Actuator systems and methods for controlling aerodynamic control surfaces of aircraft including a first actuator (226) receiving a first input and a first linear translation element (232) that moves based thereon, the first linear translation element operably connected to a first portion of the control surface. A first sensor assembly (238) is disposed relative to the first actuator that generates an output based on a displacement of the first translation element. A second actuator (228) receives a second input and a second linear translation element (236) moves based on the second input, the second linear translation element operably connected to a second portion of the control surface. A second sensor assembly (240) is disposed relative to the second actuator that generates a second sensor output based on a displacement of the second translation element. A controller (218) generates the inputs and receives the sensor outputs to determine if an error condition exists for the system.
AERODYNAMIC CONTROL SURFACE MOVEMENT MONITORING SYSTEM FOR AIRCRAFT
SYSTEM ZUR ÜBERWACHUNG DER AERODYNAMISCHEN STEUERFLÄCHENBEWEGUNG FÜR FLUGZEUGE
SYSTÈME DE SURVEILLANCE DE MOUVEMENT DE SURFACE DE COMMANDE AÉRODYNAMIQUE D'AÉRONEF
2021-12-29
Patent
Electronic Resource
English
AERODYNAMIC CONTROL SURFACE MOVEMENT MONITORING SYSTEM FOR AIRCRAFT
European Patent Office | 2018
|Aerodynamic control surface movement monitoring system for aircraft
European Patent Office | 2019
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