Hguides with artificial and laminated dielectric slabs
H-guide dielectric losses reduction by use of artificial and laminated dielectric slabs
Tischer, F. J.↗
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Results for “lamination”
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Lamination residual stresses in multilayered fiber composites
Residual stresses arising from fabrication processes in laminates
Chamis, C. C.↗
Investigation of flow characteristics of some wire-form and laminate-form porous materials
Flow characteristics of wire-form and laminate-form porous materials
Kaufman, A.↗
Study and production of polybenzimidazole billets, laminates, and cylinders
Mechanical properties and physical, chemical, and thermal tests of polybenzimidazole and carbon fabric laminates for spacecraft thermal insulation
Marks, B. S.↗
Experimental evaluation of low cycle thermal fatigue in a turbine vane fabricated from laminated porous material
Analysis of low cycle thermal fatigue in laminated porous wall turbine vanes
Nealy, D. A.↗
Lamination residual stresses in cross-plied fiber composites
Longitudinal and transverse residual stresses arising in lamination fabrication process of cross-plied fiber composites
Chamis, C. C.↗
Built-in bleeder system in laminated plastic structures
Method is described for interplying resin absorbing, glass bleeder cloth with the layup for fabricating laminated nonflammable plastic structures with wrinkle-free surfaces.
Aguilar, A. G.↗
Experimental investigation of the flow, oxidation, cooling, and thermal-fatigue characteristics of a laminated porous sheet material
The basic flow and oxidation characteristics of a laminated porous material (Lamilloy) are presented. The oxidation characteristics of Lamilloy are compared to a wireform-type porous material for the case when both materials are made from Hastelloy-X alloy. The cooling performance of an air cooled vane made from Lamilloy, as determined from cascade tests made at gas temperatures ranging from 1388 to 1741 C (2350 to 3165 F) is also discussed, as well as of a cascade-type thermal fatigue test of the Lamilloy vane.
Hickel, R. O.↗
Thermally stable laminating resins
Improved thermally stable laminating resins were developed based on the addition-type pyrolytic polymerization. Detailed monomer and polymer synthesis and characterization studies identified formulations which facilitate press molding processing and autoclave fabrication of glass and graphite fiber reinforced composites. A specific resin formulation, termed P10P was utilized to prepare a Courtaulds HMS reinforced simulated airfoil demonstration part by an autoclave molding process.
Jones, R. J.↗
A layered composite with a broken laminate
The problem of a laminate composite in the presence of a crack located normal to the bond lines is considered. Stress analysis of the limiting case when the crack extends to the bond lines is carried out. An integral transform technique is used to formulate the problem in terms of a singular integral equation. The power of stress singularity around the crack tip terminating at the interface is obtained using the above technique. The singular integral equation is solved numerically and the effect of material properties on the stress intensity factor is calculated.
Gupta, G. D.↗
Graphite/polyimide laminates with near-zero thermal expansion
Composite structures can be laminated to have very low coefficients of thermal expansion. Such structures are light and strong and have many uses where expansion or contraction with temperature change is undesirable. One application is with instruments that measure thermal expansion.
Reynolds, W. N.↗
Transparent polymeric laminates
Laminate prepared from epoxy-boroxine and phenolphthalein polycarbonate has high mechanical strength at elevated temperature and is resistant to impact, fire, and high-energy thermal radiation. Polycarbonate is prepared by reaction of phenolphthalein with phosgene in presence of amine catalyst and immiscible organic solvent phase.
Parker, J. A.↗
Development and evaluation of polyimide laminates for printed wiring board applications
A developmental and evaluation program on polyimide laminates as printed wiring boards is described. The development of an experimental polyimide with low linear coefficient of thermal expansion normal to the plane of the board is discussed, and its properties are evaluated along with two commercial polyimide printed wiring boards for comparison with the type G-10 epoxy board. Thermal cycling data indicate an urgent need for effectively controlling the expansion normal to the plane of the board in order to minimize solder joint damage.
Patterson, W. J.↗
A study of fracture phenomena in fiber composite laminates
The extension of linear elastic fracture mechanics from ostensibly homogeneous isotropic metallic alloys to heterogeneous anisotropic advanced fiber composites is considered. It is analytically demonstrated that the effects of material anisotropy do not alter the principal characteristics exhibited by a crack in an isotropic material. The heterogeneity of fiber composites is experimentally shown to have a negligible effect on the behavior of a sufficiently long crack. A method is proposed for predicting the fracture strengths of a large class of composite laminates; the values predicted by this method show good agreement with limited experimental data. The limits imposed by material heterogeneity are briefly discussed, and areas for further study are recommended.
Konish, H. J., Jr.↗
A layered composite with a broken laminate.
The problem of a laminate composite in presence of a crack located normal to the bond lines is considered. Stress analysis of the limiting case when the crack extends to the bond lines is carried out. Integral transform technique is used to formulate the problem in terms of a singular integral equation from which the power of stress singularity around the crack tip terminating at the interface is obtained. The singular integral equation is solved numerically and the effect of material properties on the stress intensity factor is calculated.
Gupta, G. D.↗
BUCLAP2: A computer program for instability analysis of laminated long plates subjected to combined inplane loads. User's manual
The usage of the computer program BUCLAP2 is described. The program is intended for linear instability analysis of long, rectangular flat and curved laminated plates with arbitrary orientation of orthotropic axes in each layer. The loadings considered are combinations of inplane normal and shear loads. Arbitray elastic boundary conditions are included for the sides of the plate Instructions for use of the program are included along with Input data requirements, output information, and sample problems. For program description, see .
Halstead, D. W.↗
BUCLAP2: A computer program for instability analysis of laminated long plates subjected to combined inplane loads
This program description document describes the program structure and the design details of a CDC 6600 FORTRAN 4 digital computer program, BUCLAP2, which uses minimum energy principles to do an elastic stability analysis of curved and flat laminated rectangular long plates subjected to combined inplane normal and shear loads. Given the geometry, the material properties, and slected boundary conditions for the plate element, the program calculates the minimum buckling load for various wave lengths. The two parallel ends of the program calculates the minimum buckling load for various wave lengths. The two parallel ends of the long plate must be simply supported and arbitrary elastic boundary conditions may be imposed along either one or both external longitudinal sides. For guide to program use, see
Halstead, D. W.↗
Method of laminating structural members
A laminate is obtained by providing a lightweight core material, such as a honeycombed plastic or metal, within the cavity defined by an annular mold cavity frame. Face sheets, which are to be bonded to the core material, are provided on opposite sides of the frame and extend over the frame, thus sealing the core material in the cavity. An adhesive is provided between the core material and the face sheets and the combined thickness of the core material and adhesive is a close fit within the opposed face sheets. A gas tight seal, such as an O-ring gasket, is provided between the frame and the face sheet members to form a gas tight cavity between the face sheet members and the frame. External heat and pressure are used to bond the face sheets to the core material. Gas pressure is introduced into the sealed cavity to minimize out-gasing of the adhesive.
Heier, W. C.↗