COMPRESSIVE PROPERTIES STUDY ON SEMI-CIRCLE AND SINGLE JOINT STRINGER END OF WING

Abstract

Abstract: Compression tests were performed on semi-circle and single joint stringer end of wing upper panel samples. Load-strain curves through the strain flowers around the holes under axial compression load were obtained. The results show that breaks mainly appear on the area near the first row fasteners on joint and stringer flange. A finite element analysis model is established, for which the result is slightly higher than the experimental result because the damage and rigidity are not introduced during the finite element analysis.

Key words: upper panel, compression test, strain, failure, finite element analysis

CLC Number:

TB332

ZHANG Ming-xing. COMPRESSIVE PROPERTIES STUDY ON SEMI-CIRCLE AND SINGLE JOINT STRINGER END OF WING[J]. Fiber Reinforced Plastics/Composites, 2016, 0(11): 27-31.

References

[1] 李玮, 段成红, 吴祥. 碳纤维复合材料强度的有限元模拟[J]. 玻璃钢/复合材料, 2011(1): 21-24.
[2] 李成, 郑艳萍. 机械连接结构中含圆孔复合材料板的盈利计算及仿真分析[J]. 玻璃钢/复合材料, 2007(3): 3-5.
[3] 张承学, 魏兵, 惠战荣, 等. 复合材料单筋长桁端头低能量冲击试验研究[J]. 研究与探索, 2007(10): 248-251.
[4] 张俊鼎, 陈斌. 复合材料机翼上壁板剖面形状选择研究[J].科技信息, 2013(12): 445-447.
[5] Zimmermann R. Klein H, Kling A. Buckling and postbuckling of stringer stiffened fiber composite curved panels-tests and computations[J]. Compos struct, 2006, 73(2): 150-161.
[6] Kai H. Failure analysis of bolted composite joints exhibiting in-plane failure modes[J]. Journal of Composite Materials,1996, 30 (3): 358-383.
[7] Orifici AC, Thomson RS, Herszberg Ⅰ, et al. Analysis methodology for failure in postbuckling skin-stiffener interfaces[J]. Compos Struct., 2008, 86(1-3): 186-193.
[8] Mahmood M S, Larry B L. Effects of materials nonlinearity on the three-dimensional stress state of pin-loaded composite laminates[J]. Journal of Composite Materials, 1996, 30 (7): 839-861.
[9] Faggiani A, Falzon BG. Numberical analysis of stiffener runout section[J]. Appl Compos Mater., 2007, 14(2): 145-158.
[10] Tserpes K I , Labeas G, Papanikos P , et al . Strength prediction of bolted joint s in graphite/ epoxy composite laminates[J]. Composites Part B : Engineering, 2002, 33(7): 521-529.
[11] Falzon BG, Davies GAO. The behavior of compressively loaded stiffener runout specimens-Part I: Experiments[J]. J Compos Mater., 2003, 37(5): 381-400.
[12] Psarras S, Pinho ST, Falzon BG. Design of composite stiffener run-outs for damage tolerant[J]. Finite Elem Anal Des., 2011, 47(8):949-954.
[13] Psarras S, Pinho ST, Falzon BG. Investigating the use of compliant webs in the damage-torlerance design of stiffener run-outs[J]. Compos Part B: Eng., 2013, 45(1):70-77.
[14] Shoumei Wang, Yao xin han. Finite element analysis for load distribution of multi-fastener joints [J]. Composite material, 1988, 22(2): 125-135.
[15] 陈绍杰. 复合材料设计手册[M]. 北京: 航空工业出版社, 1990.