An actuator system (100) for controlling a flight surface of an aircraft (10) includes a first actuator (200) having a first actuator input and a first linear translation element that moves based on rotational motion received at the first actuator input and a first laser distance sensor (212) disposed inside the first actuator (200) that generates a first output based on a displacement of the first linear translation element. The system also includes a second actuator (202) having a second actuator input and a second linear translation element that moves based on rotational motion received at the second actuator input and a second laser distance sensor (214) disposed inside the second actuator (202) that generates a second output based on a displacement of the second linear translation element. 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.
LASER REFLECTION AERODYNAMIC CONTROL SURFACE MOVEMENT MONITORING SYSTEM
AERODYNAMISCHES LASER-REFLEXIONS-STEUERFLÄCHEN-BEWEGUNGSÜBERWACHUNGSSYSTEM
SYSTÈME DE SURVEILLANCE DE MOUVEMENT DE SURFACE DE COMMANDE AÉRODYNAMIQUE À RÉFLEXION LASER
26.02.2020
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
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