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  • 11
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    A parametric shell analysis of the shuttle 51-L SRB AFT field joint (1990)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Following the Shuttle 51-L accident, an investigation was conducted to determine the cause of the failure. Investigators at the Langley Research Center focused attention on the structural behavior of the field joints with O-ring seals in the steel solid rocket booster (SRB) cases. The shell-of-revolution computer program BOSOR4 was used to model the aft field joint of the solid rocket booster case. The shell model consisted of the SRB wall and joint geometry present during the Shuttle 51-L flight. A parametric study of the joint was performed on the geometry, including joint clearances, contact between the joint components, and on the loads, induced and applied. In addition combinations of geometry and loads were evaluated. The analytical results from the parametric study showed that contact between the joint components was a primary contributor to allowing hot gases to blow by the O-rings. Based upon understanding the original joint behavior, various proposed joint modifications are shown and analyzed in order to provide additional insight and information. Finally, experimental results from a hydro-static pressurization of a test rocket booster case to study joint motion are presented and verified analytically.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TM-102748 , NAS 1.15:102748
    Format: application/pdf
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  • 12
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    Detailed analysis and test correlation of a stiffened composite wing panel (1991)
    In:  Other Sources
    Details
    Publication Date: 2018-12-01
    Description: New finite element analysis methods are examined by application to a complicated composite wing panel from the V-22 rotorcraft. A detailed FEM model with a relatively coarse mesh of 9-node elements was generated, and linear and nonlinear stress analyses, first-ply failure analyses, and buckling analyses were conducted. At low values of applied load, i.e., up to the design ultimate load of the panel, the linear stress analysis accurately predicted the strains and structural response characteristics of the panel.
    Keywords: STRUCTURAL MECHANICS
    Format: text
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  • 13
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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
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  • 14
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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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  • 15
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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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  • 16
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    Minimum-weight designs for hat-stiffened composite panels under uniaxial compression (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Optimum hat-stiffened compression panel designs are determined by a structural synthesis technique. The effects of simplifying assumptions made in the buckling analysis for the optimization program are investigated by a linked plate element program. Optimization results for hat-stiffened graphite-epoxy panels show a 50-percent weight savings over optimized aluminum panels. Composite panels are shown to possess a variety of proportions at nearly constant weight.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TN-D-7779 , L-9739
    Format: application/pdf
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  • 17
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    A computer program for plotting stress-strain data from compression, tension, and torsion tests of materials (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computer program for plotting stress-strain curves obtained from compression and tension tests on rectangular (flat) specimens and circular-cross-section specimens (rods and tubes) and both stress-strain and torque-twist curves obtained from torsion tests on tubes is presented in detail. The program is written in FORTRAN 4 language for the Control Data 6000 series digital computer with the SCOPE 3.0 operating system and requires approximately 110000 octal locations of core storage. The program has the capability of plotting individual strain-gage outputs and/or the average output of several strain gages and the capability of computing the slope of a straight line which provides a least-squares fit to a specified section of the plotted curve. In addition, the program can compute the slope of the stress-strain curve at any point along the curve. The computer program input and output for three sample problems are presented.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TM-X-3091 , L-9384
    Format: application/pdf
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  • 18
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    Performance of statistical energy analysis (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Statistical energy analysis (SEA) methods have been developed for high frequency modal analyses on random vibration environments. These SEA methods are evaluated by comparing analytical predictions to test results. Simple test methods are developed for establishing SEA parameter values. Techniques are presented, based on the comparison of the predictions with test values, for estimating SEA accuracy as a function of frequency for a general structure.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-124322 , MDC-G4741
    Format: application/pdf
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  • 19
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    Transonic panel flutter (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: FEM is here used to ascertain the stability and aeroelastic response of thin, 2D panels subjected to Mach 0.8-2.5 flows. In the absence of shocks, it is found that the Euler equations used to represent the unsteady flowfield dynamics predict response behaviors resembling those obtained via potential flow methods. Where shocks do play a significant role in the overall motion of the panel, divergence and limit cycle flutter are observed. In the Mach 1.4-1.5 range, flutter involved the higher modes of the panel, tending toward possible chaotic motion.
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA PAPER 93-1476 , ; 15 p.|AIAA, ASME, ASCE, AHS, and ASC, Structures, Structural Dynamics and Materials Conference, 34th and AIAA and ASME, Adaptive Structures Forum; Apr 19, 1993 - Apr 22, 1993; La Jolla, CA; United States
    Format: text
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  • 20
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    Reliability of stiffened structural panels: Two examples (1992)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The reliability of two graphite-epoxy stiffened panels that contain uncertainties is examined. For one panel, the effect of an overall bow-type initial imperfection is studied. The size of the bow is assumed to be a random variable. The failure mode is buckling. The benefits of quality control are explored by using truncated distributions. For the other panel, the effect of uncertainties in a strain-based failure criterion is studied. The allowable strains are assumed to be random variables. A geometrically nonlinear analysis is used to calculate a detailed strain distribution near an elliptical access hole in a wing panel that was tested to failure. Calculated strains are used to predict failure. Results are compared with the experimental failure load of the panel.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TM-107687 , NAS 1.15:107687 , ATCOM-TR-92-B-015 , ASME Winter Annual Meeting: Symposium on Reliability Technology; Nov 08, 1992 - Nov 13, 1992; Anaheim, CA; United States
    Format: application/pdf
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