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  • 1
    Publication Date: 2019-05-29
    Description: Theoretical solution for buckling problem of orthotropic cylindrical panels under axial compression
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-69870 , LMSC-M-77-65-3
    Format: application/pdf
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  • 2
    Publication Date: 2019-06-28
    Description: A one term analysis is presented for the elastic buckling of prismatic structures with either classical simple support or completely clamped boundary conditions on the transverse ends. Results suggest that a one term solution based on an appropriate choice of coordinate functions may lead to satisfactory buckling loads for other prismatic structures with completely clamped and other end conditions.
    Keywords: STRUCTURAL MECHANICS
    Type: Computers and Structures; 12; Nov. 198
    Format: text
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  • 3
    Publication Date: 2019-06-28
    Description: This paper investigates the effects of boundary conditions and panel width on the axially compressive buckling behavior of unstiffened, isotropic, circular cylindrical panels. Numerical results are presented for eight different sets of boundary conditions along the straight edges of the panels. For all sets of boundary conditions except one (SSI), the results show that the panel buckling loads monotonically approach the complete cylinder buckling load from above as the panel width is increased. Low buckling loads, sometimes less than half the complete cylinder buckling load, are found for simply supported panels with free in-plane edge displacements (SSI). The SSI buckling loads are below the complete cylinder load even for '360deg panels'. It is also observed that the prevention of circumferential edge displacement is the most important in-plane boundary condition from the point of view of increasing the buckling load, and that the prevention of edge rotation (i.e. clamping) in the circumferential direction also significantly increases the buckling load. Parametric studies are also performed to determine the effects of variations in panel length and thickness on the buckling loads.
    Keywords: Structural Mechanics
    Type: Computers and Structures; 6; 1; 29-35
    Format: text
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  • 4
    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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  • 5
    Publication Date: 2019-06-27
    Description: Numerical results of buckling of shells of revolution for computer program
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-1049 , REPT.-4-17-67-1
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  • 6
    Publication Date: 2019-06-27
    Description: Basic equations and method of solution for computerized analysis of shells of revolution with axisymmetric collapse and nonsymmetric bifurcation buckling behavior
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-1050 , LAC-4-17-67-1, V. 2
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  • 7
    Publication Date: 2019-06-27
    Description: Computer program for analysis of shells of revolution with axisymmetric loading
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-1051 , REPT.-4-17-67-4
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  • 8
    Publication Date: 2019-06-27
    Description: Computer program performs stability analyses for a wide class of shells without unduly restrictive approximations. The program uses numerical integration, finite difference of finite element techniques to solve with reasonable accuracy almost any buckling problem for shells exhibiting orthotropic behavior.
    Keywords: MATHEMATICS AND INFORMATION SCIENCES
    Type: LAR-10290
    Format: application/pdf
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  • 9
    Publication Date: 2019-07-13
    Description: Probabilistic predictions based on the IPACS code are presented for the material and structural response of unnotched and notched, IM6/3501-6 Gr/Ep laminates. Comparisons of predicted and measured modulus and strength distributions are given for unnotched unidirectional, cross-ply and quasi-isotropic laminates. The predicted modulus distributions were found to correlate well with the test results for all three unnotched laminates. Correlations of strength distributions for the unnotched laminates are judged good for the unidirectional laminate and fair for the cross-ply laminate, whereas the strength correlation for the quasi-isotropic laminate is judged poor because IPACS did not have a progressive failure capability at the time this work was performed. The report also presents probabilistic and structural reliability analysis predictions for the strain concentration factor (SCF) for an open-hole, quasi-isotropic laminate subjected to longitudinal tension. A special procedure was developed to adapt IPACS for the structural reliability analysis. The reliability results show the importance of identifying the most significant random variables upon which the SCF depends, and of having accurate scatter values for these variables.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-198429 , NAS 1.26:198429 , E-10027 , NIPS-96-08129
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  • 10
    Publication Date: 2019-07-13
    Description: An approach of structural optimization has been used to optimize the weight of a simply supported, corrugated hat stiffened composite panel under uniaxial compression. The approach consists of the employment of nonlinear mathematical programming techniques to reach an optimum solution. Some simplifying assumptions are made in the stress analysis to obtain faster convergence to an optimum solution. With these simplifying assumptions the number of unknown design parameters is reduced to twelve.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-132314
    Format: application/pdf
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