Item Details

Effects of Gyroscopic Cross Coupling Between Pitch and Yaw on the Handling Qualities of VTOL Aircraft

by John F. Garren, Jr.
Format
Book; Government Document; Online; EBook
Published
Washington, [D.C.] : National Aeronautical and Space Administration, 1961.
Language
English
Series
NASA Technical Note
Summary
Gyroscopic cross coupling between pitch and yaw was simulated with a variable-stability helicopter while hovering in a yawing maneuver to ascertain the effect of cross coupling on handling qualities. Pilot ratings of the controllability of cross coupling were obtained for various combinations of longitudinal control power, angular velocity about the yaw axis, and simulated engine angular momentum. A theoretical investigation, supplemented by simulator data, was undertaken to determine the effect of longitudinal damping on the coupling controllability. Also, a comparison was made between flight and simulator data. The results indicated that for an aircraft with otherwise satisfactory longitudinal handling qualities, the level of cross coupling is satisfactory when less than 30 percent of the available longitudinal control will trim out the largest gyroscopic coupling moment which might be encountered. Increased longitudinal damping resulted in a significant increase in the controllability of pitch-yaw gyroscopic cross coupling.
Description
21 p. : ill. ; 26 cm.
Mode of access: Internet.
Notes
  • Document ID: 20040006489.
  • "NASA TN D-973."
  • "Langley Research Center, Langley Air Force Base, Va."
  • "November 1961."
  • Cover title.
  • Includes bibliographical references (p. 11).
Series Statement
NASA technical note ; D-973
Logo for Copyright Not EvaluatedCopyright Not Evaluated
Technical Details

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    a| Effects of gyroscopic cross coupling between pitch and yaw on the handling qualities of VTOL aircraft / c| by John F. Garren, Jr.
    260
      
      
    a| Washington, [D.C.] : b| National Aeronautical and Space Administration, c| 1961.
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    a| 21 p. : b| ill. ; c| 26 cm.
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    a| NASA technical note ; v| D-973
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    a| Document ID: 20040006489.
    500
      
      
    a| "NASA TN D-973."
    500
      
      
    a| "Langley Research Center, Langley Air Force Base, Va."
    500
      
      
    a| "November 1961."
    500
      
      
    a| Cover title.
    504
      
      
    a| Includes bibliographical references (p. 11).
    520
      
      
    a| Gyroscopic cross coupling between pitch and yaw was simulated with a variable-stability helicopter while hovering in a yawing maneuver to ascertain the effect of cross coupling on handling qualities. Pilot ratings of the controllability of cross coupling were obtained for various combinations of longitudinal control power, angular velocity about the yaw axis, and simulated engine angular momentum. A theoretical investigation, supplemented by simulator data, was undertaken to determine the effect of longitudinal damping on the coupling controllability. Also, a comparison was made between flight and simulator data. The results indicated that for an aircraft with otherwise satisfactory longitudinal handling qualities, the level of cross coupling is satisfactory when less than 30 percent of the available longitudinal control will trim out the largest gyroscopic coupling moment which might be encountered. Increased longitudinal damping resulted in a significant increase in the controllability of pitch-yaw gyroscopic cross coupling.
    538
      
      
    a| Mode of access: Internet.
    650
      
    0
    a| Yawing (Aerodynamics)
    650
      
    0
    a| Pitching (Aerodynamics)
    650
      
    0
    a| Gyroscopic instruments.
    650
      
    0
    a| Vertically rising aircraft x| Handling characteristics.
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    a| United States. b| National Aeronautics and Space Administration.
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    a| Langley Research Center.
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