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江苏科技信息 ›› 2015, Vol. 32 ›› Issue (30): 52-53,68.doi: 10.3969/j.issn.1004-7530.2015.30.021

• 论文 • 上一篇    下一篇

复合材料层合板与铝合金板不规则连接钉载分配分析

张冠彪   

  1. 上海飞机设计研究院,上海,201210
  • 出版日期:2015-10-25 发布日期:2015-10-25

Pin Load Distribution Analysis on Irregular Joints of Composite Laminate and Alloy Plate

Zhang Guanbiao   

  • Online:2015-10-25 Published:2015-10-25

摘要： 飞机结构中复合材料层合板与金属板连接不可避免，由于尺寸、空间、重量等因素的影响，连接部位会出现不规则连接，而在以往研究中主要针对复合材料规则连接结构进行分析，不规则连接结构的钉载分配情况不明确，不利于进行复合材料结构设计和强度分析。文章基于二维有限元分析方法，利用有限元软件MSC.PATRAN/NASTRAN对复合材料层合板与铝合金板不规则连接结构进行分析，考虑螺栓的直径、材料以及连接板的属性，利用Fastener单元模拟螺栓，计算得到各螺栓载荷分配情况。结果表明该连接结构螺栓载荷分配不均匀，螺栓承受最大载荷超过螺栓承载平均值的30.7%，同时说明螺栓间距对载荷分布有影响。

关键词: 复合材料连接, 钉载分配, 数值分析, Fastener

Abstract: The joint of composite laminate and alloy plate is inevitable in aircraft structure. Due to the size,space, weight and other factors,there would be irregular joints. While in the previous studies,only analysis on the regular connection structure is involved. Load distribution in the irregular joint is not clear and is not conducive to the composite structure design and stress analysis. Based on two-dimensional FEA ,this paper used MSC.PATRAN/NASTRAN to analysis the irregular composite laminate and alloy plate connection structure. With bolt diameters, materials and other properties of connection plates ,bolts can be simulated by Fastener element and finally the load distribution of each bolt was calculated. The results show that the load distribution is not uniform on this structure. The maximum load is30.7%above the average ,while implies that the bolt spacing effects the load distribution.