HIGH SPEED TURN COORDINATION FOR ROTARY WING AIRCRAFT

A helicopter flight control system (21) includes a model following control system architecture which automatically provides a coordinating yaw command signal to the helicopter tail rotor to coordinate helicopter flight during a banked turn. The control system processes information from a variety of...

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Bibliographic Details
Main Authors SKONIECZNY, JOSEPH, P, FOGLER, DONALD, L., JR, KELLER, JAMES, F, GOLD, PHILIPP, J, DRYFOOS, JAMES, B
Format Patent
LanguageEnglish
Published 18.03.1993
Subjects
AEROPLANES
AIRCRAFT
AVIATION
CONTROLLING
COSMONAUTICS
HELICOPTERS
PERFORMING OPERATIONS
PHYSICS
REGULATING
SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
TRANSPORTING
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Summary:A helicopter flight control system (21) includes a model following control system architecture which automatically provides a coordinating yaw command signal to the helicopter tail rotor to coordinate helicopter flight during a banked turn. The control system processes information from a variety of helicopter sensors (31) in order to provide the coordinating yaw command signal on an output line (72) to the tail rotor (20) of the helicopter. Système (21) de commande de vol pour hélicoptère comportant une architecture de système de commande fondée sur un modèle qui fournit un signal coordinateur de commande de lacet au rotor arrière de l'hélicoptère afin de coordonner le vol de l'hélicoptère pendant un virage incliné. Ledit système de commande traite les informations provenant d'une série de capteurs (31) situés sur l'hélicoptère afin de fournir le signal de commande de lacet coordinateur sur une ligne de sortie (72) au rotor arrière (20) de l'hélicoptère.
Bibliography:Application Number: WO1992US06453