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  • 1
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    Element Load Data Processor (ELDAP) Users Manual (2015)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Often, the shear and tensile forces and moments are extracted from finite element analyses to be used in off-line calculations for evaluating the integrity of structural connections involving bolts, rivets, and welds. Usually the maximum forces and moments are desired for use in the calculations. In situations where there are numerous structural connections of interest for numerous load cases, the effort in finding the true maximum force and/or moment combinations among all fasteners and welds and load cases becomes difficult. The Element Load Data Processor (ELDAP) software described herein makes this effort manageable. This software eliminates the possibility of overlooking the worst-case forces and moments that could result in erroneous positive margins of safety and/or selecting inconsistent combinations of forces and moments resulting in false negative margins of safety. In addition to forces and moments, any scalar quantity output in a PATRAN report file may be evaluated with this software. This software was originally written to fill an urgent need during the structural analysis of the Ares I-X Interstage segment. As such, this software was coded in a straightforward manner with no effort made to optimize or minimize code or to develop a graphical user interface.
    Keywords: Structural Mechanics; Computer Programming and Software
    Type: NASA/TM-2015-218126 , E-18876
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    TIME MODES AND LINEAR SYSTEMS (2000)
    Elsevier
    Details
    Publication Date: 2000-04-01
    Print ISSN: 0022-460X
    Electronic ISSN: 1095-8568
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics , Physics
    Published by Elsevier
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    PAPER CURRENT
  • 3
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    Time modes and nonlinear systems (2010)
    Elsevier
    Details
    Publication Date: 2010-06-01
    Print ISSN: 0022-460X
    Electronic ISSN: 1095-8568
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics , Physics
    Published by Elsevier
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    PAPER CURRENT
  • 4
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    Influence of thickness and camber on the aeroelastic stability of supersonic throughflow fans (1991)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: An engineering approach was used to include the nonlinear effects of thickness and camber in an analytical aeroelastic analysis of casecades in supersonic acial flow (supersonic leading-edge locus). A hybrid code using Lighthill's nonlinear piston theory and Lane's linear potential theory was developed to include these nonlinear effects. Lighthill's theory was used to calculate the unsteady pressures on the noninterference surface regions of the airfoils in cascade. Lane's theory was used to calculate the unsteady pressures on the remaining interference surface regions. Two airfoil profiles were investigated (a supersonic throughflow fan design and a NACA 66-206 airfoil with a sharp leading edge). Results show that compared with predictions of Lane's potential theory for flat plates, the inclusion of thickness (with or without camber) may increase or decrease the aeroelastic stability, depending on the airfoil geometry and operating conditions. When thickness effects are included in the aeroelastic analysis, inclusion of camber will influence the predicted stability in proportion to the magnitude of the added camber. The critical interblade phase angle, depending on the airfoil profile and operating conditions, may also be influenced by thickness and camber. Compared with predictions of Lane's linear potential theory, the inclusion of thickness and camber decreased the aerodynamic stiffness and increased the aerodynamic damping at Mach 2 and 2.95 for a cascade of supersonic throughflow fan airfoils oscillating 180 degrees out of phase at a reduced frequency of 0.1.
    Keywords: AERODYNAMICS
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 7; 404-411
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Supersonic axial-flow fan flutter (1988)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Lane's (1957) analytical formulation of the unsteady pressure distribution on an oscillating two-dimensional flat plate cascade in supersonic axial flow has been developed into a computer code. This unsteady aerodynamic code has shown good agreement with other published data. This code has also been incorporated into an existing aeroelastic code to analyze the NASA Lewis supersonic through-flow fan design.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA, Lewis Research Center, Lewis Structures Technology, 1988. Volume 1: Structural Dynamics; p 393-403
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Post clamp (1990)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A pair of spaced collars are mounted at right angles on a clamp body by retaining rings which enable the collars to rotate with respect to the clamp body. Mounting posts extend through aligned holes in the collars and clamp body. Each collar can be clamped onto the inserted post while the clamp body remains free to rotate about the post and collar. The clamp body is selectively clamped onto each post.
    Keywords: MECHANICAL ENGINEERING
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Optical measurement of propeller blade deflections in a spin facility (1990)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A nonintrusive optical system for measuring propeller blade deflections has been used in the NASA Lewis dynamic spin facility. Deflection of points at the leading and trailing edges of a blade section can be obtained with a narrow light beam from a low power helium-neon laser. A system used to measure these deflections at three spanwise locations is described. Modifications required to operate the lasers in a near-vacuum environment are also discussed.
    Keywords: AERODYNAMICS
    Type: NASA-TM-103115 , E-5439 , NAS 1.15:103115
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Theoretical and Experimental Unsteady Aerodynamics Compared for a Linear Oscillating Cascade With a Supersonic Leading-Edge Locus (2005)
    In:  CASI
    Details
    Publication Date: 2018-06-02
    Description: Experimental data were obtained to help validate analytical and computational fluid dynamics (CFD) codes used to compute unsteady cascade aerodynamics in a supersonicaxial- flow regime. Results from two analytical codes and one CFD code were compared with experimental data. One analytical code did not account for airfoil thickness or camber; another, using piston theory (piston code), accounted for thickness and camber upstream of the first shockwave/airfoil impingement locations. The Euler CFD code accounted fully for airfoil shape.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Research and Technology 2004; NASA/TM-2005-213419
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Optical Measurement Of Propfan Deflections (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Optoelectronic system measures deflections of rotating propfan. In addition to 0.5-mW HeNe lasers, system includes Schottky-barrier photodetectors, neutral-density filters, signal amplifiers, output-signal-recording device, and digitizer. Laser beam passes through plane of rotation of propfan blades. Beam is one of three that measure displacements at different blade sections. Additional laser beam at bottom generates shaft-rotation timing signal.
    Keywords: ELECTRONIC SYSTEMS
    Type: LEW-15678 , Laser Tech. Brief.; 2; 1; P. 96
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Influence of thickness and camber on the aeroelastic stability of supersonic throughflow fans: An engineering approach (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An engineering approach was used to include the nonlinear effects of thickness and camber in an analytical aeroelastic analysis of cascades in supersonic acial flow (supersonic leading-edge locus). A hybrid code using Lighthill's nonlinear piston theory and Lanes's linear potential theory was developed to include these nonlinear effects. Lighthill's theory was used to calculate the unsteady pressures on the noninterference surface regions of the airfoils in cascade. Lane's theory was used to calculate the unsteady pressures on the remaining interference surface regions. Two airfoil profiles was investigated (a supersonic throughflow fan design and a NACA 66-206 airfoil with a sharp leading edge). Results show that compared with predictions of Lane's potential theory for flat plates, the inclusion of thickness (with or without camber) may increase or decrease the aeroelastic stability, depending on the airfoil geometry and operating conditions. When thickness effects are included in the aeroelastic analysis, inclusion of camber will influence the predicted stability in proportion to the magnitude of the added camber. The critical interblade phase angle, depending on the airfoil profile and operating conditions, may also be influenced by thickness and camber. Compared with predictions of Lane's linear potential theory, the inclusion of thickness and camber decreased the aerodynamic stifness and increased the aerodynamic damping at Mach 2 and 2.95 for a cascade of supersonic throughflow fan airfoils oscillating 180 degrees out of phase at a reduced frequency of 0.1.
    Keywords: AERODYNAMICS
    Type: NASA-TM-101949 , E-4642 , NAS 1.15:101949
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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