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Benefits of variable rotor speed in integrated helicopter/engine controlCurrent helicopter flight and propulsion controls are typically designed with the assumption that rotor speed will be held to a constant setpoint. A new flight and propulsion control system using a continuously variable rotor speed command is proposed to improve the maneuverability and agility of helicopter systems. In this new approach, the flight control system generates an optimal variable rotor speed command in addition to conventional control commands in a framework of integrated flight/propulsion control. The benefits (i.e. improved maneuverability and agility) of varying rotor speed during transient maneuvers are demonstrated using a bob-up maneuver as an example. In particular, two types of benefits are identified in different maneuver conditions. One comes from a thrust augmentation, while the other comes from an exchange of rotational and translational energy. In the example, a simple linear dynamic hover model is used with an optimal control design method to generate the optimal rotor speed command.
Document ID
19930067441
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Iwata, Takanori
(NASA Ames Research Center Moffett Field, CA, United States)
Rock, Stephen M.
(Stanford Univ. CA, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Publication Information
Publication: In: AIAA Guidance, Navigation and Control Conference, Monterey, CA, Aug. 9-11, 1993, Technical Papers. Pt. 3 (A93-51301 22-63)
Publisher: American Institute of Aeronautics and Astronautics
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA PAPER 93-3851
Accession Number
93A51438
Funding Number(s)
CONTRACT_GRANT: NCA2-594
Distribution Limits
Public
Copyright
Other

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