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  • STRUCTURAL MECHANICS  (121)
  • ASTROPHYSICS
  • 1970-1974  (121)
  • 1960-1964
  • 1972  (57)
  • 1971  (64)
Collection
Keywords
Years
  • 1970-1974  (121)
  • 1960-1964
Year
  • 1
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    Thick high aspect ratio wing, part 2 (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Transonic flutter and buffeting for elastic wind tunnel models of straight wing proposed for space shuttles
    Keywords: STRUCTURAL MECHANICS
    Type: NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 3 APR. 1971; P 201-229
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Response of an acoustically loaded panel excited by supersonically convected turbulence (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Structural panel under acoustic loading by supersonic convected turbulence, deriving responses with finite Fourier transforms
    Keywords: STRUCTURAL MECHANICS
    Type: ; - DISCRETE CONTROL S
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Measurements of the response of a panel excited by shock boundary-layer interaction (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Plate excitation by supersonic turbulent and shock boundary layers, measuring wall pressure fluctuation and panel displacement
    Keywords: STRUCTURAL MECHANICS
    Type: ; - DISCRETE CONTROL S
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Residual strength and crack propagation tests on C-130 airplane center wings with service-imposed fatigue damage (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Fourteen C-130 airplane center wings, each containing service-imposed fatigue damage resulting from 4000 to 13,000 accumulated flight hours, were tested to determine their fatigue crack propagation and static residual strength characteristics. Eight wings were subjected to a two-step constant amplitude fatigue test prior to static testing. Cracks up to 30 inches long were generated in these tests. Residual static strengths of these wings ranged from 56 to 87 percent of limit load. The remaining six wings containing cracks up to 4 inches long were statically tested as received from field service. Residual static strengths of these wings ranged from 98 to 117 percent of limit load. Damage-tolerant structural design features such as fastener holes, stringers, doublers around door cutouts, and spanwise panel splices proved to be effective in retarding crack propagation.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-2075 , ER-11178
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    C-130: Results of center wing residual strength and crack propagation test program (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Fourteen C-130 airplane center wings which had experienced from approximately 4,000 to 13,000 hours of flight service and its associated fatigue damage were tested to destruction, seven in upbending and seven in downbending. Six wings were tested directly for static residual strength in the fatigue-damaged condition as received from field service. The other eight wings were tested in crack propagation cyclic testing at a prescribed stress level for a maximum of 10,000 cycles. Then the stress level was reduced and testing was continued up to a maximum of 20,000 total cycles. Cyclic testing was performed with constant-amplitude stresses at a stress ratio of +0.1. Maximum cyclic skin stresses were approximately 18,000 psi. At the conclusion of cyclic testing, a static test to destruction was conducted to determine the residual strength of each fatigue-damaged specimen.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-112008 , ER-11178 , LSR-7221-70-012A
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    NASA TECHNICAL REPORTS
  • 6
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    Optimum mass-strength analysis for orthotropic ring-stiffened cylinders under axial compression (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An analysis was developed to calculate the minimum mass-strength curve for an orthotropic cylinder subjected to axial compressive loading. The analysis, which includes the effects of ring and stringer eccentricities, is in a general form so that various cylinder wall and stiffener geometries can be considered. Several different ring-stiffened orthotropic configurations were studied. The minimum mass-strength curves and the dimensions associated with these curves are presented for (in order of decreasing efficiency) a tubular double bead, a nonsymmetric double bead, a Z-stiffened skin, and a trapezoidal corrugation. A comparison of efficiencies of the configurations shows a tubular element cylinder to be more efficient than a 3-percent core-density honeycomb-sandwich cylinder. It was found that for an optimized Z-stiffened skin, the location of the Z-stiffeners (internal or external) made a negligible difference in efficiency.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TN-D-6772 , L-7060
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Supersonic flutter of sandwich panels - Effects of face sheet bending stiffness, rotary inertia, and orthotropic core shear stiffnesses (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Numerical analysis of supersonic flutter of flat rectangular, biaxilly stressed sandwich panels
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TN-D-6427 , A-3868
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Thermal and stress analysis of an Attached Inflatable Decelerator /AID/ deployed in the Mars and Earth atmospheres (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Trajectory, thermodynamic, and stress analyses of spacecraft inflatable decelerators in Mars and Earth atmospheres
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-111920 , GER-14939
    Format: application/pdf
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  • 9
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    Analysis of transient, linear wave propagation in shells by the finite difference method (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The applicability of the finite difference method to propagation problems in shells, and the response of a cylindrical shell with cutouts to both longitudinal and radial transient excitations are investigated. It is found that the only inherent limitation of the finite difference method is its inability to reproduce accurately response discontinuities. The short wave length limitations of thin shell theory create significant convergence difficulties may often be overcome through proper selection of finite difference mesh dimensions and temporal or spatial smoothing of the excitation. Cutouts produce moderate changes in early and intermediate time response of a cylindrical shell to axisymmetric pulse loads applied at one end. The cutouts may facilitate the undesirable late-time transfer of load-injected extensional energy into nonaxisymmetric flexural response.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-1885
    Format: application/pdf
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  • 10
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    Analysis of the transient response of shell structures by numerical methods. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper examines some basic considerations underlying dynamic shell response analysis and the impact of these considerations upon the practical aspects of solution by numerical methods. Emphasis is placed on the solution of linear problems. The present states of development of the finite difference and finite element methods are reviewed, and techniques for the treatment of temporal variation are discussed. An examination is made of the frequency parameters characteristic of thin shell theory, applied excitations, and spatial mesh geometries, and the significance of these parameters with respect to computational convergence is illustrated.
    Keywords: STRUCTURAL MECHANICS
    Type: Dynamic response of structures; Symposium; Jun 28, 1971 - Jun 29, 1971; Stanford, CA
    Format: text
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