A flight control system (100, 200) for a flight control surface (102) includes a first actuator control electronics (ACE) (202), a second ACE (204), a third ACE (206), a first remote electronics unit (REU) (208), and a second REU (210). The first ACE (202) is configured to generate a first control signal for the flight control surface (102). The second ACE (204) is configured to generate a second control signal for the flight control surface (102). The third ACE (206) is configured to generate a third control signal for the flight control surface (102). The first REU (208) is coupled to the first ACE (202) and the second ACE (204), and configured to operate, based on the first control signal and the second control signal, an actuator (216, 220) coupled to the flight control surface (102). The second REU (210) is coupled to the second ACE (204) and the third ACE (206), and configured to operate, based on the second control signal and the third control signal, the actuator (216, 220).
REDUNDANT FLIGHT CONTROL SYSTEM AND METHOD OF USE
REDUNDANTES FLUGSTEUERUNGSSYSTEM UND VERFAHREN ZUR VERWENDUNG
SYSTÈME DE COMMANDE DE VOL REDONDANT ET PROCÉDÉ D'UTILISATION
2020-06-03
Patent
Elektronische Ressource
Englisch
TERMINOLOGY FOR REDUNDANT FLIGHT CONTROL SYSTEMS
SAE Technical Papers | 1971
Lockheed L-1101 avionic flight control redundant systems
NTRS | 1976
|