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.

An aerofoil shaped body includes a plurality of longitudinal spars, an upper aerofoil cover, and a lower aerofoil cover. The spars and the covers are made of composite laminate material. One of the spars is integrally formed with one of the covers to form a spar-cover such that the composite laminate material of the spar extends continuously into the cover through a fold region created between the spar and the cover. The fold region has a fold axis extending substantially in the longitudinal direction, and the fold axis projected onto two orthogonal planes has curvature in both those planes.

A composite wingbox structure formed of reinforced thermoplastic. The composite includes carbon fiber reinforcement and a plurality of insulation elements to localize the heat formed during the process of manufacturing the structure. The process of manufacturing the wingbox includes the steps of interleaving a series of insulations elements within a plurality of laminae and consolidating the insulation elements and laminae to form a laminate. The laminate is then aligned with a support structure such that the insulation elements overlie the supports structure. The laminate is then fused to the support structure using a non-contact heating process, such as inductive welding.

An aircraft joint includes a first component having an outer aerodynamic surface and an inner surface, a second component having an outer aerodynamic surface and an inner surface, and a strap assembly bridging between the inner surfaces of the first and second components. The strap assembly has a first strap part attached to the inner surface of the first component, a second strap part attached to the inner surface of the second component, and a third strap part received in the first and second strap parts in a sliding manner. The third strap part when received in the first and second strap parts constrains movement of the first component relative to the second component in a direction normal to the outer aerodynamic surfaces of the first and second components in the vicinity of the strap assembly.

A winglet is disclosed including first and second covers, a front spar, a rear spar, a rib, and a mid spar between the front spar and the rear spar. The rib and each spar are joined to the first cover and to the second cover. The mid spar has a length and the mid spar curves along all or part of its length. The length of the mid spar extends from an inboard end of the mid spar to an outboard end of the mid spar, and the rib wraps around the inboard or outboard end of the mid spar.

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 leading edge slat of a wing element of an aircraft. The aircraft defining a mark including a main fuselage axis x and a spanwise axis y. The wing procuring a lift along an axis z. The wing element having a skin forming the leading edge slat, a spar linked to the skin and a stiffening structure linked on the leading edge side to the spar and to the skin. The stiffening structure being formed from a formed sheet metal having a plurality of bosses distributed according to the length of the leading edge. The bosses extending between the spar and the inner face of the skin.

Aircraft landing gear forward trunnion support assemblies and related methods are described herein. An example aircraft wing disclosed herein includes a rear spar having a rear side and a front side opposite the rear side and a forward trunnion support assembly. The forward trunnion support assembly includes first and second vertical support fittings coupled to the rear side of the rear spar, and a trunnion housing with a bearing. The trunnion housing is coupled between the first and second vertical support fittings. A central axis of the bearing is perpendicular to the rear side of the rear spar. The forward trunnion support assembly also includes a side load fitting disposed on the rear side of the rear spar. A first end of the side load fitting is coupled to the second vertical support fitting, and a second end of the side load fitting is coupled to the rear spar.

Examples include an apparatus configured for attaching a rib of an aircraft wing to a panel of the aircraft wing, the apparatus including: an insert that is configured to be attached, via an interference fit, to a hole in the rib; a shear tie including a socket at a first end of the shear tie, where the shear tie is configured to be attached to the panel at a second end of the shear tie; a ball stud including a shaft and a ball that is opposite the shaft, where the shaft is configured to be attached to the insert and the ball is configured to be positioned within the socket; and a fastener that is configured to secure the ball within the socket, thereby attaching the ball stud to the shear tie.

Examples include an apparatus configured for attaching a rib of an aircraft wing to a panel of the aircraft wing, the apparatus including: an insert that is configured to be attached, via an interference fit, to a hole in the rib; a shear tie including a socket at a first end of the shear tie, where the shear tie is configured to be attached to the panel at a second end of the shear tie; a ball stud including a shaft and a ball that is opposite the shaft, where the shaft is configured to be attached to the insert and the ball is configured to be positioned within the socket; and a fastener that is configured to secure the ball within the socket, thereby attaching the ball stud to the shear tie.