Composite Materials Research Progress

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192 Giangiacomo Minak and Andrea Zucchelli Figure 21. (A) fixture system, (B)experimental device. AE sensors Cutting directions 40 mm 250 mm Detected AE sources External fibers direction Figure 22. Damaged zone area detected by AE emission and tensile specimens cutting directions for the High damage level. Some plates were also analyzed by C-Scan and MicroCT and in these cases the value of damaged area evaluated by AE was confirmed. Nine plates had the external ply fibres oriented in the direction of the specimen axis and other nine had the external ply fibres orthogonal to the specimen axis, so that two different
Damage Evaluation and Residual Strength Prediction of CFRP Laminates … 193 stacking sequences were produced, respectively [0,90,45,-45]s and [90,0,45,-45]s , as shown in figure 22. Analogous tensile tests were run, for each stacking sequence, on nine undamaged specimens cut from undamaged zones of the same plates in order to get reference values. Tensile tests were performed by means of the same servo-hydraulic machine in displacement control with a head speed of 0.02 mm/s and a gauge length of 150 mm. Also in the case of tensile tests the AE have been monitored by a Physical Acoustic Corporation (PAC) PCI-DSP4 device with two transducers PAC R15, setting the amplitude threshold at 40 dB. Case study 2: Results and Discussion Transversal load test In figure 23 are shown macro photos of the loaded side (a) and of the back side (b) of damaged plates for the three different damage levels. Figure 23. Damaged zones (inside the dotted circles) for the three damage levels (Low, Medium, High) on the loaded surface (a) and on the back surface (b).
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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)
Page 156 and 157: 142 Yuanxin Zhou, Hassan Mahfuz, Vi
Page 158 and 159: 144 Material Yuanxin Zhou, Hassan M
Page 160 and 161: 146 SEM Analysis Yuanxin Zhou, Hass
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
Page 184 and 185: 170 ⎟ ⎞ ⎠ s ⎜ ⎛ ⎝ = a E
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
Page 241 and 242: Bending force [N] Research Directio
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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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Composite Materials Research Progress

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