An aircraft wing is provided with a positionally fixed closure fairing to close a cut-out opening in the leading edge of the wing associated with a wing leading edge slat so as to direct incident airflow to the wing leading edge from a lower surface of the aircraft wing to an upper surface of the aircraft wing.

A wing leading edge device includes a flow body having a front side, which is delimited by a first spanwise edge and a second spanwise edge, a back side, which is delimited by the first spanwise edge and the second spanwise edge, a front skin arranged on the front side, a back skin arranged on the back side, and at least one stiffening arrangement between the front skin and the back skin in the region of the first spanwise edge, wherein the front skin extends continuously and free from interruptions between the first spanwise edge and the second spanwise edge and covers the at least one stiffening arrangement.

A wing leading edge device includes a flow body having a front side, which is delimited by a first spanwise edge and a second spanwise edge, a back side, which is delimited by the first spanwise edge and the second spanwise edge, a front skin arranged on the front side, a back skin arranged on the back side, and at least one stiffening arrangement between the front skin and the back skin in the region of the first spanwise edge, wherein the front skin extends continuously and free from interruptions between the first spanwise edge and the second spanwise edge and covers the at least one stiffening arrangement.

A slat control system for an aircraft may include a flight control computer configured to generate a gap command in response to an occurrence of a gap-command condition. The slat control system may further include an edge control system including an edge control device having a plurality of control device positions including at least one designated control device position. The slat control system may additionally include a device actuation system configured to move a leading edge device of an aircraft. The edge control system may be configured to automatically command the device actuation system to extend the leading edge device from a sealed position to a gapped position when the edge control device is in the designated control device position and the gap command is received by the edge control system.

A slat control system for an aircraft may include a flight control computer configured to generate a gap command in response to an occurrence of a gap-command condition. The slat control system may further include an edge control system including an edge control device having a plurality of control device positions including at least one designated control device position. The slat control system may additionally include a device actuation system configured to move a leading edge device of an aircraft. The edge control system may be configured to automatically command the device actuation system to extend the leading edge device from a sealed position to a gapped position when the edge control device is in the designated control device position and the gap command is received by the edge control system.

An aerodynamic structure for use on an upper surface of an aircraft wing is disclosed. The wing includes a slat operable between a stowed configuration in which the slat is stowed in a slat recess of the wing, and a deployed configuration in which the slat extends out of the slat recess. When the slat is in the deployed configuration, an end face of the slat recess is exposed, the end face intersecting with the upper surface of the wing at a recess edge. The aerodynamic structure, adjacent to the recess edge, has a volume shaped to encourage air flowing over the recess edge onto the upper surface during flight, to remain attached.

A motionless skew detection system for an aircraft is disclosed, and includes a flight control surface of an aircraft wing, two drive mechanisms for operating the flight control surface, a first load sensor and a second load sensor for each of the two drive mechanisms, and a control module. Each of the two drive mechanisms are located on opposing sides of the flight control surface and each of the two drive mechanisms include at least a first linkage including a first outer surface and a second linkage including a second outer surface. The first load sensor is disposed along the first outer surface of the first linkage and the second load sensor is disposed along the second outer surface of the second linkage. The control module is in signal communication with the first load sensor and the second load sensor of each drive mechanism.

A wing for an aircraft is disclosed including a main wing, a slat, and a connection assembly movable connecting the slat to the main wing. The connection assembly includes an elongate slat track, wherein the front end of the slat track is mounted to the slat, wherein the rear end and the intermediate portion of the slat track are mounted to the main wing by a roller bearing including a guide rail mounted to the main wing and a first roller unit mounted to the rear end of the slat track and engaging the guide rail. The roller bearing includes a second roller unit mounted to the main wing and engaging an engagement surface at the intermediate portion of the slat track

A wing for an aircraft is disclosed having a main wing, a slat, and a connection assembly movable connecting the slat to the main wing, wherein the connection assembly includes an elongate slat track, wherein the front end of the slat track is mounted to the slat, wherein the rear end and the intermediate portion of the slat track are mounted to the main wing by a roller bearing comprising a guide rail mounted to the main wing and a first roller unit mounted to the rear end of the slat track and engaging the guide rail, and wherein the roller bearing includes a second roller unit mounted to the main wing and engaging an engagement surface at the intermediate portion of the slat track.

A wing for an aircraft is disclosed having a main wing, a slat, and a connection assembly movable connecting the slat to the main wing, wherein the connection assembly includes an elongate slat track, wherein the front end of the slat track is mounted to the slat, wherein the rear end and the intermediate portion of the slat track are mounted to the main wing by a roller bearing comprising a guide rail mounted to the main wing and a first roller unit mounted to the rear end of the slat track and engaging the guide rail, and wherein the roller bearing includes a second roller unit mounted to the main wing and engaging an engagement surface at the intermediate portion of the slat track.