A wing for an aircraft, comprising a main wing and a slat assembly with a slat and a connection assembly with a slat track. The front end of the slat track is mounted to the slat, and the rear end and/or the intermediate portion of the slat track are mounted to the main wing by a roller or slide bearing. The slat track is movable along the track longitudinal axis. The connection assembly includes a drive unit. The drive unit includes a rotary actuator mounted to the main wing and having at least one drive arm rotatably driven about a rotation axis and drivingly engaging the slat track, and one of the drive arm and the slat track has at least one groove and the other one of the drive arm and the slat track comprises at least one spigot drivingly engaging the groove.

A wing for an aircraft, comprising a main wing and a slat assembly with a slat and a connection assembly with a slat track. The front end of the slat track is mounted to the slat, and the rear end and/or the intermediate portion of the slat track are mounted to the main wing by a roller or slide bearing. The slat track is movable along the track longitudinal axis. The connection assembly includes a drive unit. The drive unit includes a rotary actuator mounted to the main wing and having at least one drive arm rotatably driven about a rotation axis and drivingly engaging the slat track, and one of the drive arm and the slat track has at least one groove and the other one of the drive arm and the slat track comprises at least one spigot drivingly engaging the groove.

Flap actuation systems for aircraft are described herein. An example flap actuation system includes a fixed beam coupled to and extending downward from a fixed wing portion of an aircraft wing and a rocking lever plate pivotably coupled to the fixed beam. The rocking lever plate is coupled to a forward end of a flap bracket disposed on a bottom side of a flap of the wing. The flap actuation system also includes a crank arm, a crank rod coupled between the crank arm and the rocking lever plate, and a flap link coupled between the rocking lever plate and an aft end of the flap bracket, such that actuation of the crank arm pivots the rocking lever plate to move the flap between a stowed position and a deployed position relative to the fixed wing portion.

Flap actuation systems for aircraft are described herein. An example flap actuation system includes a fixed beam coupled to and extending downward from a fixed wing portion of an aircraft wing and a rocking lever plate pivotably coupled to the fixed beam. The rocking lever plate is coupled to a forward end of a flap bracket disposed on a bottom side of a flap of the wing. The flap actuation system also includes a crank arm, a crank rod coupled between the crank arm and the rocking lever plate, and a flap link coupled between the rocking lever plate and an aft end of the flap bracket, such that actuation of the crank arm pivots the rocking lever plate to move the flap between a stowed position and a deployed position relative to the fixed wing portion.

The present disclosure relates to a flight control device that can be mounted to a body of a wing of an aircraft to reduce or eliminate backlash in electromechanical actuators (EMAs). The flight control device can include a flight control member and first and second actuators for moving the flight control member relative to the wing of the aircraft. The first and second actuators can be mechanically isolated from one another except for their mutual connection to the flight control member. The first and second actuators can cooperate to apply torsional loading to the flight control member about an axis of the flight control member to reduce or eliminate backlash.

The present disclosure relates to a flight control device that can be mounted to a body of a wing of an aircraft to reduce or eliminate backlash in electromechanical actuators (EMAs). The flight control device can include a flight control member and first and second actuators for moving the flight control member relative to the wing of the aircraft. The first and second actuators can be mechanically isolated from one another except for their mutual connection to the flight control member. The first and second actuators can cooperate to apply torsional loading to the flight control member about an axis of the flight control member to reduce or eliminate backlash.

A flap actuation mechanism incorporates a coupler rod eccentrically supported at an aft end and at a forward end. The coupler rod is configured to translate from an aft position to a forward position. An inboard crank arm is coupled to the rotary actuator and engaged to the aft end of the coupler rod. The inboard crank is configured rotate responsive to rotation of the rotary actuator thereby inducing translation of the coupler rod. An outboard crank arm engaged to a forward end of the coupler rod and is configured to rotate responsive to translation of the coupler rod. A flap drive arm is attached to the outboard crank arm and is configured to rotate with the outboard crank arm from a stowed position to a deployed position responsive to translation of the coupler rod from the aft position to the forward position.

A flap support mechanism includes a track rotatably connected to an aft fitting of a wing. A forward roller and an aft roller extend laterally from a flap structure, the forward roller and aft roller constrained in a slot in the track. The slot has a profile configured to induce both translation and rotation in the flap, in concert with rotation of the track about the aft fitting, thereby passively mirroring motion of the flap induced by an actuator driven primary main flap support.

A flap support mechanism includes a track rotatably connected to an aft fitting of a wing. A forward roller and an aft roller extend laterally from a flap structure, the forward roller and aft roller constrained in a slot in the track. The slot has a profile configured to induce both translation and rotation in the flap, in concert with rotation of the track about the aft fitting, thereby passively mirroring motion of the flap induced by an actuator driven primary main flap support.

Example aircraft spoiler actuation systems and related methods are disclosed herein. An example spoiler actuation system includes a rotary actuator, a first output shaft coupled to the rotary actuator, a second output shaft coupled to the rotary actuator, the first output shaft opposite the second output shaft, a first actuator rod coupled to the spoiler at a first location, and a second actuator rod coupled to the spoiler at a second location, the second location spaced apart from the first location. The rotary actuator is operatively coupled to the first actuator rod via the first output shaft and to the second actuator rod via the second output shaft to cause the spoiler to move between one of a stowed position and a raised position or the stowed position and a drooped position.