中国航空学报(英文版)2024,Vol.37Issue(1) :118-137.DOI:10.1016/j.cja.2023.05.027

An interlaminar damage shell model for typical composite structures

Jie ZHOU Zhen WU Zhengliang LIU Xiaohui REN
中国航空学报(英文版)2024,Vol.37Issue(1) :118-137.DOI:10.1016/j.cja.2023.05.027

An interlaminar damage shell model for typical composite structures

Jie ZHOU 1Zhen WU 2Zhengliang LIU 1Xiaohui REN3
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作者信息

  • 1. School of Aeronautics,Northwestern Polytechnical University,Xi'an 710072,China
  • 2. School of Aeronautics,Northwestern Polytechnical University,Xi'an 710072,China;National Key Laboratory of Strength and Structural Integrity,Xi'an 710065,China
  • 3. School of Mechanical Engineering,Xi'an Aeronautical University,Xi'an 710065,China
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Abstract

Using the plate/shell elements in commercial software,accurate analysis of interlaminar initial damage in typical composite structures is still a challenging issue.To propose an accurate and efficient model for analysis of interlaminar initial damage,the following work is carried out:(A)A higher-order theory is firstly proposed by introducing the local Legendre polynomials,and then a novel shell element containing initial damage prediction is developed,which can directly predict transverse shear stresses without any postprocessing methods.Unknown variables at each node are independent of number of layers,so the proposed model is more efficient than the 3D-FEM.(B)Compression experiment is carried out to verify the capability of the proposed model.The results obtained from the proposed model are in good agreement with experimental data.(C)Sev-eral examples have been analyzed to further assess the capability of the proposed model by compar-ing to the 3D-FEM results.Moreover,accuracy and efficiency have been evaluated in different damage criterion by comparing with the selected models.The numerical results show that the pro-posed model can well predict the initial interlaminar damage as well as other damage.Finally,the model is implemented with UEL subroutine,so that the present approach can be readily utilized to analyze the initial damage in typical composite structures.

Key words

Compression experiment/Finite element method/Initial damage/Interlaminar stress/Plate/shell element

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基金项目

National Natural Science Foundation of China(12172295)

&&(SKLLIM1902)

Natural Science Foundation in Shaanxi Province,China(2019JQ-909)

出版年

2024
中国航空学报(英文版)
中国航空学会

中国航空学报(英文版)

CSTPCDEI
影响因子:0.847
ISSN:1000-9361
参考文献量54
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