张华伟,邵延汤,向陈世,等.碳纤维复合材料层合板低速冲击损伤应力分析[J].精密成形工程,2023,15(1):106-112.
ZHANG Hua-wei,SHAO Yan-tang,XIANG Chen-shi,et al.Stress Analysis for Damage of Carbon Fiber Composite Laminates under Low Speed Impact[J].Journal of Netshape Forming Engineering,2023,15(1):106-112. |
| 碳纤维复合材料层合板低速冲击损伤应力分析 |
| Stress Analysis for Damage of Carbon Fiber Composite Laminates under Low Speed Impact |
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| DOI：10.3969/j.issn.1674-6457.2023.01.014 |
| 中文关键词: 碳纤维复合材料层合板 低速冲击 损伤分析 力学机理 应力 数值模拟 |
| 英文关键词: carbon fiber composite laminate low speed impact damage analysis mechanical mechanism stress numerical simulation |
| 基金项目:国家自然科学基金(51475086);广东石油化工学院校级科研基金(2020rc020);茂名市科技计划(2022025) |
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| 中文摘要: |
| 目的 为掌握碳纤维复合材料板在低速冲击载荷作用下的损伤规律，延缓失效破坏，对其冲击损伤的应力状态进行研究。方法 基于ABAQUS平台，建立碳纤维复合材料层合板低速冲击有限元模型，采用Hashin失效准则和VUMAT用户子程序，对碳纤维复合材料层合板的冲击过程进行数值模拟，同时考虑层合板层内与层间失效，以此来研究低速冲击条件下复合材料的损伤机理，分析冲击损伤过程中的应力变化趋势，讨论应力的分布状态。重点研究铺层角度及铺层距离冲头远近对应力的影响。结果 不同角度铺层的应力传播轨迹均沿着纤维方向和垂直于纤维方向同时扩展，应力均先增加至极限值而后迅速下降;铺层角度越大，板料的承载能力越弱，0°铺层的极限应力为1 432 MPa，而90°铺层的极限应力降至1 206 MPa;离冲头越远的铺层应力越小，达到峰值的时间更早且率先下降，说明远离冲头的铺层更早发生失效。结论 揭示了碳纤维层合板在低速冲击载荷作用下的应力状态及其对损伤的影响规律，能够为复合材料层合板零件设计提供参考。 |
| 英文摘要: |
| The work aims to investigate the stress state for the impact damage in order to master the damage laws of carbon fiber composite laminates under the low speed impact and postpone the failure of parts. Based on ABAQUS platform, the finite element model of carbon fiber composite laminates under low speed impact was set up. The impact process on the carbon fiber composite laminates was simulated to study the damage mechanism under the low speed impact with the Hashin failure criterion and the user subroutine of VUMAT. The stress change trend during the impact damage process was analyzed, with both of the layer failure and the interface failure considered. The stress distribution state was discussed, and the main focus was put on the effects of the ply angle and the distance between the ply and punching head on the stress. The results indicated that the stress propagation trajectories of plies of different angles extended both in the fiber direction and in the direction perpendicular to the fiber at the same time, the stress values increased first to the limit value and then decreased quickly. However, as the ply angle increased, the loading capacity weakened. The limit stress value in 0° ply was 1 432 MPa, whereas the limit stress value in 90° ply decreased to 1 206 MPa. As the plies were further from the upper head, the stresses in the plies were smaller. The stresses in the plies far from the upper head amounted to the peak and descended earlier, which meant that the plies far from upper head failed earlier. The research results reveal the stress state of carbon fiber composite laminate under the low speed impact and the influencing laws of the stress state on damage, and can provide reference for design of the composite laminate parts. |
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