A wing for an aircraft includes: a main wing having an outer skin defining an interior space of the main wing, a slat, and a connection assembly for movably connecting the slat to the main wing, such that the slat is movable in a predefined motion between a retracted position and at least one extended position. The connection assembly includes an elongate and curved slat track, wherein a first end section of the slat track is connected to the slat, a first bearing at least partly arranged outside the interior space of the main wing, a second bearing spaced apart from the first bearing and arranged within the interior space of the main wing. The slat track is movably and rotatably supported on the main wing by the first and second bearing, such that the first and second bearing support the predefined motion.

A wing for an aircraft includes: a main wing having an outer skin defining an interior space of the main wing, a slat, and a connection assembly for movably connecting the slat to the main wing, such that the slat is movable in a predefined motion between a retracted position and at least one extended position. The connection assembly includes an elongate and curved slat track, wherein a first end section of the slat track is connected to the slat, a first bearing at least partly arranged outside the interior space of the main wing, a second bearing spaced apart from the first bearing and arranged within the interior space of the main wing. The slat track is movably and rotatably supported on the main wing by the first and second bearing, such that the first and second bearing support the predefined motion.

A wing assembly includes a swept wing body, a leading edge of the wing body extending outward and rearward from a wing root to a wing edge; a first slat selectively movably connected to the wing body; and a second slat selectively movably connected to the wing body, the second slat being disposed outboard of the first slat, a flexible sealing member disposed and connected between the first slat and the second slat; at least a portion of the first slat, at least a portion of the second slat, and at least a portion of the flexible sealing member defining a slat gap therebetween, at least a majority of the slat gap being substantially parallel to a predetermined local airflow direction. An aircraft is also disclosed which includes a fuselage; and two oppositely disposed wing assemblies connected to the fuselage.

A wing (5) for an aircraft (1) including a fixed wing (7), a high-lift device (15) and a hold-down arrangement (27) between two supports (23, 25) and having a first hold-down element (29) attached to the high-lift device (15) and a second hold-down element (31) attached to the fixed wing (7). The first hold-down element (29) contacts the second hold-down element (31) when the high-lift device (15) is in a retracted position to prevent a trailing edge (22) of the high-lift device (15) from detaching from an upper surface (19) of the fixed wing (7). One of the hold-down elements (29, 31) is a load-limited hold-down element (32) which is destroyed when loads transmitted through the hold down elements (29, 31) exceed a threshold. Once destroyed, the trailing edge (22) of the high-lift device (15) is not prevented from detaching from the upper surface (19).

A wing (5) for an aircraft (1) including a fixed wing (7), a high-lift device (15) and a hold-down arrangement (27) between two supports (23, 25) and having a first hold-down element (29) attached to the high-lift device (15) and a second hold-down element (31) attached to the fixed wing (7). The first hold-down element (29) contacts the second hold-down element (31) when the high-lift device (15) is in a retracted position to prevent a trailing edge (22) of the high-lift device (15) from detaching from an upper surface (19) of the fixed wing (7). One of the hold-down elements (29, 31) is a load-limited hold-down element (32) which is destroyed when loads transmitted through the hold down elements (29, 31) exceed a threshold. Once destroyed, the trailing edge (22) of the high-lift device (15) is not prevented from detaching from the upper surface (19).

Certain aspects of the present disclosure provide techniques for an aerodynamic surface actuation system, including: a plurality of outer tracks, wherein each outer track of the plurality of outer tracks includes: an inner outer roller channel; and an outer inner roller channel positioned above the inner outer roller channel; an aerodynamic surface connected to a carrier, wherein the carrier includes rollers configured to move within inboard inner roller channels of the plurality of outer tracks; and a plurality of fixed rollers mounted to one or more longitudinal structural elements in an aerodynamic structure, wherein the plurality of fixed rollers are disposed within the outer roller channels of the plurality of outer tracks.

Certain aspects of the present disclosure provide techniques for an aerodynamic surface actuation system, including: a plurality of outer tracks, wherein each outer track of the plurality of outer tracks includes: an inner outer roller channel; and an outer inner roller channel positioned above the inner outer roller channel; an aerodynamic surface connected to a carrier, wherein the carrier includes rollers configured to move within inboard inner roller channels of the plurality of outer tracks; and a plurality of fixed rollers mounted to one or more longitudinal structural elements in an aerodynamic structure, wherein the plurality of fixed rollers are disposed within the outer roller channels of the plurality of outer tracks.

Certain aspects of the present disclosure provide techniques for an aerodynamic surface actuation system, including: a middle track connected to an aerodynamic surface and configured to move along a plurality of intermediate tracks, wherein one or more inner surfaces of the middle track are configured to interface with one or more outer surfaces of the plurality of intermediate tracks; a plurality of outer tracks, each including a flange and configured to interface with one or more inner surfaces of the plurality of intermediate tracks; and an actuator configured to control a position of the middle track and a position of the plurality of intermediate tracks via a plurality of linkages.

Certain aspects of the present disclosure provide techniques for an aerodynamic surface actuation system, including: a plurality of outer tracks, wherein each outer track of the plurality of outer tracks include: an inner roller channel; and an outer roller channel positioned above the inner roller channel; an aerodynamic surface connected to a carrier, wherein the carrier includes: a plurality of rollers configured to move within inner roller channels of the plurality of outer tracks; and a carrier rack; a plurality of fixed rollers mounted to a plurality of longitudinal structural elements in an aerodynamic structure, wherein the plurality of fixed rollers are disposed within outer roller channels of the plurality of outer tracks; and a plurality of fixed racks, wherein each fixed rack of the plurality of fixed racks is mounted to a longitudinal structural element of the plurality of longitudinal structural elements.

Certain aspects of the present disclosure provide techniques for an aerodynamic surface actuation system, including: a plurality of outer tracks, wherein each outer track of the plurality of outer tracks includes: an inner outer roller channel; and an outer inner roller channel positioned above the inner outer roller channel; an aerodynamic surface connected to a carrier, wherein the carrier includes rollers configured to move within inboard inner roller channels of the plurality of outer tracks; and a plurality of fixed rollers mounted to one or more longitudinal structural elements in an aerodynamic structure, wherein the plurality of fixed rollers are disposed within the outer roller channels of the plurality of outer tracks.