石英纤维与碳纤维混杂加筋壁板剪切后屈曲性能研究
作者:
作者单位:

1.南京航空航天大学航空学院,南京 210016;2.南京航空航天大学通用航空与飞行学院,南京 211106

作者简介:

通讯作者:

于健,男,讲师,E-mail:jian.yu@nuaa.edu.cn。

中图分类号:

O385

基金项目:


Shear Post-Buckling Behavior of Quartz Fiber and Carbon Fiber Hybrid Stiffened Panels
Author:
Affiliation:

1.College of Aerospace Engineering, Nanjing University of Aeronautics & Astronautics, Nanjing 210016, China;2.College of General Aviation and Flight, Nanjing University of Aeronautics & Astronautics, Nanjing 211106, China

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    摘要:

    针对石英纤维与碳纤维混杂加筋壁板,研究其在剪切载荷作用下的极限承载能力,分析其损伤破坏模式。使用二维Hashin准则和二次名义应力准则作为混杂复合材料加筋壁板的层内和层间失效判据,建立了考虑渐进损伤的剪切破坏分析模型,并在ABAQUS有限元软件平台进行建模与求解。开展了石英纤维与碳纤维混杂加筋壁板剪切试验,测量其破坏载荷,获得其典型破坏模式。仿真结果与试验结果的屈曲载荷和破坏载荷相对误差均在15%以内,破坏模式一致,验证了该建模分析方法的可行性与有效性。

    Abstract:

    The ultimate bearing capacity of quartz fiber and carbon fiber hybrid stiffened panels under shear load is studied and its damage mode is analyzed. The two-dimensional Hashin criterion and the secondary nominal stress criterion are used as the in-plane and interlaminar failure criteria of hybrid composite stiffened panels. Thus,a shear failure analysis model considering progressive damage is established, and the hybrid stiffened panels is modeled and solved on the ABAQUS finite element software platform. The shear tests of quartz fiber and carbon fiber hybrid stiffened panels are carried out to measure their failure loads and obtain their typical failure modes. The relative error of buckling load and failure load between simulation results and test results is within 15%, and the failure mode is consistent, which verifies the feasibility and effectiveness of the modeling and analysis method.

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钟博,王新峰,于健.石英纤维与碳纤维混杂加筋壁板剪切后屈曲性能研究[J].南京航空航天大学学报,2023,55(6):1111-1117

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  • 收稿日期:2023-03-09
  • 最后修改日期:2023-06-03
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  • 在线发布日期: 2023-12-05
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