STUDY OF COMPRESSIVE STRENGTH OF COMPOSITE STRUCTURE WITH DELAMINATION

Abstract

Abstract: The compression test of composite laminates with different delamination damage was carried out, the ultimate load and failure mode of composite laminates with different delamination damage was recorded, and the influence of delamination on the compressive strength of composite laminates was analyzed. Based on ABAQUS platform, a finite element model of composite structure with delamination was established. Hashin criterion and Camanho criterion were introduced by wrote UMAT subroutines to study the generation and evolution of fiber or matrix damage. Virtual crack closure technology (VCCT) was used in combination with B-K criterion to calculate delamination expansion. Finally, the simulation results are compared with the test results to verify the correctness of the simulation model. Using the same method, the influence of radian, size and position of delamination on failure mode and compressive strength of curved composite laminates was analyzed. The results show that the residual compressive strength of curved composite laminates with larger radian is higher than that of flat composite laminates. If the radian of the curved composite laminates is small, the larger the delamination size, the smaller the residual compressive strength of the curved composite laminates. The deeper the position of delamination, the greater the residual compressive strength of the curved composite laminates.

Key words: composite laminate, VCCT, delamination, UMAT subroutine

CLC Number:

TB332

ZHANG Dong-zhe, LIN Zhi-yu, LIN Ren-bang, YANG Yan-zhi. STUDY OF COMPRESSIVE STRENGTH OF COMPOSITE STRUCTURE WITH DELAMINATION[J]. COMPOSITES SCIENCE AND ENGINEERING, 2020, 0(12): 64-73.

References

[1] 陈群志, 关志东, 王进, 等. 分层缺陷对复合材料结构疲劳寿命影响研究[J]. 机械强度, 2004(s1): 121-123.
[2] 易美琦. 层合板分层损伤等效模拟方法及剩余强度研究[D]. 哈尔滨: 哈尔滨工业大学, 2016.
[3] 许洪明, 温卫东, 刘芳. 含分层缺陷复合材料层合板压缩强度试验研究[J]. 航空发动机, 2013, 39(3): 73-76.
[4] 矫桂琼, 丁桂珍. 分层缺陷对复合材料层合板强度影响的试验研究[C]//中国航空学会第八届全国复合材料学术会议. 中国航空学会, 2007: 994-997.
[5] 周睿, 关志东, 贾云超, 等. 分层缺陷对复合材料层板压缩性能的影响[J]. 北京航空航天大学学报, 2015, 41(2): 311-317.
[6] SINGH K L, DATTAGURU B, RAMAMURTHY T S, et al. Delamination tolerance studies in laminated composite panels[J]. Sadhana, 2000, 25(4): 409-422.
[7] 刘畅, 王康康, 赵洁. 含分层损伤碳纤维复合材料剩余强度等效评估原则[J].飞机设计, 2019, 39(3): 27-32.
[8] 孙先念, 陈浩然, 苏长健, 等. 含分层损伤复合材料层合板分层扩展研究[J]. 力学学报, 2000(2): 223-232.
[9] 姜晓伟, 朱书华, 李国弘,等. 含分层缺陷复合材料层合板分层扩展研究[J]. 航空计算技术, 2014, 44(5): 73-76.
[10] 王瑜, 赵美英, 余明. 复合材料层压板分层损伤扩展与压缩强度预测[J]. 机械科学与技术, 2011, 030(7): 1051-1055.
[11] 杜洪雨, 奚晓波, 孟力华, 等. 含分层损伤的复合材料层压板后屈曲及低周疲劳分层扩展有限元模拟研究[J]. 玻璃钢/复合材料, 2018(6): 39-43.
[12] SHORT G J, GUILD F J, PAVIER M J. Delaminations in flat and curved composite laminates subjected to compressive load[J]. Composite structures, 2002, 58(2): 249-258.
[13] RYBICKI E F, KANNINEN M F. A finite element calculation stress intensity factors by a modified crack closure integral[J]. Eng Fract Mech, 1977, 9(4): 931-938.
[14] LIU P F, HOU S J, CHU J K, et al. Finite element analysis of postbuckling and delamination of composite laminates using virtual crack closure technique[J]. Composite Structures, 2011, 93(6): 1549-1560.
[15] HASZIN Z. Failure criteria for unidirectional fiber composites[J]. Journal of Applied Mechanics, 1980, 47(2): 329-334.
[16] CAMANHO P P, MATTHEWS F L. A progressive damage model for mechanically fastened joints in composite laminates[J]. Journal of Composite Materials, 1999, 33(24): 2248-2280.