An aircraft hybrid flight control system comprising a manual control element (C), a mechanical transmission (11) interposed between the manual control element (C) and a control surface (S), an electromechanical actuator (12; 101) and a coupling unit (16; 28, 42; 108, 111) configured to connect selectively the control surface (S) to the mechanical transmission (11) in a manual control mode and to the electromechanical actuator (12; 101) in a fly-by-wire control mode; the coupling unit (16; 28, 42; 108, 111) is configured to maintain the mechanical transmission (11) in a condition of substantial continuity with said control surface (S) even in fly-by-wire mode, but for a freedom of relative motion of pre-set amplitude.
AIRCRAFT HYBRID FLIGHT CONTROL SYSTEM
HYBRIDES FLUGZEUGFLUGSTEUERUNGSSYSTEM
SYSTÈME DE COMMANDE DE VOL HYBRIDE D'AÉRONEF
04.07.2018
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |