针对具有典型铺设角[0/45/-45/90]的开孔碳纤维层合板,采用三维有限元数值模拟方法,分析了在单向拉伸载荷作用下孔边附近的层间应力,讨论了界面层参数对层间应力的影响,详细给出了典型铺设角之间层间应力的分布规律和最大层间应力产生的位置。结果表明：对于相同铺设角的界面层,沿厚度方向的位置影响层间应力的大小,但不影响分布趋势;而铺层顺序（如[角度1/角度2]或[角度2/角度1]）对层间应力的大小和分布趋势影响则较小。最大层间正应力产生于[-45/90]的界面层,位于与拉伸方向成90°的位置,是外加拉伸应力的51%;最大层间剪应力产生于[-45/0]的界面层,最大层间环向剪应力位于与拉伸方向成74°的位置,是外加拉伸应力的64%;而最大层间径向剪应力位于与拉伸方向成66°的位置,是外加拉伸应力的25%。
The interlaminar stresses of a carbon fiber-reinforced laminated plate with a hole were analyzed using three-dimensional finite element numerical simulation.This laminated plate was subjected to uniaxial forces and composed of layers with typical ply angles [0/45/-45/90].The effects of the ply parameters on the interlaminar stress distribution were investigated;in the meantime,the maximum value and detailed distribution of interlaminar stresses in different typical interfaces were presented.The results show that the location of interfaces along thickness only affects the magnitudes of interlaminar stresses but not the trend of distribution,and the stacking sequence（[angle 1/angle 2] or [angle 2/angle 1]） affects neither the magnitudes of interlaminar stresses nor the trend of distribution.Furthermore,the maximum normal stress of interface occurs between [-45/90] layers at 90° from the loading axis with its value reaching 51% of the value of applied stress,the maximum interlaminar shearing stress occurs between layers： the maximum circle shearing stress occurs at 74° with its value reaching 64% of the value of applied stress,and the maximum radial shearing stress occurs at 66° with its value reaching 25% of the value of applied stress.
参考文献
| [1] | Lagunegrand L, Lorriot T, Harry R, Wargnier H, Quenisset J M. Initiation of free-edge delamination in composite laminates [J]. Composites Science and Technology, 2006, 66(10): 1315-1327. |
| [2] | 李磊, 王毅, 侯乃先, 岳珠峰. 带圆孔层合板孔边层间应力分析、失效研究及软件开发 [J]. 机械强度, 2008, 30(4): 633-637. |
| [3] | 李成, 铁瑛, 郑艳萍. 含复杂孔形复合材料孔边应力场的数值分析[J]. 玻璃钢/复合材料, 2007(6): 18-20. |
| [4] | Pipes R B, Pagano N J. Interlaminar stresses in composite laminates under uniform axial extension [J]. J Compos Mater, 1970, 4: 538-548. |
| [5] | 单辉祖, 黄明聪, 施振东. 含圆孔层合板层间应力分析的边界层理论 [J]. 力学学报, 1989, 21(5): 596-606. |
| [6] | 陈荣庚, 陈万吉. 基于整体-局部位移假设的高阶理论及其三角形板单元[J]. 复合材料学报, 2000, 17(3): 96-102. |
| [7] | Ko C C, Lin C C. Method for calculating the interlaminar stresses in symmetric laminates containing a circular hole [J]. AIAA J, 1992, 30(1): 197-204. |
| [8] | 张培新, 李亚智. 受面内载荷的层压复合材料的层间应力分析[J]. 机械强度, 2006, 28(2): 224-228. |
| [9] | 李亚智, 郭晓波, 黄志远. 基于组合单元的层压复合材料三维应力分析[J]. 复合材料学报, 2009, 26(3): 207-212. |
| [10] | 王丹勇, 温卫东, 崔海涛. 含孔复合材料层压板静拉伸三维逐渐损伤分析[J]. 力学学报, 2005, 37(6): 788-794. |
| [11] | Fagiano C, Abdalla M M, Kassapoglou C, Gurdal Z. Interlaminar stress recovery for three-dimensional finite elements [J]. Composites Science and Technology, 2010, 70(3): 530-538. |
- 下载量()
- 访问量()
- 您的评分：
-
10%
-
20%
-
30%
-
40%
-
50%