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  • 1
    facet.materialart.
    Unknown
    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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    NASA TECHNICAL REPORTS
  • 2
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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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    NASA TECHNICAL REPORTS
  • 3
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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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    NASA TECHNICAL REPORTS
  • 4
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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
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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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
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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