An aircraft (5) including a wing (3) and a winglet (1) at the end of the wing, the winglet including: a root (7); a tip (9); a transition region (11) extending away from the root; and a wing-like region (13) extending from the distal end of the transition region to the tip. When the aircraft wing (3) is under the worst-case static loading, the tip of the winglet is located at the maximum spanwise extent of the winglet (1), but when the aircraft wing (3) is under the no-load condition, the wing-like region (13) is canted inboard such that the tip (9) of the winglet (1) is located inboard of the maximum spanwise extent of the winglet.

A powered aerodynamic lift device positioned on a leading edge of an aerodynamic lifting element (ALE), e.g. an airfoil, at least one slat/nacelle/EDF lift assembly comprising: a slat, a two or more nacelles positioned beneath the slat, each nacelle housing an electric ducted fan (EDF). The nacelles are spaced apart to create gaps between the slat and the airfoil for accelerated air to pass through. The lift assembly is under the operational control of and/or further comprises: a master control unit linked to a power source, e.g. batteries to power the EDFs. The device provides the ALE and aircraft with: increased lift and additional thrust during aircraft take offs, climbs, descents, and landings; enhanced low-speed control and reduced loss-of-control during an aircraft's takeoff and landing; improved aircraft handling during gusts and crosswinds. The present invention also comprises an ALE or aircraft with at least one lift assembly installed thereon.

A wing tip device for fixing to the outboard end of a wing, the wing defining a wing plane, the wing tip device comprising: an upper wing-like element projecting upwardly with respect to the wing plane and having a trailing edge; and a lower wing-like element fixed with respect to the upper wing-like element and having a root chord and a trailing edge, the lower wing-like element root chord intersecting with the upper wing-like element, and the lower wing-like element projecting downwardly from the intersection, wherein the upper wing-like element is larger than the lower wing-like element and the trailing edge of the lower wing-like element is adjacent the trailing edge of the upper wing-like element at the intersection, and wherein an included angle between the upper and lower wing-like elements at the intersection is less than, or equal to, 160 degrees. Also, a wing with the wing tip device; an aircraft with the wing; a method of fitting, or retro-fitting, the wing tip device to a wing; a method of modifying an existing wing tip device; and a method of operating a wing with the wing tip device.

A wing tip device for fixing to the outboard end of a wing, the wing defining a wing plane, the wing tip device comprising: an upper wing-like element projecting upwardly with respect to the wing plane and having a trailing edge; and a lower wing-like element fixed with respect to the upper wing-like element and having a root chord and a trailing edge, the lower wing-like element root chord intersecting with the upper wing-like element, and the lower wing-like element projecting downwardly from the intersection, wherein the upper wing-like element is larger than the lower wing-like element and the trailing edge of the lower wing-like element is adjacent the trailing edge of the upper wing-like element at the intersection, and wherein an included angle between the upper and lower wing-like elements at the intersection is less than, or equal to, 160 degrees. Also, a wing with the wing tip device; an aircraft with the wing; a method of fitting, or retro-fitting, the wing tip device to a wing; a method of modifying an existing wing tip device; and a method of operating a wing with the wing tip device.

A folding wing having a wing tip device (3) rotatable between flight and ground configurations, about an Euler axis of rotation (11). The wing tip device (3) and a fixed wing (1) are separated along an oblique cut plane (13) passing through the upper and lower surfaces of the folding wing. A rotational joint (15) for coupling the wing tip device (3) to the fixed wing (1) during rotation between the ground and flight configurations. The rotational joint includes a follower (17a) and a guide (17b), one which being fixed relative to the wing tip device and the other being fixed relative to the fixed wing. The follower and guide interlock such as by interlocking rings. The follower is received in the guide such that during rotation between the ground and flight configurations the follower moves along the arcuate path defined by the guide.

Airflow-dependent deployable fences for aircraft wings are described. An example apparatus includes a fence coupled to a wing of an aircraft. The fence is movable relative to the wing between a stowed position in which a panel of the fence extends along a skin of the wing, and a deployed position in which the panel extends at an upward angle away from the skin. The panel is configured to impede a spanwise airflow along the wing when the fence is in the deployed position. The fence is configured to move from the stowed position to the deployed position in response to an aerodynamic force exerted on a deployment vane of the fence.

Airflow-dependent deployable fences for aircraft wings are described. An example apparatus includes a fence coupled to a wing of an aircraft. The fence is movable relative to the wing between a stowed position in which a panel of the fence extends along a skin of the wing, and a deployed position in which the panel extends at an upward angle away from the skin. The panel is configured to impede a spanwise airflow along the wing when the fence is in the deployed position. The fence is configured to move from the stowed position to the deployed position in response to an aerodynamic force exerted on a deployment vane of the fence.

Automated deployable fences for aircraft wings are described. An example apparatus includes a fence, a latching actuator, and a biasing actuator. The fence is coupled to a wing of an aircraft. The fence is movable relative to the wing between a stowed position in which a panel of the fence extends along a skin of the wing, and a deployed position in which the panel extends at an upward angle away from the skin. The panel impedes a spanwise airflow along the wing when the fence is in the deployed position. The latching actuator is movable between a first position in which the latching actuator maintains the fence in the stowed position, and a second position in which the latching actuator releases the fence from the stowed position. The latching actuator moves from the first position to the second position in response to a control signal received at the latching actuator. The biasing actuator moves the fence from the stowed position to the deployed position in response to the latching actuator moving from the first position to the second position.

Automated deployable fences for aircraft wings are described. An example apparatus includes a fence, a latching actuator, and a biasing actuator. The fence is coupled to a wing of an aircraft. The fence is movable relative to the wing between a stowed position in which a panel of the fence extends along a skin of the wing, and a deployed position in which the panel extends at an upward angle away from the skin. The panel impedes a spanwise airflow along the wing when the fence is in the deployed position. The latching actuator is movable between a first position in which the latching actuator maintains the fence in the stowed position, and a second position in which the latching actuator releases the fence from the stowed position. The latching actuator moves from the first position to the second position in response to a control signal received at the latching actuator. The biasing actuator moves the fence from the stowed position to the deployed position in response to the latching actuator moving from the first position to the second position.

Aircraft, auto speed brake control systems, and methods for controlling drag of an aircraft are provided. In one example, an aircraft includes an aircraft structure. A drag device is operatively coupled to the aircraft structure between a stowed and a deployed position and/or an intermediate deployed position. A speed brake controller is in communication with the drag device to control movement. An autothrottle-autospeedbrake controller is in communication with the speed brake controller and is configured to receive data signals. The autothrottle-autospeedbrake controller is operative to direct the speed brake controller to control movement of the drag device between the stowed position and the deployed position and/or the intermediate deployed position in response to at least one of the data signals.