A motor assembly, control system and associated method monitor the rotational engagement of an input shaft associated with a motor with an output shaft configured to controllably position a control surface. In this regard, a control system includes a motor assembly and an associated controller. The motor assembly includes a motor configured to rotate an input shaft and a first encoder configured to determine a rotational position of the input shaft. The motor assembly also includes an output shaft, such as a capstan, and a second encoder configured to determine a rotational position of the output shaft. The output shaft is rotatably coupled to the input shaft associated with the motor via a clutch. The controller is configured to identify slippage of the clutch based upon information provided by the first and second encoders regarding the rotational positions of the input shaft and the output shaft, respectively.

A brake rod for a steering/braking mechanism includes a rod body having a longitudinal axis, a rod end at a first end of the rod body, the rod end having a bore therethrough having a bore axis arranged generally perpendicular to the rod longitudinal axis, and a rod end shield mounted to the rod and extending in a longitudinal direction axially beyond the rod end.

A brake rod for a steering/braking mechanism includes a rod body having a longitudinal axis, a rod end at a first end of the rod body, the rod end having a bore therethrough having a bore axis arranged generally perpendicular to the rod longitudinal axis, and a rod end shield mounted to the rod and extending in a longitudinal direction axially beyond the rod end.

A wing stall compensation mechanism employs an upper door having forward upper hinge end pivotally coupled to an upper wing structure for rotation about an upper axis and a free aft upper end. A lower door has a free aft lower end and a forward lower hinge end pivotally coupled to a lower wing structure for rotation about a lower axis and a 2-bar coupler linkage is disposed between and pivotally coupled to the upper door and lower door. Downward rotation of the upper door in response to wing surface airflow separation causes contraction of the coupler linkage inducing upward rotation of the lower door from a closed position that inhibits airflow through a flap slot to an open position that enables airflow through the flap slot, to thereby restore wing surface airflow effectiveness.

A wing stall compensation mechanism employs an upper door having forward upper hinge end pivotally coupled to an upper wing structure for rotation about an upper axis and a free aft upper end. A lower door has a free aft lower end and a forward lower hinge end pivotally coupled to a lower wing structure for rotation about a lower axis and a 2-bar coupler linkage is disposed between and pivotally coupled to the upper door and lower door. Downward rotation of the upper door in response to wing surface airflow separation causes contraction of the coupler linkage inducing upward rotation of the lower door from a closed position that inhibits airflow through a flap slot to an open position that enables airflow through the flap slot, to thereby restore wing surface airflow effectiveness.

An actuation device for a thrust reverser includes thrust-reversal movable elements carried by a nacelle and displaceable between a retracted and deployed position. The actuating device includes two actuators mounted on the nacelle and connected to a motor and to the movable elements. The actuation device drives the movable elements in a retraction or deployment direction over a course of the actuators between the retracted and deployed position. The actuation device further includes locks for locking the movable elements in the retracted position and antideployment members associated with the actuators which allow free operation of the actuators in the direction of retraction and retain the actuators in the direction of deployment. The antideployment bodies further provide free operation of the actuators in the direction of deployment over part of the actuators stroke that corresponds to a shift from an over-retraction position to the retraction position of the movable elements.

An actuation device for a thrust reverser includes thrust-reversal movable elements carried by a nacelle and displaceable between a retracted and deployed position. The actuating device includes two actuators mounted on the nacelle and connected to a motor and to the movable elements. The actuation device drives the movable elements in a retraction or deployment direction over a course of the actuators between the retracted and deployed position. The actuation device further includes locks for locking the movable elements in the retracted position and antideployment members associated with the actuators which allow free operation of the actuators in the direction of retraction and retain the actuators in the direction of deployment. The antideployment bodies further provide free operation of the actuators in the direction of deployment over part of the actuators stroke that corresponds to a shift from an over-retraction position to the retraction position of the movable elements.

A wing for an aircraft having a fixed wing, a foldable wing tip portion rotatably attached to the fixed wing and an actuation unit for rotating the foldable wing tip portion relative to the fixed wing about a hinge axis is disclosed. The actuation unit includes a traction means for transmitting traction between the fixed wing and the foldable wing tip portion, a main wheel attached to the foldable wing tip portion and in contact with the traction means and a drive means for generating traction to be transmitted by the traction means. The actuation unit generates traction with the drive means in the traction means so that the foldable wing tip portion can be rotated relative to the fixed wing.

A wing for an aircraft having a fixed wing, a foldable wing tip portion rotatably attached to the fixed wing and an actuation unit for rotating the foldable wing tip portion relative to the fixed wing about a hinge axis is disclosed. The actuation unit includes a traction means for transmitting traction between the fixed wing and the foldable wing tip portion, a main wheel attached to the foldable wing tip portion and in contact with the traction means and a drive means for generating traction to be transmitted by the traction means. The actuation unit generates traction with the drive means in the traction means so that the foldable wing tip portion can be rotated relative to the fixed wing.

A spoiler for an aircraft wing is movable between a stowed configuration and a deployed configuration in a “pop-up” manner. The spoiler includes a hinged top flap movable between a first position and a second position, wherein in the first position the hinged top flap is constrained by an actuator, and in the second position the hinged top flap is unconstrained by the actuator. When the hinged top flap is in the second position, airflow over the top surface of the aircraft wing acts to pull the spoiler into the deployed position.