航空学报 > 2022, Vol. 43 Issue (6): 525899-525899   doi: 10.7527/S1000-6893.2022.25899

含离散源损伤的复合材料壁板的剩余强度评估

汪厚冰, 王夏涵, 林国伟, 李新祥, 杨胜春   

  1. 中国飞机强度研究所 全尺寸飞机结构静力/疲劳航空科技重点实验室, 西安 710065
  • 收稿日期:2021-06-01 修回日期:2022-03-01 出版日期:2022-06-15 发布日期:2022-02-28
  • 通讯作者: 汪厚冰,E-mail:wanghoby@sina.com E-mail:wanghoby@sina.com
  • 基金资助:
    民机科研项目(MJ-2015-F-038)

Residual strength evaluation of curved hat-stiffened composite panels with discrete-source damage

WANG Houbing, WANG Xiahan, LIN Guowei, LI Xinxiang, YANG Shengchun   

  1. Aeronautics Science and Technology Key Laboratory of Full Scale Aircraft Structure Statics and Fatigue, Aircraft Strength Research Institute of China, Xi'an 710065, China
  • Received:2021-06-01 Revised:2022-03-01 Online:2022-06-15 Published:2022-02-28
  • Supported by:
    Civil Aircraft Scientific Research Project (MJ-2015-F-038)

摘要: 为研究含离散源损伤的碳纤维增强树脂基复合材料曲面帽形加筋壁板在内压-轴压联合载荷下的剩余强度,对7长桁4框的复合材料曲面帽形加筋壁板进行了试验和分析。结果表明,与离散源损伤距离超过1个典型长桁间距壁板的蒙皮和长桁在轴压载荷作用下轴向应变分布较均匀;加载过程中,损伤区附近应力重新分配,降低了应力集中,离散源损伤可简化为圆孔;基于FD判据和经典层压板理论的计算方法能较准确的计算出含离散源损伤的曲面帽形加筋壁板在内压-轴压联合载荷下的剩余强度;并针对复合材料曲面帽形加筋壁板的结构特点、应变分布特征及破坏模式提出一种在内压-轴压联合载荷下轴向剩余强度的工程估算方法;计算结果均与试验结果吻合较好。

关键词: 离散源损伤, 复合材料, 帽形加筋壁板, 剩余强度, 联合载荷

Abstract: Experiments and analysis on curved hat-stiffened composite panels with 7 stringers and 4 frames are conducted to investigate the residual strength of panels with discrete-source damage under combined internal pressure and axial compression. The research indicates that axial strain of stringers and skin is equal more than one stringer spacing from discrete-source damage, stress is redistributed near discrete-source damage, stress concentration reduces, and discrete-source damage can be simplified as a round hole. The research also proved that the method based on FD criterion and the classical laminate theory can be used to predict the residual strength of curved hat-stiffened composite panels with discrete-source damage under combined internal pressure and axial compression. An empirical method was proposed to estimate the residual strength of the curved hat-stiffened composite panels with discrete-source damage under combined internal pressure and axial compression based on the structural characteristics, strain distribution and failure mode. The calculated results are in good agreement with the experimental results.

Key words: discrete-source damage, composite, curved hat-stiffened panels, residual strength, combined loading

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