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Use of an optimized controller and a finite-state stall model to find trimmed helicopter flight controlsAn auto-pilot is applied to helicopter rotor flap-lag-torsion equations in order to obtain the control settings for a trimmed flight condition. The rotor aerodynamic description includes a state-space dynamic stall model for lift and for pitching moments. Thus, an attempt is made to trim the rotor for flight conditions in which significant stall and torsional deformations are present. The auto-pilot is extended to Q-bladed rotors by a series of time-delay terms. As a result, the optimum gains and time constants depend upon the number of blades as well as upon the torsional stiffness.
Document ID
19910060757
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Peters, David A.
(Georgia Inst. of Tech. Atlanta, GA, United States)
Chouchane, Mnaouar
(Georgia Inst. of Tech. Atlanta, GA, United States)
Fulton, Mark
(Georgia Institute of Technology Atlanta, United States)
Date Acquired
August 14, 2013
Publication Date
September 1, 1989
Subject Category
Aircraft Stability And Control
Accession Number
91A45380
Funding Number(s)
CONTRACT_GRANT: NAG1-710
Distribution Limits
Public
Copyright
Other

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