the composite changed from bending-induced matrix-cracking to an intensive fiber-breakage mode causing local shear perforation. The damage mode transition allows us to detect the transition velocity as a ballistic limit, which is one of the critical factors for discussing the bird-strike resistance of composite fan blades.
机译：我们提出了一个数值模拟，以解决遭受软，高速冲击的复合板的冲击诱导变形和损伤，以应用于复合风扇叶片的鸟击问题。基于拉格朗日乘数法开发了一种新的稳定接触算法，以预测施加到板上的适当冲击力，以便在不引起严重数值不稳定的情况下解决高速下的软体碰撞。通过讨论单向复合板的损伤特性，可以简单地模拟鸟击对复合风扇叶片的影响。将软体冲击器的模型与适当的接触算法相结合，我们可以捕获从低速时的整体弯曲模式到高速时的局部变形模式的转变，从而可以使用弹药的损伤分析来讨论弹道极限层压板。随着冲击速度的增加，复合材料中的损伤从弯曲引起的基体开裂变为强烈的纤维断裂模式，导致局部剪切穿孔。损伤模式过渡使我们能够将过渡速度检测为弹道极限，这是讨论复合风扇叶片抗鸟击性能的关键因素之一。

著录项

  • 来源
    《Composite Structures》 |2011年第5期|p.1416-1423|共8页
  • 作者

    M. Nishikawa; K. Hemmi; N. Takeda;

  • 作者单位

    Department of Nanomechanics, Tohoku University, 6-6-01 Aoba-yama, Aoba-ku, Sendai 980-8579, Japan;

    Department of Aeronautics and Astronautics, The University of Tokyo, 5-1-5 Kashiwanoha, Kashiwa-shi, Chiba 277-8561, Japan;

    Department of Advanced Energy, The University of Tokyo, 5-1-5 Kashiwanoha, Kashiwa-shi, Chiba 277-8561, 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

    composite fan blade; bird-strike impact; damage; computational modeling; finite-element analysis;

    机译：复合风扇叶片;鸟击冲击损伤;计算建模;有限元分析;

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