A wing component for an aircraft, comprising a leading edge part and a trailing edge part pivotably mounted to the leading edge part so as to pivot about a pivot axis, an actuator unit configured for moving the trailing edge part relative to the leading edge part, and a damper device configured for damping uncontrolled movement between the leading edge part and the trailing edge part. The trailing edge part comprises a first part portion and a second part portion arranged next to each other in a span direction and configured to pivot about the pivot axis individually, the damper device comprises a damping element coupled between the first part portion and the second part portion to damp relative movement of the first part portion and the second part portion.

A wing component for an aircraft, comprising a leading edge part and a trailing edge part pivotably mounted to the leading edge part so as to pivot about a pivot axis, an actuator unit configured for moving the trailing edge part relative to the leading edge part, and a damper device configured for damping uncontrolled movement between the leading edge part and the trailing edge part. The trailing edge part comprises a first part portion and a second part portion arranged next to each other in a span direction and configured to pivot about the pivot axis individually, the damper device comprises a damping element coupled between the first part portion and the second part portion to damp relative movement of the first part portion and the second part portion.

An aircraft wing with a moveable leading edge device mounted towards the leading edge of the wing is disclosed. The leading edge device is moveable between a first configuration and a second configuration. In the first configuration, the leading edge device is substantially flush with the low pressure surface. In the second configuration, the surface of the leading edge device is retracted into the wing profile. The second configuration creates a void in the lower surface of the wing which modifies the airflow over the surfaces. The oncoming airflow can enter the void. In the second configuration, the leading edge device reduces the lift on the wing, acting to reduce the lift induced strain on the wing during high speed flight or to help manoeuvre the wing. The leading edge device may also be configured to move into a third configuration.

An aircraft wing with a moveable leading edge device mounted towards the leading edge of the wing is disclosed. The leading edge device is moveable between a first configuration and a second configuration. In the first configuration, the leading edge device is substantially flush with the low pressure surface. In the second configuration, the surface of the leading edge device is retracted into the wing profile. The second configuration creates a void in the lower surface of the wing which modifies the airflow over the surfaces. The oncoming airflow can enter the void. In the second configuration, the leading edge device reduces the lift on the wing, acting to reduce the lift induced strain on the wing during high speed flight or to help manoeuvre the wing. The leading edge device may also be configured to move into a third configuration.

A trailing edge system for a wing of an aircraft comprises a flap device arrangement configured for being mounted at a trailing edge of an aircraft wing, wherein at least two movable flap devices of the flap device arrangement are spaced apart from each other. A torque element is connecting the movable flap devices for transmitting a torque to the movable flap devices in order to actuate a rotational movement of the movable flap devices. An actuator for rotationally driving the torque element is provided. Also a method of operating control surfaces of an aircraft wing and an aircraft and aircraft wing with such a system.

An air vehicle has a body, more than one wing located on the body creating a lifting force, at least one control surface located on the wing and movable along the direction in which the wing extends, an open position in which the control surface moves out of the wing in the direction in which the wing extends and increases the lifting force acting on the body, a closed position in which the control surface is moved from the open position and brought to the wing, a main actuator moving the control surface between the open and closed positions, at least one shaft enabling the control surface to be moved with the triggering of the main actuator and having one end connected to the control surface, and at least one additional actuator enabling the attack angle of the wings to be changed by rotating the wings on the body.

An air vehicle has a body, more than one wing located on the body creating a lifting force, at least one control surface located on the wing and movable along the direction in which the wing extends, an open position in which the control surface moves out of the wing in the direction in which the wing extends and increases the lifting force acting on the body, a closed position in which the control surface is moved from the open position and brought to the wing, a main actuator moving the control surface between the open and closed positions, at least one shaft enabling the control surface to be moved with the triggering of the main actuator and having one end connected to the control surface, and at least one additional actuator enabling the attack angle of the wings to be changed by rotating the wings on the body.

An apparatus for in-situ testing of a linear actuator configured to exert an actuation force in an actuation direction by movement of a first part of the actuator relative to a second part of the actuator. The apparatus includes a test device, a test actuator and a measurement device. The test device includes a first surface configured to contact the first part of the actuator, and a second surface configured to contact the second part of the actuator. The second surface is moveable relative to the first surface to alter a distance therebetween. The test actuator is configured to exert a test force in a direction opposite to the actuation direction, the test force being to drive movement of the second surface away from the first surface. The measurement device is for detecting a change in the distance between the first surface and the second surface.

An apparatus for in-situ testing of a linear actuator configured to exert an actuation force in an actuation direction by movement of a first part of the actuator relative to a second part of the actuator. The apparatus includes a test device, a test actuator and a measurement device. The test device includes a first surface configured to contact the first part of the actuator, and a second surface configured to contact the second part of the actuator. The second surface is moveable relative to the first surface to alter a distance therebetween. The test actuator is configured to exert a test force in a direction opposite to the actuation direction, the test force being to drive movement of the second surface away from the first surface. The measurement device is for detecting a change in the distance between the first surface and the second surface.

An actuator assembly includes an actuator drive source and a gust lock. The actuator drive source is operable to supply an actuator drive torque to drive a component. The gust lock is movable between a locked position, in which rotation of the drive source is prevented, and an unlocked position, in which rotation of the drive source is not prevented. The gust lock includes a lock shaft, a lock rotor, a lock motor, and a linear actuator. The lock shaft is rotatable with the drive source when the gust lock is in the unlocked position. The lock rotor is rotatable with the lock shaft. The lock motor is configured to supply a lock drive torque. The linear actuator is coupled to receive the lock drive torque and is configured, upon receipt of the lock drive torque, to move between an engaged position and a disengaged position.