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  • 1
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    Thermomechanical buckling of multilayered composite panels with cutouts (1994)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: A study is made of the thermomechanical buckling of flat unstiffened composite panels with central circular cutouts. The panels are subjected to combined temperature changes and applied edge loading (or edge displacements). The analysis is based on a first-order shear deformation plate theory. A mixed formulation is used with the fundamental unknowns consisting of the generalized displacements and the stress resultants of the plate. Both the stability boundary and the sensitivity coefficients are evaluated. The sensitivity coefficients measure the sensitivity of the buckling response to variations in the different lamination and material parameters of the panel. Numerical results are presented showing the effects of the variations in the hole diameter, laminate stacking sequence, fiber orientation, and aspect ratio of the panel on the thermomechanical buckling response and its sensitivity coefficients.
    Keywords: COMPOSITE MATERIALS
    Type: AIAA Journal (ISSN 0001-1452); 32; 7; p. 1507-1519
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Failure Analysis and Mechanisms of Failure of Fibrous Composite Structures (1983)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The state of the art of failure analysis and current design practices, especially as applied to the use of fibrous composite materials in aircraft structures is discussed. Deficiencies in these technologies are identified, as are directions for future research.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-CP-2278 , L-15641 , NAS 1.55:2278 , Mar 23, 1982 - Mar 25, 1982; Hampton, VA; United States
    Format: application/pdf
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  • 3
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    Effective thermoelastic and thermal properties of unidirectional fiber-reinforced composites and their sensitivity coefficients (1993)
    In:  Other Sources
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    Publication Date: 2019-08-27
    Description: Three-dimensional finite element models are used to assess the accuracy of the thermoelastic and thermal properties of unidirectional fiber-reinforced composites predicted by six different micromechanical models. The six models are: simple mechanics of materials type equations, fiber substructuring model, vanishing fiber diameter model, self-consistent model, Mori-Tanaka model, and method of cells. In addition, the finite element models are used to assess the accuracy of derivatives of the effective properties, with respect to each of the constituent material properties and fiber-volume ratio, computed using the six micromechanical models. The predictions of the micromechanical and finite element models for four advanced composite material systems are compared with experimental data. The results obtained in the present study show that the predictions of the Mori-Tanaka model and the method of cells are closer to those of the finite element models than those of all the other micromechanical models.
    Keywords: COMPOSITE MATERIALS
    Type: Composite Structures (ISSN 0263-8223); 26; 1-2; p. 7-23.
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Transverse shear stresses and their sensitivity coefficients in multilayered composite panels (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: A computational procedure is presented for the accurate determination of transverse shear stresses and their sensitivity coefficients in flat multilayered composite panels subjected to mechanical and thermal loads. The sensitivity coefficients measure the sensitivity of the transverse shear stresses to variations in the different lamination and material parameters of the panel. The panel is discretized by using either a three-field mixed finite element model based on a two-dimensional first- order shear deformation plate theory or a two-field degenerate solid element with each of the displacement components having a linear variation throughout the thickness of the laminate. The evaluation of transverse shear stresses can be conveniently divided into two phases. The first phase consists of using a superconvergent recovery technique for evaluating the in-plane stresses in the different layers. In the second phase, the transverse shear stresses are evaluated by using piecewise integration, in the thickness direction, of the three-dimensional equilibrium equations. The same procedure is used for evaluating the sensitivity coefficients of the transverse shear stresses. The effectiveness of the computational procedure is demonstrated by means of numerical examples of multilayered cross-ply panels subjected to transverse loading, uniform temperature change, and uniform temperature gradient through the thickness of the panel. In each case the standard of the comparison is taken to be the exact solution of the three dimensional thermoelasticity equations of the panel.
    Keywords: COMPOSITE MATERIALS
    Type: AIAA Journal (ISSN 0001-1452); 32; 6; p. 1259-1269
    Format: text
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    NASA TECHNICAL REPORTS
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