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摘要:Numerical and experimental study was conducted to investigate the failure mode and strength performance of stiffened composite panel repaired by bolted joints under compressive load, and the results were then compared with those from virgin stiffened composite panel without any damage.A finite element analysis model was established for repaired and virgin stiffened composite panels under compressive load, the 3 D Hashin criteria was applied to identify the composite structure failure, and the secondary stress criteria was adopted to identify the adhesive failure between the base laminate and the stiffener.The failure modes of repaired stiffened composite panels were stiffened composite panels breaking off along the bolt joints.The experimental results were consistent with the finite element analysis results, indicating the reliability of the finite element analysis model.
会议名称:

Workshop 8 2018

会议时间:

2018-08-21

会议地点:

中国云南昆明

  • 专辑:

    工程科技Ⅰ辑; 工程科技Ⅱ辑

  • 专题:

    材料科学; 航空航天科学与工程

  • 分类号:

    TB33;V267.4

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