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Quasi-isotropic

Acoustic Emission to Model the Fatigue Behaviour of Quasi-Isotropic Carbon-Epoxy Laminate Composites. [Pg.45]

In this study, the cumulative AE counts have been used to quantify the fatigue damage development in quasi-isotropic CFRP laminates and a model based on AE data has been formulated. [Pg.45]

The results presented below were obtained using a 2 mm thick carbon fiber reinforced epoxy composite laminate with 16 layers. The laminate was quasi isotropic with fiber orientations 0°, 90° and 45°. The laminate had an average porosity content of approximately 1.7%. The object was divided in a training area and an evaluation area. The model parameters were determined by data solely from the training area. Both ultrasound tranducers used in the experiment had a center frequency of 21 MHz and a 6 dB bandwidth of 70%. [Pg.890]

Quasi-isotropic laminates have the same ia-plane stiffness properties ia all directions (1), which are defined ia terms of the [A] matrix of the laminate. For the laminate to be quasi-isotropic. [Pg.13]

It is also important to note that although the laminae [ 45] indicates that Ex = Ey =. GN/m, this laminate is not isotropic or even quasi-isotropic. As shown in Chapter 2, in an isotropic material, the shear modulus is linked to the other elastic properties by the following equation... [Pg.217]

Some laminates do exhibit quasi-isotropic behaviour. The simplest one is [0, 60]j. For this laminate... [Pg.218]

First, we need a common, unambiguous manner of writing how a laminate is specified to be laid-up, i.e., stacking-sequence notation. Then, quasi-isotropic, balanced, and hybrid laminates are defined. [Pg.219]

The term quasi-isotropic iaminate is used to describe laminates that have isotropic extensionai stiffnesses (the same in all directions in the plane of the laminate). As background to the definition, recall that the term isotropy is a material property whereas laminate stiffnesses are a function of both material properties and geometry. Note also that the prefix quasi means in a sense or manner. Thus, a quasi-isotropic laminate must mean a laminate that, in some sense, appears isotropic, but is not actually isotropic in all senses. In this case, a quasi-isotropic... [Pg.219]

Figure 4-21 Unbonded View of Simple Quasi-isotropic Laminates Balanced Laminates... Figure 4-21 Unbonded View of Simple Quasi-isotropic Laminates Balanced Laminates...
Quasi-isotroplc laminates do not behave like Isotropic homogeneous materials. Discuss why not, and describe how they do behave. Why is a two-ply laminate with a [0°/90°] sacking sequerx and equat-thickness layers not a quasi-isotropic laminate Determine whether the extensional stiffnesses are the same irrespective of the laminate axes for the two-ply and three-ply cases. Hint use the invariant properties In Equation (2.93). [Pg.222]

Quasi-isotropic construction It approximates isotropy by orientation of plies in several or more directions. [Pg.507]

Experimental results are presented that show that high doses of electron radiation combined with thermal cycling can significantly change the mechanical and physical properties of graphite fiber-reinforced polymer-matrix composites. Polymeric materials examined have included 121 °C and 177°C cure epoxies, polyimide, amorphous thermoplastic, and semicrystalline thermoplastics. Composite panels fabricated and tested included four-ply unidirectional, four-ply [0,90, 90,0] and eight-ply quasi-isotropic [0/ 45/90]s. Test specimens with fiber orientations of [10] and [45] were cut from the unidirectional panels to determine shear properties. Mechanical and physical property tests were conducted at cold (-157°C), room (24°C) and elevated (121°C) temperatures. [Pg.224]

Fig. 6.23. R-curve prediction ( — ) and experimental data (O) for a carbon fiber-epoxy matrix quasi-isotropic [C/ 45°/90 ), laminate. After Wells and Beaumont (1987). Fig. 6.23. R-curve prediction ( — ) and experimental data (O) for a carbon fiber-epoxy matrix quasi-isotropic [C/ 45°/90 ), laminate. After Wells and Beaumont (1987).
Fig. 6.24. Comparison of notched strength of carbon fiber-epoxy matrix quasi-isotropic [0°/ 45°/90°... Fig. 6.24. Comparison of notched strength of carbon fiber-epoxy matrix quasi-isotropic [0°/ 45°/90°...
One of the most important properties which control the damage tolerance under impact loading and the CAI is the failure strain of the matrix resin (see Fig. 8.8). The matrix failure strain influences the critical transverse strain level at which transverse cracks initiate in shear mode under impact loading, and the resistance to further delamination in predominantly opening mode under subsequent compressive loading (Hirschbuehler, 1987 Evans and Masters, 1987 Masters, 1987a, b Recker et al., 1990). The CAI of near quasi-isotropic composite laminates which are reinforced with AS-4 carbon fibers of volume fractions in the range of 65-69% has... [Pg.339]

Fig. 8.7. Damage area of 24 ply quasi-isotropic carbon fiber reinforced composite laminates containing different resin matrices. After Srinivasan et al. (1992). Fig. 8.7. Damage area of 24 ply quasi-isotropic carbon fiber reinforced composite laminates containing different resin matrices. After Srinivasan et al. (1992).
Sohi. M.M., Hahn, H.T. and Williams, J.G. (1987). The effect of resin toughness and modulus on compressive failure modes of quasi-isotropic graphite/epoxy laminates. In Toughened Composites. ASTM STP 937 (N.J. Johnston cd.). ASTM. Philadelphia, PA. pp 37 60. [Pg.365]

The final mechanism of stress relief is thermomechanically activated chain scission. Primary bond breakage can be homolytic, ionic or by a degrading chemical reaction. It is worthwhile to note that the relative slippage of chains, microfibrils and fibrils reduces or prevents the mechanical scission of chains in quasi-isotropic polymeric solids. In other words, chain scission is an important mode of fracture only in highly oriented thermoplastic fibers or in thermosets. [Pg.52]

Figure 14.10 Photograph of a quasi-isotropic Gr/PEEK laminate in which a bend was propagated further into the workpiece, showing overcurvature... Figure 14.10 Photograph of a quasi-isotropic Gr/PEEK laminate in which a bend was propagated further into the workpiece, showing overcurvature...
Fig. la and b. Mechanical work W (1), elastic heat Q (2), internal energy change AU (3) and heat to work ratio q (4) as a function of strain e (uniform deformation) or s (unidirectional deformation) for quasi-isotropic Hookean solid 8. a — positive a and P b — negative a and p. The arrows indicate inversion points (see text)... [Pg.37]

This result stresses the fact that the heat effects can be detected only at such deformation modes of quasi-isotropic Hookean solids that are accompanied by a change in volume. Thus, the thermal effects are the consequence of the change of the vibrational entropy which in turn is a result of the volume change. It is very important to emphasize now that the internal energy and entropy changes are closely interrelated and their values are of the same order of magnitude. [Pg.39]


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See also in sourсe #XX -- [ Pg.239 ]




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Directional property quasi-isotropic

Laminate quasi-isotropic

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