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  • AIRCRAFT STABILITY AND CONTROL  (2)
  • STRUCTURAL MECHANICS  (2)
  • 2000-2004
  • 1980-1984  (4)
  • 1945-1949
  • 1
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    Three-dimensional Stress Analysis Using the Boundary Element Method (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The boundary element method is to be extended (as part of the NASA Inelastic Analysis Methods program) to the three-dimensional stress analysis of gas turbine engine hot section components. The analytical basis of the method (as developed in elasticity) is outlined, its numerical implementation is summarized, and the approaches to be followed in extending the method to include inelastic material response indicated.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Lewis Research Center Nonlinear Struct. Anal.; p 149-160
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Flight test experience with high-alpha control system techniques on the F-14 airplane (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Improved handling qualities of fighter aircraft at high angles of attack can be provided by various stability and control augmentation techniques. NASA and the U.S. Navy are conducting a joint flight demonstration of these techniques on an F-14 airplane. This paper reports on the flight test experience with a newly designed lateral-directional control system which suppresses such high angle of attack handling qualities problems as roll reversal, wing rock, and directional divergence while simultaneously improving departure/spin resistance. The technique of integrating a piloted simulation into the flight program was used extensively in this program. This technique had not been applied previously to high angle of attack testing and required the development of a valid model to simulate the test airplane at extremely high angles of attack.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 81-2505 , Flight Testing Conference; Nov 11, 1981 - Nov 13, 1981; Las Vegas, NV
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    3-D inelastic analysis methods for hot section components (base program) (1984)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A 3-D inelastic analysis methods program consists of a series of computer codes embodying a progression of mathematical models (mechanics of materials, special finite element, boundary element) for streamlined analysis of combustor liners, turbine blades, and turbine vanes. These models address the effects of high temperatures and thermal/mechanical loadings on the local (stress/strain) and global (dynamics, buckling) structural behavior of the three selected components. These models are used to solve 3-D inelastic problems using linear approximations in the sense that stresses/strains and temperatures in generic modeling regions are linear functions of the spatial coordinates, and solution increments for load, temperature and/or time are extrapolated linearly from previous information. Three linear formulation computer codes, referred to as MOMM (Mechanics of Materials Model), MHOST (MARC-Hot Section Technology), and BEST (Boundary Element Stress Technology), were developed and are described.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-174700 , NAS 1.26:174700 , PWA-5940-19 , ASR-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    A Summery of an In-flight Evaluation of Control System Pure Time Delays During Landing Using the F-8 DFBW Airplane (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An in-flight investigation of the effect of pure time delays on low L/D space shuttle type landing tasks was undertaken. The results indicate that the sensitivity of the pilot ratings to changes in pure time delay in pitch is strongly affected by the task and only slightly affected by changes in control system augmentation mode. Low L/D spot landings from a lateral offset were twice as sensitive to pure time delay as normal low L/D landings. For comparison purposes, formation flying was also investigated, and was found to be less sensitive to time delay than the landing tasks.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 80-1626 , Atmospheric Flight Mechanics Conference; Aug 11, 1980 - Aug 13, 1980; Danvers, MA
    Format: text
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    NASA TECHNICAL REPORTS
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