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  • 11
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    Stress analysis of pressure vessel assembly (1977)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: A radome assembly capable of withstanding large hydrostatic pressures was designed with a sapphire hemisperical dome and a plastic housing. These two parts were connected with a stainless steel flange ring. A finite-element stress analysis of this assembly was accomplished and an experimental load test was performed to verify the predicted stresses.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA, Washington 6th NASTRAN (R) Users' Colloq.; p 405-417
    Format: text
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  • 12
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    Structural dynamic and aeroelastic considerations for hypersonic vehicles (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Structural dynamic and aeroelastic considerations applicable to hypersonic vehicles are discussed. Emphasis is given to aerospace plane configurations. The definition of aerothermoelasticity and the operational flight environment are reviewed, and structural dynamic and aeroelastic areas of concern are individually discussed, including vibration, landing and taxiing, propellant dynamics, acoustics, lifting surface flutter, panel flutter, control surface buzz, buffeting, gust response, and static aeroelasticity. Recent research results from all-moveable delta-wing aerolastic studies, engine inlet lip aeroelastic analysis, and studies of thermal effects on vibration frequencies, aerodynamic heating effects on flutter, and active control of aeroelastic response are reviewed.
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA PAPER 91-1255
    Format: text
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  • 13
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    Modal characteristics of a stiffened composite cylinder with open and closed end conditions (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The structural and acoustic modal frequencies and the loss factors of a composite fuselage model under free-free end and support-end conditions are evaluated. The fuselage model is a composite filament wound, cylindrical structure composed of carbon fibers embedded in an epoxy resin and has a ply orientation of +,-45, +,-32, 0, -,+32, and -,+45. A computer aided test system was utilized to obtain resonance frequencies, modal damping, and mode shape coefficients. Sound pressure and phase survey data are utilized to estimate acoustic modal freuencies and reverberation time was measured to calculate the acoustic loss factors. The derived structural and acoustic modal parameters are compared to analytical data from a computer prediction model. The data reveal that the acoustic modal frequencies and mode shape correlate well with predicted data, and there is fair agreement between structural modal frequencies and mode shape for the two data sets.
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA PAPER 86-1908
    Format: text
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  • 14
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    BUNVIS-RG - An exact buckling and vibration program for lattice structures, with repetitive geometry and substructuring options (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The exact FORTRAN computer program BUNVIS-RG which uses an exact stiffness matrix method to find eigenvalues and modes of three-dimensional planes, is presented in detail. It is shown that BUNVIS-RG solution times can be predicted fairly accurately from two computer dependent constants, the number of nodes and members in the frame, and the maximum node number difference of any pair of connected nodes. The program's use of repetitive geometry, stayed column substructures and nonuniform member options was found to enhance efficiency and range of application.
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA PAPER 86-0868
    Format: text
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  • 15
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    A new approach to the explanation of the flutter mechanism (1966)
    In:  CASI
    Details
    Publication Date: 2019-05-29
    Description: Structural stability of bending torsion flutter model
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TN-D-3125
    Format: application/pdf
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  • 16
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    Flutter Investigation at a Mach Number of 7.2 of Models of the Horizontal-tail and Vertical-tail Surfaces of the X-15 Airplane (1959)
    In:  CASI
    Details
    Publication Date: 2019-05-30
    Description: Flutter studies at Mach 7.2 of horizontal and vertical tail surface models of X-15 aircraft
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-MEMO-4-14-59L
    Format: application/pdf
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  • 17
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    The semi-elliptical surface crack - A solution by the alternating method (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: A numerical solution to the three-dimensional equations of elasticity is presented for the problem of a semi-elliptical surface crack in the surface of a finite thickness solid. The alternating method is used to develop the numerical results which incorporate the effects on the stress intensity factor due to the presence of both the front and the back surfaces. The stress intensity factor is presented as a function of position along the crack border for a variety of crack shapes and crack depths. A comparison of the results of this study is made with previous theoretical and experimental work.
    Keywords: STRUCTURAL MECHANICS
    Type: International Journal of Fracture; 12; Feb. 197
    Format: text
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  • 18
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    Stress-intensity factors for a surface crack in a finite solid. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: A solution to the problem of a circular crack partially embedded in a solid of finite thickness is presented. A superposition and iteration technique is used to determine the stress-intensity factor numerically. The stress-intensity factor is determined as a function of position around the crack front for a variety of crack depths. The results of this study are compared with experimental data for a semielliptical surface flaw in a brittle material.
    Keywords: STRUCTURAL MECHANICS
    Type: ASME PAPER 71-APMW-6
    Format: text
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  • 19
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    The partially closed Griffith crack (1973)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: A solution is presented for a Griffith crack subjected to an arbitrary polynomial loading function which causes one end of the crack to remain closed. Closed form expressions are presented for the crack opening length and for the stress and displacements in the plane of the crack. The special case of pure bending is presented as an example and for this case the stress intensity factor is computed.
    Keywords: STRUCTURAL MECHANICS
    Type: International Journal of Fracture; 9; Mar. 197
    Format: text
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  • 20
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    The elliptical crack subjected to nonuniform shear loading. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: The equations of elasticity are solved for the problem of a flat elliptical crack which has nonuniform shear stresses applied to its surfaces. The shear stresses are prescribed independently in two directions on the crack surface and are expressed in the form of a third-degree polynomial. Mode-two and mode-three stress-intensity factors are presented in analytical and graphical form as functions of position along the crack border.
    Keywords: STRUCTURAL MECHANICS
    Type: ASME PAPER 73-APMW-42 , Applied Mechanics Western Conference; Sept. 17-19, 1973; Menlo Park, CA
    Format: text
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