An aircraft assembly is disclosed having a cover with an outer aerodynamic surface and an aperture with a stop adjacent an edge of the aperture, and a moveable device for extending through the aperture in the cover. The moveable device carries a panel attached to the moveable device by a plurality of leaf springs. The assembly is configured so that when the moveable device is moved towards a retracted position the panel bears against the stop forming a substantially flush surface with the outer aerodynamic surface of the cover surrounding the aperture. The panel is displaced from the moveable device by elastic deformation of at least some of the leaf springs.

An aircraft assembly is disclosed having a cover with an outer aerodynamic surface and an aperture with a stop adjacent an edge of the aperture, and a moveable device for extending through the aperture in the cover. The moveable device carries a panel attached to the moveable device by a plurality of leaf springs. The assembly is configured so that when the moveable device is moved towards a retracted position the panel bears against the stop forming a substantially flush surface with the outer aerodynamic surface of the cover surrounding the aperture. The panel is displaced from the moveable device by elastic deformation of at least some of the leaf springs.

Aircraft and associated methods, apparatus, system and storage devices for automatically positioning of lift control devices such as high lift devices including slats and flaps so an aircraft equipped with this technology will not need to count on the crew to command the lift control devices.

Integrated slat chine apparatus and methods are described. An example apparatus includes a chine and a slat. The chine is coupled to an airfoil. The chine includes a lateral surface. The slat is located adjacent the lateral surface of the chine and coupled to the airfoil. The slat is movable relative to the airfoil between a stowed position and a deployed position. The slat is to expose the lateral surface of the chine when the slat is in the deployed position and to cover the lateral surface of the chine when the slat is in the stowed position.

An airfoil blade assembly including a blade which includes a lift generating section with a first profiled body defined between a pressure surface and a suction surface. The first profiled body extends from a first leading edge to a first trailing edge with a first chord extending form the first leading edge to the first trailing edge and being perpendicular to the radial direction. At least one flow deflector extends along either the pressure surface or the suction surface within the lift generating section of the blade. The at least one flow deflector defines a second profiled body extending between a second leading edge and a second trailing edge with a second chord extending between the second leading edge and the second trailing edge. The second profiled body defines an outer surface facing away from respective pressure surface or suction surface along which the flow deflector extends.

An airfoil blade assembly including a blade which includes a lift generating section with a first profiled body defined between a pressure surface and a suction surface. The first profiled body extends from a first leading edge to a first trailing edge with a first chord extending form the first leading edge to the first trailing edge and being perpendicular to the radial direction. At least one flow deflector extends along either the pressure surface or the suction surface within the lift generating section of the blade. The at least one flow deflector defines a second profiled body extending between a second leading edge and a second trailing edge with a second chord extending between the second leading edge and the second trailing edge. The second profiled body defines an outer surface facing away from respective pressure surface or suction surface along which the flow deflector extends.

An aircraft (1) having a wing (3) and a wing tip device (4) at the tip of the wing (3), the wing tip device (4) having front and rear spars (14, 13), wherein the wing tip device (4) has a cross-brace spar (18) that links the front and rear spars and is oriented such that it is oblique to the front and rear spars (14, 13).

An aircraft (1) having a wing (3) and a wing tip device (4) at the tip of the wing (3), the wing tip device (4) having front and rear spars (14, 13), wherein the wing tip device (4) has a cross-brace spar (18) that links the front and rear spars and is oriented such that it is oblique to the front and rear spars (14, 13).

A wingless vertical take-off and landing (VTOL) vehicle has a main body including airfoil sections on either side of a central module in which a load may be carried. Articulated forward thrust systems are mounted on a leading edge of the main body and lateral members are located on either side of the main body and form winglets. At least one rear vertical-thrust system may also be provided and, in one embodiment, is mounted in an aperture aft of the central module. The forward thrust systems transition between a vertical flight configuration and a horizontal flight configuration. The lateral members are configured as both vortex-damping members and also to channel backwash from the forward thrust systems over the airfoil formed by the main body.

An aircraft (1) having a wing (3) and a wing tip device (4) at the tip of the wing (3), wherein the wing tip device (4) includes a rib (16) positioned in a span wise region (C) of the wing tip device (4) in which transonic flow occurs when the aircraft (1) is in flight. A method of designing an aircraft (1) including predicting where transonic flow occurs on the wing tip device (4) when the aircraft (1) is in flight, and designing the wing tip device (4) with a rib (16) positioned in the span wise region (C) of the wing tip device (4) in which the predicted transonic flow occurs.