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  • STRUCTURAL MECHANICS  (15)
  • 1980-1984  (5)
  • 1970-1974  (10)
  • 1
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    Perturbation solution of a hyperbolic equation governing longitudinal wave propagation in certain nonuniform bars (1970)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Longitudinal wave propagation in variable section bars, solving hyperbolic equation of motion by perturbation method
    Keywords: STRUCTURAL MECHANICS
    Type: ; YAL SOCIETY (
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Interactive design of large end rings on stiffened conical shells using composites (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Design study methods and results for a composite reinforced base ring for the conical aeroshell structure of the planetary lander vehicle for Project Viking, an unmanned mission to Mars, are presented. The aeroshell is a ring and stringer-stiffened conical shell structure having a half angle of 70 degrees with a large base ring mounted at the outer edge of the cone and a large pay-load ring in the interior with many smaller rings spaced along the inside shell surface. The purpose of the structure is to develop the aerodynamic drag required to decelerate the lander in the Mars atmosphere to facilitiate a soft landing. The design of a shell structure of this complexity requires the use of the latest technology available in a large general-purpose shell buckling program. The large general-purpose non-linear shell buckling program (BOSOR 2) which was used for this purpose is described.
    Keywords: STRUCTURAL MECHANICS
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  • 3
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    Structural efficiency studies of corrugated compression panels with curved caps and beaded webs (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Curved cross-sectional elements are employed in structural concepts for minimum-mass compression panels. Corrugated panel concepts with curved caps and beaded webs are optimized by using a nonlinear mathematical programming procedure and a rigorous buckling analysis. These panel geometries are shown to have superior structural efficiencies compared with known concepts published in the literature. Fabrication of these efficient corrugation concepts became possible by advances made in the art of superplastically forming of metals. Results of the mass optimization studies of the concepts are presented as structural efficiency charts for axial compression.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TP-2272 , L-15703 , NAS 1.60:2272
    Format: application/pdf
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  • 4
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    Design considerations for composite fuselage structure of commercial transport aircraft (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The structural, manufacturing, and service and environmental considerations that could impact the design of composite fuselage structure for commercial transport aircraft application were explored. The severity of these considerations was assessed and the principal design drivers delineated. Technical issues and potential problem areas which must be resolved before sufficient confidence is established to commit to composite materials were defined. The key issues considered are: definition of composite fuselage design specifications, damage tolerance, and crashworthiness.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-159296 , LR-29540
    Format: application/pdf
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  • 5
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    Stress analysis and buckling of J-stiffened graphite-epoxy panel (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A graphite epoxy shear panel with bonded on J stiffeners was investigated. The panel, loaded to buckling in a picture frame shear test is described. Two finite element models, each of which included the doubler material bonded to the panel skin under the stiffeners and at the panel edges, were used to make a stress analysis of the panel. The shear load distributions in the panel from two commonly used boundary conditions, applied shear load and applied displacement, were compared with the results from one of the finite element models that included the picture frame test fixture.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TP-1607 , L-13256
    Format: application/pdf
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  • 6
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    Buckling test of a 3-meter-diameter corrugated graphite-epoxy ring-stiffened cylinder (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A three m diameter by three m long corrugated cylindrical shell with external stiffening rings was tested to failure by buckling. The corrugation geometry for the graphite epoxy composite cylinder wall was optimized to withstand a compressive load producing an ultimate load intensity of 157.6 kN/m without buckling. The test method used to produce the design load intensity was to mount the specimen as a cantilevered cylinder and apply a pure bending moment to the end. A load introduction problem with the specimen was solved by using the BOSOR 4 shell of revolution computer code to analyze the shell and attached loading fixtures. The cylinder test loading achieved was 101 percent of design ultimate, and the resulting mass per unit of shell wall area was 1.96 kg/sq m.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TP-2032 , L-14659 , NAS 1.60:2032
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  • 7
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    Design detail verification tests for a lightly loaded open-corrugation graphite-epoxy cylinder (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Flat corrugated graphite-epoxy panels were tested in compression to verify selected design details of a ring-stiffened cylinder that was designed to support an axial compressive load of 157.6 kN/m without buckling. Three different sizes of subcomponent panels, with the same basic corrugation geometry, were tested: (1) 60.96-cm-long by 45.72-cm-wide panels to evaluate the local buckling strength of the shell wall design; (2) 91.44-cm-long by 45.72-cm-wide panels to evaluate a longitudinal joint and the load-introduction method; and (3) 254.0-cm-long by 91.44-cm-wide panels with four simulated-ring stiffeners to evaluate the ring-attachment method. The test results indicate that the modified shell-wall design, the longitudinal joint, the load-introduction method, and the stiffener-attachment method for the proposed cylinder have adequate strength to support the design load.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TP-1981 , L-14795 , NAS 1.60:1981
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  • 8
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    Buckling tests of two 4.6-meter-diameter, magnesium ring-stiffened conical shells loaded under external pressure (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Two ring-stiffened magnesium conical shells with a 120 deg apex angle and a 4.6-meter diameter were loaded to failure by a uniform external pressure. The cones differed from one another only in the number of internal stiffening rings. Test specimen details, test procedure, and test results are discussed. Both buckling and prebuckling data are compared with appropriate theoretical predictions. Measured strains in skin and rings agreed well with theoretical predictions. Extensive imperfection measurements were made and reported on both cones in the as fabricated condition.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TN-D-7303 , L-8835
    Format: application/pdf
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  • 9
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    A recurrence matrix method for the analysis of longitudinal and torsional vibrations in non-uniform multibranch beams with variable boundary conditions (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An approximate method for calculating the longitudinal and torsional natural frequencies and associated modal data of a beamlike, variable cross section multibranch structure is presented. The procedure described is the numerical integration of the first order differential equations that characterize the beam element in longitudinal motion and that satisfy the appropriate boundary conditions.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TM-X-71973
    Format: application/pdf
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  • 10
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    Compressive instability and strength of uniaxial filament-reinforced epoxy tubes (1970)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Column buckling, local buckling, and crushing strengths of uniaxial filament-reinforced epoxy tubes
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TN-D-5697 , L-6905
    Format: application/pdf
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