摘要
为研究含冲击损伤复合材料加筋壁板剪切强度,提升飞机机体结构的安全性,以复合材料加筋壁板为研究对象,基于二维Hashin失效准则建立冲击前后剪切仿真模型,分析对比冲击前后剪切试验。结果表明,冲击仿真模型可较为精确地预测冲击的凹坑深度和损伤分布,凹坑深度相对误差为0.7%,冲击损伤分布基本相同,损伤均无明显向外扩张,由冲击正面至背面逐渐减弱。冲击后剪切仿真模型可较为精确地预测冲击后剪切的破坏载荷和模式,破坏载荷相对误差为7.47%,冲击后剪切破坏模式与试验破坏模式基本相同。
This paper intends to study the shear strength of composite stiffened plates with impact damage and improve the safety of aircraft body structure.Taking composite stiffened panels as the study object,the study works by establishing the impact and post-impact shear simulation models based on two-dimensional Hashin failure criterion;analyzing and compared effects of the impact and post-impact shear tests.The results show that the impact simulation model can predict the depth and damage distribution after impact,and with the relative error of the depth by 0.7%,the impact damage distribution is basically the same,without obvious outward expansion,and gradually weakened from impact front to back.The post-impact shear simulation model can predict the failure load and failure mode of post-impact shear,with the relative error of failure load by 7.47%,basically the same as experimental failure mode.
作者
李万
孟政委
张伟
Li Wan;Meng Zhengwei;Zhang Wei(The Fifth Military Representative Office of the Naval Equipment Department in Wuhan Area,Wuhan 430000,China;Experiment&Meterage Center,China Special Aircraft Research Institute,Jingmen 448035,China)
出处
《黑龙江科技大学学报》
2023年第2期196-201,共6页
Journal of Heilongjiang University of Science And Technology
基金
工信部民用飞机专项科研资助项目(MJZ53N21)。
关键词
复合材料
加筋壁板
冲击损伤
剪切强度
composite material
stiffened panels
impact damage
shear strength
