Ply structure

Pioneering work in the development of an isocyanate-bound particleboard in the U.S. has been conducted by the Ellingson Lumber Company. This work has resulted in a proprietary process for bonding cellulosic materials with polymeric MDI to produce a multiple-ply structure panel (7.,. 8, 9.) Advantages cited for this process include a tolerance for up to 22% moisture in the wood raw material without predrying and the ability to also include significant quantities of bark and needles. 

Thus, the major difference between our ILM structure to that utilized by previous workers lies In the fact that we have a single-ply structure wherein the liquid membrane is Immobilized within the pores of a mlcroporous hydrophobic support as compared to the two-ply structure of GE workers discussed above. To be noted also Is that moisture condensation on the hydrophobic supports does not automatically lead to flooding due to the hydrophobic nature of the surface (unlike that with hydrophilic membranes). 

Fig. 11.1 Schematic depiction of the textile ply structures in (a) a bias- or cross-ply tyre ...

The distinction between structural and nonstructural bonds is not always clear. For example, is a hot melt adhesive used in retaining a fabric s plies structural or nonstructural One could argue that such an adhesive may be placed in either classification. However, the superglues (cyanoacrylates)... 

Self-twist yarn n. An inherently twist-stable, two-ply structure having a ply twist that is alternately S- and Z-directed along the yarn. 

Nerurkar, N.L., Sen, S., Huang, A.H., Elliott, D.M., Mauck, R.L., 2010. Engineered disc-like angle-ply structures for intervertebral disc replacement. Spine 35 (8), 867—873. 

Once the least-squares fits to Slater functions with orbital exponents e = 1.0 are available, fits to Slater function s with oth er orbital expon cn ts can be obtained by siin ply m ii Itiplyin g th e cc s in th e above three equations by It remains to be determined what Slater orbital exponents to use in electronic structure calculation s. The two possibilities may be to use the "best atom" exponents (e = 1. f) for II. for exam pie) or to opiim i/e exponents in each calculation. The "best atom expon en ts m igh t be a rather poor ch oicc for mo lecular en viron men ts, and optirn i/.at ion of non linear exponents is not practical for large molecules, where the dimension of the space to be searched is very large.. 4 com prom isc is to use a set of standard exponents where the average values of expon en ts are optirn i/ed for a set of sin all rn olecules, fh e recom -mended STO-3G exponents are... 

There are, of course, many more aspects of composite hardware design that differ from metallic bonded structure but do not necessarily involve adhesive bonding. For instance there are many types of reinforcement tape and fabric to choose from, the orientation of the plies must be chosen, the ply stackups must be balanced to avoid part warping after cure, a minimum number of plies must be used to prevent non-visible impact damage that significantly affects the load carrying capability of the part, etc. 

If no laminae have failed, the load must be determined at which the first lamina fails (so-called first-ply failure), that is, violates the lamina failure criterion. In the process of this determination, the laminae stresses must be found as a function of the unknown magnitude of loads first in the laminate coordinates and then in the principal material directions. The proportions of load (i.e., the ratios of to Ny, to My,/ etc.) are, of course, specified at the beginning of the analysik The loaa parameter is increased until some individual lamina fails. The properties, of the failed lamina are then degraded in one of two ways (1) totally to zero if the fibers in the lamina fail or (2) to fiber-direction properties if the failure is by cracking parallel to the fibers (matrix failure). Actually, because of the matrix manipulations involved in the analysis, the failed lamina properties must not be zero, but rather effectively zero values in order to avoid a singular matrix that could not be inverted in the structural analysis problem. The laminate strains are calculated from the known load and the stiffnesses prior to failure of a lamina. The laminate deformations just after failure of a lamina are discussed later. 

In their pioneering paper on laminated plates, Reissner and Stavsky investigated an approximate approach (in addition to their exact approach) to calculate deflections and stresses for antisymmetric angie-ply laminated plates [5-27]. Much later, Ashton extended their approach to structural response of more general unsymmetrically laminated plates and called it the reduced stiffness matrix method [5-28]. The attraction of what is now called the Reduced Bending Stiffness (RBS) method is that an unsymmetrically laminated plate can be treated as an orthotropic plate using only a modified D matrix in the solution, i.e.,... 

In the theory of radiationless transitions as covered in this paper (6,4g), the two non BO terms are treated as perturbations (not externally plied, but arising as imperfections within this model of molecular structure) that can induce transitions between unperturbed states each of which is taken to be a specific Bom-Oppenheimer product state ... 

Thus, any laminate may consist of plies selected from paper, polyester, numerous other plastic films, foils, coatings, adhesive layers, metalization, etc. The choice of laminate structure is usually governed by technical requirements, cost of base materials, cost of lamination processes, cost of printing cylinder and process, and the amount of laminate required (quantity), the yield from which the cost per area of laminate is derived. 

Snieckus and his group members [104] used the known domino Sonogashira/ Castro-Stephens reaction [105, 106] for the synthesis of the natural product pli-cadin (6/1-209), this having been isolated from Psorelia plicata in 1991 [107]. In this synthesis, Pd°-catalyzed reaction of the alkyne 6/1-210 and the iodobenzene derivative 6/1-211 in the presence of Cul led to the furan 6/1-212, which was transformed into 6/1-209 via 6/1-213 (Scheme 6/1.54). There are some discrepancies of the physical data of the natural and the synthetic product thus, it might be possible that the natural product has a different structure. It should also be mentioned that the... 

To visualize chromosomes more accurately, various stains are plied so that the bands in chromosomes can be seen (Fig II-3-1). The bands tend to reflect differences in chromosome structure or composition (e.g., regions rich in CG bases versus those rich in AT bases). 

Composite structures in service are often subjected to complex 3-D load paths. In general, a delamination will be subjected to a crack driving force with a mode I opening, a mode II forward shear and a mode III anti-plane shear, as illustrated in Fig 3.29. Because delamination is constrained to grow between individual plies, both interlaminar tension and shear stresses are commonly present at the... 

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