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A piloted simulator investigation of static stability and stability/control augmentation effects on helicopter handling qualities for instrument approachA ground simulator experiment was conducted on the Flight Simulator for Advanced Aircraft at Ames Research Center to investigate the influence of several static stability and stability/control augmentation design parameters on helicopter flying qualities during terminal area operations in instrument conditions. Effects of light turbulence were included. Two levels of static stability in each rotational axis (pitch, roll, yaw) were examined for a hingeless rotor configuration. The variations in pitch and roll were: (1) stable and (2) neutral static stability; in yaw there were two stable levels. Four types of stability/control augmentation were also examined for the lower level of static stability in each axis. This latter investigation covered three helicopter rotor types: hingeless, articulated, and teetering. Four pilots performed a total of 105 evaluations of these parameters for a representative VOR instrument approach task. Pilot rating results indicate the acceptability of neutral static stability longitudinally and laterally and the need for pitch-roll attitude augmentation to achieve a satisfactory system.
Document ID
19810055756
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Lebacqz, J. V.
(NASA Ames Research Center Moffett Field, CA, United States)
Forrest, R. D.
(FAA Moffett Field, CA, United States)
Date Acquired
August 11, 2013
Publication Date
January 1, 1980
Subject Category
Aircraft Stability And Control
Report/Patent Number
AHS 80-30
Meeting Information
Meeting: Annual Forum of the American Helicopter Society
Location: Washington, DC
Start Date: May 13, 1980
End Date: May 15, 1980
Sponsors: American Helicopter Society
Accession Number
81A40160
Distribution Limits
Public
Copyright
Other

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