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  • STRUCTURAL MECHANICS  (6)
  • Lunar and Planetary Science and Exploration  (3)
  • 1
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    On 3-D inelastic analysis methods for hot section components (1986)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The objective of this program is to produce a series of new computer codes that permit more accurate and efficient three-dimensional inelastic structural analysis of combustor liners, turbine blades, and turbine vanes. Each code embodies a progression of mathematical models for increasingly comprehensive representation of the geometrical features, loading conditions, and forms of nonlinear material response that distinguish these three groups of hot section components.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA, Lewis Research Center, Turbine Engine Hot Section Technology 1986; p 255-256
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    The 3-D inelastic analysis methods for hot section components (base program) (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The objective of this program is to produce a series of new computer codes that permit more accurate and efficient three dimensional inelastic analysis of selected hot section components - combustor liners, turbine blades and turbine vanes. The computer codes embody a progression of mathematical models and are streamlined to take advantage of geometrical features, loading conditions, and forms of material response that distinguish each group of selected components.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Lewis Research Center Turbine Eng. Hot Sect. Technol. (HOST); p 179-180
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    The 3-D inelastic analysis methods for hot section components (base program) (1984)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A series of computer codes are sought that would permit more accurate and efficient three-dimensional inelastic structural analysis of combustor liners, turbine blades, and turbine vanes. Each code embodies a progression of mathematical models for increasingly comprehensive representation of the geometrical features, loading conditions, and forms of nonlinear material response that distinguish these three groups of hot section components.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Lewis Research Center Turbine Engine Hot Section Technology, 1984; 4 p
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    SSME single crystal turbine blade dynamics (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A study was performed to determine the dynamic characteristics of the Space Shuttle main engine high pressure fuel turbopump (HPFTP) blades made of single crystal (SC) material. The first and second stage drive turbine blades of HPFTP were examined. The nonrotating natural frequencies were determined experimentally and analytically. The experimental results of the SC second stage blade were used to verify the analytical procedures. The analytical study examined the SC first stage blade natural frequencies with respect to crystal orientation at typical operating conditions. The SC blade dynamic response was predicted to be less than the directionally solidified blade. Crystal axis orientation optimization indicated the third mode interference will exist in any SC orientation.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-179644 , E-3671 , NAS 1.26:179644
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Three-dimensional inelastic analysis methods for hot section components (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The objective of this program is to produce a series of new computer codes that permit more accurate and efficient three-dimensional inelastic structural analysis of combustor liners, turbine blades, and turbine vanes. Each code embodies a progression of mathematical models for increasingly comprehensive representation of the geometrical features, loading conditions, and forms of nonlinear material response that distinguish these three groups of hot section components.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA, Lewis Research Center, Turbine Engine Hot Section Technology, 1987; p 239-240
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Imaging services flight software on the Mars Exploration Rovers (2005)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Keywords: Lunar and Planetary Science and Exploration
    Type: IEEE SMC 2005 - International Conference on Systems, Man and Cybernetics; Oct 10, 2005 - Oct 12, 2005; Waikoloa,HI; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    General 3D acquisition and tracking of dot targets on a Mars Rover prototype (2005)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Keywords: Lunar and Planetary Science and Exploration
    Type: IEEE SMC 2005 - International Conference on Systems, Man and Cybernetics; Oct 10, 2005; HI; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Imaging services flight software on the Mars Exploration Rovers (2005)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The Imaging Services module of the Mars Exploration Rovers' on-board flight software is responsible for providing image data to the rest of the system.
    Keywords: Lunar and Planetary Science and Exploration
    Type: IEEE SMC 2005 - International Conference on Systems, Man and Cybernetics; Oct 12, 2005; HI; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    The effect of steady aerodynamic loading on the flutter stability of turbomachinery blading (1990)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An aeroelastic analysis is presented which accounts for the effect of steady aerodynamic loading on the aeroelastic stability of a cascade of compressor blades. The aeroelastic model is a two degree of freedom model having bending and torsional displacements. A linearized unsteady potential flow theory is used to determine the unsteady aerodynamic response coefficients for the aeroelastic analysis. The steady aerodynamic loading was caused by the addition of airfoil thickness and camber and steady flow incidence. The importance of steady loading on the airfoil unsteady pressure distribution is demonstrated. Additionally, the effect of steady loading on the tuned flutter behavior and flutter boundaries indicates that neglecting either airfoil thickness, camber or incidence could result in nonconservative estimates of flutter behavior.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-187055 , E-5929 , NAS 1.26:187055 , International Gas Turbine and Aerospace Congress and Exposition; Jun 03, 1991 - Jun 06, 1991; Orlando, FL; United States
    Format: application/pdf
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