Abstract: An Unmanned Aerial System configured to receive a request from a user and fulfill that request using an Unmanned Aerial Vehicle. The Unmanned Aerial System selects a distribution center that is within range of the user, and deploys a suitable Unmanned Aerial Vehicle to fulfill the request from that distribution center. The Unmanned Aerial System is configured to provide real-time information about the flight route to the Unmanned Aerial Vehicle during its flight, and the Unmanned Aerial Vehicle is configured to dynamically update its mission based on information received from the Unmanned Aerial System.

Abstract: A method of manufacturing an aerodynamic structure, for example, an aircraft wing tip, is disclosed. The method includes providing an upper cover having a plurality of lugs, providing a lower cover having a plurality of lugs, measuring the distance between a lug on the upper cover and corresponding lug on the lower cover, selecting, from the plurality of different sized links, a link suitably sized to correspond to the measured distance between the lug on the upper cover and corresponding lug on the lower cover, connecting the selected link to the lug on the upper cover and corresponding lug on the lower cover; and repeating those steps such that each lug on the upper cover is joined to a corresponding lug on the lower cover.

Abstract: A method of manufacturing an aerodynamic structure, for example, an aircraft wing tip, is disclosed. The method includes providing an upper cover having a plurality of lugs, providing a lower cover having a plurality of lugs, measuring the distance between a lug on the upper cover and corresponding lug on the lower cover, selecting, from the plurality of different sized links, a link suitably sized to correspond to the measured distance between the lug on the upper cover and corresponding lug on the lower cover, connecting the selected link to the lug on the upper cover and corresponding lug on the lower cover; and repeating those steps such that each lug on the upper cover is joined to a corresponding lug on the lower cover.

Abstract: A section of an aircraft wing including a leading edge of the aircraft wing. A leading edge part of the section includes ribs; and a skin fixedly attached to the ribs to form a spanwise series of adjacent cells. Each cell includes an enclosed volume bounded by the skin at the leading edge and a pair of the ribs. At least one cell of the series of adjacent cells is a dry cell include a mounting point for mounting a leading edge high-lift device support apparatus in the dry cell. The skin at the leading edge provides a primary load path for carrying at least some of a spanwise primary load experienced by the section when in use on an aircraft.

Abstract: A locking pin associated with one of a fixed wing and a wing tip device, and a bush associated with the other of the fixed wing and wing tip device, the bush configured to receive the locking pin. The bush is located within a bush housing arranged to allow relative movement of the bush in the direction of a longitudinal axis of the locking pin when the locking pin is received within the bush.

Abstract: A control mechanism includes an existing aerodynamic device, such as a slat 5, that moves between at least one deployed position and a retracted position; and a load-alleviation mechanism 10 arranged to move the aerodynamic device into a load-alleviation position in response to a load 18, such as a gust of wind acting over a predetermined threshold. During flight, an aircraft can experience gusts of wind that cause strain on the wings 4. The addition of a load-alleviation mechanism to a pre-existing aircraft component allows for gust loading to be alleviated without adding significantly to the weight or complexity of the aircraft. The control mechanism may be retro-fitted to existing aircraft.

Abstract: A spar assembly for an aircraft wing extends between an upper cover and a lower cover and includes linkages spaced consecutively along the length of the spar assembly, each linkage extending from an upper pivot, to a lower pivot, thereby joining upper and lower attachment structures of the spar assembly together. Each linkage includes a pair of fixed-length links pivotably connected at one end about a center pivot and pivotably connected at respective other ends. The spar assembly includes a drive bar connected to the center pivot of each of the linkages, and an actuator arranged to move the drive bar along the length of the spar assembly. When the actuator moves the drive bar along the length of the spar structure, the links in each pair of links are rotated relative to each other about the center pivot, thereby moving the upper and lower covers and warping the wing.

Abstract: An aircraft (2) including a wing (1), the wing (1) having a fixed wing (3) and a wing tip device (4) at the tip of the fixed wing (3), the wing tip device (4) being rotatable relative to the fixed wing (3) between flight and ground configurations, the aircraft including a rotational joint (10) with a rotation mechanism (11) that rotatably couples the wing tip device (4) to the fixed wing (3) and a locking mechanism including a locking bore (53, 54) and a locking pin (51) that is receivable in the locking bore to lock the wing tip device (4) in one of the flight or ground configurations, wherein the rotational joint includes an alignment mechanism including an alignment pin (61) and an alignment bore (62, 63) and at least one of the alignment pin and alignment bore is tapered such that engagement of the alignment pin (61) in the alignment bore acts to guide the locking bore and locking pin into alignment.

Abstract: An aircraft wing (10) comprising a fixed wing (14) and a movable wing tip device (12). The wing tip device is movable between a flight configuration and a ground configuration, whereby in the ground configuration the span of the wing is reduced compared to the flight configuration. A locking mechanism (30) is provided to lock the wing tip device in the flight configuration, the locking mechanism includes a receiving socket (34) with a first latch and a second latch, and a locking pin (32). In the locked configuration, the locking pin is inserted into the receiving socket such that the first latch and second latch prevents removal of the locking pin from the receiving socket.

Abstract: A wing arrangement for an aircraft, comprising a wing having a base section and a tip section pivotably connected to base section such that the tip section is pivotable about a pivot axis between a deployed position and a stowed position. The wing arrangement also comprises a latching arrangement which includes an engagement portion, a latching actuator selectively movable between a first actuator position and a second actuator position, an elastically deformable structure, and a latching element. When the tip section is pivoted from the stowed or deployed position into an engagement position, the elastically deformable structure is initially deformed, and as the tip section pivots further into the deployed or stowed position, the elastic deformation of the elastically deformable structure decreases.

Abstract: An aerodynamic structure for an aircraft including a first region having a first magnetic sealing surface, movably connected to a second region having a second magnetic sealing surface. The structure is moveable between a first configuration in which the first sealing surface contacts the second sealing surface such that the first region and the second region form a continuous aerodynamic surface, and a second configuration in which a gap exists between the first and second magnetic sealing surfaces and. The magnetic sealing surfaces are configured such that an attractive magnetic force exists between the magnetic sealing surfaces in the first configuration. The aerodynamic structure is configured such that during movement between the first and second configurations, relative movement of the first and second regions occurs along a direction at an angle in the range 1-90° to the normal of the first sealing surface and/or the second sealing surface.

Abstract: An control mechanism includes an existing aerodynamic device, such as a slat 5, that moves between at least one deployed position and a retracted position; and a load-alleviation mechanism 10 arranged to move the aerodynamic device into a load-alleviation position in response to a load 18, such as a gust of wind acting over a predetermined threshold. During flight, an aircraft can experience gusts of wind that cause strain on the wings 4. The addition of a load-alleviation mechanism to a pre-existing aircraft component allows for gust loading to be alleviated without adding significantly to the weight or complexity of the aircraft. The control mechanism may be retro-fitted to existing aircraft.

Abstract: A locking pin associated with one of a fixed wing and a wing tip device, and a bush associated with the other of the fixed wing and wing tip device, the bush configured to receive the locking pin. The bush is located within a bush housing arranged to allow relative movement of the bush in the direction of a longitudinal axis of the locking pin when the locking pin is received within the bush.

Abstract: A spar assembly for an aircraft wing extends between an upper cover and a lower cover and includes linkages spaced consecutively along the length of the spar assembly, each linkage extending from an upper pivot, to a lower pivot, thereby joining upper and lower attachment structures of the spar assembly together. Each linkage includes a pair of fixed-length links pivotably connected at one end about a center pivot and pivotably connected at respective other ends. The spar assembly includes a drive bar connected to the center pivot of each of the linkages, and an actuator arranged to move the drive bar along the length of the spar assembly. When the actuator moves the drive bar along the length of the spar structure, the links in each pair of links are rotated relative to each other about the center pivot, thereby moving the upper and lower covers and warping the wing.

Abstract: A section of an aircraft wing including a leading edge of the aircraft wing. A leading edge part of the section includes ribs; and a skin fixedly attached to the ribs to form a spanwise series of adjacent cells. Each cell includes an enclosed volume bounded by the skin at the leading edge and a pair of the ribs. At least one cell of the series of adjacent cells is a dry cell include a mounting point for mounting a leading edge high-lift device support apparatus in the dry cell. The skin at the leading edge provides a primary load path for carrying at least some of a spanwise primary load experienced by the section when in use on an aircraft.

Abstract: An aircraft wing comprises a fixed wing, and a wing tip device at the tip thereof. The wing tip device is configurable between (i) a flight configuration for use during flight, and (ii) a ground configuration for use during ground based operations. In the ground configuration with span of the wing is reduced. The wing further comprises a locking mechanism including a locking pin with a longitudinal axis, the locking pin associated with one of the fixed wing and the wing tip device, and a bush associated with the other of the fixed wing and wing tip device, the bush configured to receive the locking pin. The bush is located within a bush housing arranged to allow relative movement of the bush in the direction of the longitudinal axis of the locking pin when the locking pin is received within the bush.

Abstract: A wing (5) having a base section (5) and a tip section (13), the base section (7) having a first end portion (9) and a second end portion (11), the tip section (13) having a third end portion (15) and a fourth end portion (17), wherein the second end portion (11) and the third end portion (15) are coupled so that the tip section (13) is pivotable with respect to the base section (7) about a pivot axis (19, 19?), and an actuating arrangement having an actuator (21) which is coupled to the base section (7) and the tip section (13) and which is operable to effect a pivotal movement of the tip section (13) relative to the base section (7) between a stowed position and a deployed position.

Abstract: A section of an aircraft wing including a leading edge of the aircraft wing. A leading edge part of the section includes ribs; and a skin fixedly attached to the ribs to form a spanwise series of adjacent cells. Each cell includes an enclosed volume bounded by the skin at the leading edge and a pair of the ribs. At least one cell of the series of adjacent cells is a dry cell include a mounting point for mounting a leading edge high-lift device support apparatus in the dry cell. The skin at the leading edge provides a primary load path for carrying at least some of a spanwise primary load experienced by the section when in use on an aircraft.

Abstract: The invention provides an aircraft wing, comprising a fixed wing and a wing tip device at the tip. The wing tip device is configurable between: (i) a locked flight configuration for use during flight and (ii) a ground configuration for use during ground-based operations. The wing further comprises a locking mechanism for locking the folding wing tip device in the locked flight configuration. A rotatable locking member is associated with one of the folding wing tip device and the fixed wing, and a locking pin associated with the other. The rotatable locking member comprises a guide surface to guide the locking pin to a locked configuration, in which the guide surface is shaped such that the locking pin is urged toward the rotation axis of the rotatable locking member by a camming action of the guide surface on the locking pin, thereby preloading the locking mechanism.

Abstract: An aircraft wing (10) comprising a fixed wing (14) and a movable wing tip device (12). The wing tip device is movable between a flight configuration and a ground configuration, whereby in the ground configuration the span of the wing is reduced compared to the flight configuration. A locking mechanism (30) is provided to lock the wing tip device in the flight configuration, the locking mechanism includes a receiving socket (34) with a first latch and a second latch, and a locking pin (32). In the locked configuration, the locking pin is inserted into the receiving socket such that the first latch and second latch prevents removal of the locking pin from the receiving socket.