Composite Materials Research Progress

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174 Giangiacomo Minak and Andrea Zucchelli During the test, the AE were monitored by a Physical Acoustic Corporation (PAC) PCI- DSP4 device with two transducers PAC R15 setting up the amplitude threshold at 40 dB. A B 140 mm 110 mm AE transducers Grips AE transducers Specimen Grips 250 mm Figure 4. (A) specimen for tensile test and test set-up with AE transducers position, (B) the specimen fixing grips and external AE noise insulation devices. 25 mm
Damage Evaluation and Residual Strength Prediction of CFRP Laminates … 175 The AE transducers were placed in a linear configuration located at a distance of 110 mm, as shown in figure 4A. The Elastic modulus was measured by means of HBM LY41- 6/350 strain-gauges. Case study 1: results and discussion The experimental results analysis and discussion is here organized in two phases: the first one in which the only classical mechanical information (stress and strain) are considered, and the second one in which the AE information is analyzed and related to the material mechanical response. The stress-strain curves in Figure 5 show the effect of the fibre orientation and volume percentage and also the small, but not negligible, influence of the plies sequence in the laminates. In particular the AP diagram was qualitatively different from the other laminate ones because of the different failure mechanism that was fibre-dominated for UD and QI and matrix-dominated for AP. In fact, the mechanical response of AP laminates with respect to in plane tensile load was strongly nonlinear and the ultimate stress value was about 60 MPa. The two aspects that determined the behaviour of AP laminate were the fibre direction (±45°) and the low volume percentage of fibres. Visual inspection revealed also a marked necking due to the high percentage of matrix forming the composite and the sliding of fibres in it. Stress (MPa) 2500 2000 1500 1000 500 UD QI2 QI1 QI3 AP 0 0.000 0.010 0.020 0.030 0.040 0.050 0.060 0.070 0.080 0.090 Strain Figure 5. Examples of stress-strain diagram for the different types of laminates. From the stress-strain diagram it was possible to determine some of the most significant information regarding the mechanical response of laminates. In particular the elastic modulus (EX) and the ultimate strength were estimated considering all tested specimens. In table 2 are summarized the theoretical Elastic modulus, estimated by means of the lamination theory, and
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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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Page 138 and 139: 124 W.H. Zhong, R.G. Maguire, S.S.
Page 144 and 145: 130 Yuanxin Zhou, Hassan Mahfuz, Vi
Page 154 and 155: 140 Heat Flow (W/g) Heat Flow (W/g)
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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Research Directions in the Fatigue
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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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