COMPRESSIVE PROPERTIES STUDIES ON ANGLE CUTTING AND SINGLE JOINT COMPOSITE STRINGER END OF AIRCRAFT CENTER WING

Abstract

Abstract: Angle cutting and single joint stringer end samples of center wing were made and subjected to compression test. Load-strain curves under axial compression load were obtained. The results show that non-linear deformation appeared and under the increasing load, bolts connecting rib flange, skin and stringer were sheared and failed on connection. The largest strain appears on the the first row fastners on the rib flange and skin.

Key words: center wing, upper panel, compression, shear, non-linear, FEA

CLC Number:

TB332

ZHANG Ming-xing. COMPRESSIVE PROPERTIES STUDIES ON ANGLE CUTTING AND SINGLE JOINT COMPOSITE STRINGER END OF AIRCRAFT CENTER WING[J]. Fiber Reinforced Plastics/Composites, 2018, 0(4): 27-31.

References

[1] Camanho P. P., Davila, et al. Mixed-mode decohesion finite elements for the simulation of delamination in composite materials[J]. NASA-Technical Paper, 2002.
[2] 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.
[3] Kong C., Lee I.C., Kim C.G., et al. Postbuckling and failure of stiffened composite panels under axial compression[J]. Compos Struct, 1998, 42(1): 13-21.
[4] 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.
[5] 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.
[6] 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.
[7] Greenhalgh E., Garcia H.G.. Fracture mechanisms and failure processes at stiffener run-outs in polymer matrix composite stiffened panels[J]. Compos. Part A: Appl. Sci. Manuf., 2004, 35(12): 1447-1458.
[8] Falzon B.G., Hitchings, et al. Fracture mechanics using a 3D composite element[J]. Compos. Struct., 1999, 45(1): 29-39.
[9] 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.
[10] Shuart M.J., Ambur, et al. Technology integration box beam failure study[J]. NASA Technical Report, 1992.
[11] Faggiani, Andrea, Falzon, et al. Numerical analysis of stiffener runout sections[J]. Applied Composite Materials, 2007(14): 145-158.
[12] J Reinoso, A Blázquez, A Estefani, et al. A composite runout specimen subjected to tension-compression loading conditions: Experimental and global-local finite element analysis[J]. Composite Structures, 2013, 101(15): 274-289.
[13] P. Badalló, D. Trias, E. Lindgaard. Damage tolerance optimization of composite stringer run-out under tensile load[J]. Composite Structures, 2015(133): 98-104.
[14] J Reinoso, A Blázquez, F París. Damage simulations in composite structures in the presence of stress gradients[J]. Modeling Damage Fatigue & Failure of Composite, 2016: 391-424.
[15] P Upadhyaya, S Roy, MH Haque, et al. A novel numerical-experimental approach for predicting delamination in high temperature polymer matrix composites[J]. Composite Structures, 2013, 104(5):118-124.
[16] Reinoso J., Blázquez A., Távara L., et al. Damage tolerance of composite runout panels under tensile loading[J]. Composites Part B: Engineering, 2016(96): 79-93.