Goodrich Actuation Systems Sas

Laurent Schwartz

Arnaud De La Chevasnerie

Jerome Socheleau

Jérôme Socheleau

A system for controlling an electromechanical actuator of an aircraft includes a locking device configured to mechanically lock said actuator in a first fixed position and to mechanically unlock said actuator from said first fixed position and a controller configured to be in bi-directional communication with both said locking device and said actuator. The controller is configured to monitor a position of said actuator during flight and to detect when said actuator has not moved for a set amount of time, said controller further being configured to instruct said locking device to lock said actuator in said first, locked position when said set time has been reached. In addition, there is provided a method for controlling the thermal properties of an electromechanical actuator of an aircraft.

EMA thermal management optimization

A connecting rod assembly for a flight control surface actuation system, the assembly comprising a connecting rod for connecting a flight control surface to a rotary actuator and a position sensor mounted to the connecting rod for sensing the position of the connecting rod relative to a rotary actuator.

Connecting rod for a flight control surface actuation system

An actuator drive disconnection system comprises a housing and a drive coupling mounted in the housing, the drive coupling coupling a drive motor to an actuator drive train. A manually operable drive disconnection mechanism selectively moves the drive coupling from a first position in which the motor and actuator drive train are coupled and a second position in which the motor and actuator drive train are disconnected. The drive disconnection mechanism comprises an operating element which is manually extended from the housing to move the drive coupling from the first position to the second position.

Actuator drive disconnection system

A rotary actuator for controlling a flight control surface and a flight control surface actuation assembly including the rotary actuator. The actuator comprises a rotary output shaft for driving a flight control surface, a locking mechanism for selectively preventing rotation of the rotary output shaft and a torque limiter for allowing the locking mechanism to be bypassed upon the locking mechanism experiencing a torque above a predetermined limit.

Rotary actuator for controlling a flight control surface

An actuator including a pair of load sensors arranged in the load path through the actuator. The load sensors are antagonistically preloaded and their outputs electrically connected to a processor for calculating a load in the actuator from the difference in loads measured by the respective load sensors.

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Orsay, France

Laurent Schwartz