A control method and system for controlling a main rotor of a rotorcraft to perform a stage of flight in auto-rotation. The control system has a control member for controlling the collective pitch of the blades of the main rotor. The control member is movable over an amplitude of positions between two extreme physical stops. A calculation unit calculates a collective pitch angle for the blades of the main rotor, referred to as an “auto-rotation collective pitch”. This enables the main rotor to rotate at a speed of rotation that is optimum for the stage of flight in auto-rotation of the rotorcraft. A motor means controls the position of the control member at a predetermined position, referred to as the “auto-rotation position”, in which the control member generates a control setpoint for servo-controlling the current collective pitch of the blades of the main rotor on the “auto-rotation collective pitch”.
PROCEDE DE COMMANDE D'UN ROTOR PRINCIPAL DE GIRAVION, SYSTEME DE COMMANDE ASSOCIE ET GIRAVION EQUIPE D'UN TEL SYSTEME DE COMMANDE
A METHOD OF CONTROLLING A MAIN ROTOR OF A ROTORCRAFT, AN ASSOCIATED CONTROL SYSTEM, AND A ROTORCRAFT FITTED WITH SUCH A CONTROL SYSTEM
STEUERUNGSVERFAHREN EINES HAUPTROTORS EINES DREHFLÜGELFLUGZEUGS, ENTSPRECHENDES STEUERUNGSSYSTEM UND DREHFLÜGELFLUGZEUG, DAS MIT EINEM SOLCHEN STEUERUNGSSYSTEM AUSGESTATTET IST
2018-04-18
Patent
Electronic Resource
French
IPC: | B64C AEROPLANES , Flugzeuge |
European Patent Office | 2017
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