The mechanical properties of Ti/APC-2/Kevlar/epoxy
hybrid composite laminates after low velocity impact were investigated at room
temperature. There were three types of samples, including three layered
[Ti/(0/90)s/Ti], five layered [Ti/(0/90)2/]s and nine layered [Ti/Kevlar/Ti/(0/90)2/]s. The lay-ups of APC-2 were crossply,
while Ti layers were treated by chromic acid anodic method. Ti and APC-2 were stacked
to fabricate the composite laminates via hot press curing process. Kevlar
layers were added to fabricate nine-layered composite laminates via vacuum
assisted resin transfer molding.The drop-weight tests were conducted with a
hemispherical nosed projectile in 10 mm diameter. The impact loads were 5 kg
and 10 kg and impact heights were adjusted to penetrate samples or the maximum
height 1.50 m. The static tensile tests were conducted to measure the residual
mechanical properties after impact. The free body drop tests were also
simulated by using finite element method and software ANSYS LS-DYNA3D.The results showed that
the bottom Ti layer absorbed more internal energy than the top Ti layer, then
the cracks were found in the bottom Ti layer more often. The ultimate tensile
strength reduced significantly after impact. The initial longitudinal
compliance increased with the impact height increasing and decreased after the
samples penetrated. Comparing the experimental data with the numerical results,
it was found that the
damage of the latter was more serious than that of the former. On the
conservative side, the results of numerical simulation are acceptable and
References
[1]
Ditchek, B.M., Breen, K.R., Sun, T.S. and Venables, J.D. (1980) Morphology and Composition of Titanium Adherends Prepared for Adhesive Bonding. SAMPE P. O. BOX 613 AZUSA CA, 13-24.
[2]
Dan-Jumbo, E., Leewood, A.R. and Sun, C.T. (1989) Impact Damage Characteristics of Bismaleimides and Thermoplastic Composite Laminates. Composite Material: Fatigue Fracture ASTM International, 2, 356-317. https://doi.org/10.1520/STP10425S
[3]
Lin, C.T., Kao, P.W. and Yang, F.S. (1991) Fatigue Behavior of Carbon Fiber-Reinforced Aluminum Laminates. Composite, 22, 135-141. https://doi.org/10.1016/0010-4361(91)90672-4
[4]
Castrodeza, E.M., Ipina, J.E.P. and Bastian, F.L. (2002) Experimental Techniques for Fracture Instability Toughness Determination of Unidirectional Fibre Metal Laminates. Fatigue Fracture Engineering Material Structure, 25, 999-1008. https://doi.org/10.1046/j.1460-2695.2002.00552.x
[5]
Vlot, A. (1993) Impact Properties of Fiber Metal Laminates. Composite Engineering, 3, 911-927. https://doi.org/10.1016/0961-9526(93)90001-Z
[6]
Vlot, A. (1996) Impact loading on Fibre Metal Laminates. International Journal Impact Engineering, 18, 291-307. https://doi.org/10.1016/0734-743X(96)89050-6
[7]
Gunnink, J.W. (1988) Damage Tolerance and Supportability Aspects of Arall Laminate Aircraft Structures. Composite Structure, 10, 83-104. https://doi.org/10.1016/0263-8223(88)90062-1
[8]
Khalili, S.M.R., Mittal, R.K. and Kalibar, S.G. (2005) A Study of the Mechanical Properties of Steel/Aluminium/GRP Laminates. Material Science Engineering: A, 12, 137-140. https://doi.org/10.1016/j.msea.2005.08.016
[9]
Zhou, Y.X., Wang, Y. and Mallick, P.K. (2004) An Experimental Study on the Tensile Behavior of Kevlar Fiber Reinforced Aluminum Laminates at High Strain Rates. Material Science Engineering: A, 381, 355-362. https://doi.org/10.1016/j.msea.2004.04.027
[10]
Jen, M.H.R., Tseng, Y.C. and Li, P.Y. (2007) Fatigue Response of Hybrid Magnesium/Carbon-Fiber/PEEK Nanocomposite Laminates at Elevated Temperature. Journal Japan Society Experimental Mechanics, 7, s56-s60.
[11]
Jen, M.H.R., Chang, C.K. and Sung, Y.C. (2015) Fabrication and Mechanical Properties of Ti/APC-2 Hybrid Nanocomposite Laminates at Elevated Temperatures. Journal Composite Material, 50, 2035-2045. https://doi.org/10.1177/0021998315599590
[12]
Asundi, A. and Choi, A.Y.N. (1997) Fiber Metal Laminates: An Advanced Material for Future Aircraft. Journal Material Processing Technology, 63, 384-394. https://doi.org/10.1016/S0924-0136(96)02652-0
[13]
Dorey, G., Bishop, S.M. and Curtis, P.T. (1985) On the Impact Performance of Carbon Fibre Laminates with Epoxy and PEEK Matrices. Composite Science Technology, 23, 221-237. https://doi.org/10.1016/0266-3538(85)90019-3
[14]
Joshi, S.P. and Sun, C.T. (1985) Impact Induced Fracture in a Laminated Composite. Journal Composite Material, 19, 51-66. https://doi.org/10.1177/002199838501900104
[15]
Jen, M.H.R., Chang, C.K., Sung, Y.C. and Hsu, F.C. (2010) Fabrication of Ti/APC-2 Nanocomposite Laminates and Their Fatigue Response at Elevated Temperature. 5th International Conference on Fatigue Composite, Nanjing, October 2010, 317-325.
[16]
Ramani, K., Weidner, W.J. and Kumar, G. (1998) Silicon Sputtering as a Surface Treatment to Titanium Alloy for Bonding with PEKEKK. International Journal Adhesion Adhesives, 18, 401-412. https://doi.org/10.1016/S0143-7496(98)00042-6
[17]
Sun, C.T. and Rechak, S. (1988) Effect of Adhesive Layers on Impact Damage in Composite Laminates. In: Composite Materials: Testing and Design (Eighth Conference), ASTM International, 97-1-97-27. https://doi.org/10.1520/STP26130S
[18]
Vlot, A. and Gunnink, J.W. (2011) Fibre Metal Laminates: An Introduction. Springer Science & Business Media.
[19]
Wu, C.L., Zhang, M.Q., Rong, M.Z. and Friedrich, K. (2005) Silica Nanoparticles Filled Polypropylene: Effects of Particle Surface Treatment, Matrix Ductility and Particle Species on Mechanical Performance of the Composites. Composite Science Technology, 65, 635-645. https://doi.org/10.1016/j.compscitech.2004.09.004
![\"\"](\"Edit_ea4cf0ee-9bf8-4523-826b-a23a326accdf.bmp\")
![\"\"](\"Edit_3ce7f600-91e5-425c-b6bd-d6bf4856fedc.bmp\")
