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  • AIRCRAFT STABILITY AND CONTROL  (2)
  • Engineering  (1)
  • 1985-1989  (3)
  • 1930-1934
  • 1915-1919
  • 1
    Electronic Resource
    Electronic Resource
    On numerical modelling of embedded subsonic flow (1986)
    Chichester : Wiley-Blackwell
    International Journal for Numerical Methods in Fluids 6 (1986), S. 103-112 
    Details
    ISSN: 0271-2091
    Keywords: Supersonic ; Subsonic ; Mach Disc ; Compressible Pressure-correction ; Engineering ; Engineering General
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Notes: An analytical model has been developed for computing embedded subsonic flow in rocket plumes from underexpanded axisymmetric supersonic nozzles. Numerical procedures based on the analysis have been incorporated in a simplified, non-reacting exhaust structure program and calculations for representative plume conditions performed. The technique is numerically stable and has provided satisfactory predictions of Mach-disc associated embedded subsonic flow.
    Additional Material: 7 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/fld.1650060302
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    Paper (German National Licenses)
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  • 2
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    Adaptation of a modern medium helicopter (Sikorsky S-76) to higher harmonic control (1985)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Sikorsky Aircraft has performed analytical studies, design analyses, and risk reduction tests have been performed for Higher Harmonic Control (HHC) on the S-76. The S-76 is an 8 to 10,000 lb helicopter which cruises at 145 kts. Flight test hardware has been assembled, main servo frequency response tested and upgraded, aircraft control system shake tested and verified, open loop controllers designed and fabricated, closed loop controllers defined and evaluated, and rotors turning ground and flight tests planned for the near future. Open loop analysis shows that about 2 deg of higher harmonic feathering at the blade 75% radius will be required to eliminate 4P vibration in the cockpit.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA. Ames Research Center Rotorcraft Dynamics 1984; p 365-378
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Analysis of potential helicopter vibration reduction concepts (1985)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Results of analytical investigations to develop, understand, and evaluate potential helicopter vibration reduction concepts are presented in the following areas: identification of the fundamental sources of vibratory loads, blade design for low vibration, application of design optimization techniques, active higher harmonic control, blade appended aeromechanical devices, and the prediction of vibratory airloads. Primary sources of vibration are identified for a selected four-bladed articulated rotor operating in high speed level flight. The application of analytical design procedures and optimization techniques are shown to have the potential for establishing reduced vibration blade designs through variations in blade mass and stiffness distributions, and chordwise center-of-gravity location.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA. Ames Research Center Rotorcraft Dynamics 1984; p 343-363
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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