Item Details

Fundamental Limitations on V/STOL Terminal Guidance Due to Aircraft Characteristics

Julian Wolkovitch, Charles W. LaMont, and D. William Lochtie
Format
Book; Government Document; Online; EBook
Published
Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service [distributor], 1971.
Language
English
Series
NASA Contractor Report
Summary
A review is given of limitations on approach flight paths of V/STOL aircraft, including limits on descent angle due to maximum drag/lift ratio. A method of calculating maximum drag/lift ratio of tilt-wing and deflected slipstream aircraft is presented. Derivatives and transfer functions for the CL-84 tilt-wing and X-22A tilt-duct aircraft are presented. For the unaugmented CL-84 in steep descents the transfer function relating descent angle to thrust contains a right-half plane zero. Using optimal control theory, it is shown that this zero causes a serious degradation in the accuracy with which steep flight paths can be followed in the presence of gusts.
Description
xvi, 167 p. : ill. ; 27 cm.
Mode of access: Internet.
Notes
  • "NASA CR-1901."
  • "December 1971."
  • Cover title.
  • Includes bibliographical references (p. 164-167).
Series Statement
NASA contractor report ; NASA CR-1901
Logo for Copyright Not EvaluatedCopyright Not Evaluated
Technical Details

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    a| Fundamental limitations on V/STOL terminal guidance due to aircraft characteristics / c| Julian Wolkovitch, Charles W. LaMont, and D. William Lochtie.
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    a| Washington, D.C. : b| National Aeronautics and Space Administration ; a| Springfield, Va. : b| For sale by the National Technical Information Service [distributor], c| 1971.
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    a| xvi, 167 p. : b| ill. ; c| 27 cm.
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    a| NASA contractor report ; v| NASA CR-1901
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    a| "NASA CR-1901."
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    a| "December 1971."
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    a| Cover title.
    504
      
      
    a| Includes bibliographical references (p. 164-167).
    520
      
      
    a| A review is given of limitations on approach flight paths of V/STOL aircraft, including limits on descent angle due to maximum drag/lift ratio. A method of calculating maximum drag/lift ratio of tilt-wing and deflected slipstream aircraft is presented. Derivatives and transfer functions for the CL-84 tilt-wing and X-22A tilt-duct aircraft are presented. For the unaugmented CL-84 in steep descents the transfer function relating descent angle to thrust contains a right-half plane zero. Using optimal control theory, it is shown that this zero causes a serious degradation in the accuracy with which steep flight paths can be followed in the presence of gusts.
    536
      
      
    a| Prepared by Mechanics Research, Inc., Los Angeles, Calif. for Langley Research Center b| NAS1-9163
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    a| Mode of access: Internet.
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    a| Transfer functions. 2| nasat
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    a| Optimal control. 2| nasat
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    a| Flight paths. 2| nasat
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    a| Flight characteristics. 2| nasat
    650
      
    7
    a| Control theory. 2| nasat
    650
      
    7
    a| V/STOL aircraft. 2| nasat
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    a| Lift drag ratio. 2| nasat
    650
      
    7
    a| Descent trajectories. 2| nasat
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    7
    a| Approach. 2| nasat
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    a| Lochtie, D. William.
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    a| LaMont, Charles W.
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    a| Lewis Research Center.
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    a| Mechanics Research, inc.
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    b| UIU c| UIUC d| 20141113 s| google u| uiug.30112106857011 y| 1971 r| pd q| bib

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