Systems and methods are provided for assembling a wing. Methods include suspending an upper wing panel of an aircraft beneath a shuttle, translating a rib to a position it, and placing the rib into contact with, then affixing the rib to, the upper wing panel, while suspended. Some methods include installing ribs and spars to the upper wing panel, and joining a lower wing panel to the ribs and spars, while the upper wing panel is suspended. Some methods involve joining ribs to spars (e.g., all, or some) to produce a support structure that is then affixed to the upper wing panel. Systems include a shuttle that suspends an upper wing panel, and a cart that includes supports to hold a rib, a chassis to translate the rib to a position beneath the upper wing panel, and a lifting apparatus to lift the rib into contact with the upper wing panel.

The method for producing an assembly is a method for producing an assembly equipped with a member to be reinforced (20), a reinforcing member body (41), and a filler (42), wherein the reinforcing member body (41) has a pair of flanges (44) arranged spaced on the surface (20B) of the member to be reinforced (20), a web (45), and a connection portion (46) which connects the flanges (44) and the web (45) and forms a filler space (V) with the surface (20B). The method for producing an assembly includes a step for inserting a filler (42) into the filler space (V), a step for attaching a crack control member (43) to cover the end of the filler (42), a step for joining the flanges (44) and the member to be reinforced (20), and a step for curing at least the member to be reinforced (20).

A shear web foot for a wind turbine blade is described. The shear web foot extends longitudinally and comprises a base for attaching to an internal surface of the blade and first and second side walls. The side walls extend respectively from opposite longitudinal sides of the base. At least part of each side wall is inclined relative to the base and inclined towards the other side wall. A web-foot interior is defined at least in part by the base and the first and second side walls. One or more internal walls are located in the web-foot interior. The one or more internal walls extend between the base and the first and/or second side walls and are spaced apart from the first and second side walls to define a plurality of chambers within the web-foot interior.

A wing for an aircraft includes a first end, a second end, and a skin extending longitudinally from the first end to the second end. The wing also includes at least one channel positioned within the skin and extending longitudinally between the first and second ends. The at least one channel defines a longitudinal translation path for translating at least one electrical power source longitudinally between the first and second ends.

An aircraft assembly is disclosed having a wing tip device connected to a wing tip of a wing by a first connector, a second connector, and a third connector. The wing tip device includes a front device spar and a rear device spar. The first connector is associated with the rear device spar. The second connector is spaced apart in a chordwise direction forward of the first connector, and the third connector is spaced apart in a chordwise direction rearward of the first connector. The third connector includes a spigot mounting formation.

A rib mounting assembly for an aircraft is disclosed including a rib post and a seal member. The rib post has a rib post foot to mount with a longitudinal spar and a rib post web upstanding from the rib post foot. The seal member has a seal body and a mounting flange. The mounting flange is mounted with the rib post foot and the seal body extends from an end of the rib post.

A wing leading-edge device is disclosed having a slat body having a front side with a forward skin and a back side with a rearward skin, and at least a drive arrangement having at least one lug and a slat track, wherein the back side extends between an upper spanwise edge of the forward skin and a lower spanwise edge of the forward skin. The back side is defined by a continuously curved profile contour for receiving a fixed leading edge, and the at least one lug is at least partially arranged between the back side and the front side. The slat track is coupled with the first lug. The connection points to the slat body are shifted far forward to improve the load introduction and reduce moments acting on the drive mechanism.

An airfoil body is provided for an aircraft which includes a first skin, a second skin, a plurality of first stiffeners and a plurality of second stiffeners. The first stiffeners are configured from or otherwise include first stiffener composite material. The first stiffeners extends widthwise between and are connected to the first skin and the second skin. Each of the first stiffeners has a first stiffener longitudinal centerline that extends spanwise along the first skin and the second skin. The second stiffeners are configured from or otherwise include second stiffener composite material. The second stiffeners extend widthwise between and are connected to the first skin and the second skin. Each of the second stiffeners has a second stiffener longitudinal centerline that extends lengthwise along the first skin and the second skin.

An aircraft wing assembly including 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 wing structure for a vehicle, and a vehicle. The wing structure comprises at least one multi-connecting-rod structure. The multi-connecting-rod structure is arranged in a direction extending from the main body of a vehicle to a wingtip, each multi-connecting-rod mechanism comprises a plurality of connecting rods, and connecting rods which are adjacent to each other are connected by means of a motor. The present technical solution provides a wing structure having the feature of a morphing wing having a large range in both chordwise and spanwise directions. The wing structure has the capability of changing airfoil and changing a pitch angle within a large range, the capability of twisting along a spanwise direction at a distal portion, the capability of swinging perpendicularly within a large range along the plane in which the main body of the vehicle is located, and the capability of swinging longitudinally within a large range along the main body of the vehicle, adjustment can be performed on a complex flow field or environment, the motion speed and the motion efficiency are significantly improved, and high maneuvering actions can be achieved.