STUDIES ON SEMI-CIRCLE DEPTH INFLUENCE ON COMPRESSIVE PROPERTIES OF COMPOSITE STRINGER OF AIRCRAFT

Abstract

Abstract: Semi-circle depth stringer end samples of center wing are made, and compression test is carried out. Load-strain curves under axial compression load were obtained. The results show that non-linear deformation appeared, and the failure load is greatly influenced by the semi-circle depth. Failure load increases with the semi-circle depth. The largest strain appears on the first row fasteners on the rib flange and skin.

Key words: semi-circle, depth, compression, failure

CLC Number:

TB332

ZHANG Ming-xing. STUDIES ON SEMI-CIRCLE DEPTH INFLUENCE ON COMPRESSIVE PROPERTIES OF COMPOSITE STRINGER OF AIRCRAFT[J]. Fiber Reinforced Plastics/Composites, 2018, 0(8): 83-88.

References

[1] Kinet D., Mégret P., Goossen K.W., et al. Fiber bragg grating sensors toward structural health monitoring in composite materials[J]. Challenges and Solutions. Sensors., 2014(14): 7394-7419.
[2] 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.
[3] 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.
[4] Di Sante R. Fibre optic sensors for structural health monitoring of aircraft composite structures[J]. Recent Advances and Applications. Sensors., 2015(15): 18666-18713.
[5] Hill K.O., Meltz G.. Fiber bragg grating technology fundamentals and overview[J]. Lightwave Technol., 1997(15): 1263-1276.
[6] 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.
[7] Kang H.K., Park J.W., Ryu C.Y., et al. Development of fibre optic ingress/egress methods for smart composite structures[J]. Smart Mater. Struct, 2000, 9(2): 149.
[8] Kong C., Lee I.C., Kim C. G., et al. Postbuckling and failure of stiffened composite panels under axial compressio[J]. Compos. Struct., 1998, 42(1): 13-21.
[9] Psarras S, Pinho S T, Falzon B G. 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.
[10] Falzon B G, Davies G A O, Greenhalgh E. Failure of thickskinned stiffener runout sections loaded in uniaxial compression[J]. Composite structures, 2001, 53(2): 223-233.
[11] Shuart M. J., Ambur D. R., Davis D. D. J., et al. Technology integration box beam failure study: N95-28847[R]. NASA Technical Report , 1992.
[12] Faggiani, Andrea, Falzon B.G.. Numerical analysis of stiffener runout sections[J]. Applied Composite Materials, 2007(14): 145-158.
[13] Falzon B. G., Hitchings D., Besant T.. Fracture mechanics using a 3D composite element[J]. Compos. Struct., 1999, 45(1): 29-39.
[14] A.C. Orifici, R.S. Thomson, R. Degenhardt, et al. Degradation investigation in a postbuckling composite stiffened fuselage panel[J]. Composite structures, 2008, 82(2): 217-224.
[15] Torsten Moecker, Hans-guenther Reimerdes. Postbuckling simulation of curved stiffened composite panels by the use of strip elements[J]. Composite structures, 2006, 73(2): 237-243.
[16] P. Badallo., D.Trias., E. Lindgaard. Damage tolerance optimization of composite stringer run-out under tensile load[J]. Composite structures, 2015, 133(2): 98-104.