Composite Materials Research Progress

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194 Giangiacomo Minak and Andrea Zucchelli In the picture of the low damage level lamina, both in the loaded side (L-a) and in the back side (L-b) the indentation is barely visible by the naked eye. The medium level damage laminas present a slightly larger mark on the loaded side (M-a) and some fibre breakage with matrix leakage on the back side (M-b). Finally the highly damaged lamina pictures (H-a) and (H-b) show fibre failure on both sides. Figure 24. Fibres failure on the loaded surface for the Low load level: fractures on fibres are evidenced by the arrows. Figure 25. Tensile fibre failure on the back surface for the Medium load level: fracture on one fibre is evidenced by the arrows.
Damage Evaluation and Residual Strength Prediction of CFRP Laminates … 195 Investigating more deeply the loaded side of the low damage level laminate it was possible to find a number of broken fibres due to local shear [29], as it is shown in the SEM image of figure 24. A different failure mode for the fibre is shown in the SEM image of figure 25. 3 2.5 2 1.5 1 0.5 Indentation: Maimum Load (kN) Load (kN) B 3 2.5 2 1.5 1 0.5 0 0 2 4 6 8 10 12 14 0 0 2 4 6 8 10 12 14 M 3 2.5 2 1.5 1 0.5 P 0 0 2 4 6 8 10 12 14 Displacement (mm) Figure 26. Transversal load-displacement curves for the three damage levels. 3.0 2.5 2.0 1.5 1.0 0.5 Load Energy 0.0 0.0 0.0 2.0 4.0 6.0 8.0 10.0 12.0 14.0 Indentation: Maximum displacement (mm) 30.0 25.0 20.0 15.0 10.0 5.0 Indentation: Total Strain Energy (J) Figure 27. Maximum displacement, maximum load and total strain energy of the transversal loading tests.
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COMPOSITE MATERIALS RESEARCH PROGRE
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Copyright © 2008 by Nova Science P
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vi Contents Chapter 9 Recent Advanc
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viii Lucas P. Durand scale transiti
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x Lucas P. Durand machine. In paral
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In: Composite Materials Research Pr
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Multi-scale Analysis of Fiber-Reinf
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T300 fibers (Soden et al., 1998; Ag
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1 I L = L : r v Multi-scale Analysi
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I E ⎡0 ⎢ ⎢0 ⎢ ⎢ ⎢ ⎢0
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Applied macroscopic load Correspond
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Optimization of Laminated Composite
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⎧σ x ⎫ ⎡ mE ⎪ ⎪ ⎢ x
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and γ 2 γ 0 Optimization of Lamin
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4 x 10 5 4 3 2 1 Compliance (Nmm) 0
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3.5 3 2.5 2 1.5 1 Optimization of L
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110 W.H. Zhong, R.G. Maguire, S.S.
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112 Reinforcement: Advanced materia
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130 Yuanxin Zhou, Hassan Mahfuz, Vi
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140 Heat Flow (W/g) Heat Flow (W/g)
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Page 158 and 159: 144 Material Yuanxin Zhou, Hassan M
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Page 162 and 163: 148 Yuanxin Zhou, Hassan Mahfuz, Vi
Page 164 and 165: 150 Governing Equation For the fibe
Page 166 and 167: 152 ⎧ UU = ⎨ ⎩ ⎧ UD = ⎨
Page 170 and 171: 156 Stress (MPa) 120 80 40 0 Yuanxi
Page 180 and 181: 166 Giangiacomo Minak and Andrea Zu
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Page 202 and 203: 188 A B E (MPa) D 250000 200000 150
Page 204 and 205: 190 D D 1.0 0.9 0.8 0.7 0.6 0.5 0.4
Page 218 and 219: 204 Conclusion Giangiacomo Minak an
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Page 225 and 226: Research Directions in the Fatigue
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Damage Variables in Impact Testing
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F peak [kN] 16 14 12 10 8 6 4 2 0 D
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Eletromechanical Field Concentratio
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MV/m. Eletromechanical Field Concen
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276 S.C. Tjong developed in the pas
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278 S.C. Tjong ultrasonic waves gen
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280 S.C. Tjong applications. Goujon
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282 S.C. Tjong nanoparticles were p
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284 S.C. Tjong where DL is lattice
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286 S.C. Tjong stress is temperatur
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288 S.C. Tjong threshold stress res
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290 S.C. Tjong NC Al, and the NC Al
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292 S.C. Tjong (a) (b) Figure 19. T
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294 S.C. Tjong Apart from forming u
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296 S.C. Tjong [29] Saravanan, M.;
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298 braids, 115 broadband, 211 bubb
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300 endothermic, 139 endurance, 32
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302 isostatic pressing, 279, 288 It
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304 piezoelectricity, 261 pitch, 12
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306 67, 69, 70, 71, 72, 73, 84, 94,
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