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  • 1
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    Fiber shape effects on metal matrix composite behavior (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: The effects of different fiber shapes on the behavior of metal matrix composites is computationally simulated. A three-dimensional finite element model consisting of a group of nine unidirectional fibers in a three by three unit cell array of a SiC/Ti-15-3 metal matrix composite is used in the analysis. The model is employed to represent five fiber shapes that include a circle, an ellipse, a kidney, and two different cross shapes. The distribution of stresses and the composite material properties, such as moduli, coefficients of thermal expansion, and Poisson's ratios, are obtained from the finite element analysis using the various fiber shapes. Comparisons of these results are used to determine the sensitivity of the composite behavior to the different fiber shapes. In general, fiber dominated properties are not affected by fiber geometry and matrix dominated properties are only moderately affected.
    Keywords: COMPOSITE MATERIALS
    Type: In: International SAMPE Symposium and Exhibition, 37th, Anaheim, CA, Mar. 9-12, 1992, Proceedings (A93-15726 04-23); p. 378-389.
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  • 2
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    METCAN demonstration manual, version 1.0 (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The various features of the Metal Matrix Composite Analyzer (METCAN) computer program to simulate the high temperature nonlinear behavior of continuous fiber reinforced metal matrix composites are demonstrated. Different problems are used to demonstrate various capabilities of METCAN for both static and cyclic analyses. A complete description of the METCAN output file is also included to help interpret results.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-TM-105607 , E-6944 , NAS 1.15:105607
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  • 3
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    Metal matrix composite analyzer (METCAN) user's manual, version 4.0 (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Metal Matrix Composite Analyzer (METCAN) is a computer code developed at Lewis Research Center to simulate the high temperature nonlinear behavior of metal matrix composites. An updated version of the METCAN User's Manual is presented. The manual provides the user with a step by step outline of the procedure necessary to run METCAN. The preparation of the input file is demonstrated, and the output files are explained. The sample problems are presented to highlight various features of METCAN. An overview of the geometric conventions, micromechanical unit cell, and the nonlinear constitutive relationships is also provided.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-TM-105244 , E-6571 , NAS 1.15:105244
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  • 4
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    The use of curvilinear fiber format to improve buckling resistance of plates with central circular holes (1990)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The potential gain in buckling resistance is explored by using the curvilinear format with a plate containing a centrally located circular hole and subjected to a uniaxial compressive load. The buckling loads for a uniform stress loading and simple support boundary conditions were examined. The method of analysis is outlined for the buckling improvement study. Several designs that represent an improvement over a baseline quasi-isotropic design (a design that is quite good for buckling resistance) are discussed. The tensile load of these designs is examined. A recommended design is presented that not only shows an improved buckling capacity, but also shows improved tensile performance. Follow-on activities are also discussed.
    Keywords: COMPOSITE MATERIALS
    Type: NASA. Langley Research Center, Eighth DOD(NASA)FAA Conference on Fibrous Composites in Structural Design, Part 1; p 167-178
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  • 5
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    METCAN verification status (1990)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The status of the verification (comparisons of predictions with experimental data) of the METCAN (METal-matrix Composite ANalyzer) code at high temperature is summarized. Verification includes select available room temperature of W/Cu composites for different fiber volume ratios. It also includes high temperature properties for thermal expansion, moduli, strength and stress/strain behavior for SiC/Ti composites. Furthermore it includes limited cases for thermal fatigue strength degradation. The verification results summarized herein indicate that METCAN simulates complex high temperature metal matrix composite bahavior with reasonable accuracy and that it can be used with confidence to identify in-situ nonlinear behavior that influences composite properties.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-TM-103119 , E-5443 , NAS 1.15:103119
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  • 6
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    METCAN updates for high temperature composite behavior - Simulation/verification (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The continued verification (comparisons with experimental data) of the METCAN (Metal Matrix Composite Analyzer) computer code is updated. Verification includes comparisons at room and high temperatures for two composites, SiC/Ti-15-3 and SiC/Ti-6-4. Specifically, verification of the SiC/Ti-15-3 composite includes comparisons of strength, modulus, and Poisson's ratio as well as stress-strain curves for four laminates at room temperatures. High temperature verification includes comparisons of strength and stress-strain curves for two laminates. Verification of SiC/Ti-6-4 is for a transverse room temperature stress-strain curve and comparisons for transverse strength at three temperatures. Results of the verification indicates that METCAN can be used with confidence to simulate the high temperature nonlinear behavior of metal matrix composites.
    Keywords: COMPOSITE MATERIALS
    Type: International SAMPE Symposium and Exhibition; Apr 15, 1991 - Apr 18, 1991; San Diego, CA; United States
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  • 7
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    Computational simulation of matrix micro-slip bands in SiC/Ti-15 composite (1992)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Computational simulation procedures are used to identify the key deformation mechanisms for (0)(sub 8) and (90)(sub 8) SiC/Ti-15 metal matrix composites. The computational simulation procedures employed consist of a three-dimensional finite-element analysis and a micromechanics based computer code METCAN. The interphase properties used in the analysis have been calibrated using the METCAN computer code with the (90)(sub 8) experimental stress-strain curve. Results of simulation show that although shear stresses are sufficiently high to cause the formation of some slip bands in the matrix concentrated mostly near the fibers, the nonlinearity in the composite stress-strain curve in the case of (90)(sub 8) composite is dominated by interfacial damage, such as microcracks and debonding rather than microplasticity. The stress-strain curve for (0)(sub 8) composite is largely controlled by the fibers and shows only slight nonlinearity at higher strain levels that could be the result of matrix microplasticity.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-TM-105762 , E-7179 , NAS 1.15:105762 , 1992 Winter Annual Meeting of ASME; Nov 08, 1992 - Nov 13, 1992; Anaheim, CA; United States
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  • 8
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    Fiber shape effects on metal matrix composite behavior (1992)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The effects of different fiber shapes on the behavior of a SiC/Ti-15 metal matrix composite is computationally simulated. A three-dimensional finite element model consisting of a group of nine unidirectional fibers is used in the analysis. The model is employed to represent five different fiber shapes: a circle, an ellipse, a kidney, and two different cross shapes. The distribution of microstresses and the composite material properties, such as moduli, coefficients of thermal expansion, and Poisson's ratios, are obtained from the finite element analysis for the various fiber shapes. Comparisons of these results are used to determine the sensitivity of the composite behavior to the different fiber shapes and assess their potential benefits. No clear benefits result from different fiber shapes though there are some increases/decreases in isolated properties.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-TM-106067 , E-7672 , NAS 1.15:106067 , International SAMPE Symposium and Exhibition; Mar 09, 1992 - Mar 12, 1992; Anaheim, CA; United States
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  • 9
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    A Coupled Layerwise Analysis of the Thermopiezoelectric Response of Smart Composite Beams Beams (1995)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Thermal effects are incorporated into previously developed discrete layer mechanics for piezoelectric composite beam structures. The updated mechanics explicitly account for the complete coupled thermoelectromechanical response of smart composite beams. This unified representation leads to an inherent capability to model both the sensory and actuator responses of piezoelectric composite beams in a thermal environment. Finite element equations are developed and numerical results are presented to demonstrate the capability of the current formulation to represent the behavior of both sensory and active smart structures under thermal loadings.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-TM-106889 , E-9528 , NAS 1.15:106889 , AIAA PAPER 95-1101 , Structures, Structural Dynamics, and Materials Conference; Apr 10, 1995 - Apr 13, 1995; New Orleans, LA; United States
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  • 10
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    Innovative design of composite structures: The use of curvilinear fiber format to improve buckling resistance of composite plates with central circular holes (1990)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The gains in buckling performance are explored that can be achieved by deviating from the conventional straightline fiber format and considering the situation whereby the fiber orientation in a layer, or a group of layers, can vary from point to point. The particular situation studied is a simply supported square plate with a centrally located hole loaded in compression. By using both a sensitivity analysis and a gradient-search technique, fiber orientation in a number of regions of the plate are selected so as to increase the buckling load relative to baseline straightline designs. The sensitivity analysis is used to determine which regions of the plate have the most influence on buckling load, and the gradient search is used to find the design that is believed to represent the absolute maximum buckling load for the conditions prescribed. Convergence studies and sensitivity of the final design are discussed. By examining the stress resultant contours, it is shown how the curvilinear fibers move the load away from the unsupported hole region of the plate to the supported edges, thus increasing the buckling capacity. The tensile capacity of the improved buckling design is investigated, and it is shown that both tensile capacity and buckling capacity can be improved with the curvilinear fiber concept.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-CR-186454 , NAS 1.26:186454 , VPI-E-90-05
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