An aircraft has a fuselage, a wing assembly, and a pair of struts. The wing assembly has a center wing structure and a pair of outer wing structures. The center wing structure is coupled to the fuselage at a wing-fuselage joint, and has a pair of engine mounting locations respectively on opposite sides of a wing centerline. Each of the struts is coupled to the fuselage at a strut-fuselage joint, and to one of the outer wing structures at a strut-wing joint. Each strut-fuselage joint is located below and aft of the wing-fuselage joint. Each outer wing structure is coupled to the center wing structure at a mid-wing joint located no further inboard than the engine mounting location, and no further outboard than the strut-wing joint.

Methods of assembling an aircraft wing includes adhering fuel dams to stringers and adhering the fuel dams to ribs. Fuel dams include a fuel-dam body that defines a channel shaped to receive a portion of a stringer of an aircraft wing. The fuel-dam body includes a stringer adherent surface, a rib adherent surface, and a pair of spaced-apart flanges extending from the rib adherent surface and positioned to project from the rib adherent surface on opposing sides of a notch of a rib.

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.

In one aspect, there is a method of making a composite skin for a tiltrotor aircraft including providing a first skin in a mold, the first skin having a periphery defined by a forward edge, an aft edge, and outboard ends; providing a plurality of honeycomb panels having an array of large cells onto the first skin, each cell having a width of at least 1 cm; assembling the plurality of honeycomb panels along the longitudinal axis of the first skin to form a honeycomb core having an outer perimeter within the periphery of the first skin; positioning a second skin onto the honeycomb core, the second skin having an outer perimeter within the periphery of the first skin; and curing an adhesive to create a bond between the first skin, the honeycomb core, and the second skin to form a composite skin.

A wing mounting, comprising: ⋅a base (11); ⋅a wing bracket (25) pivotally mounted to the base, configured to rotate relative to the base within an operational angular range; and ⋅at least one biasing element configured to bias the wing bracket away from the boundaries of the operational angular range, wherein the at least one biasing element (120) is configured to bias the wing bracket within a biasing range adjacent the respective boundaries of the operational angular range, but substantially not to bias the wing bracket within an inner angular range including the middle of the operational angular range.

A thrust generator comprising: a motor (17), and a wing mounting (10), comprising a base (11) and a wing (2, 20), the base connected to the motor and configured to rotate the wing mounting about a stroke axis (13) within an angular stroke range, wherein the wing comprises a wing panel (24) having a first longitudinal edge (5) and a second longitudinal edge (6), the wing panel defining a wing surface (4) between the first and second longitudinal edges, and wherein the wing panel is configurable between: a first configuration in which the first longitudinal edge of the wing panel defines a leading edge and the second longitudinal edge of the wing panel defines a trailing edge; and a second configuration in which the second longitudinal edge of the wing panel defines a leading edge and the first longitudinal edge of the wing panel defines a trailing edge, the thrust generator being configured to rotate the wing mounting about the stroke axis in a first direction when the wing panel is in the first configuration and to rotate the base about the stroke axis in a second direction when the wing panel is in the second configuration.

Embodiments are directed to systems and methods for two or more cured composite assemblies that are bonded together to form a tubular composite structure, wherein each of the cured composite assemblies do not have a tubular shape. The tubular composite structure may form a spar for an aerodynamic component, for example. The two or more cured composite assemblies may comprise carbon or fiberglass composite materials or a combination of materials. Each of the cured composite assemblies may further comprise axial edges that are configured to be bonded to another of the cured composite assemblies, wherein the axial edges have a sloped shape. An adhesive agent may be applied on the axial edges for bonding two cured composite assemblies. Alternatively, or additionally, one or more fasteners may be used to attach the axial edges of at least two cured composite assemblies.

A multispar lifting surface including a multispar torsion box having corner reinforcements, a movable control surface, and an axial rod fitting. The movable control surface includes a movable element, a hinged connection joined to the movable element, and an axial rod joining the hinged connection to the rear spar of the multispar torsion box. The axial rod fitting is configured to join the axial rod and the multispar torsion box; and includes a longitudinal profile resting against the rear spar, and a lug joined to the longitudinal profile at one end and to the axial rod at another end; the lug defining a plane including the longitudinal axis of the axial rod. This multispar lifting surface is able to support sideward forces without any additional structure.

The invention relates to a rolled product made of aluminum alloy with a thickness of at least 50 mm comprising (in weight %): Zn 6.9-7.5; Mg 1.8-2.2; Cu 1.8-2.2, where the sum Cu+Mg is between 3.8 and 4.2; Zr 0.04-0.14; Mn 0-0.1; Ti 0-0.15; V 0-0.1; Fe≤0.15; If ≤0.15; impurities ≤0.05 each and ≤0.15 total, balance aluminum. The invention also relates to the method of manufacturing such a product. The products according to the invention are particularly advantageous because they have a very favorable compromise between static mechanical strength, toughness and environmental-assisted cracking performance under conditions of high stress and humid environment.

Structural composite airfoils include a primary structural element, a secondary structural element defining the trailing edge of the structural composite airfoil, and a discrete leading edge structure defining the leading edge of the structural composite airfoil. The primary structural element includes an upper skin panel, a lower skin panel, and a middle C-channel spar that is coupled to the upper skin panel and the lower skin panel. The discrete leading edge structure is coupled to the upper leading edge end of the upper skin panel and to the lower leading edge end of the lower skin panel. The upper skin panel may include a first panel bend adjacent the discrete leading edge structure, and the lower skin panel may include a second panel bend adjacent the discrete leading edge structure.