An actuator system (100) for controlling a flight surface (24, 26) of an aircraft (10) includes a first actuator (200; 300) having a first actuator input (204; 310) and a first linear translation element (208; 304) that moves based on rotational motion received at the first actuator input (204; 310) and a first sensor (212; 308) coupled to the first linear translation element (208; 304) that generates a first output based on a displacement of the first linear translation element (208; 304). The system also includes a second actuator (202; 300) having a second actuator input (206; 310) and a second linear translation element (210; 304) that moves based on rotational motion received at the second actuator input (206; 310) and a second sensor (214; 308) coupled to the second linear translation element (210; 304) that generates a second output based on a displacement of the second linear translation element (210; 304). The system also includes a control unit (102) that receives the first and second outputs and determines if an error condition exists for the system based on first and second output.
AERODYNAMIC CONTROL SURFACE MOVEMENT MONITORING SYSTEM
AERODYNAMISCHES STEUERFLÄCHENBEWEGUNGS-ÜBERWACHUNGSSYSTEM
SYSTÈME DE SURVEILLANCE DE MOUVEMENT DE SURFACE DE COMMANDE AÉRODYNAMIQUE
2018-12-12
Patent
Electronic Resource
English
LASER REFLECTION AERODYNAMIC CONTROL SURFACE MOVEMENT MONITORING SYSTEM
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