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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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  • 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
    Format: text
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  • 3
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    Finite element large-amplitude free and forced vibrations of rectangular thin composite plates (1989)
    In:  Other Sources
    Details
    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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  • 5
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    Using PAFEC as a preprocessor for COSMIC/NASTRAN (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Programs for Automatic Finite Element Calculations (PAFEC) is a general purpose, three dimensional linear and nonlinear finite element program (ref. 1). PAFEC's features include free format input utilizing engineering keywords, powerful mesh generating facilities, sophisticated data base management procedures, and extensive data validation checks. Presented here is a description of a software interface that permits PAFEC to be used as a preprocessor for COSMIC/NASTRAN. This user friendly software, called PAFCOS, frees the stress analyst from the laborious and error prone procedure of creating and debugging a rigid format COSMIC/NASTRAN bulk data deck. By interactively creating and debugging a finite element model with PAFEC, thus taking full advantage of the free format engineering keyword oriented data structure of PAFEC, the amount of time spent during model generation can be drastically reduced. The PAFCOS software will automatically convert a PAFEC data structure into a COSMIC/NASTRAN bulk data deck. The capabilities and limitations of the PAFCOS software are fully discussed in the following report.
    Keywords: STRUCTURAL MECHANICS
    Type: COSMIC 11th NASTRAN User's Colloq.; p 21-32
    Format: application/pdf
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  • 6
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    A finite element method for nonlinear panel flutter (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-01-25
    Description: Panel flutter is the self excited oscillations of a plate in supersonic flow. Linear theory gives no information about the panel's deflections and stresses. Hence, the service life of the panel cannot be predicted by linear methods. Nonlinear structural theory determines the limit cycle oscillating frequency, and also panel deflections and stresses. Panel fatigue life, therefore, can be predicted. For a more thorough understanding of panel flutter behavior, the geometric nonlinearity effects due to large deflections must be considered in the formulation. The Galerkin's method was used in the investigation of limit cycle oscillations of panels in supersonic flow in the spatial domain, and the panel deflections. All nonlinear flutter methods and results presently available were limited to a linear or linearized aerodynamic theory. Extension of the finite element flutter formulation to include nonlinear hypersonic aerodynamic loading and finite element nonlinear panel flutter results are presented.
    Keywords: STRUCTURAL MECHANICS
    Type: Carleton Univ., Proceedings of the Twelfth Canadian Congress of Applied Mechanics, Volumes 1 and 2; p 118-119
    Format: text
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  • 7
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    A preliminary thermal distortion analysis of the proposed A0S0 experiment support structure (1965)
    In:  CASI
    Details
    Publication Date: 2019-05-29
    Description: Mathematical model for calculating thermal distortion of AOSO experiment support structure and equations for expressing interaction loads and rotational deflections
    Keywords: STRUCTURAL MECHANICS
    Type: X-430-65-493 , NASA-TM-X-55360
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  • 8
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    Thermal/structural analysis of a transpiration cooled nozzle (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The 8-foot High Temperature Tunnel (HTT) at LaRC is a combustion driven, high enthalpy blow down wind tunnel. In Mar. 1991, during check out of the transpiration cooled nozzle, pieces of platelets were found in the tunnel test section. It was determined that incorrect tolerancing between the platelets and the housing was the primary cause of the platelet failure. An analysis was performed to determine the tolerance layout between the platelets and the housing to meet the structural and performance criteria under a range of thermal, pressure, and bolt preload conditions. Three recommendations resulted as a product of this analysis.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TM-104184 , NAS 1.15:104184
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  • 9
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    Structural analysis of a thermal insulation retainer assembly (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In January 1989 an accident occurred in the National Transonic Facility wind tunnel at NASA Langley Research Center that was believed to be caused by the failure of a thermal insulation retainer. A structural analysis of this retainer assembly was performed in order to understand the possible failure mechanisms. Two loading conditions are important and were considered in the analysis. The first is the centrifugal force due to the fact that this retainer is located on the fan drive shaft. The second loading is a differential temperature between the retainer assembly and the underlying shaft. Geometrically nonlinear analysis is required to predict the stiffness of this component and to account for varying contact regions between various components in the assembly. High, local stresses develop in the band part of the assembly near discontinuities under both the centrifugal and thermal loadings. The presence of an aluminum ring during a portion of the part's operating life was found to increase the stresses in other regions of the band. Under the centrifugal load, high bending stresses develop near the intersection of the band with joints in the assembly. These high bending stresses are believed to be the most likely cause for failure of the assembly.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TM-101580 , NAS 1.15:101580
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  • 10
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    Coupled bending-torsion steady-state response of pretwisted, nonuniform rotating beams using a transfer-matrix method (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Using the Newtonian method, the equations of motion are developed for the coupled bending-torsion steady-state response of beams rotating at constant angular velocity in a fixed plane. The resulting equations are valid to first order strain-displacement relationships for a long beam with all other nonlinear terms retained. In addition, the equations are valid for beams with the mass centroidal axis offset (eccentric) from the elastic axis, nonuniform mass and section properties, and variable twist. The solution of these coupled, nonlinear, nonhomogeneous, differential equations is obtained by modifying a Hunter linear second-order transfer-matrix solution procedure to solve the nonlinear differential equations and programming the solution for a desk-top personal computer. The modified transfer-matrix method was verified by comparing the solution for a rotating beam with a geometric, nonlinear, finite-element computer code solution; and for a simple rotating beam problem, the modified method demonstrated a significant advantage over the finite-element solution in accuracy, ease of solution, and actual computer processing time required to effect a solution.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TM-100596 , NAS 1.15:100596
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