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Optimal autorotational descent of a helicopter with control and state inequality constraintsA point-mass model of the OH-58A helicopter has been used to ascertain the autorotation profiles which minimize helicopter impact velocity while remaining within the bounds of the main rotor's collective pitch and angular speed. The optimal control strategies are comparable to those employed by pilots in autorotational landings. It is noted that a possibility exists for the reduction of the height-sink rate restriction zone of OH-58A helicopters, using optimal energy-management techniques.
Document ID
19900058289
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Lee, Allan Y.
(JPL Pasadena, CA, United States)
Date Acquired
August 14, 2013
Publication Date
October 1, 1990
Publication Information
Publication: Journal of Guidance, Control, and Dynamics
Volume: 13
ISSN: 0731-5090
Subject Category
Aircraft Stability And Control
Accession Number
90A45344
Funding Number(s)
CONTRACT_GRANT: NCC2-106
Distribution Limits
Public
Copyright
Other

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