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  • STRUCTURAL MECHANICS  (254)
  • 1975-1979  (254)
  • 1955-1959
  • 1940-1944
  • 1976  (254)
  • 1940
  • 1
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    The NASTRAN demonstration program manual (level 16.0) (1976)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The types of problems that can be solved with NASTRAN are presented. The nature of the problem, the underlying theory, the specific geometric and physical input quanties, and the comparison of theoretical and NASTRAN results are discussed. At least one problem for each of the rigid formats and nearly all of the elements or provided. The features of NASTRAN demonstrated by specific problems are described. The results obtained are valid.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-SP-224(03)
    Format: application/pdf
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  • 2
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    The NASTRAN theoretical manual (level 16.0) (1976)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The manual is a commentary on the NASTRAN computer program, introducing the program to all interested persons. The manual's most important function is to present the developments of the analytical and numerical procedures that underlie the program. This manual is one of the four manuals which document the NASTRAN computer program.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-SP-221(03)
    Format: application/pdf
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  • 3
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    Thermal and Structural Analysis of Helicopter Transmission Housings Using NASTRAN (1976)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: The application of NASTRAN to improve the design of helicopter transmission housings is described. A finite element model of the complete forward rotor transmission housing for the Boeing Vertol CH-47C helicopter was used to study thermal distortion and stress, stress and deflection due to static and dynamic loads, load paths, and design optimization by the control of structural energy distribution. The analytical results are correlated with test data and used to reduce weight and to improve strength, service life, failsafety, and reliability. The techniques presented, although applied herein to helicopter transmissions, are sufficiently general to be applicable to any power transmission system.
    Keywords: STRUCTURAL MECHANICS
    Type: NASTRAN: User''s Experiences; Oct 05, 1976 - Oct 06, 1976; Moffett Field, CA; United States
    Format: application/pdf
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  • 4
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    Proof test criteria for thin walled pressure vessels (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: Proof tests were conducted on surface-flaw pressure-vessel specimens of 2219-T87 aluminum base metal and weld metal at three different temperatures: 72, -320, and -423 F, and for three different metal sheet thicknesses: 0.125, 0.250, and 0.375 in. It was found that significant stable crack growth under increasing load can occur prior to failure. Initial flaw shapes and material conditions have a significant effect on the extent of crack growth. Stable crack growth initiates at a lower K sub Ii/K sub cr ratio and is more severe in weld metal specimens than in base metal specimens. Low aspect ratio flaws experience more growth in the depthwise direction than higher aspect ratio flaws. Proof testing assures that any first cycle failure will be by leakage, not by catastrophic failure.
    Keywords: STRUCTURAL MECHANICS
    Type: Sagamore Army Materials Research Conference; Sept. 9, 1976; Raquette Lake, NY
    Format: text
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  • 5
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    Ductile fracture of cylindrical vessels containing a large flaw (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The fracture process in pressurized cylindrical vessels containing a relatively large flaw is considered. The flaw is assumed to be a part-through or through meridional crack. The flaw geometry, the yield behavior of the material, and the internal pressure are assumed to be such that in the neighborhood of the flaw the cylinder wall undergoes large-scale plastic deformations. Thus, the problem falls outside the range of applicability of conventional brittle fracture theories. To study the problem, plasticity considerations are introduced into the shell theory through the assumptions of fully-yielded net ligaments using a plastic strip model. Then a ductile fracture criterion is developed which is based on the concept of net ligament plastic instability. A limited verification is attempted by comparing the theoretical predictions with some existing experimental results.
    Keywords: STRUCTURAL MECHANICS
    Type: National Symposium on Fracture Mechanics; Aug 25, 1975 - Aug 27, 1975; Pittsburgh, PA
    Format: text
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  • 6
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    On a model of calculating bond strength (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Diffusion bonding is a fabricating process to join the fibers and a matrix together forming a composite. The efficiency of the bonding process depends on temperature, time, and pressure. Based on a simplified pair potential model, an expression for the bond-energy at the fiber-matrix interface is formulated in terms of the above-mentioned three parameters. From this expression and the mean atomic distance, the bond-strength between the fibers and the matrix can be calculated.
    Keywords: STRUCTURAL MECHANICS
    Type: International Conference on Composite Materials; Apr 07, 1975 - Apr 11, 1975; Geneva; Switzerland*US|Apr 14, 1975 - Apr 18, 1975; Boston, MA; US
    Format: text
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  • 7
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    Stresses in acoustically excited panels and shuttle insulation tiles (1976)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Natural vibration and acoustic response results are presented for a 36 x 18 inch panel with 18 6 x 6-inch tiles of 1.0, 1.6 and 2.3 inch thicknesses. Computed results for an untiled panel are compared with experiments performed earlier. Natural frequency and acoustic response comparisons are also given for independent analyses performed upon tiled and untiled panels. The results indicate the general applicability of the computer programs developed for use as shuttle design and analysis tools.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-145222
    Format: application/pdf
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  • 8
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    Cyclic structural analysis of air-cooled gas turbine blades and vanes (1976)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The creep fatigue behavior of a fully impingement cooled blade for four cyclic cases was analyzed by using the Elas 55, finite element, nonlinear structural computer program. Expected cyclic lives were calculated by using the method of strainrange partitioning for reversed inelastic strains and time fractions for ratcheted tensile creep strains. Strainrange partitioning was also applied to previous results from a one dimensional cyclic analysis of a film impingement cooled vane. The analyses indicated that strainrange partitioning is more applicable to a constrained airfoil such as the film impingement cooled vane than to the relatively unconstrained fully impingement cooled airfoil.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TM-X-73494 , E-8892 , Aerospace Eng. Conf.; Nov 29, 1976 - Dec 02, 1976; San Diego, CA; United States
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  • 9
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    Mode 1 stress intensity factors for round compact specimens (1976)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The mode 1 stress intensity factors were computed for round compact specimens by the boundary collocation method. Results are presented for ratios A sub T/R sub 0 in the range 0.3 to 0.8, where A sub t is the distance from the specimen center to the crack tip for a specimen of diameter 2R sub 0.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TM-X-73472 , E-8857 , Task Group E-24.01.12 of Comm. E-24 of the Am. Soc. for Testing and Mater.; Oct 05, 1976; Philadelphia
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  • 10
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    Treatment of multiaxial creep-fatigue by strainrange partitioning (1976)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Strainrange partitioning is a recently developed method for treating creep-fatigue interaction at elevated temperature. Most of the work to date has been on uniaxially loaded specimens, where as practical applications often involve load multiaxiality. It is shown how the method can be extended to treat multiaxiality through a set of rules for combining the strain components in the three principal directions. Closed hysteresis loops, as well as plastic and creep strain ratcheting are included. An application to hold-time tests in torsion will be used to illustrate the approach.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TM-X-73488 , Winter Annual Meeting of the Am. Soc. of Mechanical Engineers; Dec 06, 1976 - Dec 10, 1976; New York
    Format: application/pdf
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