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  • 1
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    Large-amplitude finite element flutter analysis of composite panels in hypersonic flow (1993)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA Journal (ISSN 0001-1452); 31; 6; p. 1090-1099.
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Finite element method for large-amplitude two-dimensional panel flutter at hypersonic speeds (1991)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA Journal (ISSN 0001-1452); 29; 290-298
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    NASA TECHNICAL REPORTS
  • 3
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    Finite element large-amplitude free and forced vibrations of rectangular thin composite plates (1989)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: A finite element formulation is presented for determining the large-amplitude free and steady-state forced vibration response of arbitrarily laminated anisotropic composite rectangular thin plates. The nonlinear stiffness and harmonic force matrices of an arbitrarily laminated composite rectangular plate element are developed for nonlinear free and forced vibration analyses. The linearized updated-mode method with nonlinear time function approximation is employed for the solution of the system nonlinear eigenvalue equations. The amplitude-frequency relations for convergence with gridwork refinement, different boundary conditions, aspect ratios, lamination angles and number of plies are presented. The finite element results are compared with available approximate continuum solutions.
    Keywords: STRUCTURAL MECHANICS
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  • 4
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    Large deflection, large amplitude vibrations and random response of symmetrically laminated plates (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: STRUCTURAL MECHANICS
    Type: Journal of Aircraft (ISSN 0021-8669); 22; 929
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Use of NASTRAN in a university environment (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A survey was conducted in the middle of the 1977-78 school year. Each faculty member of the civil engineering, engineering mechanics, and mechanical and aerospace engineering departments was asked to give information on the present (Level 15.5) and future projected (Level 17) usage of NASTRAN programs. Results from the survey study are summarized.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Marshall Space Flight Center Seventh NASTRAN User's Colloq.; p 67-70
    Format: application/pdf
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  • 6
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    NASTRAN nonlinear vibration analysis of beam and frame structures (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A capability for the nonlinear vibration analysis of beam and frame structures suitable for use with NASTRAN level 15.5 is described. The nonlinearity considered is due to the presence of axial loads induced by longitudinal end restraints and lateral displacements that are large compared to the beam height. A brief discussion is included of the mathematical analysis and the geometrical stiffness matrix for a prismatic beam (BAR) element. Also included are a brief discussion of the equivalent linearization iterative process used to determine the nonlinear frequency, the required modifications to subroutines DBAR and XMPLBD of the NASTRAN code, and the appropriate vibration capability, four example problems are presented. Comparisons with existing experimental and analytical results show that excellent accuracy is achieved with NASTRAN in all cases.
    Keywords: STRUCTURAL MECHANICS
    Type: NASTRAN: Users' Experiences; p 259-284
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  • 7
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    Application of the TRPLT1 element to large amplitude free vibrations of plates (1977)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: A finite element formulation is developed for analyzing large amplitude free flexural vibrations of thin plates in NASTRAN. Stress distributions in the plate, in addition to deflection shapes and nonlinear frequencies are determined. Linearized equations of motion governing large amplitude oscillations of plates and a linearized geometrical stiffness matrix are presented. The solution procedure and convergence characteristics are discussed. The quasi-linear geometrical stiffness matrix for an eighteen degree-of-freedom higher order triangular plate element is evaluated by using a seven-point numerical integration. Nonlinear frequencies for square, rectangular, rhombic, and isosceles triangular plates, with edges simply supported or clamped, are compared with earlier solutions. The present formulation is found to give results entirely adequate for engineering purposes.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA, Washington 6th NASTRAN (R) Users' Colloq.; p 275-298
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  • 8
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    A condensed form of NASTRAN (1977)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: The Interactive Graphics Finite Element System, IGFES, is described along with its supporting analysis software, graphics terminal support package and hardware configurations. IGFES provides an interactive design tool for structural engineers via pre- and postprocessing of finite element data. The system currently runs on an IBM 360/44 OS-MFT system or a PDP 11/40 DOS/BATCH system. Graphics devices are supported using an inhouse developed, device independent terminal support package. Support is available for the Calcomp 563 drum plotter, Tektronix 4002A storage display terminal and the Lundy Electronics 20 inch standalone refresh display system. IGFES and its associated systems are written in FORTRAN IV.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA, Washington 6th NASTRAN (R) Users' Colloq.; p 299-325
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  • 9
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    Addition of higher order plate elements to NASTRAN (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Two plate elements, the linear strain triangular membrane element CTRIM6 and the higher order plate bending element CTRPLT1, were added to NASTRAN Level 16.0. The theoretical formulation, programming details, and bulk data information pertaining to the addition of these elements are discussed. Sample problems illustrating the use of these elements are presented.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Ames Res. Center NASTRAN: User's Experiences; p 439-478
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  • 10
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    Application of NASTRAN to large deflection supersonic flutter of panels (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Flat panel flutter at high supersonic Mach number is analyzed using NASTRAN Level 16.0 by means of modifications to the code. Two-dimensional plate theory and quasi-steady aerodynamic theory are employed. The finite element formulation and solution procedure are presented. Modifications to the NASTRAN code are discussed. Convergence characteristics of the iteration processes are also briefly discussed. Effects of aerodynamic damping, boundary support condition and applied in-plane loading are included. Comparison of nonlinear vibration and linear flutter results with analytical solutions demonstrate that excellent accuracy is obtained with NASTRAN.
    Keywords: STRUCTURAL MECHANICS
    Type: NASTRAN: User's Experiences; p 67-98
    Format: application/pdf
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