含预置裂纹的CFRP层合板弯曲性能研究
|
摘要
分别对含有不同位置、角度和长度预置裂纹的T700/6240复合材料层合板进行三点弯曲实验并结合微观表征手段以研究不同裂纹参数对层合板弯曲性能和失效方式的影响,并建立裂纹长度与试样弯曲强度和模量之间的关系模型。利用ABAQUS有限元软件建立含有预置裂纹的复合材料层合板三点弯曲模型,对比验证有限元方法与实验结果的一致性。结果表明,含有不同参数预置裂纹层合板的弯曲强度和模量均小于完好试样,预置裂纹位置从层合板的上层移至下层,弯曲强度下降幅度由19. 10%减小至6. 24%,模量的下降幅度在11. 34%～12. 97%之间;裂纹角度的增加对弯曲强度没有趋势性影响,但会导致其弯曲模量不断降低,裂纹角度为90°时较完好试样分别降低了19. 10%和12. 97%;裂纹长度的增加导致弯曲强度和模量分别呈线性和三次曲线递减。有限元仿真计算结果与实验值对比的误差小于10%,验证了有限元方法的可靠性。
In this paper,three-point bending tests combined with microscopic characterization methods were carried out on T700/6240 composite laminates with embedded fiber fracture of different positions,angles and lengths to study the effects of different parameters on the bending properties and failure modes of the laminate,and the relationship model between fiber fracture length and bending strength and modulus was established. A three-point bending model of composite laminates with fiber fracture was established by using finite element software ABAQUS. The consistency between the finite element method and the experimental results was verified. The results show that the bending strength and modulus of laminates with different fiber fracture parameters are smaller than the intact specimens. And when fiber fracture position moves from the upper layer to the lower layer of the laminate,the descend range of bending strength could decrease from19. 10% to 6. 24%,and the descend range of modulus is between 11. 34% and 12. 97%. The increase of crack angle has no trend effect on the bending strength,however it could lead to continuous reduction of modulus.When the crack angle is 90°,comparing with the intact sample,the bending strength and modulus could reduce 19. 10% and 12. 97%,respectively. The increase of fiber fracture length could cause the bending strength and modulus to decrease linearly and cubically, respectively. The error ratio between the finite element calculation result and the experimental value is less than 10%,which verifies the reliability of the finite element method.
In this paper,three-point bending tests combined with microscopic characterization methods were carried out on T700/6240 composite laminates with embedded fiber fracture of different positions,angles and lengths to study the effects of different parameters on the bending properties and failure modes of the laminate,and the relationship model between fiber fracture length and bending strength and modulus was established. A three-point bending model of composite laminates with fiber fracture was established by using finite element software ABAQUS. The consistency between the finite element method and the experimental results was verified. The results show that the bending strength and modulus of laminates with different fiber fracture parameters are smaller than the intact specimens. And when fiber fracture position moves from the upper layer to the lower layer of the laminate,the descend range of bending strength could decrease from19. 10% to 6. 24%,and the descend range of modulus is between 11. 34% and 12. 97%. The increase of crack angle has no trend effect on the bending strength,however it could lead to continuous reduction of modulus.When the crack angle is 90°,comparing with the intact sample,the bending strength and modulus could reduce 19. 10% and 12. 97%,respectively. The increase of fiber fracture length could cause the bending strength and modulus to decrease linearly and cubically, respectively. The error ratio between the finite element calculation result and the experimental value is less than 10%,which verifies the reliability of the finite element method.
引文
[1]贺雍律,张鉴炜,黄春芳,等.CFRP层合板抗分层损伤技术研究进展[J].材料导报,2018,32(13):2288-2294,2303.
[2]张聪.纤维增强热塑性复合材料复合过程中纤维断裂研究[D].北京:北京化工大学,2015.
[3]高相胜.复合材料层板的分层扩展三维有限元分析[D].沈阳:东北大学,2008.
[4]茅人杰,孙国钧.单向纤维增强复合材料中纤维断裂及其发展[J].力学季刊,1997(2):160-168.
[5]张泰峰,张勇,蔡增杰,等.纤维增强复合材料层合板刚度退化研究[J].青岛理工大学学报,2010,31(3):98-103.
[6]姚卫星,翟洪军.纤维断裂引起层合板多向刚度减缩的细观力学模型[J].南京航空航天大学学报,2002,34(5):413-417.
[7]CRAVEN R,SZTEFEK P,OLSSON R.Investigation of impact damage in multi-directional tape laminates and its effect on local tensile stiffness[J].Compos Sci Technol,2008,68(12):2518-2525.
[8]宫文然.含分层损伤复合材料(CFRP)层合板结构屈曲和后屈曲力学行为研究[D].天津:天津大学,2015.
[9]Fibre-reinforced plastic composites-Determination of flexural properties:ISO 14125:1998[S].https://www.iso.org/standard/23637.html.
[10]李典森,卢子兴,李嘉禄,等.三维编织T300/环氧复合材料的弯曲性能及破坏机理[J].航空材料学报,2009,29(5):82-87.
[11]田亮,罗宇,梁嫄,等.纤维/织物增强复合材料层压板弯曲性能及破坏机理实验研究[J].实验技术与管理,2013(10):38-43.
[12]VINOD S,VINAY S,VINAY N,et al.Fracture morphology of carbon fiber reinforced plastic composite laminates[J].Mater Res,2010,13(3):417-424.
[13]习年生,于志成,陶春虎.纤维增强复合材料的损伤特征及失效分析方法[J].航空材料学报,2000,20(2):55-63.
[14]施建伟,张彦飞,杜瑞奎,等.复合材料层合板三点弯曲分层损伤有限元模拟[J].工程塑料应用,2015(2):60-63.
[15]叶金蕊,李嘉,刘卫平,等.分层缺损对复合材料结构压缩强度的影响[J].科技导报,2013,31(7):23-27.
[2]张聪.纤维增强热塑性复合材料复合过程中纤维断裂研究[D].北京:北京化工大学,2015.
[3]高相胜.复合材料层板的分层扩展三维有限元分析[D].沈阳:东北大学,2008.
[4]茅人杰,孙国钧.单向纤维增强复合材料中纤维断裂及其发展[J].力学季刊,1997(2):160-168.
[5]张泰峰,张勇,蔡增杰,等.纤维增强复合材料层合板刚度退化研究[J].青岛理工大学学报,2010,31(3):98-103.
[6]姚卫星,翟洪军.纤维断裂引起层合板多向刚度减缩的细观力学模型[J].南京航空航天大学学报,2002,34(5):413-417.
[7]CRAVEN R,SZTEFEK P,OLSSON R.Investigation of impact damage in multi-directional tape laminates and its effect on local tensile stiffness[J].Compos Sci Technol,2008,68(12):2518-2525.
[8]宫文然.含分层损伤复合材料(CFRP)层合板结构屈曲和后屈曲力学行为研究[D].天津:天津大学,2015.
[9]Fibre-reinforced plastic composites-Determination of flexural properties:ISO 14125:1998[S].https://www.iso.org/standard/23637.html.
[10]李典森,卢子兴,李嘉禄,等.三维编织T300/环氧复合材料的弯曲性能及破坏机理[J].航空材料学报,2009,29(5):82-87.
[11]田亮,罗宇,梁嫄,等.纤维/织物增强复合材料层压板弯曲性能及破坏机理实验研究[J].实验技术与管理,2013(10):38-43.
[12]VINOD S,VINAY S,VINAY N,et al.Fracture morphology of carbon fiber reinforced plastic composite laminates[J].Mater Res,2010,13(3):417-424.
[13]习年生,于志成,陶春虎.纤维增强复合材料的损伤特征及失效分析方法[J].航空材料学报,2000,20(2):55-63.
[14]施建伟,张彦飞,杜瑞奎,等.复合材料层合板三点弯曲分层损伤有限元模拟[J].工程塑料应用,2015(2):60-63.
[15]叶金蕊,李嘉,刘卫平,等.分层缺损对复合材料结构压缩强度的影响[J].科技导报,2013,31(7):23-27.