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  • STRUCTURAL MECHANICS  (9)
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  • 1
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    An approximate buckling analysis for rectangular orthotropic plates with centrally located cutouts (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An approximate analysis for predicting buckling of rectangular orthotropic composite plates with centrally located cutouts is presented. In this analysis, prebuckling and buckling problems are converted from a two-dimensional to a one-dimensional system of linear differential equations with variable coefficients. The conversion is accomplished by expressing the displacements as series with each element containing a trigonometric function of one coordinate and a coefficient that is an arbitrary function of the other coordinate. Ordinary differential equations are then obtained from a variational principle. Analytical results obtained from the approximate analysis are compared with finite element analyses for isotropic plates and for specially orthotropic plates with central circular cutouts of various sizes. Experimental results for the specially orthotropic plates are also presented. In nearly all cases, the approximate analysis predicts the buckling mode shapes correctly and predicts the buckling loads to within a few percent of the finite element and experimental results.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TP-2528 , L-16032 , NAS 1.60:2528
    Format: application/pdf
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  • 2
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    Nonlinear response and failure characteristics of internally pressurized composite cylindrical panels (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Results of an experimental and analytical study of the nonlinear response and failure characteristics of internally pressurized 4- to 16-ply-thick graphite-epoxy cylindrical panels are presented. Specimens with clamped boundaries simulating the skin between two frames and two stringers of a typical transport fuselage were tested to failure. Failure results of aluminum specimens are compared with the graphite-epoxy test results. The specimens failed at their edges where the local bending gradients and interlaminar stresses are maximum. STAGS nonlinear two-dimensional shell analysis computer code results are used to identify regions of the panels where the response is independent of the axial coordinate. A geometrically nonlinear one-dimensional cylindrical panel analysis was derived and used to determine panel response and interlaminar stresses. Inclusion of the geometric nonlinearity was essential for accurate prediction of panel response. The maximum stress failure criterion applied to the predicted tensile stress in the fiber direction agreed best with the experimentally determined first damage pressures.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-176148 , NAS 1.26:176148 , COMS-85-07 , VPI-E-85-16 , IR-52
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  • 3
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    Effect of axial impact on the static flexure of graphite/epoxy beams (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: Graphite-epoxy beams were subjected to an eccentric axial impact load in a drop tower test fixture in order to study their large displacement flexural behavior. The time history of the transient axial load exhibited a large magnitude occurring just after impact, which was many times greater than the static failure load. The damage caused by this peak dynamic load was measured by the reduction in energy absorption of the impacted beam relative to a virgin beam in static tests. For the thirty-ply specimens, the amount of damage increased with increasing axial stiffness.
    Keywords: STRUCTURAL MECHANICS
    Type: American Society for Composites, Technical Conference; Sept. 23-25, 1987; Newark, DE; United States
    Format: text
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  • 4
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    Nonlinear response and failure characteristics of clamped internally pressurized graphite-epoxy cylindrical panels (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The nonlinear response and failure characteristics of internally pressurized 4- to 16-ply cylindrical panels of graphite/epoxy are experimentally and analytically studied. Tests simulated the skin of a typical transport aircraft fuselage under loading to eventual failure. Aluminum test specimens were similarly tested and compared. All graphite/epoxy panels are found to withstand the internal pressures applied, which are well above the proof pressure loading expected for transport fuselage structures.
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA PAPER 84-0955
    Format: text
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  • 5
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    Response of long shallow cylindrical panels to radial line loads (1984)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The large displacement static response of shallow orthotropic panels subjected to lateral loading is examined both theoretically and experimentally. The panels are circular cylindrical open shells which are also thin and long. The straight edges are simply supported at a fixed distance apart, and the curved edges are free. The lateral load is a spatially uniform line load acting along the generator direction of the cylinder, and is directed radially inward toward the center of curvature. The load induces a circumferential thrust, and the panel can, and does, snap-through to an inverted configuration at the buckling load. The effect of load position on the response is also examined. The test panels discussed in the paper are /(90/0)3/S graphite-epoxy laminates. Nominal dimensions are a radius of 60 in., a thickness of 0.060 in., and an arc length of 12 in. Very good agreement between theory and experiment is achieved.
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA PAPER 84-0954
    Format: text
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  • 6
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    A nonlinear analysis of infinitely long graphite-epoxy cylindrical panels loaded with internal pressure (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The structural response of internally pressurized composite cylindrical panels, representative of a transport aircraft's fuselage skins, is predicted by means of a one-dimensional, geometrically nonlinear analysis. An analytical study is conducted for the response of 4-, 8-, and 16-ply graphite/epoxy skins. The results obtained indicate that the response is geometrically nonlinear, and that a boundary layer with a severe bending gradient exists at the panel edges. The importance of through-the-thickness shearing deformations in the bending boundary layer is illustrated through comparison of analyses based on Kirchhoff-Love and shear deformation theories. Numerical results for the bending boundary layer lengths of the different panels are presented, and two bending boundary layers are predicted with the shear deformation theory.
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA PAPER 85-0770 , Structures, Structural Dynamics, and Materials Conference; Apr 15, 1985 - Apr 17, 1985; Orlando, FL
    Format: text
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  • 7
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    Static and dynamic response of graphite-epoxy curved frames (1990)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Experiments were conducted to measure the three-dimensional static and vibratory response of two graphite-epoxy, thin-walled, open section frames. The frames are semicircular with a radius of three feet. One specimen had an I cross section and the other had a channel cross section. The experimental data is used to evaluate a mixed finite element model of the frames that is based on Vlasov-type, thin-walled, open section curved beam theory.
    Keywords: STRUCTURAL MECHANICS
    Type: Technical Conference of the American Society for Composites; Jun 12, 1990 - Jun 14, 1990; East Lansing, MI; United States
    Format: text
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  • 8
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    Response of composite material shallow arch to concentrated load (1986)
    In:  Other Sources
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    Publication Date: 2019-07-12
    Keywords: STRUCTURAL MECHANICS
    Type: Journal of Aircraft (ISSN 0021-8669); 23; 529-536
    Format: text
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  • 9
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    Buckling of composite cylinders under combined compression and torsion Theoretical/experimental correlation (1981)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Elastic buckling loads for laminated composite circular cylindrical shells under combined axial compression and torsion are plotted on a dimensionless load plane and determined experimentally from boron/epoxy and graphite/epoxy specimens with symmetric and asymmetric layups. Good correlation is achieved between the theoretical and experimental interaction curves. The theoretical buckling loads are obtained from Fluegge's cylindrical shell equations and for pure torsion there is good correlation, but for the pure axial compression the correlation is rather poor.
    Keywords: STRUCTURAL MECHANICS
    Type: Symposium on Test methods and design allowables for fibrous composites; Oct 02, 1979 - Oct 03, 1979; Dearborn, MI
    Format: text
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