In-plane deformation behavior of unidirectional carbon fiber/epoxy prepreg layups

被引:0
|
作者
Chen P. [1 ,2 ]
Zhao Y. [1 ]
Chen F. [2 ]
Zhang B. [1 ]
机构
[1] School of Materials Science and Engineering, Beihang University, Beijing
[2] Composite Center, Shanghai Aircraft Manufacturing Corporation Ltd., Shanghai
关键词
Bias extension method; Deformation mechanism; Hot diaphragm forming; Pin-joined net(PJN) theory; Unidirectional thermoset prepreg;
D O I
10.13801/j.cnki.fhclxb.20190730.006
中图分类号
学科分类号
摘要
In order to fully understand the deformation behavior of prepreg in the process of hot diaphragm forming, the in-plane deformation mechanism of unidirectional carbon fiber/epoxy thermoset prepreg at high temperature was studied using the bias extension method. The effects of testing temperature, tensile rate, preheating time and stacking sequence on the in-plane deformation were investigated. Using digital image correlation technology, the specimen deformation and fiber rotation were captured during testing process. The results show that increasing temperature or decreasing tensile rate can promote the deformation of unidirectional carbon fiber/epoxy thermoset prepreg. Stacking sequence has a great influence on the deformation behavior of the unidirectional carbon fiber/epoxy thermoset prepreg stacks. The fiber rotation of [45/-45/90]S layup is easier than that of [45/90/-45]S layup, and the former has lower deformation resistance. The Pin-joined net (PJN) theory was used to predict the fiber rotation angle during the deformation process of the unidirectional carbon fiber/epoxy thermoset prepreg stacks, and the prediction value was compared with the experiment value. The results show that the prediction values deviate greatly from the experiment values, indicating that the PJN theory is not suitable for the prediction of the fiber rotation angle during the deformation of unidirectional carbon fiber/epoxy thermoset prepreg. Being preheated at 80℃ can increase the deformation resistance of the prepreg. © 2020, Editorial Office of Acta Materiae Compositae Sinica. All right reserved.
引用
收藏
页码:1049 / 1055
页数:6
相关论文
共 19 条
  • [1] HUANG Ying, The analysis on the hot diaphragm preforming process for composite material, Mechanical Design and Manufacturing Engineering, 44, 9, pp. 20-22, (2015)
  • [2] YANG Bo, WANG Fei, CHEN Yongqing, Development of manufacturing technology in large composites wing spar, Aeronautical Manufacturing Technology, 22, pp. 74-77, (2013)
  • [3] SJOLANDER J, HALLANDER P, AKERMO M., Forming induced wrinkling of composite laminates: A numerical study on wrinkling mechanisms, Composites Part A: Applied Science and Manufacturing, 81, pp. 41-51, (2016)
  • [4] WU Zhien, Hot drape forming of composite, Aeronautical Manufacturing Technology, pp. 113-116, (2009)
  • [5] CHEN Yali, Application of composite forming technique in military freighter A400M, Aerospace Manufacturing Technology, 10, pp. 32-35, (2008)
  • [6] WANG Yongjun, YANG Kai, CHEN Senlin, Et al., Hot-diaphragm for thermosetting carbon woven fabric composite with C-shape structure, Fiber Reinforced Plastics/Composites, 3, pp. 59-65, (2015)
  • [7] SMILEY A J, PIPES R B., Analysis of the diaphragm forming of continuous fiber reinforced thermoplastics, Journal of Thermoplastic Composite Materials, 1, 4, pp. 298-321, (1988)
  • [8] YU X, CARTWRIGHT B, MCGUCKIN D, Et al., Intra-ply shear locking in finite element analyses of woven fabric forming processes, Composites Part A: Applied Science and Manufacturing, 37, 5, pp. 790-803, (2006)
  • [9] BOISSE P, HAMILA N, VIDAL-SALLE E, Et al., Simulation of wrinkling during textile composite reinforcement forming. Influence of tensile, in-plane shear and bending stiffnesses, Composites Science and Technology, 71, 5, pp. 683-692, (2011)
  • [10] THIJE R H W T, AKKERMAN R., Solutions to intra-ply shear locking in finite element analyses of fibre reinforced materials, Composites Part A: Applied Science and Manufacturing, 39, 7, pp. 1167-1176, (2008)